Форум Новости Космонавтики

ЦитироватьА мне интересна их, скажем так, нетрадиционная конструктивно-компоновочная схема: твердотопливная первая ступень и ЖСУ на высококипящих компонентах! Обычно делают наоборот. Что характерно: твердотопливная ступень выгорает раньше, чем ускорители и те её тащат дальше.

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ЦитироватьА мне интересна их, скажем так, нетрадиционная конструктивно-компоновочная схема: твердотопливная первая ступень и ЖСУ на высококипящих компонентах! Обычно делают наоборот. Что характерно: твердотопливная ступень выгорает раньше, чем ускорители и те её тащат дальше.

Ничего особенного. Практически, это единый ракетный блок (а не два) с разнородной ДУ.

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ЦитироватьА мне интересна их, скажем так, нетрадиционная конструктивно-компоновочная схема: твердотопливная первая ступень и ЖСУ на высококипящих компонентах! Обычно делают наоборот. Что характерно: твердотопливная ступень выгорает раньше, чем ускорители и те её тащат дальше.

Ничего особенного. Практически, это единый ракетный блок (а не два) с разнородной ДУ.

Но ведь это же нерационально! Тащить выгоревший ТТРД

ЦитироватьА вот вопрос: почему Мк3, имея три ступени, из которых верхняя - довольно мощная криогенная, имеет грузоподъемность на низкой орбите всего лишь 10т при стартовой массе, сопоставимой с Протоном? Маловато! :twisted:

ЦитироватьА вот вопрос: почему Мк3, имея три ступени, из которых верхняя - довольно мощная криогенная, имеет грузоподъемность на низкой орбите всего лишь 10т при стартовой массе, сопоставимой с Протоном? Маловато! :twisted:

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ЦитироватьА вот вопрос: почему Мк3, имея три ступени, из которых верхняя - довольно мощная криогенная, имеет грузоподъемность на низкой орбите всего лишь 10т при стартовой массе, сопоставимой с Протоном? Маловато! :twisted:

Ну дык нижняя твердотопливная. 8)

ЦитироватьА вот вопрос: почему Мк3, имея три ступени, из которых верхняя - довольно мощная криогенная, имеет грузоподъемность на низкой орбите всего лишь 10т при стартовой массе, сопоставимой с Протоном? Маловато! :twisted:

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ЦитироватьА вот вопрос: почему Мк3, имея три ступени, из которых верхняя - довольно мощная криогенная, имеет грузоподъемность на низкой орбите всего лишь 10т при стартовой массе, сопоставимой с Протоном? Маловато! :twisted:

Так это она скорее всего как раз без верхней криогенной столько тащит. Ей же, как-никак, тогда придётся всю бандуру ЦБ на орбиту вытолкнуть. (Кста, можно сравнить с РН "Спутник" ;) )
А с криогенной, возможно, вытаскивает ненамного больше из-за провала тяговооруженности.

ЦитироватьМожет быть ... :roll: Хотя для 3-й ступени тяговооруженность может быть и 0,4-0,5, а у Дельты-4Хэви и того ниже.

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ЦитироватьМожет быть ... :roll: Хотя для 3-й ступени тяговооруженность может быть и 0,4-0,5, а у Дельты-4Хэви и того ниже.

А Вы точно знаете тяговооруженность верхней ступени у Дельты-4Хэви? ;) Уверен, она в этом варианте недозаправлена (мож даже наполовину).

Цитировать2SpaceR
У вас известное заблуждение тех, кто не видел разрез ракеты. Ферма - межбаковая, сопло криогенной ступени расположено ниже. Там ЦБ на гептиле очень короткий получился.

Цитировать2SpaceR
У вас известное заблуждение тех, кто не видел разрез ракеты. Ферма - межбаковая, сопло криогенной ступени расположено ниже. Там ЦБ на гептиле очень короткий получился.

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Цитировать2SpaceR
У вас известное заблуждение тех, кто не видел разрез ракеты. Ферма - межбаковая, сопло криогенной ступени расположено ниже. Там ЦБ на гептиле очень короткий получился.

Спасибо!
Решили не заморачиваться со сбросом переходника?
Спорное решение. :roll:
А время работы ТТУ и гептилового ЦБ теперь одинаковое?
Или ТТУ сбрасываются раньше?

ЦитироватьТ.е. гептиловый ЦБ запускается после сброса ТТУ?

Цитировать2SpaceR
У вас известное заблуждение тех, кто не видел разрез ракеты. Ферма - межбаковая, сопло криогенной ступени расположено ниже. Там ЦБ на гептиле очень короткий получился.

ЦитироватьДля иллюстрации: схема 3 ступени Delta IV Хэви
(https://img.novosti-kosmonavtiki.ru/6390.jpg)

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ЦитироватьМожет быть ... :roll: Хотя для 3-й ступени тяговооруженность может быть и 0,4-0,5, а у Дельты-4Хэви и того ниже.

А Вы точно знаете тяговооруженность верхней ступени у Дельты-4Хэви? ;) Уверен, она в этом варианте недозаправлена (мож даже наполовину).

:shock:  А нафига ж тогда для Хэви более тяжелую 5-метровую третью ступень делали? :shock:  Чтоб потом недозаправлять?! :lol:

ЦитироватьНу, там наверное и на ГПО прирост небольшой будет, но на низкий круг полностью заправленная верхняя ступень (если учесть полное время ее работы) скорее всего вообще не сможет выйти.

ЦитироватьУ двигателя RL-10B-2 (Pratt & Whitney) тяга в пустоте 11223 кгс
Масса заправленной 3 ступени
* 4-х метровый диаметр - 24170 кг; тяговоруженность ступени - 0.464
* 5-и метровый диаметр - 30710 кг; тяговоруженность ступени - 0.365

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ЦитироватьНу, там наверное и на ГПО прирост небольшой будет, но на низкий круг полностью заправленная верхняя ступень (если учесть полное время ее работы) скорее всего вообще не сможет выйти.

Тем не менее, для чего то ее сделали, 5-метровую ступень. А на низкую орбиту, со скрипом, но по прикидкам в спредшите, выводит более 21 тонны :wink:

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ЦитироватьУ двигателя RL-10B-2 (Pratt & Whitney) тяга в пустоте 11223 кгс
Масса заправленной 3 ступени
* 4-х метровый диаметр - 24170 кг; тяговоруженность ступени - 0.464
* 5-и метровый диаметр - 30710 кг; тяговоруженность ступени - 0.365

А теперь учтите массу ПГ! :D

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ЦитироватьНу, там наверное и на ГПО прирост небольшой будет, но на низкий круг полностью заправленная верхняя ступень (если учесть полное время ее работы) скорее всего вообще не сможет выйти.

Тем не менее, для чего то ее сделали, 5-метровую ступень. А на низкую орбиту, со скрипом, но по прикидкам в спредшите, выводит более 21 тонны :wink:

Ок, ошибся, прошу прощения...  :oops:
Хотя в 21 тонну всё же не верится.  :?

Ну а для чего - я же выше указал. Как я понимаю, разработчики всех этих Кейхоулов и прочих Лакроссов стараются не утруждать себя апоейными ДУ.
Чем такое пояснение не нравится-то?

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ЦитироватьУ двигателя RL-10B-2 (Pratt & Whitney) тяга в пустоте 11223 кгс
Масса заправленной 3 ступени
* 4-х метровый диаметр - 24170 кг; тяговоруженность ступени - 0.464
* 5-и метровый диаметр - 30710 кг; тяговоруженность ступени - 0.365

А теперь учтите массу ПГ! :D

Mass of payload is dependent on mission!  :P Last one was TOP Secret!!! :roll:
(https://img.novosti-kosmonavtiki.ru/49104.png)

ЦитироватьCapacity (separated spacecraft mass):
    * geosynchronous orbit (GEO) 6,275 kg
    * escape orbit 9,306 kg
    * C3 performance of 30 km

ЦитироватьFrigate, спасибо :).
То есть тяговооруженность крайне низкая для последней ступени на НОО. Наверняка недозаправляют.

Проблема недозаправленной ступени в том, что из-за больших пустых объемов колебания топлива могут достигать большой амплитуды, сильно влияя на усточивость РН. И если эта задача, возможно, решаема для Боинга, то не могу того же уверенно говорить об ISRO.
Так что видимо им разумнее (да и по деньгам тоже ;) ) запускать на НОО двухступенчатую конфигурацию, без CUS.

ЦитироватьПроблема в том, что с недозаправленной (повторюсь, зачем недозаправлятьь, если есть более легкая 4-хметровая модель? :lol: ) посоледней ступенью, Дельта-4Хэви не может вывести на НОО ПГ заявленной массы.

ЦитироватьПути Боинга неиповедимы :P, но возвращаясь к обсуждению индийских РН могу сказать что задержка с полетом GSLV Mk.2 обусловлена отработкой криогенного блока для верхней ступени (который должен заменить российский 12КРБ).  

По последним данным, запуск в 2009 году, ПН - индийский спутник 2009 GSat 4 (HealthSat) на GEO.  :idea:

А вот этапы большого пути ISRO:
(https://img.novosti-kosmonavtiki.ru/60462.jpg)

ЦитироватьПроблема в том, что с недозаправленной (повторюсь, зачем недозаправлятьь, если есть более легкая 4-хметровая модель? :lol: ) посоледней ступенью, Дельта-4Хэви не может вывести на НОО ПГ заявленной массы.

ЦитироватьА вот этапы большого пути ISRO:

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ЦитироватьА вот этапы большого пути ISRO:

Я правильно понял, что на срезе голубые, фиолетовые, зеленые, и красные кружки это блоки с ЖРД а оранжевые - ТТРД?
- Какие необычные схемы!! :D

Вообще сильно большая картинка, ее-бы порубить на несколько частей..

ЦитироватьА на ТТУ бачки с вонючкой по бокам?

ЦитироватьНо ведь это же нерационально! Тащить выгоревший ТТРД

ЦитироватьБыл неправ. С недозаправкой примерно в 8 т масса ПГ увеличивается примерно на 2 т. Но подтверждения того, что ступень действительно недозаправлдяется - нет. Было бы неплохо уточнимть. В любом случае, выгоднее было бы использовать 4-хметровую ступень (ведь ничто не мешало применять 5-метровый ГО на Титане-4 с диаметром ступеней 3,05 м.

ЦитироватьБыл неправ. С недозаправкой примерно в 8 т масса ПГ увеличивается примерно на 2 т. Но подтверждения того, что ступень действительно недозаправлдяется - нет. Было бы неплохо уточнимть.

ЦитироватьВ любом случае, выгоднее было бы использовать 4-хметровую ступень (ведь ничто не мешало применять 5-метровый ГО на Титане-4 с диаметром ступеней 3,05 м.

ЦитироватьКасательно новых индийских РН неясен такой вопрос: почему не анонсировано ни одного моноблочного носителя на новом РДТТ диаметром 3,4 м ?
Имхо разрабатывать такой супердвиж только для этих модификаций неокупаемо. Можно было бы неслабо поднять мощь тем же PSLV и GSLV mk2.

ЦитироватьВообще сильно большая картинка, ее-бы порубить на несколько частей..

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ЦитироватьВообще сильно большая картинка, ее-бы порубить на несколько частей..

Извиняюсь вдогонку - была картинка меньшего размера (но тогда не разглядеть деталей). Резать было некогда
- и так счастье,  что индийский site вдруг заработал (последние полгода ничего путного не показывал  :twisted:).

ЦитироватьА 4 тонны на геостационар это разве слабый рынок?

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ЦитироватьА 4 тонны на геостационар это разве слабый рынок?

Уже сейчас порядка 50 % спутников он вообще не сможет вывести на ГПО, а к моменту создания носителя эта доля будет еще больше. На оставшиеся же еще нужно получить заказы, так что скорее всего GSLV Мк.3 останется носителем для внутреннего потребления.

ЦитироватьНо все же более рационально было бы сперва отработать их на моноблочной РН. А таковой в перспективном ряду ISRO что-то пока не наблюдается.

ЦитироватьIndia hopes to join cryogenic rocket engine club January 2010
By Venkatachari Jagannathan | 04 December 2009 | 5:03pm

Chennai, Dec 4 (IANS) India's heaviest rocket - the 49-metre tall, 414-tonne Geosynchronous Launch Vehicle (GSLV), powered by the indigenous cryogenic engine, will be launched in January 2010, making it a member of the sel ect club of countries possessing this technology.

Chennai, Dec 4 (IANS) India's heaviest rocket - the 49-metre tall, 414-tonne Geosynchronous Launch Vehicle (GSLV), powered by the indigenous cryogenic engine, will be launched in January 2010, making it a member of the sel ect club of countries possessing this technology.

Officials of Indian Space Research Organisation (ISRO) say the space agency will start the new year in style, launching the GSLV-D3 carrying the two-tonne communication satellite GSAT-4 sometime next month and not December as hoped earlier.

Speaking to IANS on the condition of anonymity, an ISRO official said: 'The launch is expected in January. Fr om the time the satellite reaches the spaceport, one needs at least 30 days' time for checking the systems prior to the launch. The satellite is yet to reach the spaceport.'

The GSAT-4 was supposed to reach ISRO's spaceport Sriharikota last month, but is now expected during the middle of this month.

ISRO's director for Publications and Public Relations S.Satish told IANS from Bangalore: 'Twenty days' time is sufficient for checking the satellite systems at the spaceport.' However, he declined to comment on the probable month of launch.

ISRO's chairman Dr.K.Radhakrishnan was not available for comment on the subject.

GSAT-4 will carry a multi-beam Ka-band bent pipe and regenerative transponder and navigation payload in C, L1 and L5 bands. The satellite can guide civil and military aircraft.

GSAT-4 will also carry a scientific payload, TAUVEX, comprising three ultra violet band telescopes developed by Tel Aviv University and Israel space agency (ELOP) for surveying a large part of the sky in the 1,400-3,200 angstrom wavelengths.

Meanwhile, the ISRO scientists are checking and rechecking the various systems in the cryogenic engine and examining the technical data.

An ISRO official told IANS the test results are being reviewed by experts to be doubly sure about its efficiency so that rocket's third stage can deliver the satellite into geo transfer orbit (GTO) fr om wh ere it will be taken to an altitude of 36,000 km above earth and then positioned.

The cryogenic engine reached Sriharikota fr om ISRO's facility in Mahendragiri in Tamil Nadu in October.

ISRO officials told IANS the checks show the cryogenic stage is in a healthy condition and fit for flight.

Only a few countries like the US, Russia, France, Japan and China possess the technical expertise to develop their cryogenic engines and India is expected to join this club.

For all the five earlier GSLV missions, ISRO had used Russian cryogenic engines.

While GSLVs with Russian cryogenic engines have been designated as operational rockets after two developmental flights, the one that will go up in January is called 'developmental flight 3' (GSLV D3) as it will be fired by the ISRO-developed cryogenic engine.

The last GSLV went up on Sep 2, 2007, carrying the 2,130 kg INSAT-4CR satellite.

According to an ISRO official the rocket's two fuel stages - the first stage solid fuel booster and four strap-on motors and the second stage liquid engine has been assembled. The last stage is the cryogenic stage.

In December 2008, the indigenously developed cryogenic upper stage engine passed the flight acceptance test with the engine tested for 200 seconds.

The development of cryogenic engines involves mastering materials technology, operating rotary pumps and turbines which run at 42,000 revolutions per minute (RPM).

The development of a cryogenic engine is crucial for ISRO to build more powerful GSLV rockets that can carry four-tonne satellites.

ISRO is lagging behind in launching its GSAT series due to not having a indigenously-developed cryogenic engine. GSAT was supposed to have gone up two years back.

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ЦитироватьFrigate пишет:

ИМХО похоже полетит "самостийний" индийский:
CE-20 Engine
(http://upload.wikimedia.org/wikipedia/en/thumb/7/7d/IndianCryoEngine25.JPG/450px-IndianCryoEngine25.JPG)

ЦитироватьThe specifications of the engine as listed on the LPSC handouts:

* Operating Cycle - Gas Generator
* Propellant Combination - LOX / LH2
* Thrust Nominal (Vacuum) - 200 kN
* Operating Thrust Range - 180 kN to 220 kN (To be set at any fix values)
* Chamber Pressure (Nom) - 6 MPa
* Engine Mixture ratio (Oxidizer/Fuel by weight) - 5.05
* Engine Specific Impulse - 443 ± 3 seconds
* Engine Burn Duration (Nom) - 595 seconds
* Total Flow rate - 462 kg/sec
* Nozzle Area ratio - 100
* Mass - 588 kg

Андрей Суворов пишет:

В total flow rate кто-то потерял десятичную запятую. А, может, "же", т.е. 9,81
Движок с УИ 443 и тягой 20 тонн жрёт 45 кило топлива в секунду, а не 450.
Кстати, либо они врут насчёт УИ, либо у кого-то калькулятор сломался, либо расход приведён не для номиналки.
Расход 46,2 кг/с при тяге 200 кН соответствует УИ 441 секунда.

Ну, либо в Индии "же" другое  :D  

Frigate пишет:

Не стреляйте в пианиста - играет так, как умеет  8) .
Вот картинка с выставки Aero India 2009 (проходила в феврале этого года):
(http://s16.radikal.ru/i190/0912/25/dab87cf87d43.jpg)

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ЦитироватьДмитрий В. пишет:

А СЕ-20 разве не для верхней ступени GSLV-III?

Frigate пишет:

СЕ-20 - Cryogenic Engine thrust 20 tonnf;
CS25 Cryogenic Stage 25 tonnes of propellant (для верхней ступени GSLV-III)

ЦитироватьIndigenous cryogenic engine to power GSLV-D3 news      

05 December 2009      

India will join a sel ect group of countries possessing cryogenic engine technology when it launches its biggest rocket, the 49-metre tall, 414-tonne Geosynchronous Launch Vehicle (GSLV), in January 2010. To date, only a few countries like the US, Russia, France, Japan and China possess the technology.

The GSLV-D3 will carry the GSAT-4, a two-tonne communication satellite, as its payload.

The launch of the GSLV-D3 is taking place in January 2010 instead of December this year as earlier planned. According to ISRO sources, it takes at least 30 days after a satellite arrives at the launch centre to check all systems prior to launch. They said the satellite is yet to reach the launch centre and is expected by the middle of this month.

The GSAT-4 will carry a multi-beam Ka-band bent pipe and regenerative transponder and navigation payload in C, L1 and L5 bands. It will be able to guide civil and military aircraft.

The GSAT-4 will also carry a scientific payload, TAUVEX, comprising three ultra violet band telescopes developed by Tel Aviv University and Israel space agency (ELOP) for surveying a large part of the sky in the 1,400-3,200 angstrom wavelengths.

Meanwhile, intensive checks are being carried out on the cryogenic engine and technical data examined.

The cryogenic engine will power the third stage of the GSLV launcher, which will position the GSAT-4 in Geo-synchronous Transfer Orbit (GTO), at an altitude of 36,000 km above the earth.

All earlier GSLV missions had used Russian cryogenic engines. The last GSLV went up on 2 September 2007, carrying the 2,130 kg INSAT-4CR satellite.

After two developmental flights, GSLVs with Russian cryogenic engines were designated as operational rockets, but GSLV-D3 will once again be designated a development flight as an ISRO built cryogenic engine will be powering one of the stages for the first time.

While the first stage of the GSLV is a solid fuel booster with four strap-on motors, the second stage is a liquid engine. Both these stages have been assembled. The third, and the last, is the cryogenic stage.

Indigenous cryogenic engine

The indigenously developed cryogenic engine passed its flight acceptance tests last year December, after burning for 200 seconds. Earlier, on 15 November 2007, it underwent successful ground testing burning for full flight duration of 720 seconds at the Liquid Propulsion test facility at Mahendragiri, Tamil Nadu.

The development of the cryogenic engine began in 1986 but ran into a series of problems forcing ISRO to enter into a $120 million contract with Russian space agency Glavkosmos for the supply of two cryogenic engines with transfer of technology arrangements.

The United States promptly imposed sanctions against Glavkosmos and ISRO, on the grounds that this transfer violated the Missile Technology Control Regime (MTCR) guidelines, blacklisting both organisations in the process.

Then Russian president Boris Yeltsin got Glavkosmos to renegotiate its deal with ISRO, under which there would be no transfer of technology and ISRO would get to buy two KVD-1 engines from Glavkosmos. The number was enlarged subsequently on Indian request.

India's first cryogenic engine test was aborted after 15 seconds instead of the planned duration of 30 seconds. The data obtained fr om this test, however, allowed a successful ground test of 480 seconds to follow on 4 August 2007.

According to ISRO, with the development of the indigenous Cryogenic Upper Stage (CUS) the organisation has mastered complexities in the fabrication of stage tanks, structures, and engine and its sub-systems and control components.

The CUS employs special materials like aluminum, titanium, nickel and their alloys, bi-metallic materials and polyimides.

The CSU programme is very significant for India's space programme as it will help launch a new class of space launchers – the GSLV Mk-III. These vehicles will be capable of initially launching satellites of 4,400 kg weight into Geo-synchronous Transfer Orbit.

Subsequently the payload will be upgraded to 6,000 kg.

ЦитироватьIndia to test world's third largest solid rocket booster
December 6th, 2009 - 5:30 pm ICT by IANS  

By Venkatachari Jagannathan
Chennai, Dec 6 (IANS) The Indian space agency is expected to take a major step in January towards realising its next generation rocket by ground-firing the world's third largest - in terms of fuel mass and length - solid rocket booster developed in-house.

An Indian Space Reasearch Organisation (ISRO) official said: "The large solid propellant booster project was taken up nearly a decade ago and will achieve its first milestone next month."

Recently, ISRO Chairman K. Radhakrishnan said the static testing of the booster will happen soon.

The 200-tonne solid propellant rocket booster - designed to power ISRO's next generation (geosynchronous launch vehicle) GSLV Mark III - will be ground tested at India's space port Satish Dhawan Space Centre, Sriharikota, 80 km from here.

The stage is expected to burn for 103 seconds.

In terms of fuel mass and length GSLV Mark III's 200 tonne, 25 metre long solid boosters will rank after US Space Shuttle's booster (fuel mass of 440 tonne, 37.8 metre) and Europe's Ariane (fuel mass 240 tonne, length 31.6 metre).

Measured in terms of diametre ISRO's new solid booster will rank second in the world with 3.2 metre while that of Space Shuttle and Ariane measure were 3.6 metre and 3.05 metre respectively.

As to fuel burn time the ranking will be in the order of Ariane (130 seconds), Space Shuttle (123 seconds) and GSLV Mark III (103 seconds).

However, the US is developing much larger first stage solid rocket motor for its new rocket Ares1. The diametre is 3.77 metre, length 52 metre with a propellant capacity of 625 tonne with a burn time of 123 seconds.

While the US recovers Space Shuttle booster steel casings for re-use, ISRO has no such plans as it requires parachutes for soft landing on the Indian seas and the issues relating to reuse.

"The steel casing has to be cleaned of salt deposits and refurbished for re-0use," the ISRO official told IANS on condition of anonymity as he is not authorised to speak to the media.

The 42.4-metre-tall GSLV Mark III rocket with a lift off weight of 630 tonne is being designed to reach towards the heavens sometime in 2011 carrying communication satellites weighing upto five tonne thereby making India self sufficient in respect of launch vehicles.

The first stage of the three fuel stage rocket will be two identical solid boosters strapped onto the second stage, the L110 re-startable liquid stage.

The third stage is the cryogenic stage powered by liquid oxygen and liquid hydrogen.

The large payload fairing measures 5 metre in diameter and can accommodate a payload volume of 100 cubic metre.

ISRO's existing rockets - the three stage GSLV and four stage Polar Satellite Launch Vehicle (PSLV)- has a lower carrying capacity.

The present GSLV can carry a luggage of 2.5 tonne to be ejected in geo-transfer orbit (GTO) while PSLV can sling 1.6 tonne and 1.1 tonne satellites into polar orbit and GTO respectively.

Interestingly, January 2010 will be a landmark month in ISRO's calendar for one more reason.

The space agency will be flying its GSLV powered by its own cryogenic engine.

Box: Solid propellant boosters of different rockets

Parameter...................... Space Shuttle......... Ariane 5........ GSLV MK III

...........................................USA................... Europe..............India

1.Diameter (metre).............. 3.6...................... 3.05................ 3.2

2.Length (metre).................. 37.8..................... 31.6................ 25

3.Number of Segments.......... 4.......................... 3.................... 3

4.Propellant Type ............Ap+Al+HTPB........Ap+Al+HTPB.....Ap+Al+HTPB

5.Total Mass (tonne).............500....................... 276................ 220

6.Propellant Mass (tonne).....440........................ 240................ 200

7.Average Thrust(tons)...... 1,040....................... 500............... 400

8.Nozzzle gimballing.........8 degree................. 6 degree........ 8 degree

9.Firing duration (seconds).. 123........................ 130............... 103

10.Motor case Material........ Steel..................... Steel............. Steel

Source: Industry

ЦитироватьFrigate пишет:

Идя навстречу пожеланиям форумчан (спасибо за намёк, Salo) выкладываю "картинки с выставки"
по космической тематике. Заранее предупреждю - снимки не мои.  8)

Индийские РН
(http://s43.radikal.ru/i101/0909/93/3d1738c52958.jpg)

РН GSLV Mk-III
(http://s42.radikal.ru/i098/0909/f0/33b5fd6604f7.jpg)
(http://i075.radikal.ru/0909/4a/0718635a628e.jpg)
(http://s50.radikal.ru/i129/0909/85/9381413d552c.jpg)

ЖРД
(http://i027.radikal.ru/0909/03/ebc39859198c.jpg)
(http://i025.radikal.ru/0909/63/1e63bc992245.jpg)
(http://s52.radikal.ru/i135/0909/3b/d645accce03a.jpg)

РН GSLV Mk-II
(http://s45.radikal.ru/i110/0909/39/565b1ac4cd62.jpg)
(http://i017.radikal.ru/0909/2b/f4e444c85164.jpg)(http://i023.radikal.ru/0909/36/2cd2f0e991d9.jpg)

ЦитироватьFrigate пишет:

KVD-1A:
(http://s48.radikal.ru/i120/0912/6e/7a7bce2dabe4.jpg)

ЦитироватьFrigate пишет:

ЦитироватьGSLV- Mk-2 will be an improved version with greater payload capability (upto 2,250 Kg [78]) on the fourth flight due in 2005  :oops:  [79]that will use:

Indigenous CUSP (cryogenic upper stage program) with larger fuel capacity (variously reported from 15 tonne[80] to 25 tonne [81 ,82]) and uprated thrust of 9.5 tonne [83] instead of Russian 12KRB's 12.5 tonne propellant and 7.5 tonne thrust. For the 15 tonne stage increased thrust shall be applied during initial 300 seconds after which thrust will revert back to standard 7.5 tonne [84](the last two KRB stages procured from Russia will likely be such 15 tonne stage, that would be approx 1.3m longer). The Indian CUSP reached a milestone when it successfully ran for 1000 seconds [85] on September 14, 2002 at full 9.5 tonne thrust [86], indicating ISRO's CUSP program is geared to realize C20 stage.

Короче - подстраховывая индийцев, Хруничев поставит поледние 2 криогенных блока:
- с тягой маршевого двигетеля 9.5 тонн (Точно такая же как у индийского "самостийного" РБ  :idea:  );
- РЗТ 15 тонн  :!:  ;
- Длина РБ будет ~ на 1.3 м больше (У 12КРБ длина 8.7 м и диаметр 2.8 м);
- По моим прикидочным расчетам :roll: (У 12КРБ начальная масса 15,1 тонн):
- начальная масса РБ 18,000 кг
- конечная масса РБ 3,000 кг
Похоже это изделие должно называться 15КРБ, а не 12КРБ  8)  

Цитировать

ЦитироватьАндрей Суворов пишет:

Ну, про 15КРБ уже был разговор здесь когда-то. Индусы очень давно хотели удлинить его, наши не соглашались, говорили, что проблемы с жёсткостью и собственными резонансными частотами...

Frigate пишет:

Российско-индийские работы по носителю GSLV И.Черный. "Новости космонавтики" 2002 N11:

ЦитироватьПараллельно ISRO обратилось к российской стороне с просьбой провести модернизацию двух блоков 12КРБ, находящихся в производстве в Центре Хруничева и готовящихся к поставкам в Индию, с целью увеличения массы ПГ, выводимого на геопереходную орбиту (ГПО) (с 1500 кг у существующего варианта GSLV Mk I до 2200 кг). По расчетам специалистов Центра, это можно сделать путем форсирования двигателя КВД-1 с 7.5 до 9.5 тс, увеличения массы заправляемых компонентов топлива 12КРБ с 12.5 до 15 т при параллельной плановой модернизации первой и второй ступеней носителя и его навесных жидкостных стартовых ускорителей, проводимой силами ISRO. После серии переговоров стороны подписали документы на модернизацию двух КРБ, и в январе 2002 г. ISRO выдало исходные данные для проведения работ.

Для сохранения надежности разгонного блока российские специалисты предлагают три основополагающих принципа доработок: запуск на ГПО должен осуществляться по одноимпульсной схеме (т.е. при однократном включении ЖРД); форсированный уровень тяги намечается использовать только в первые 300 сек полета при общей продолжительности работы двигателя 790 сек; массовое соотношение компонентов топлива блока необходимо понизить с 6.23 до 5.15, чтобы при форсировании ЖРД не повышать температуру в его камере сгорания и газогенераторе (форсирование достигается за счет повышения давления в камере сгорания путем замены регулятора тяги без существенных изменений уровней давлений в топливных баках).

Модернизация 12КРБ не должна привести к существенным изменениям компоновки: удлинятся баки (горючего - на 1005 мм, окислителя - на 325 мм), увеличится длина магистралей ПГС, гаргротов и БКС. Необходимо будет доработать наземное оборудование технического и стартового комплексов, транспортно-технологический контейнер, механическое оборудование, средства обеспечения заправки и эксплуатационную документацию. Поскольку длина 12КРБ возрастет, будет модернизирован блок отрывных разъемов, через который осуществляются все связи разгонного блока с наземным оборудованием. Кроме того, потребуется доработка программного обеспечения автоматизированного комплекса управления подготовкой и заправкой 12КРБ.

ЦитироватьFrigate пишет:

India's Cryogenic Engine Set For Integration With Rocket (http://www.space-travel.com/reports/India_Cryogenic_Engine_Set_For_Integration_With_Rocket_999.html)

ЦитироватьThe indigenous cryogenic engine develops a thrust of 73 kilo Newtons (kN) in vacuum with a specific impulse of 454 seconds and provides a payload capability of 2200 Kg to Geosynchronous Transfer Orbit (GTO) for GSLV.

The engine works on 'Staged Combustion Cycle' with an integrated turbopump running at around 42,000 rotations per minute (rpm). It is also equipped with two steering engines developing a thrust of 2 kN each to enable three-axis control of the launch vehicle during the mission.

Another unique feature of this engine is the closed loop control of both thrust and mixture ratio, which ensures optimum propellant utilisation for the mission.

The cryogenic engine is now in the process of being integrated with propellant tanks, stage structures and associated feed lines.

ЦитироватьFrigate пишет:

Возвращаясь к основной теме (КВРБ):

Индия не будет закупать российские 12КРБ (передача криогенной ракетной технологии не состоялась под давлением США).

Взамен Индия разработала национальный РБ (CUS Cryogenic Upper Stage C12.5 для РН GSLV-II)

РЗТ 12500 кг
Тяга (в пустоте) - 69500 н
Расход компонентов топлива 16.5 кг/сек
Таким образом удельный импульс 429сек  :!:  

ЦитироватьFrigate пишет:

ISRO crosses yet another milestone

ЦитироватьSaturday, Dec 20 2008
The Indian Space Research Organisation (ISRO) has successfully conducted
a test of its indigenous cryogenic (supercooled fuel) engine to be used in the
next geosynchronous launch vehicle (GSLV-D3) mission...

ISRO plans to use its own first cryogenic engine in place of the
Russian-made engine in the upper stage of the rocket that will deploy
the satellite with navigation and technology payloads into the
geosynchronous transfer orbit (GTO).

The cryogenic engine develops a thrust of 73 kN in
vacuum with a specific impulse of 454 seconds and can carry 2.2 tonnes.

Молодцы индийцы - довели движок "до ума"!  8)
"Под лежачий камень вода не течет" :oops:

Для сравнения: GSLV Payload to GTO 2,500 kg (это с 12КРБ)

ЦитироватьFrigate пишет:

Пока ещё не летал (2009 год). Кстати его называют indigenous - это "самостiйний" в переводе с индийского на "рiдну мову", хотя у нас - indigenous people это австралийские аборигены.

По РБ C-25 гораздо больше информации и выглядит он посолиднее:

Разгонный Блок C25
Ракета-носитель GSLV-III
Удельный импульс 443 сек
Начальная масса 30366 кг
РЗТ 25790 кг
Конечная масса 4576 кг
Двигатель CE20
Тяга в пустоте 20458кгс

ЦитироватьВ смысле, вот это?

(http://www.b14643.de/Spacerockets_1/India/GSLV/Gallery/gslv--Mk3.jpg). (http://www.b14643.de/Spacerockets_1/India/GSLV/Gallery/gslv-MkIII.JPG)

ЦитироватьКажется, был уже разрез по-лучше. Тогда еще обсуждали неоптимальность куцего ЦБ и больших ТТУ. Они же еще, вроде, как не разредялются - одна цельная 1-я ступень. И ТТУ работают дольше ЦБ...

ЦитироватьThe GSLV-III or Geosynchronous Satellite Launch Vehicle Mark III , is a launch vehicle currently under development by the Indian Space Research Organization. GSLV Mk III is conceived and designed to make ISRO fully self reliant in launching heavier communication satellites of INSAT-4 class, which weigh 4500 to 5000  kg. It would also enhance the capability of the country to be a competitive player in the multimillion dollar commercial launch market. The vehicle envisages multi-mission launch capability  for GTO, LEO, Polar and intermediate circular orbits.

GSLV-Mk III is designed to be a three stage vehicle, with 42.4 m tall with a lift off weight of 630 tonnes. First stage comprises two identical S200 Large Solid Booster (LSB) with 200 tonne solid propellant, that are strapped on to the second stage, the L110 re-startable liquid stage. The third stage is the C25 LOX/LH2 cryo stage. The large payload fairing measures 5 m in diameter and can accommodate a payload volume of 100 cu m. The development work on Mk III is progressing as per schedule for a launch in 2011.

Typical Parameters of GSLV Mark III
 Lift-off weight    629 tonne
 Pay Load   4 Tonne in to Geosynchronous Transfer Orbit (GTO)
 Height   49 metre

ЦитироватьGSLV Mk-3 (LVM3)
(https://img.novosti-kosmonavtiki.ru/80534.jpg)

Weight    629 ton
Height   49 m
GTO Weight   10 ton
GEO Weight        4.5 - 5 ton

GSLV-Mk III will launch a four ton payload into geosynchronous transfer orbit and up to 10-ton satellites in low Earth orbit. The launcher was initially expected to become operational by 2010/2011 with first flight in 2009-10.  However, in October 2009, outgoing ISRO chief G Madhavan Nair said that first flight of the launcher had been rescheduled for 2011, because of ISRO's focus on the Manned Space Program.

The launcher will be eventually used for the Indian manned space flight program. It will allow the Indian Manned Spacecraft to carry three astronauts instead of the two planned with the GSLV Mk II.
 
The launcher is not a derivative of GSLV. It is a completely new design.

It is a three-stage launcher with a 110 ton core liquid propellant stage (L-110) using two Vikas engines, a strap-on stage with two solid propellant H200 motors, each with 200 ton propellant (S-200), and a cryogenic upper stage with a propellant loading of 25 tonne (C-25).

ЦитироватьBox: Solid propellant boosters of different rockets

Parameter...................... Space Shuttle......... Ariane 5........ GSLV MK III

...........................................USA................... Europe..............India

1.Diameter (metre).............. 3.6...................... 3.05................ 3.2

2.Length (metre).................. 37.8..................... 31.6................ 25

3.Number of Segments.......... 4.......................... 3.................... 3

4.Propellant Type ............Ap+Al+HTPB........Ap+Al+HTPB.....Ap+Al+HTPB

5.Total Mass (tonne).............500....................... 276................ 220

6.Propellant Mass (tonne)......440........................240................200

7.Average Thrust(tons).........1,040......................500................400

8.Nozzzle gimballing...........8 degree................. 6 degree........ 8 degree

9.Firing duration (seconds)....123........................130................103

10.Motor case Material..........Steel......................Steel..............Steel

Source: Industry

ЦитироватьISRO to up mission rate; developing semi-cryogenic technology news

27 November 2009
Bangalore: The Indian Space Research Organisation (ISRO) will step up the frequency of missions, even as it sets larger objectives for itself in areas of national development and space science. The organisation will also seek to create synergy between space, defence, aeronautics and atomic energy sectors, according to the newly installed chairman, K Radhakrishnan.

''The Indian Space Research Organisation will aim at launching between six and eight missions every year to meet its objectives in the areas of national development and space science,'' ISRO chairman, K Radhakrishnan said here Thursday.

''We must look to create synergy between the space industry and the aircraft, defence and atomic energy sectors,'' he said in his address to the 23rd National Convention of Aerospace Scientists here. ''The Indian space industry is robust, comprising 500 firms and employing a total of 15,000 people.''

India's first launch vehicle with an indigenous cryogenic engine, the GSLV-D3 (Geo-synchronous Satellite Launch Vehicle) was in the final stages of preparation, he said. The launch is scheduled for December 2009, though Radhakrishnan did not reveal the launch date.

Radhakrishnan also revealed that Indian space scientists were developing semi-cryogenic propulsion technology, which will use kerosene and allow Indian launcher rockets to carry payloads of upto six-tonnes, nearly three times more than their current capability.

[color=yellow:4aec22dc45]While cryogenic technology uses liquid hydrogen and liquid oxygen, semi-cryogenic technology will use pure kerosene (aviation-grade) instead of liquid hydrogen.[/color]

ЦитироватьTuesday, December 22, 2009
Ground-firing of S200

ISRO is supposed to take the first step towards the launch of GSLV-Mk III by ground-firing the S200 booster in January, 2010. S200 is a major component of the Mk-III, providing the thrust at lift-off of the launch vehicle.

The S200 is the third biggest solid booster of any launch vehicle in active service, after the space Shuttle's SRBs and Ariane-5's EAP. This in a way shows that India is going beyond what was historically thought to be a Soviet-based space program. It's a matter of fact that Soviet and soviet based programs like the Chinese, never use solid propellent on their heavy-launch vehicles. Whereas, it's the western space programs that are famous for their extensive use of solids in heavy-lift vehiclea and crew-launch vehicles.

The S200 is a expendable stage carrying 200 tons of propellant with a lenght of 25 m and diameter of 3.2 m. The thrust at liftoff should be around 7000 kN. But, the average thrust output should be around 4500 kN to go with the stated burn-time of 103-104 seconds.

The ground-firing of the S200 will mark the successful development of 2 stages of the Mk-III, viz the L110 and the S200. The C25 is the final stage that remains. According to reports, ISRO has already finalized the design of CE-20 and that the process of fabrication also seems to have started. Once the engine is completed, its will be tested extensively following which there will be full-stage firing of the C25 stage.

Althought ISRO has quoted a launch of 2011 for the Mk-III, it would be an almost improbable task given the status of the upper stage. Fabrication to certication normally takes around 2-3 years. So, it would be safe to assume that the probable launch date of Mk-III would more-likely be 2012-13.

ЦитироватьНасколько всё-таки индийские ТТУ несовершенны.  :(

11.Specific Impulse(seconds).........291......................271................206

ЦитироватьУ SRB Шаттла секундный расход 440 000 кг/123 с = 3577 кг/с
УИ=тяга/расход=1 040 000 кгс/3577 кг/с = 290,7 с

У S200 секундный расход 200 000 кг/103 с=1942 кг/с
УИ=тяга/расход=400 000 кгс/1942 кг/с= 206 с

Где ошибка?

Цитировать

ЦитироватьУ SRB Шаттла секундный расход 440 000 кг/123 с = 3577 кг/с
УИ=тяга/расход=1 040 000 кгс/3577 кг/с = 290,7 с

У S200 секундный расход 200 000 кг/103 с=1942 кг/с
УИ=тяга/расход=400 000 кгс/1942 кг/с= 206 с

Где ошибка?

Может в неверной инфе? Например у бустера шаттла на википедии написана масса пустого 91т а с топливом 591т, получается уи 256 с.

ЦитироватьЕдинственно чему можно верить это УИ S200 в 206 с. :roll:
Но он скорее всего земной. Вакуумный видимо около 230 с.

ЦитироватьТак у него ж тяга не постоянная, в районе начала максимум наверняка.

ЦитироватьSuccessful static testing of Solid Propellant Booster Rocket Stage S200 for GSLV Mk III Launch Vehicle

(https://img.novosti-kosmonavtiki.ru/61795.jpg)(https://img.novosti-kosmonavtiki.ru/61796.jpg)

Indian Space Research Organisation successfully conducted the static test of its largest solid booster S200 at Satish Dhawan Space Centre (SDSC), Sriharikota today (January 24, 2010). The successful test of S200 makes it the third largest solid booster in the world, next to the RSRM solid booster of Space Shuttle and P230 solid booster of ARIANE-5. The S200 solid booster will form the strap-on stage for the Geosynchronous Satellite Launch Vehicle Mark III (GSLV-Mk III) which is currently under advanced stage of development for launching 4 ton class of communication satellites.

S200 solid booster contains 200 tonnes of solid propellant in three segments. The motor measures 22 meter long and 3.2 meter in diameter. The design, development and successful realisation of S200 solid booster were a pure indigenous effort involving Vikram Sarabhai Space Centre, Thiruvananthapuram and Satish Shawan Space Centre (SDSC) at Sriharikota with the participation of Indian Industries. The S200 solid booster derived its heritage from the solid boosters developed earlier for the ISRO launch vehicle programme. The preparation and casting of S200 solid booster segments were carried out at the newly established Solid Propellant Plant (SPP) at SDSC, Sriharikota.

During the test, the S200 booster was fired for 130 seconds and generated a peak thrust of about 500 tonnes. The performance of the booster was exactly as predicted. Nearly 600 health parameters were monitored during the test and the initial data indicates normal performance.

Todays successful test of S200 is a major milestone in the solid rocket motor programme of ISRO and a vital step in the development of GSLV Mk III.

ЦитироватьНадо заметить, что этот РДТТ уже приближается к Европейским/Американским. Качающееся сопло, относительно высокий УИ...

ЦитироватьА интересно, что дешевле ТТУ или  ЖРД ? т.е. чем дешевле выводить в конечном итоге?

ЦитироватьОдно я знаю, что ЖРД меньше отравляет атмосферу по сравнению.

ЦитироватьОдно я знаю, что ЖРД меньше отравляет атмосферу по сравнению.

Цитировать

ЦитироватьОдно я знаю, что ЖРД меньше отравляет атмосферу по сравнению.

Тут вы сильно заблуждаетесь. В выхлопе ТТРД полно соляной кислоты и хлорорганики, в то время, как у ЖРД проценты (к полному выхлопу) окислов азота, в основном же молекулярный азот и вода.

ЦитироватьОдно я знаю, что ЖРД меньше отравляет атмосферу по сравнению.

Цитировать(http://beta.thehindu.com/multimedia/dynamic/00027/AVN23_GSLV_27187e.jpg)
ALL SET FOR ANOTHER MILESTONE: The L-110 stage of GSLV Mk-III undergoing final preparations for testing at the test stand at Mahendragiri, near Nagercoil, in Tamil Nadu. It is called L-110 stage because it is powered by 110 tonnes of liquid propellants. Photo: ISRO

CHENNAI, January 23, 2010
Towards self-reliance in launch vehicle technology
T. S. Subramanian

GSLV Mk-III, is the most powerful rocket to be built by ISRO, will make India totally self-reliant in launch vehicle technology for launching INSAT class of communication satellites which are now being put in orbit for India by the European launcher Ariane-5.

"Towards sustained self-reliance in accessing space, GSLV Mk-III, the next generation launch vehicle," announces a stylish poster on India's Geo-synchronous Satellite Launch Vehicle Mark III, which is currently under development.

The poster, along with a model of the GSLV Mk-III, was prominently displayed in the Indian Space Research Organisation's (ISRO) pavilion, "Pride of India," during the Indian Science Congress held recently at Thiruvananthapuram.

The GSLV Mk-III will make India totally self-reliant in launch vehicle technology for launching INSAT class of communication satellites which are now being put in orbit for India by the European launcher Ariane-5.

In the fourth week of this month, the ISRO will cross a milestone in its efforts to develop this aerial powerhouse called the GSLV Mk-III when one of its two gigantic strap-on booster motors, S-200, erupts into life and fires for about 130 seconds. The motor will fire at the massive new test facility built at the Satish Dhawan Space Centre (SDSC), Sriharikota. The motor is called S-200 because it is powered by 200 tonnes of solid propellants.

The Vikram Sarabhai Space Centre (VSSC), Thiruvananthapuram, has designed S-200, and propellant casting has been done in a newly built plant at Sriharikota. The final preparation for ground-testing of the motor is progressing at Sriharikota and test readiness is being reviewed by the Test Authorisation Board chaired by SDSC Director M.C. Dathan.

In February first week, the ISRO will cross another milestone when the GSLV Mk-III's core stage (L-110), powered by 110 tonnes of liquid propellants, fires for about 200 seconds at the huge test stand at the Liquid Propulsion Systems Centre (LPSC) at Mahendragiri near Nagercoil in Tamil Nadu.

Short-duration test

A test for 15 seconds will be done to validate the performance of the engine and the associated ground facilities before the long-duration test is conducted for 200 seconds. The final preparations for testing the L-110 stage are on at Mahendragiri under the guidance of LPSC Director M.K.G. Nair.

Sub-systems are getting ready for undergoing tests at the same facility for the upper cryogenic stage, which will be fuelled by 25 tonnes of liquid oxygen and liquid hydrogen.

If everything goes on schedule, the first flight of the GSLV Mk-III will take place by the end of 2011. It is the most powerful rocket to be built by the ISRO, weighing 630 tonnes and 43.5 metres tall. It can put a satellite weighing four tonnes in a geo-synchronous transfer orbit with a perigee of about 200 km and an apogee of 36,000 km. It can put a satellite weighing 10 tonnes in a near-earth orbit at an altitude of about 300 km.

It has three stages. The two boosters, S-200, form the first stage. The boosters hug the core/second liquid stage. Above this liquid stage is the cryogenic stage.

"S-200 stage is the third largest stage in the world. Preparations are on for the first static test of the S-200 motor at Sriharikota. It will be a milestone in the GSLV Mk-III's development," said VSSC Director P.S. Veeraraghavan. S-200 is the third largest booster after the NASA Space Shuttle and Arianespace Ariane-5's boosters.

According to N. Narayana Moorthy, Project Director, GSLV Mk-III, the ISRO executed a massive programme of building the infrastructure needed for the project at Sriharikota, Mahendragiri and in Thiruvananthapuram. Out of Rs. 2,500 crore allocated to the project, Rs. 1,600 crore was earmarked for building infrastructure including facilities for assembling and testing the solid, liquid and cryogenic engines and their stages, and integration halls at Sriharikota, Mahendragiri and in Thiruvananthapuram. A big plant for manufacturing the solid propellants needed for S-200 boosters has come up at Sriharikota.

"The ISRO has built big facilities in the launch complex at Sriharikota for handling and integration of the GSLV Mk-III. These include erection of a new mobile launch pedestal since the core vehicle's diameter is four metres," said Mr. Narayana Moorthy. Major facilities have come up at the VSSC and Sriharikota for structural testing of different hardware including propellant tanks and light alloy structures.

"We have completed building most of the infrastructure and we are starting the testing phase. The launch schedule will depend on the outcome of the ground tests," said Mr. Narayana Moorthy.

GSLV Mk-III's motor S-200 will be tested in the last week of January If everything goes on schedule, the first flight will take place by 2011-end

ЦитироватьThe GSLV has flown five times since 2001 with a Russian hydrogen-fueled third stage originally built for the Proton rocket. The Russian third stage is blamed for two minor mishaps in 2001 and 2007 that resulted in an underperformance of the rocket, leaving its payloads in slightly different orbits than planned.

Цитировать

ЦитироватьНадо заметить, что этот РДТТ уже приближается к Европейским/Американским. Качающееся сопло, относительно высокий УИ...

А массовое совершенство существенно лучше.

ЦитироватьДмитрий В. пишет:

А еще они хотят на Луну!

"В 2015 году Индия намерена реализовать свой первый пилотируемый полет, а в перспективе — высадиться на Луну. Сценарий индийской лунной миссии, озвученный на 60-м конгрессе IAF, основан на использовании двух тяжелых РН.
Первая, стартовой массой 3075 т, несет разгонную ступень C60 массой 67 т (включая 60 т криогенного топлива) и лунный модуль (17 т). Ракета будет оснащена криогенной первой ступенью C800 (800 т топлива), окруженной восемью твердотопливными ускорителями S230 (230 т топлива в каждом).
Вторая РН, стартовой массой 1690 т, должна вывести на орбиту служебный (25 т) и командный (6 т) модули лунного корабля. Эта ракета аналогична первой, но оснащена лишь четырьмя ускорителями. В остальном сценарий напоминает миссию Saturn – Apollo".

ЦитироватьFrigate пишет:

Старый - исключительно для Вас (в смысле "история болезни" и "приступы лунатизма" [Шутливо] :P:
Presentation on the Indian space program given at the recent IAC2009 meeting in South Korea:

The plan of India to land on the Moon in 2025

ЦитироватьDuring the 60th IAC (International Astronautical Congress) in Daejeon (South Korea), a plenary session (15 October 2009, a.m.) was dedicated to Human Lunar Exploration. Dr. V. Admurthy, Associate Director, ISRO VSSC (Vikram Sarabhai Space Center), presented the ambitions of India in the exploration of the Moon, Mars, of asteroids and comets. During his 6-minute speech, he spoke about the preparation of a probe to explore the Toutatis asteroid to be launched on 20 October 2015 and will fly by Toutatis in August 2020 when it comes close to our planet. He described the strategy of India's Department of Space to achieve manned spaceflight around the Earth and to the lunar surface! In his conclusion, he insisted on the economical, architectural and ethical aspects of manned lunar missions, on the technological spin-offs and the international character of such an venture. India affirms its readiness to contribute to this challenging odyssey.

On a slide (see images below), Theo Pirard, who attended the conference, discovered the projected plan of the Indian manned Mission on the Moon, which is the result of recent feasibility studies made by ISRO. This plan offers some similarities with the US Constellation programme for the return to the Moon but no date could be announced, because of lack of money.

(https://img.novosti-kosmonavtiki.ru/10665.jpg)
(https://img.novosti-kosmonavtiki.ru/10666.jpg)

ЦитироватьTwo new super-boosters, derived from the next GSLV MkIII launcher, have to be developed by India for operations from Sriharikota Island:

- The 3.075-t rocket, consisting of 8 S230 (solid boosters of 230 t) and SC800 (core stage with semi-cryogenic engines of 2000 kN and 800 t of cryogenic propellant) as the 1st stage and of C60 (1 engine and 60 t of cryogenic propellant) as the 2nd /upper stage) will put into low earth orbit the EDS (Earth Departing Stage) of 67 t with the LM (Lunar Module) of 17 t.

- The 1.690-t rocket, consisting of 4 S230 (solid boosters of 230 t) and SC500 (core stage with semi-cryogenic engines of 2000 kN and 500 t of cryogenic propellant) as the fist stage and of C60 (1 engine and 60 t of cryogenic propellant) as the upper stage will launch the manned CM (Crew Module) of 6 t with its SM (Service Module) of 25 t.

The EDS has to send in trans-lunar trajectory a payload of around 48-50 t. India is starting the technological R & D efforts for the semi-cryogenic engine of 2000-KN thrust, which represents a great challenge for its future in space.

You can find the video of his presentation on YouTube (minute 16.00 -22.10) on the site http://www.iafastro.com/index.html?title=IAC2009_Plenary_7.

There is also a description of the Russian project to visit the Moon with manned spaceships and a short presentation of the Chinese Space Programme, including the next Chang'E missions of lunar exploration.

А вообще смеётся тот, кто стреляет последним - у Индии может и не хватать средств,
но зато есть ОГРОМНАЯ политическая ВОЛЯ, и лично я желаю им успеха [Восклицание]
Может быть индо-китайская космическая гонка заставит пересмотреть планы РКА и
НАСА в отношении Луны [Вопрос]
Огромное спасибо за статью пользователю TopSpacer [/b0]с сайта www.hobbyspace.com (Опубликована в декабре 2009 года).
Video

ЦитироватьFrigate пишет:

Слайды из презентации V. Adimurthy (ISRO):
(http://i055.radikal.ru/1002/d9/e1715d30c5c3.jpg)(http://s42.radikal.ru/i096/1002/0d/b9b3a1aa535a.jpg)(http://i073.radikal.ru/1002/94/ff08ae2c49cc.jpg)
(http://s47.radikal.ru/i116/1002/c7/e4faa6a059f3.jpg)(http://s004.radikal.ru/i208/1002/5a/20f2567cc1e7.jpg)

ЦитироватьFrigate пишет:

Flight-Testing Of Cryogenic Stage Of GSLV In April (http://www.space-travel.com/reports/Flight_Testing_Of_Cryogenic_Stage_Of_GSLV_In_April_999.html)

(https://img.novosti-kosmonavtiki.ru/10685.jpg)

ЦитироватьIndian Space Research Organisation Chairman K. Radhakrishnan has said the flight- testing of the indigenous cryogenic stage of the GSLV D3 would be conducted in April.

Talking to reporters after receiving the Doctor of Science (Honoris Causa) at the fifth convocation of SRM University here, Radhakrishnan said: The vehicle would carry GAST-4, a communication satellite. Though we had several GSLV flights, we were using the Russian cryogenic stages."

"As far as cryogenic engine and stages were concerned, ISRO had tested engines for 7,500 seconds," he added.

The country's first unmanned lunar mission, Chandrayaan, was launched in late October, 2008.

The second unmanned project, Chandrayaan-II, will be launched in the first quarter of 2013 - a prelude to the manned space mission.

India is emerging as a major player in the multi-billion dollar space research and space missions.

ЦитироватьGearing up for future

Mon, Feb 15 01:51 AM

Scientists at Indian Space Research Organisation (ISRO) are all fired up these days. Buoyed by the recent success of the ground test of the S-200 solid propellant rocket motor for the geosynchronous satellite launch vehicle mark III (GSLV-Mk III)—the third largest solid propellant boosters in the world after the US Space Shuttle's booster and Europe's Ariane and the largest solid rocket booster in Asia—they have reached a milestone in space technology.

The development is significant as the S200 forms a key component of the GSLV-Mk III launch vehicle that ISRO is developing and is currently under advanced stage of development for launching 4-tonne class of heavy communication satellites. More specifically, ISRO is developing the GSLV-Mk III to enhance the capability of the country to be a competitive player in the multi-million dollar commercial launch market. It will also allow India to become less dependent on foreign rockets for heavy lifting.

India is keenly developing its GSLV technology to enhance indigenous launching capabilities for heavy satellites of four tonne category. Unlike the polar satellite launch vehicle (PSLV), which is used to put lighter satellites into orbit 600 to 800 km above the earth's surface, the GSLV is used to put heavier satellites into the geosynchronous orbit which is 36,000 km above the earth's surface. Hence, GSLV is a much bigger and more powerful rocket. ISRO is also considering usage of GSLV for the Chandrayaan-II mission scheduled for 2012. Earlier, ISRO used PSLV to launch Chandrayaan-I.

Confidence of ISRO scientists is already high as the US space agency NASA signed an agreement with the Indian space agency to use data from Indian satellite Oceansat-2, for various American agencies for research activities, including weather forecasting. Launched on September 23, 2009 using the PSLV from Sriharikota, Oceansat-2 is designed to provide service continuity for operational users of the ocean colour monitor (OCM) instrument on Oceansat-1.

ISRO chief K Radhakrishnan says, "GSLV-Mk III is expected in the coming years. And a major milestone in the development is going to be the static testing of the systems." He adds, "We could realise the world's third largest propellant boosters H200 with 200 tonne of propellants mixed in India, in a plant which is mostly automatic. It is located in Sriharikota with our own technology and the ingredients based on our technology coming from the Indian industry ."

ISRO officials inform that GSLV-Mk III is conceived and designed to make the space agency fully self reliant in launching heavier communication satellites of INSAT-4 class, which weigh 4,500 to 5,000 kg. The vehicle envisages multi-mission launch capability for geostationary transfer orbit (GTO), low earth orbit (LEO), polar and intermediate circular orbits.

S200 solid booster contains 200 tonne of solid propellant in three segments. The motor measures 22 meter long and 3.2 meter in diameter. The design, development and successful realisation of S200 solid booster were a pure indigenous effort involving Vikram Sarabhai Space Centre, Thiruvananthapuram and Satish Shawan Space Centre (SDSC) at Sriharikota with the participation of Indian companies. The S200 solid booster derived its heritage from the solid boosters developed earlier for the ISRO launch vehicle programme. The preparation and casting of S200 solid booster segments were carried out at the newly established solid propellant plant (SPP) at SDSC, Sriharikota.

During the test, the S200 booster was fired for 130 seconds and generated a peak thrust of about 500 tonne. The performance of the booster was exactly as predicted, ISRO officials inform. Nearly 600 health parameters were monitored during the test and the initial data indicated normal performance.

The GSLV-Mk III is a three-stage satellite launch vehicle with a 110 tonne core liquid propellant stage (L-110) and a strap-on stage with two solid propellant motors, each with 200 tonne propellant (S-200). Once operational, GSLV Mk-III will have a lift-off weight of about 629 tonne. In place of small solid strap-on boosters used in the PSLV, the GSLV uses four liquid boosters that are derived from the PSLV second stage. The same solid first stage and liquid second stage are carried over from the PSLV. The third stage is a cryogenic hydrogen/oxygen upper stage.

The development work on GSLV-Mk III began in October 2002. ISRO executed a massive programme of building the infrastructure needed for the project at Sriharikota, Mahendragiri and in Thiruvananthapuram. Out of Rs 2,500 crore allocated to the project, Rs. 1,600 crore was earmarked for building infrastructure including facilities for assembling and testing the solid, liquid and cryogenic engines and their stages, and integration halls at Sriharikota, Mahendragiri and in Thiruvananthapuram. A facility for manufacturing the solid propellants needed for S-200 boosters has also been set up at Sriharikota.

"ISRO has built big facilities in the launch complex at Sriharikota for handling and integration of the GSLV Mk-III. These include erection of a new mobile launch pedestal since the core vehicle's diameter is four metres," say ISRO officials. Major facilities have also been built for structural testing of different hardware, including propellant tanks and light alloy structures.

In 2008, the government gave the go ahead to ISRO to develop an indigenous semi-cryogenic engine that would power the core stages of future Indian launch vehicles. The project has been one of the priorities of ISRO and it plans to complete the development phase of the project by 2012. India has been importing the cryogenic engines from Russia since 1991. So far, India has launched five GSLV rockets. But now ISRO has developed its own cryogenic engines and all the tests have been completed successfully.

ISRO plans to replace the core stage of GSLV-Mk III with a more powerful engine. The new core stage will be powered by a single, possibly ground-ignited semi cryogenic engine with the propellant mass being similar to the present 110 tonne. This change will increase the capability of Mk-III to about 6 tonne to GTO and about 15 tonne to LEO. Upper stage upgrades could further increase the GTO performance.

The timeline of these upgrades would depend on timeline of development of the GSLV-Mk III programme. By current estimates, this will happen no sooner than 2015 possibly even later. But testing these new technologies on GSLV-Mk III could act as a testing ground for the future family of launch vehicles. The flight testing of the indigenous cryogenic stage of the GSLV D3 would be conducted in April. The vehicle would carry GAST-4, a communication satellite.

ISRO scientists are developing next generation rockets capable of carrying more astronauts, and orbiting heavier satellites. Senior scientists at the country's space agency say the GSLV Mk III will ultimately make the country self-sufficient in launching the entire range of satellites. "If everything goes through successfully, we can attempt a launch by 2011 beginning," ISRO officials inform.

Truly, Indian rocket scientists are gearing up for future missions.

Huma Siddiqui

ЦитироватьДмитрий В. пишет:

Хм, а где обещанные в первую неделю февраля ОСИ ступени L110? :roll:

ЦитироватьMarch 06, 2010

Static testing of L110 liquid core stage of GSLV- MkIII launch vehicle conducted

Indian Space Research Organisation conducted the static test of its liquid core stage (L110) of GSLV Mk III launch vehicle, for 150 seconds at its Liquid Propulsion Systems Centre (LPSC) test facility at Mahendragiri at 16:00 hrs yesterday (March 5, 2010).

While the test was originally targeted for 200 seconds it was stopped at 150 seconds since a deviation in one of the parameters was observed. About 500 important parameters were monitored during the static test. The next static test for 200 seconds will be conducted after analysis of this data.

GSLV Mk III launch vehicle is being developed for launching 4 tonne class of satellites in Geo-synchronous Transfer Orbit (GTO). Measuring 17 meters in length and 4 meters in diameter, L110 is an earth storable liquid propellant stage with propellant loading of 110 tonnes. L110 stage uses two high-pressure Vikas engines in a clustered configuration and draws its heritage from the second stage of PSLV and GSLV and strapons of GSLV.

ЦитироватьSunday, March 7, 2010 at 9:23 AM
L110 Liquid Engine Static Test failed - ISRO

ISRO HQ Bangalore, March 6: A static ground test of a core stage of a new-generation heavyweight rocket for the future GSLV MK3, planned by the Indian Space Research Organisation, has failed, the space agency announced today.

The liquid-fuelled core stage of the GSLV-Mk3 rocket was to fire for 200 seconds during the ground test at Isro's Liquid Propulsion Systems Centre in Mahendragiri, Tamil Nadu, but was stopped after 150 seconds, Isro sources said.
India's existing Geosynchronous Satellite Launch Vehicle rockets can ferry a 2,000kg- class satellite towards a geostationary orbit 37,000km above Earth. The GSLV-Mk3 is expected to carry a 4,000kg-class satellite towards a geostationary orbit.
The GSLV-Mk3 can also carry a 10,000kg payload into a low-earth orbit — an altitude of about 200km — and is thus viewed as a crucial technology that Isro will need to develop in its bid to launch manned space capsules.
"The ground test on Friday evening was stopped after engineers detected an unanticipated deviation in one of the parameters being observed during the firing," an ISRO official told. While the rocket fires in the static mode, engineers keep track of more than 500 parameters, such as temperatures at various points in the rocket, liquid flow rates and pressure levels, the official said.
The next static ground test will be conducted after analysis of this data. The liquid-fuelled stage has 110 tonnes of propellant and is similar to the liquid stages used in Isro's existing GSLV rockets — only with a greater capacity. In the existing GSLV, it burns for 150 seconds; the GSLV-Mk3 will demand 200 seconds of firing.

The test was aborted after some "minor leakage in the command system", PTI reported, quoting Isro sources. It is a "very minor problem" in which a small leak in the command line was detected by a computer, which automatically stopped the test. "There is absolutely no problem with the engine," a source said. Earlier this year, Isro had successfully conducted ground tests of S200 Solid stages of the rocket.

All the Best ISRO - For the next static test of Liquid 110 and Cryo 25...

Цитироватьhttp://only2you.blogspot.com/2010/03/l110-liquid-engine-static-test-failed.html

ЦитироватьSunday, March 7, 2010  at 9:23 AM
L110 Liquid Engine Static Test failed - ISRO

ISRO HQ Bangalore, March 6: A static ground test of a core stage of a new-generation heavyweight rocket for the future GSLV MK3, planned by the Indian Space Research Organisation, has failed, the space agency announced today.

The liquid-fuelled core stage of the GSLV-Mk3 rocket was to fire for 200 seconds during the ground test at Isro's Liquid Propulsion Systems Centre in Mahendragiri, Tamil Nadu, but was stopped after 150 seconds, Isro sources said.
India's existing Geosynchronous Satellite Launch Vehicle rockets can ferry a 2,000kg- class satellite towards a geostationary orbit 37,000km above Earth. The GSLV-Mk3 is expected to carry a 4,000kg-class satellite towards a geostationary orbit.
The GSLV-Mk3 can also carry a 10,000kg payload into a low-earth orbit — an altitude of about 200km — and is thus viewed as a crucial technology that Isro will need to develop in its bid to launch manned space capsules.
"The ground test on Friday evening was stopped after engineers detected an unanticipated deviation in one of the parameters being observed during the firing," an ISRO official told. While the rocket fires in the static mode, engineers keep track of more than 500 parameters, such as temperatures at various points in the rocket, liquid flow rates and pressure levels, the official said.
The next static ground test will be conducted after analysis of this data. The liquid-fuelled stage has 110 tonnes of propellant and is similar to the liquid stages used in Isro's existing GSLV rockets — only with a greater capacity. In the existing GSLV, it burns for 150 seconds; the GSLV-Mk3 will demand 200 seconds of firing.

The test was aborted after some "minor leakage in the command system", PTI reported, quoting Isro sources. It is a "very minor problem" in which a small leak in the command line was detected by a computer, which automatically stopped the test. "There is absolutely no problem with the engine," a source said. Earlier this year, Isro had successfully conducted ground tests of S200 Solid stages of the rocket.

All the Best ISRO - For the next static test of Liquid 110 and Cryo 25...

ЦитироватьGSLV to be launched on April 15

For the first time GSLV will be powered by home-made cryogenice engine. PSLV will take off on May 5

India's GSLV rocket, powered by home-made cryogenic engine for the first time, would be launched on April 15 from Sriharikota to place into orbit GSAT-4 experimental satellite. Previous GSLV flights were fitted with Russian engines.

The Indian Space Research Organisation (ISRO) also fixed May 5 as the date for the launch of the Cartosat-2B by Polar Satellite Launch Vehicle (PSLV).

The mission readiness review conducted by ISRO at Sriharikota yesterday finalised the dates, and gave the go-ahead for the two launches, sources in the space agency said.

Besides the Cartosat-2B, the PSLV would also have on board an Algerian satellite and some small and nano satellites, ISRO sources said.

ЦитироватьЧто-то он мне до боли напоминает... :roll:  :wink:  :)

ЦитироватьCryogenic Upper Stage Project (CUSP)

The major achievement during 2009 was the delivery of Cryogenic Upper Stage (CUS) in September 2009 after its successful flight acceptance testing during which CUS was hot tested for 720 seconds. The flight model of cryogenic engine was tested for duration of 200 seconds and test results met all the specified parameters.
The development of cryogenic engines involves mastering materials technology, operating rotary pumps and turbines that run at 42,000 rpm at cryogenic temperatures. The successful testing of CUS has enabled the country to achieve total self-reliance in launch vehicle technology.

The indigenous cryogenic engine develops a thrust of 73 kilo Newtons (kN) in vacuum with a specific impulse of 454 seconds and provides a payload capability of 2200 kg to Geosynchronous Transfer Orbit (GTO) for GSLV. The Engine works on 'Staged Combustion Cycle' with an integrated turbo pump running at around 42,000 rotations per minute (rpm). It is also equipped with two steering engines developing a thrust of 2 kN each to enable three-axis control of the launch vehicle during the mission. Another unique feature of this engine is the closed loop control of both thrust and mixture ratio, which ensures optimum propellant utilisation for the mission.

(https://img.novosti-kosmonavtiki.ru/62148.jpg)
Indigenous Cryogenic Upper Stage

GSLV-Mk III

GSLV-Mk III is envisaged to launch a four tonne satellite into Geosynchronous Transfer Orbit. GSLV-Mk III is a three-stage vehicle with a 110 tonne core liquid propellant stage (L-110) and a strap-on stage with two solid propellant motors, each with 200 tonne propellant (S-200). The upper stage will be cryogenic with a propellant loading of 25 tonne (C-25). GSLV- Mk III will have a lift-off weight of about 629 tonne and will be 42.4 m tall. The payload fairing will have a diameter of 5 metre and a payload volume of 100 cubic metre.

GSLV MkIII programme is presently in the hardware testing and qualification stage. The project has entered the phase of stage level tests for propulsion modules with the successful static test of S200 on January 24, 2010.

(https://img.novosti-kosmonavtiki.ru/62149.jpg)
S200 at its test facility

L110 development stage functional integration has been completed. Structural test facility for propellant tanks commissioned at SDSC, SHAR. Preparation and assembly of L110 stage for long duration hot test is progressing well at LPSC, Mahendragiri.

(https://img.novosti-kosmonavtiki.ru/62150.jpg)
L110 development stage

Indigenously developed turbo pump system of CE20 engine was successfully tested in integrated pressure fed mode for 60 seconds. First launch of GSLV Mk III is expected during 2011-12.

(https://img.novosti-kosmonavtiki.ru/62151.jpg)
CE20 Integrated Turbopump Hot Test in progress

ЦитироватьSemi Cryogenic Engine Development (SCED)
Semi-Cryogenic Engine development envisages the development of a high thrust engine producing 2000 kN (Vacuum) thrust with Liquid Oxygen and kerosene propellant combination for the Common Liquid Core in Unified Launch Vehicle (ULV). As part of semi-cryo engine development pre-project activities, five designs of single element pre-burner injector were realised and tested. Semi-cryo Project Report was prepared and clearance obtained. Conceptual design of the semi cryo engine has been completed.

ЦитироватьНу это только свидетельствует о достижениях хруничивцев, а так же, что ложная нац. гордость до добра не доводит.

ЦитироватьApril 15, 2010       PRINT THIS PAGE  
Flight testing of the Indigenous Cryogenic Stage in GSLV-D3 Mission not successful

The flight-testing of the indigenous Cryogenic Engine and the Stage conducted in the Geosynchronous Satellite Launch Vehicle GSLV-D3 this afternoon (April 15, 2010) was not successful.

GSLV-D3 vehicle lifted off as planned at 16:27 hrs after a countdown procedure lasting for 29 hours. The countdown went off as planned. GSLV-D3 vehicle performance was normal up to the end of the second stage (GS2) till 293 seconds.

Afterwards, the Cryogenic Stage was to ignite and burn for about 720 seconds to provide the necessary velocity to inject GSAT-4 Satellite into the intended Geosynchronous Transfer Orbit. It is yet to be ascertained whether the cryogenic engine did ignite. The vehicle was seen tumbling, lost altitude and finally splashed down in the sea.

Detailed analysis of the flight data is being carried out to find out the exact reasons for the failure and take corrective measures to realise the next flight test of the indigenous Cryogenic Engine and Stage within the next one year.

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ЦитироватьА вот вопрос: почему Мк3, имея три ступени, из которых верхняя - довольно мощная криогенная, имеет грузоподъемность на низкой орбите всего лишь 10т при стартовой массе, сопоставимой с Протоном? Маловато! :twisted:

Ну дык нижняя твердотопливная. 8)

Все равно мало! Тонн 15-18, имхо, должна была вытащить

ЦитироватьНаверняка не в первой дело. 4-х ступенчатая ракета с ТТ моторами, даже куски 3-й могут не сгореть в атмосфере.

ЦитироватьОчень странная картинка, особенно для ГПО. Что мешает стартовать строго на восток?

ЦитироватьА есть данные где падает первая ступень?

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ЦитироватьНаверняка не в первой дело. 4-х ступенчатая ракета с ТТ моторами, даже куски 3-й могут не сгореть в атмосфере.

Вторая ступень у ГСЛВ я так понимаю жидкостная а третья это уже КВРБ?

ЦитироватьВероятно, активное морское судоходство в предполагаемых районах падения, а также несогласие Таиланда, Малайзии, Вьетнама и прочих.

ЦитироватьЗ.Ы. Подозреваю, что в районе дальности 300-500 км. Если попадется - выложу сюда.

Цитировать(http://s40.radikal.ru/i088/1007/4b/bbf7d3d29f69.jpg)

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ЦитироватьНаверняка не в первой дело. 4-х ступенчатая ракета с ТТ моторами, даже куски 3-й могут не сгореть в атмосфере.

Вторая ступень у ГСЛВ я так понимаю жидкостная а третья это уже КВРБ?

Виноват, лопухнулся. Действительно нет никакой 4-й, и 3-я КВРБ.
-- Петр

ЦитироватьИнтересно, почему они не построили космодром на самом кончике Индостана? Хоть на полярное наклонение летали бы без проблем, да и на ГСО получше, чем сейчас.

ЦитироватьПересечение экватора в 3600 км от Шрихарикоты. Это гдето над Калимантаном. Ох, врёт первая картинка!

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ЦитироватьОх, врёт первая картинка!

Первая или вторая? ;)

ЦитироватьПервая показывает из GSLV только самый первый пуск.

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ЦитироватьИнтересно, почему они не построили космодром на самом кончике Индостана? Хоть на полярное наклонение летали бы без проблем, да и на ГСО получше, чем сейчас.

Шри Ланка перекрывает весь восточный сектор.

ЦитироватьА вот почему они не летают на ССО левее Шри Ланки?

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ЦитироватьИнтересно, почему они не построили космодром на самом кончике Индостана? Хоть на полярное наклонение летали бы без проблем, да и на ГСО получше, чем сейчас.

Шри Ланка перекрывает весь восточный сектор.
 А вот почему они не летают на ССО левее Шри Ланки?

ЦитироватьТак какая разница - что перекроет восточный сектор - Цейлон или Сиам?

ЦитироватьЭто как - левее? В западном направлении?

ЦитироватьЕсли лететь из Шрихарикоты строго на юг, пролетят аккурат над многомиллиардным Мадрасом. Если ещё западнее заворачивать - ещё больше густонаселенных территорий. :(
То ж самое касается и самой южной точки. При их плотности малозаселённость острова Шрихарикота вообще подарок судьбы.

ЦитироватьВот кому морской старт нужен!

ЦитироватьIndia-US Space Ties Take Off With PSLV[/size]
by Staff Writers[/size]
Mumbai, India (PTI) Jul 14, 2010
Almost a year ago on July 20, 2009, external affairs minister SM Krishna and US secretary of state Hillary Clinton met at Hyderabad House in New Delhi and signed what is known as Technology Safeguards Agreement (TSA) which strengthens Indo-US space ties.

On Monday, this pact became a reality when PSLV for the first time placed in orbit a satellite with a large number of US components. According to Isro officials, this flight is therefore politically important with regards to Indo-US relationship.

The satellite is nearly 200-kg Alsat (Algerian Satellite), owned by Algerian Space Agency and is built by a French company with several US-made parts. Isro officials said the Alsat launch was significant because it was the first one following the signing of the TSA between India and the US.

TSA facilitates the launch of US satellites and satellites with US components on Indian launch vehicles. It will cover launches involving satellites owned by US government or academic institutions or by third country space agencies and universities which have US equipment on board.

Soon after the historic Indo-US deal was clinched, executive director of Antrix Corporation, the commercial arm of Isro, K R Sridhara Murthy was quoted as saying that the agreement "will open up more satellite launch operations for India. Earlier, satellites built with US-manufactured components were not available for Indian launch vehicles,'' he said.

Officials said the launch of Alsat by India on Monday will inaugurate a new chapter in the country's space programme because it will finally open the way for the country to fly either American spacecraft or spacecraft having US parts.

According to them there were earlier instances when foreign countries were keen on launching their satellites from India primarily because of the low costs. But, American restrictions prevented them from doing so. "With Alsat the scene is now all set to change and India's market share of launching satellites will increase,'' an official told this newspaper.

ЦитироватьВы планы индийских пусков посмотрите и сразу станет ясно, кто будет тесниться.

ЦитироватьPSLV Milestones
      PSLV-C15 launched CARTOSAT-2B, ALSAT-2A, NLS 6.1 & 6.2 and STUDSAT on July 12, 2010 (Successful)
      PSLV-C14 launched Oceansat - 2 and Six Nanosatellites on September 23, 2009 (Successful)
      PSLV-C12 launched RISAT-2 and ANUSAT on April 20, 2009 (Successfully)
      PSLV-C11 launched CHANDRAYAAN-I, on October 22, 2008 (Successful)
      PSLV-C9 launched CARTOSAT-2A, IMS-1 and Eight nano-satellites on April 28, 2008 (Successful)
      PSLV-C10 launched TECSAR on January 23, 2008 (Successful)
      PSLV-C8 launched AGILE on April 23, 2007 (Successful)
      PSLV-C7 launched CARTOSAT-2, SRE-1, LAPAN-TUBSAT and PEHUENSAT-1 on January 10, 2007 (Successful)
      PSLV-C6 launched CARTOSAT-1 and HAMSAT on May 5, 2005 (Successful)
      PSLV-C5 launched RESOURCESAT-1(IRS-P6) on October 17, 2003 (Successful)
      PSLV-C4 launched KALPANA-1(METSAT) on September 12, 2002 (Successful)
      PSLV-C3 launched TES on October 22, 2001 (Successful)
      PSLV-C2 launched OCEANSAT(IRS-P4), KITSAT-3 and DLR-TUBSAT on May 26, 1999 (Successful)
      PSLV-C1 launched IRS-1D on September 29, 1997 (Successful)
      PSLV-D3 launched IRS-P3 on March 21, 1996 (Successful)
      PSLV-D2 launched IRS-P2 on October 15, 1994 (Successful)
      PSLV-D1 launched IRS-1E on September 20, 1993 (Unsuccessful)

ЦитироватьGSLV Milestones
      GSLV-D3 launched GSAT-4 on April 15, 2010 (Unsuccessful)
      GSLV-F04 launched INSAT-4CR on September 2, 2007 (Successful)
      GSLV-F02 launched INSAT-4C on July 10, 2006 (Unsuccessful)
      GSLV-F01 launched EDUSAT(GSAT-3) on September 20, 2004 (Successful)
      GSLV-D2 launched GSAT-2 on May 8, 2003 (Successful)
      GSLV-D1 launched GSAT-1 on April 18, 2001 (Successful)

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ЦитироватьВот кому морской старт нужен!

При их технологии сборки ракеты вертикально на стартовом столе он им как...
Не нужен, в общем.

ЦитироватьДо появления GSLV  MkIII никакой реальной конкуренции индийцы не составят, ибо 2200-2500 кг на ГПО слишком мало. Да и темп пусков на ГПО у них ниже всякой критики.

ЦитироватьДо появления GSLV  MkIII никакой реальной конкуренции индийцы не составят, ибо 2200-2500 кг на ГПО слишком мало. Да и темп пусков на ГПО у них ниже всякой критики.

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ЦитироватьВот кому морской старт нужен!

При их технологии сборки ракеты вертикально на стартовом столе он им как...
Не нужен, в общем.

У Индии довольно большие претензии на получение значительной доли рынка пусковых услуг.  По стоимости самый лакомый кусок этого рынка - пуски на ГСО и ГПО. Мощность индийских носителей ограничена, а разработка новых РН идет тяжело. Возможно, дешевле будет сделать морской космодром. А технологию сборкит можно и пересмотреть. Весь вопрос в соотношении эффекта и затрат.

ЦитироватьИнтересно, почему они не договорились с Мальдивами? Там полно необитаемых островов, самый экватор.

ЦитироватьISRO to conduct key test for GSLV Mk III rocket next week

Posted On: Sep 02, 2010

BANGALORE (PTI): After a failed test six months ago, Indian Space Research Organisation (ISRO) will be making a fresh attempt next week to conduct long-duration static test of a crucial liquid core stage for a new generation heavy rocket which is being developed.

"The static test of crucial liquid core stage (L110) of GSLV Mk III launch vehicle (rocket) for 200 seconds is slated for 3 pm on September eight," a senior ISRO official told PTI here.

A top ISRO team, including Director of ISRO's Liquid Propulsion Systems Centre (LPSC) S Ramakrishnan and Director of Vikram Sarabhai Space Centre (VSSC) P S Veeraraghavan, held a review meeting in Mahendragiri in Tamil Nadu on Wednesday and gave the go-ahead for the test.

Chairman of Bangalore-headquartered ISRO, K Radhakrishnan, is expected to witness the test at LPSC test facility in Mahendragiri, officials said.

ISRO conducted the test for 150 seconds at LPSC test facility on March five. While the test was originally targeted for 200 seconds, it was stopped at 150 seconds since a deviation in one of the parameters – minor leakage in the command system – was observed.

A small leak in the command line was detected by computer, which automatically aborted the test. About 500 important parameters were monitored during the static test.

ISRO has since analysed the data.

The GSLV Mk III rocket is being developed for launching four-tonne class of satellites in Geo-synchronous Transfer Orbit (GTO). Measuring 17 metres in length and four metres in diameter, the L110 is an earth storable liquid propellant stage with propellant loading of 110 tonnes.

The L110 stage uses two high-pressure Vikas engines in a clustered configuration and draws its heritage from the second stage of PSLV and GSLV and strapons of GSLV.

While in PSLV and GSLV, the liquid stage with single engine configuration burns for 150 seconds, the GSLV-Mk III requires burning for 200 seconds in a twin engine configuration.

India's PSLV and GSLV so far used one Vikas engine. But the heavy-rocket GSLV Mk III under development needs much better thrust. And hence, two Vikas engines were being used for the first time, they said.

ISRO has already successfully conducted the short-duration static test of the L110 stage, which uses two high-pressure Vikas engines in a clustered configuration.

In January this year, ISRO also successfully conducted static test of its largest solid booster S200, which would form the strap-on stage for the GSLV Mk III, at Satish Dhawan Space Centre (SDSC), Sriharikota.

The successful test of S200 made it the third largest solid booster in the world, next to the RSRM solid booster of NASA Space Shuttle and P230 solid booster of ARIANE-5.

ЦитироватьISRO proceeds on crucial liquid core stage for a new generation heavy rocket - a decisive Indian edge in Space and missile tech
Sunil Mehta
Sep. 3, 2010

Director of ISRO's Liquid Propulsion Systems Centre (LPSC) S Ramakrishnan and Director of Vikram Sarabhai Space Centre (VSSC) P. S. Veeraraghavan decided to give a green signal for the crucial test for Indian missile technology superiority.

The static test of crucial liquid core stage (L110) of GSLV Mk III launch vehicle (rocket) for 200 seconds is slated for 3 pm on September eight, according to official ISRO statements.

According to media reports, GSLV Mk III rocket is being developed for launching four-tonne class of satellites in Geo-synchronous Transfer Orbit (GTO). It will also boost Indian nuclear missile technology capabilities carrying far more load and more superior targeting technologies. Measuring 17 meters in length and 54 sq.meters in cross sectional area, L110 is an earth storage capable liquid propellant stage with propellant loading of 110 to 120 tonnes. It is ideal for heavier load and superior targeting. L110 stage uses two high-pressure Vikas engines in a clustered configuration. It is the advanced design from the legacy of the second stage of PSLV and GSLV and strapons of GSLV.

The advantage of this is that the GSLV-Mk III requires burning for 200 seconds in a twin engine configuration while in in PSLV and GSLV, the liquid stage with single engine configuration burns for 150 seconds.

ЦитироватьИндия провела испытания двигателя для лунной и пилотируемой миссий

20:01 08/09/2010

НЬЮ-ДЕЛИ, 8 сен - РИА Новости, Евгений Безека. Индия успешно провела в среду стендовые испытания жидкостной ступени для тяжелой ракеты GSLV Mark-III, которую предполагается использовать для запуска человека в космос, говорится в пресс-релизе Индийской организации космических исследований (ИСРО).

Предыдущие испытания этой ступени 5 марта 2010 года прошли неудачно: их пришлось прервать, так как было зафиксировано отклонение по одному из параметров.

Сегодняшние испытания прошли на полигоне в Махендрагири (штата Тимил-Наду) и продолжались запланированные 200 секунд. В ходе испытаний инженеры наблюдали за 500 параметрами работы ступени.

"Это важная веха на пути реализации программы ИСРО по созданию жидкостного ракетного двигателя на топливе наземного хранения и важный шаг навстречу разработке ракеты-носителя GSLV Mark-III", - говорится в пресс-релизе.

Ракета GSLV Mark-III находится на завершающей стадии создания. На ней будут применяться два подвесных ускорителя S200, содержащие 200 тонн твердого ракетного топлива, жидкостная ступень L110 с двумя двигателями "Викас" и разгонный блок на криогенном топливе С-25.

Подвесные ускорители S200 были испытаны в январе. Криогенный разгонный блок С-25 для Mark-III должен был впервые показать себя в деле 15 апреля в ходе запуска ракеты-носителя GSLV с рядом спутников на борту. Разгонный блок, однако, отказал, и ракета упала. Комиссия ИСРО установила, что причиной отказа стал бракованный кислородный насос. Новый запуск GSLV с С-25 запланирован на 2011 год. До этого момента ракеты GSLV будут запускаться в космос с использованием российских блоков "12КРБ".

Первый полет ракеты GSLV Mark-III в космос намечен на 2012 год. Ракета будет самой тяжелой среди всех индийских ракет и сможет выводить на геосинхронную орбиту аппараты массой до четырех тонн. В 2013 году GSLV Mark-III планируется использовать для реализации второй части индийской лунной миссии "Чандраян-2", в 2015 году - для возможной отправки на орбиту космонавтов.

ЦитироватьISRO plan to launch 8 spacecraft a year

Express News Service
First Published : 15 Sep 2010 03:37:36 AM IST
Last Updated : 15 Sep 2010 10:58:50 AM IST

CHENNAI: The Indian Space Research Organisation (ISRO) is planning to launch eight spacecraft a year to meet the increasing global demand, Vikram Sarabhai Space Centre (VSSC) director P S Veeraraghavan said on Tuesday.

Receiving PSOM-XL Motorcase, the critical hardware used in the launch vehicle for Polar Satellite Launch Vehicle (PSLV), he said: "Right now, we have four launches per year including PSLV and Geo-synchronous Satellite Launch Vehicle (GSLV). We need to throughput in getting various sub-systems from industries and increase our own internal work to increase it into eight launches a year."

Veeraraghavan said ISRO earned revenue of Rs 1,000 crore from commercial launch of satellites and was expecting a growth of 20-30 per cent per year. "India is among the top six space-faring countries in the world. We are capable of launching any spacecraft in polar orbit. But in geo-stationary orbit, we are short of capabilities. We could only launch a satellite with a payload of 2,380 kg," the scientist said.

However, India was planning big in GSLV through GSLV Mark III. ISRO was planning to launch heavier satellites with a payload of four tonnes. This would make the organisation fully self-reliant in launching heavier communication satellites of INSAT-4 class and also enhance the country's capability to be a competitive player in the multimillion dollar commercial launch market. The launch of GSLV Mark III has been planned for 2011-2012.

Veeraraghavan said ISRO would be launching three satellites through PSLV and one through GSLV in December. Through PSLV, we will launch ResourceSat besides two satellites of 90 kilogram each from Singapore and from Russia. Through GSLV we will put into orbit GSAT-5, a communication satellite. Both the launches will happen within a span of few weeks in December."

On the PSOM-XL motor fabricated by Ramakrishna Engineering Company, Veeraraghavan said while the six solid propellant strap-on motors in the standard PSLV carried nine tonnes of propellant, the new version PSOM-XL with a length of 13.5 metre had the capacity to carry a 12-tonne propellant. It would boost the capability of PSLV from 1,450 kg to 1,750 kg for a sun synchronous orbit. "The motor will be used in the launch of PSLV C18 and PSLV C19 in the middle of next year," he added.

ISRO was working on Human Spaceflight Programme (HSP) and had dedicated the third launchpad for manned mission. "We have sent in a Rs 450-crore-proposal for the first phase which includes unmanned orbital modules," he said.

T he programme has plans for the development of a fully autonomous orbital vehicle carrying two or three crew members to about 300 km low earth orbit and then bringing them back safely. On Chandrayaan 2, he said it would be launched by GSLV instead of PSLV. "Various payloads have been identified. It will have an orbiter developed by ISRO, a lander developed by Russia and Rover developed again by ISRO."

ЦитироватьIndia may seek international help on cryogenic engine
BY STEPHEN CLARK
SPACEFLIGHT NOW
Posted: October 12, 2010

PRAGUE -- India remains committed to perfecting an indigenous cryogenic upper stage for its most powerful rockets, but the leader of the country's space program is not ruling out asking for more Russian help.

(https://img.novosti-kosmonavtiki.ru/14596.jpg)
File photo of the Geosynchronous Satellite Launch Vehicle. Credit: ISRO

In the early stages of designing a new booster for communications satellites, India struck a deal with Russia to provide hydrogen-fueled rocket engines and technical know-how.

The agreement was quashed in 1992 after U.S. authorities imposed sanctions on Glavkosmos, the Russian company providing technology to India. The United States feared the transfer of missile technology from the fractured Soviet Union to developing states.

India responded by purchasing seven readymade cryogenic engines from Russia and starting the design of an indigenous upper stage from scratch.

The Russian design would become the third stage for India's first generation of Geosynchronous Satellite Launch Vehicles, a medium-lift rocket tailored to haul communications spacecraft to orbits high above Earth.

The GSLV first launched in 2001. Five of the rockets blasted off with Russian third stages through 2007.

The Russian stage was blamed for two minor glitches in 2001 and 2007 that stranded payloads in slightly different orbits than planned. A liquid-fueled strap-on booster triggered a dramatic explosion shortly after a launch in 2006.

Three other GSLV flights were successful.

After a $70 million development effort, India placed its first homemade cryogenic stage on the GSLV's sixth flight in April. But the third stage failed during ignition due to an anomaly in a liquid hydrogen turbopump, dooming the rocket and its payload.

(https://img.novosti-kosmonavtiki.ru/80766.jpg)
File photo of an indigenous GSLV cryogenic third stage. Credit: ISRO

Besides the new upper stage, the GSLV Mk.2 launched in April was nearly identical to previous versions of the booster.

Officials plan to fly another indigenous upper stage within a year. In the meantime, they are turning to a pair of Russian engines left over from the initial purchase nearly two decades ago.

"We ordered seven cryogenic stages," said K. Radhakrishnan, chairman of the Indian Space Research Organization, at the International Astronautical Congress in Prague. "Five have been used, and at the moment we have two stages."

The next two GSLV missions will fly with Russian stages, beginning with a launch in December to deploy the GSAT 5 communications satellite. Another GSLV will launch by the middle of 2011 with India's last Russian cryogenic engine, according to Radhakrishnan.

Earlier this year, the United States lifted sanctions levied against Glavkosmos in 1998 for weapons proliferation with Iran. The sanctions imposed for the company's partnership with India were removed in the early 1990s.

Asked whether India would consider requesting Russian assistance or purchasing more Russian engines, Radhakrishnan was non-committal.

"Let us see what we require," Radhakrishnan said. "Let us see the progress of the indigenous cryogenic upper stage."

India is also designing a cryogenic stage for the third-generation GSLV slated to debut in 2012 or 2013. The GSLV Mk.3 will be powered by a third stage consuming double the propellant of the indigenous GSLV Mk.2 engine that is now the focus of ISRO's rocket engineers.

ЦитироватьПрошла информация, что индусы собираются заказать ещё шесть РБ 12КРБ.

ЦитироватьIndia is also designing a cryogenic stage for the third-generation GSLV slated to debut in 2012 or 2013. The GSLV Mk.3 will be powered by a third stage consuming double the propellant of the indigenous GSLV Mk.2 engine that is now the focus of ISRO's rocket engineers.

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ЦитироватьFrigate пишет:

ИМХО похоже полетит "самостийний" индийский:
CE-20 Engine
(http://upload.wikimedia.org/wikipedia/en/thumb/7/7d/IndianCryoEngine25.JPG/450px-IndianCryoEngine25.JPG)

ЦитироватьThe specifications of the engine as listed on the LPSC handouts:

* Operating Cycle - Gas Generator
* Propellant Combination - LOX / LH2
* Thrust Nominal (Vacuum) - 200 kN
* Operating Thrust Range - 180 kN to 220 kN (To be set at any fix values)
* Chamber Pressure (Nom) - 6 MPa
* Engine Mixture ratio (Oxidizer/Fuel by weight) - 5.05
* Engine Specific Impulse - 443 ± 3 seconds
* Engine Burn Duration (Nom) - 595 seconds
* Total Flow rate - 462 kg/sec
* Nozzle Area ratio - 100
* Mass - 588 kg

Андрей Суворов пишет:

В total flow rate кто-то потерял десятичную запятую. А, может, "же", т.е. 9,81
Движок с УИ 443 и тягой 20 тонн жрёт 45 кило топлива в секунду, а не 450.
Кстати, либо они врут насчёт УИ, либо у кого-то калькулятор сломался, либо расход приведён не для номиналки.
Расход 46,2 кг/с при тяге 200 кН соответствует УИ 441 секунда.

Ну, либо в Индии "же" другое  :)  

Frigate пишет:

Не стреляйте в пианиста - играет так, как умеет  8) .
Вот картинка с выставки Aero India 2009 (проходила в феврале этого года):
(http://s16.radikal.ru/i190/0912/25/dab87cf87d43.jpg)

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ЦитироватьДмитрий В. пишет:

А СЕ-20 разве не для верхней ступени GSLV-III?

Frigate пишет:

СЕ-20 - Cryogenic Engine thrust 20 tonnf;
CS25 Cryogenic Stage 25 tonnes of propellant (для верхней ступени GSLV-III)

ЦитироватьТ.е. 15КРБ так и остался в мечтах?

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ЦитироватьArjun MBT пишет:

Well The above mentioned Thrust is in Vacuum or not??? We have 2 Cryogenic engine in development isnt it, One is CE-20 and the Other is CE-7.5, What is the difference, any idea?

jagjitnatt пишет:

There are more than 2 engines under development. The engine (Cryogenic Engine)CE-7.5 is not the correct name. Its called the Cryogenic Upper Stage (CUS12).
This was the engine tested on GSLV Mk III. The thrust is of course calculated in vacuum.

The engine has a thrust of 73.5 KN and can be uprated to 82 KN.

Check out.
Welcome To ISRO :: Launch Vehicles :: GSLV :: GSLV-D3

The other engines are still under development, may not surface before 2015.

ЦитироватьCASCADE TESTS ON CE 20 LOX TURBINE SECOND ROTOR BLADE PROFILE

Senthil Kumaran, R and Swamy, KMM (2006) CASCADE TESTS ON CE 20 LOX TURBINE SECOND ROTOR BLADE PROFILE. Technical Report. National Aerospace Laboratories, Bangalore.
Full text available as:
PDF - Published Version
Download (285Kb) (http://nal-ir.nal.res.in/8890/1/0613.pdf)

Abstract

LPSC, ISRO as part of their CE 20 cryogenic engine development program, desired to get the liquid oxygen [LOX] turbo pump turbine profiles tested in the NAL Transonic Cascade Tunnel to obtain basic aerodynamic performance data. The LOX turbine consists of a nozzle, first rotor, stator and second rotor. Similar profiles have been designed for the first rotor, stator and second rotor with minor changes in stagger angle and pitch. Hence, the same cascade blades were used to test the first rotor, stator and second rotor configurations at respective pitch, stagger and flow conditions. The tests on the first rotor and stator configuration have been completed earlier. The test details and results of the LOX second rotor configuration are presented in this report. The LOX second rotor configuration was tested at three different inlet flow angles and six outlets Mach numbers. Performance parameters such as profile loss, exit flow angle, flow velocities and surface Mach number distribution were evaluated.

ЦитироватьCASCADE TESTS ON CE 20 LOX TURBINE NOZZLE BLADE PROFILE

Senthil Kumaran, R and Swamy, KMM (2007) CASCADE TESTS ON CE 20 LOX TURBINE NOZZLE BLADE PROFILE. Technical Report. National Aerospace Laboratories.
Full text available as:
PDF - Published Version
Download (280Kb) (http://nal-ir.nal.res.in/8891/1/0801.pdf)

Abstract

LPSC, ISRO, as part of their CE 20 cryogenic engine development program, desired to get the liquid oxygen [LOX] turbo pump turbine profiles tested at the NAL Transonic Cascade Tunnel to obtain basic aerodynamic performance data. The first rotor, stator and the second rotor profiles of the LOX turbine have already been tested in TCT and the results have been disseminated. The present task involves the aerodynamic evaluation of the nozzle profile of LOX turbine, in TCT. This profile was tested at five different inlet flow angles and eight outlet Mach numbers, covering the design and several off design conditions. Aerodynamic performance parameters such as profile loss, exit flow angle, flow velocities and surface Mach number distribution were evaluated. The effect of incidence on these performance parameters were also studied in detail. Oil flow visualization study was done at the design condition to study the flow behavior on the blade surfaces.

ЦитироватьThe next step should be to develop a CE-20B with expander cycle allowing multiple restarts. The present CE-20 would be a gas generator cycle engine. I don't see ISRO going for higher thrust cryoengines and 200 kN will be the limit. A CE-20 with expander cycle will the GTO performance of GSLV-Mk III.

The semicryo is being developed for the common-liquid core stage which will most probably be a ground ignited stage so, cryogenic engines will only power the upper stages of future LVs.

ЦитироватьIndia-made cryogenic engine fails to lift GSLV-D3

M. Ramesh

Sriharikota, April 15

The launch of the GSLV-D3 rocket, which featured for the first time an indigenously built cryogenic engine, failed. The rocket lifted off precisely, but veered off its path, and the vehicle went out of control. Initial reports suggest that the crucial third stage - the cryogenic engine - failed to ignite.

Addressing a press conference at the Sriharikota satellite launch station, the Indian Space Research Organisation (ISRO) Chairman, Dr K. Radhakrishnan, said scientists would take a couple of days to analyse the reasons for the failure, but promised the next rocket launch with an Indian-made cryogenic engine within a year.

Dr Radhakrishnan stressed that this was only a developmental (test) flight. "We need to do some more work," he said, adding that failures were a part of the development of such complex technologies.

The GSLV-D3 rocket cost about Rs 180 crore and the satellite, Rs 150 crore. The GSat-4 was also an experimental satellite, with transponders designed to operate on frequencies not worked with in the past.

[color=yellow:470dc235be]India's efforts to develop a cryogenic engine on its own began in 1993, after the US persuaded the Russians under the Missile Technology Control Regime to give India the technology. The Russians did sell India seven cryogenic engines, five of which have been used.

Dr Radhakrishnan said that ISRO had planned eleven GSLV launches after today's launch and that programme would continue, because the fabrication work has been going on alongside.

He said that today's failure would not set the clock back on either the development of the GSLV Mark-III rocket, which has a bigger cryogenic engine and is capable of carrying satellites as heavy as 5 tonnes, or the development of semi-cryogenic engines for the lower stages of the rocket.

"Our emphasis is on achieving self-reliance," he said, noting that an indigenous cryogenic engine would cost Rs 36 crore. In contrast, an imported one would cost about Rs 90 crore.[/color]

ЦитироватьL110 test to follow S200

(https://img.novosti-kosmonavtiki.ru/63300.jpg)
L110 cluster engines undergoing testing at LPSC

Full-stage testing of the L110 is to follow the ground firing of S200 later this month. The ground-firing of S200 booster is to take place in the third week of January according to the Chairman of ISRO. This will be followed by the test of the L110 engine in the latter half of January or February at the Liquid Propulsion test facility in Mahendragiri. The Chairman retierated that the first launch of GSLV-Mk III would take place next year.

This test will pave the way for certification of the L110 stage. The L110 is India's first cluster engine stage containing a cluster of 2 Vikas engines similar to those used on the basic GSLV. The cluster engine has already been certified in 2007 and this particular test would be a full-stage test. In many ways, it represents another frontier conquered by the Indian space agency.

The L110 stage generates a thrust of around 1400 kN with a burn time of 240 seconds. The entire stage weighs at 119 tonnes with 9 tins being the empty weight. The stage will ignite 113 seconds after lift-off and burning-out at 312 seconds. The stage is also capable of multiple restarts.

The L110 will in the future be replaced by the common liquid core stage (CLC) powered by the Semi-cryogenic engine under development thus making the GSLV Mk-III more capable and providing a platform to test technologies for the UMLV family.
Monday, January 4, 2010

ЦитироватьJanuary 6, 2010 1:15 AM
Gopala Krishna says:

1. The cryogenic engines on GSLV and GSLV-MK III are different except for some minor similarities. The CE-20 engine (Mk-III) uses a gas-generator cycle, and it's for the first time that ISRO is working on gas generator cycle. The CE-7.5 engine (GSLV) is the most basic version of cryogenic engines and it can't be used on Mk-III.

ЦитироватьSemi cryogenic engine technology for future space transportation systems
Friday, 19 December 2008 00:00

The Union Cabinet approved development of Semi Cryogenic Engine technology at an estimated cost of Rs. 1,798 crores with a foreign exchange component of Rs. 588 crores. The objective is designing, fabricating and testing this advanced technology in India in six years time. This will be an important step towards self-reliance in advanced space transportation technology for India.

Storable liquid stages of PSLV and GSLV engines used presently release harmful products to the environment. The trend worldwide is to change over to eco-friendly propellants. Liquid engines working with cryogenic propellants (liquid oxygen and liquid hydrogen) and semi cryogenic engines using liquid oxygen and kerosene are considered relatively environment friendly, non-toxic and non corrosive. In addition, the propellants for semi-cryogenic engine are safer to handle & store. It will also reduce the cost of launch operations.

This advanced propulsion technology is now available only with Russia and USA. India capability to meet existing mission requirements. The semi cryogenic engine will facilitate applications for future space missions such as the Reusable Launch Vehicle, Unified Launch Vehicle and vehicle for interplanetary missions.

ЦитироватьPICTURES: Indian Space Transportation System - Present Scenario and Future Directions

The presentation titled 'Indian Space Transportation System - Present Scenarion and Future Directions' presented by Dr. B.N.Suresh on 19th June, 2009 at TIFR, Mumbai. Credit:ISRO Click on the slideshow for larger images.

Important Observations:

* Slide 20 gives us an idea of the Indian interplanetary missions on the drawing board. The slide also gives the orbital and fly-by payload capacities of PSLV, GSLV and GSLV -Mk III to Mars, Venus and Asteroid (very vague definition in this case) respectively. The approximate date for robotic missions to Venus and asteroids is mentioned in Slide 34 as 2018 (Interplanetary missions beyond Mars). The Martian mission according to ISRO will take place only after 2015.
* Slide 20 mentions the performance specifications of GSLV-Mk III i.e 4.5 tons to GTO and 10 tons to 400 km LEO. In addition it clearly specifies the growth potential to as 5 to 6 tons to GTO, a previously speculated figure. Slide 14 illustrates the flight sequence of Mk III.
* Slide 25-Slide 28 gives some information of the RLV program. Slide 25 is the image of RLV-TD. Slide 26 shows the RLV with an air-breathing engine. Slides 27 and 28 shows the configuration and flight profile of an RLV-TSTO (Two Stage to Orbit) version.
* Slides 29-33 has information regarding the Indian Human Spaceflight Programme. The slides give information about the crew vehicle and the human-rated GSLV that would launch it and the mission profile. Slide 33 has already been discussed in detail in an earlier post.

Thursday, July 8, 2010

ЦитироватьPSLV

The Polar Satellite Launch Vehicle (PSLV) is a medium capacity expendable launch vehicle, first introduced in 1993. It derived much of it's design architecture fr om it's predecessor, the ASLV. The development of PSLV necessitated many firsts for the then nascent Indian Space Program like Liquid propulsion and large solid boosters.

PSLV performance was progressively improved during the 1990s. The operational "C" version, first flown in 1997, stands 44.4 meters tall and weighs 295 metric tons at liftoff. It consists of four stages that use solid and liquid propellants alternately.

The first stage uses a 2.8 meter diameter, 20 meter long, 472 ton thrust solid motor that burns 138 tons of propellant for 107 seconds. The first stage is augmented by six solid strap-on boosters that produce 67.5 tons of thrust each for 45 seconds. Four of the strap-on boosters ignite at liftoff. The two air-start strap-ons ignite 25 seconds after liftoff. The strap-on boosters are jettisonned after burn-out. More powerful "XL" boosters carrying 12 tonnes of propellant and producing up to 73.4 tonnes of thrust debuted in 2008.

PSLV's 12.5 x 2.8 m PS-2 (L40) second stage is powered by a 73.9 ton-thrust Viking 4 engine that burns unsymmetrical dimethyl hydrazine (UDMH) fuel and nitrogen tetroxide (N2O4) oxidizer for 162 seconds. Viking 4, called "Vikas" by ISRO, was originally built by Europe's SEP for the Ariane 1 launch vehicle.
The third stage is another 2.8 meter diameter solid motor. It burns 7.6 tons of propellant for 109 seconds, producing 33.5 tons of thrust.

The fourth and final stage is a twin-engine liquid propulsion system that is housed within the payload fairing below the satellite. It burns 2.5 tons of mono-methyl hydrazine (MMH) fuel and nitrogen tetroxide (N2O4) oxidizer. The 1.43 ton thrust stage can burn for up to 420 seconds.
The vehicle is controlled by a strap-down inertial navigation/guidance system housed in a vehicle equipment bay that is mounted on top of the fourth stage. An 8.3 meter tall, 3.2 meter diameter payload fairing protects the payload during ascent through the atmosphere.

The original PSLV/GSLV launch complex was replaced in 2005 with a new, mobile launch facility. PSLV-C6 was the first rocket to use the pad. Wh ereas the original pad featured a fixed launch stand and a 75 meter tall mobile service tower, the new "second launch pad" uses rail-mobile launch stands that allow vehicles to be stacked in a vertical integration building located some distance from the launch pad itself.

The January 10, 2007 PSLV-C7 mission included the first use of a PSLV dual launch adapter, which deployed both Cartosat 2 and the SRE 1 demonstration recovery capsule and carried a small microsatellite.

The PSLV-CA (Core Alone) model premiered on April 23, 2007. The CA model did not include the six strap-on boosters used by the PSLV-C variant. Two small roll control modules and two first stage motor control injection tanks were still attached to the side of the first stage. About 400 kg of propellant was offloaded from the fourth stage compared to PSLV-C.

Chandrayaan 1, India's first lunar orbiter, was launched by the first PSLV-XL variant on October 22, 2008. PSLV-XL, boosted by more powerful, stretched strap-on boosters, weighed 22 tonnes more at liftoff than PSLV-C.

Цитировать(https://img.novosti-kosmonavtiki.ru/14769.jpg)
(https://img.novosti-kosmonavtiki.ru/14770.jpg)

PSLV variants

Extract from Evolution of Indian launch vehicle technologies published in CURRENT SCIENCE, VOL. 93, NO. 12, 25 DECEMBER 2007

PSLV was designed in 1980s for inserting 1 ton class of operational remote sensing satellites into Sun synchronous orbit. It was truly a quantum leap for Indian space technology at that time as a follow-on project of the ASLV. PSLV today is among the few launchers with a very high success rates and serves as the work-horse of ISRO.

Different configurations are designed to provide wide variations in payload capabilities ranging from 600 kg in LEO to 1900 kg in SSPO. Core-alone configuration without strap-on motors is designed to launch two satellites of 400 kg each into LEO. A three-stage configuration without strap-on motors and liquid stage will offer lower launch cost of 500 kg class of satellites into LEO.

The most interesting of these variants are the PSLV-HP and PSLV-3S, the most capable and least capable members of the PSLV family if built. The PSLV-HP is supposed to have a a capability of 1900 kg to SSPO. It was designed to launch the IRNSS constellation into orbit but there are doubts over the program following the revelation by ISRO that it was looking into the possibility of GSLV launching the IRNSS. The 3S variant without the PSLV second stage is designed to launch 500 kg payload into a 550 km LEO.
Tuesday, May 11, 2010

Цитироватьcomments to "PSLV variants"

May 12, 2010 3:47 AM
Srinath Sadda says:

 The HP version will be used to launch a constellation of seven navigation satellites between 2010 and 2012. Among other things, the efficiency of the stage 4 engine will be improved in this version.

ЦитироватьOn the PSOM-XL motor fabricated by Ramakrishna Engineering Company, Veeraraghavan said while the six solid propellant strap-on motors in the standard PSLV carried nine tonnes of propellant, the new version PSOM-XL with a length of 13.5 metre had the capacity to carry a 12-tonne propellant. It would boost the capability of PSLV from 1,450 kg to 1,750 kg for a sun synchronous orbit. "The motor will be used in the launch of PSLV C18 and PSLV C19 in the middle of next year," he added.

ЦитироватьGSLV rocket now taller, heavier

Chennai, December 17, 2010
First Published: 15:02 IST(17/12/2010)
Last Upd ated: 15:04 IST(17/12/2010)

India's geosynchronous satellite launch vehicle (GSLV), scheduled to blast off on Monday with an advanced communication satellite (GSAT-5P), is now taller by two metres and heavier by four tonnes as compared to its standard configuration. The Indian Space Research Organisation's standard configuration for the GSLV rocket is a height of 49 metres and 414 tonnes in weight at lift-off.

The rocket that would lift off Monday stands 51 metres tall and weighs 418 tonnes.

PS Veeraraghavan, director of the Vikram Sarabhai Space Centre, told IANS: "This time the fuel quantity for the cryogenic engine has increased and its thrust power has also gone up. The rocket will be carrying a heavier satellite (GSAT-5P) weighing 2,310 kg."

The Russian made cryogenic engine will be powered with 15.2 tonnes of fuel (liquid hydrogen as fuel and liquid oxygen as oxidizer), an increase of around three tonnes, and the engine's length has also increased.

The rocket has a bigger heat shield - four-metres in diameter and made of fibre reinforced plastic (FRP) - as compared to the standard configuration of 3.4-metre diameter made of aluminium alloy metal.

With the changes in rocket's configuration, necessary calibrations have been carried out in the rocket's navigational systems, control dynamics and aerodynamics so that the flight is smooth and the mission is successful, a source associated with ISRO told IANS.

Over the years, the carrying capacity of the GSLV has also increased -- from 1,530 kg in 2001 for GSAT-1 to 2,220 kg for GSAT-4 in April 2010.

The latest has a payload of 2,310 kg with 36 transponders -- an automatic receiver and transmitter of communication or broadcast signals. Successful launch of the satellite will take the agency's transponder capacity to around 235 from 200 in orbit now.

ЦитироватьThe GSLV rocket is 51-metre tall, weighs 418 tonnes and costs around `175 crore. The satellite, with a payload of 2,310 kg, has a price tag of `125 crore.

Цитироватьhttp://www.hindustantimes.com/GSLV-rocket-now-taller-heavier/Article1-639557.aspx

ЦитироватьThe rocket has a bigger heat shield - four-metres in diameter and made of fibre reinforced plastic (FRP) - as compared to the standard configuration of 3.4-metre diameter made of aluminium alloy metal.[/color]

ЦитироватьThe GSLV-FO6 has major changes incorporated as compared to the previous flights. It includes the loading of 15 tonnes of propellants in its third stage of flight and the uprating of the third stage thrust by 26 per cent, ISRO said.

ЦитироватьА так:
img / img

Цитироватьhttp://www.deccanchronicle.com/national/engine-leak-delays-gsat-5p-launch-191

ЦитироватьThe GSLV-FO6 has major changes incorporated as compared to the previous flights. It includes the loading of 15 tonnes of propellants in its third stage of flight and the uprating of the third stage thrust by 26 per cent, ISRO said.

Тяга  увеличилась до:
7,5тс X 1,26 = 9,45 тс.

ЦитироватьGSLV-FO6
А почему водородный движок не собственный? Если причину сбоя выяснили, устранить ее уже должны были.
Или так изначально и планировалось?

ЦитироватьПриятный, наверное, бонус - вроде бы первоначально обещали поднять тягу до 9 т ? (или всё же "на 2 тонны" ?  :roll: )

Но в своё время химмашевцы заявляли для форсированной версии КВД-1М тягу даже 10,5 т - когда соревновались с Воронежем за место на КВТК. Так что есть ещё куда расти.

ЦитироватьА так:

ЦитироватьА я верю заявлениям г-на Радхакришнана насчет прерывания подачи управления на 47-й секунде, да и на видео видно, что ракета стала крениться до срыва обтекателя. Чем оно было вызвано: протек ли водород и убил автомат стабилизации или просто кабель переломился как на Протоне, это пусть комиссия разбирается.

ЦитироватьЯ тоже верю, это вполне логично, интересно, что они сразу всё рассказали, а не стали устраивать засекреченное расследование.

Цитироватьzaitcev пишет:

А я верю заявлениям г-на Радхакришнана насчет прерывания подачи управления на 47-й секунде, да и на видео видно, что ракета стала крениться до срыва обтекателя. Чем оно было вызвано: протек ли водород и убил автомат стабилизации или просто кабель переломился как на Протоне, это пусть комиссия разбирается.

ЦитироватьThe vehicle lost control because there were indications that four connectors (chords) that take the signal to the first stage for controlling the rocket could have snapped. "What happened and why it happened, we have to find out. We will get into the details," Dr. Radhakrishnan said. He asserted that there was no problem with the GSLV's design. "It was only [due to] some accident that the connector snapped," he said. He was sure the problem would be overcome because "we learn from failures."

Not a major problem

Director of Vikram Sarabhai Space Centre in Thiruvananthapuram P.S. Veeraragahvan asserted that it was "not a major problem because the vehicle's design was not an issue. It was a problem of the connector snapping."

Цитироватьhttp://www.thehindu.com/news/national/article979370.ece

Цитировать.... It was a problem of the connector snapping."

ЦитироватьРакета завалилась потому что разъём отвалился?

ЦитироватьЕсли это один разъём, то просто нет слов.

Цитировать

ЦитироватьЕсли это один разъём, то просто нет слов.

Разъем там наверняка не один, другое дело, если они через один разъем заводили основной и дублированный тракт  8)

Цитировать- почему надо делать разъём так, чтобы он вообще мог отвалиться, тем более в ракете?

Цитировать

Цитировать- почему надо делать разъём так, чтобы он вообще мог отвалиться, тем более в ракете?

Ну например разъем отвалился, потому что ракета начала разваливаться  :)
Это я к тому, что отвалившийся разъем лишь одно из нештатных событий в цепочке произошедших нештатных событий и возможно не первое. Просто до этого события в цепочке индусы уже добрались

ЦитироватьТак эта цепочка, судя по сообщениям, выглядит так:
Разъединение разъема - непрохождение управляющих сигналов на исполнительные органы СУ - потеря устойчивости - выход на запредельные углы атаки - выход за пределы расчетных нагрузок при достижении Qmax - разрушение ракеты.

ЦитироватьТак эта цепочка, судя по сообщениям, выглядит так:
Разъединение разъема - непрохождение управляющих сигналов на исполнительные органы СУ - потеря устойчивости - выход на запредельные углы атаки - выход за пределы расчетных нагрузок при достижении Qmax - разрушение ракеты.

ЦитироватьДа без разницы, пусть даже всего один тракт, - почему надо делать разъём так, чтобы он вообще мог отвалиться, тем более в ракете?

ЦитироватьТогда интересно, почему разъединился разъем?

ЦитироватьИнтересный момент, что всё кабельное хозяйство от СУ до нижних ступеней проходит через внешний гаргот на третьей ступене. Может он как то повредился? Например, из за нештатных вибраций и перехода через Qmax?  Если этот гаргот "перешибить" то теряеться вся связь с СУ

Цитировать

ЦитироватьТак эта цепочка, судя по сообщениям, выглядит так:
Разъединение разъема - непрохождение управляющих сигналов на исполнительные органы СУ - потеря устойчивости - выход на запредельные углы атаки - выход за пределы расчетных нагрузок при достижении Qmax - разрушение ракеты.

Тогда интересно, почему разъединился разъем? Индусы твердят, что они все еще раз отработали и по "нижним стадиям" у них сомнений небыло.
Интересный момент, что всё кабельное хозяйство от СУ до нижних ступеней проходит через внешний гаргот на третьей ступене. Может он как то повредился? Например, из за нештатных вибраций и перехода через Qmax?  Если этот гаргот "перешибить" то теряеться вся связь с СУ

ЦитироватьQmax - это примерно 60 секунда, а проблемы начались где-то на 44-47-й. Может, из-за вибраций или еще чего разъем перестал передавать сигнал. :roll:

Цитировать

ЦитироватьОХ, щас доприкалываемся  :lol:
Вот схема ЖСЛВ, где видно, что СУ стоит над РБ:
.

Вот на этой записи старта http://www.youtube.com/watch?v=KYirFgCd8RU#ws видно облачко на 43-44 секунде полета. как раз в районе разгонного блока.
(https://img.novosti-kosmonavtiki.ru/15842.jpg)

ЦитироватьБыл не прав: белое облачко (следствие эффекта Прандтля — Глоерта) возникает на околозвуковой скорости, а максимальный скоростной напор ракета проходит несколько позже.

ЦитироватьОблачко - эффект Прандтля-Глоерта, оно не связано со скоростным напором и возникает обычно на околозвуковой скорости, а иногда и на более низкой.

Цитировать

ЦитироватьОблачко - эффект Прандтля-Глоерта, оно не связано со скоростным напором и возникает обычно на околозвуковой скорости, а иногда и на более низкой.

Я один раз такое видел на авиашоу (на Дне Амеса) с расстояния всего метров в 250. Уши целы, значит скорость была дозвуковая. У некоторых ракет с плохой тяговооруженностью оно присутствует по нескольку секунд и может выглядеть довольно неприлично - прямо как презерватив.

Цитировать

ЦитироватьДа без разницы, пусть даже всего один тракт, - почему надо делать разъём так, чтобы он вообще мог отвалиться, тем более в ракете?

Сэкономили на контровке. :)

ЦитироватьВо-первых, в большинстве таких соединителей, производимых за рубежом, соединение провода в контакт производится не пайкой а механическим обжатием контакта.

ЦитироватьПравда я не в ракетной отрасли, может быть у вас с этим строго или есть какой инструмент для подготовки кабеля к пайке.

Цитировать

ЦитироватьВо-первых, в большинстве таких соединителей, производимых за рубежом, соединение провода в контакт производится не пайкой а механическим обжатием контакта.

Пайка - не панацея. Бывало, что монтажница неаккуратно снимала изоляцию перед пайкой и оставляла насечку на проводнике. Припаяно хорошо, а потом как раз по насечке происходил облом.

ЦитироватьНа этом видео всё выглядит так, словно сорвало обтекатель.

 http://www.youtube.com/watch?v=4swAaZ6d6r8

Цитировать

ЦитироватьТогда интересно, почему разъединился разъем?

Ну например от вибрации. В самолётах они откручиваются от вибрации....

Цитировать

Цитировать

ЦитироватьТогда интересно, почему разъединился разъем?

Ну например от вибрации. В самолётах они откручиваются от вибрации....

AkycTuka... :wink:

ЦитироватьМногие разъёмы имеют байонетное соединение и раскрутиться от вибрации практически не могут.

Цитироватьhttp://isro.gov.in/parliament/2011/Budget/LUSQ3347.pdf

ЦитироватьGOVERNMENT OF INDIA
 DEPARTMENT OF SPACE
 
LOK SABHA
UNSTARRED QUESTION NO.3347
 
TO BE ANSWERED ON WEDNESDAY, MARCH 16, 2011
 
STATIC TEST ST-02
 
3347. SHRI K SHIVAKUMAR  
ALIAS  J.K. RITHEESH:
 
Will the PRIME MINISTER be pleased to state:
 
(a) whether the S-200 Static Test (ST-02), L110 Stage test has been completed as planned earlier;
 
(b)  if so, the details thereof;
 
(c) whether the work on C25 Cryogenic Engine for GSLV MK III has been completed; and
 
(d)  if so, the details thereof?  

 
ANSWER
 
MINISTER OF STATE IN THE MINISTRIES OF PARLIAMENTARY AFFAIRS, PERSONNEL, PUBLIC GRIEVANCES & PENSIONS AND IN PRIME MINISTER'S OFFICE (SHRI V.NARAYANASAMY):
 
(a) & (b) The first Static Test (ST-01) of the S-200 solid booster stage of GSLV-MkIII, was successfully conducted in January,   2010    at   Satish   Dhawan   Space  Centre,  

Sriharikota. Presently, preparations are progressing for conducting the second Static Test (ST-02) of S-200 solid booster stage.  The  test is planned during mid-2011.  
So far, stage-level tests have been completed for the L110 liquid core stage twice, at Liquid Propulsion Systems Centre (LPSC), Mahendragiri.  The first test was conducted in March 2010 for a duration of 150 seconds; and the second test was for its full flight duration of 200 seconds, in September, 2010.

(c) & (d) The work towards realization of C25 Cryogenic Engine for the GSLV-MkIII programme is progressing well.  
Major sub-systems of the C25 Cryogenic Engine such as Gas Generator, Turbo-pumps for the Liquid Oxygen (LOX) and Liquid Hydrogen (LH2) have been realised and tested.  Preparations for the testing of one of the major subsystem viz., Thrust Chamber are underway.  
The integrated test of the C25 Cryogenic Engine is planned for end 2011.  

ЦитироватьLater speaking to reporters, Mr. Chandradathan said that building of GSLV-Mk III will be over by 2012 end and launch would be in the next year.

"GSLV-Mk III has three stages. The first stage, Solid propellant booster S-200 has been tested and qualified; Second and liquid propellant stage called L-110 has also been tested. Work is yet to be completed in third and important stage, the cryogenic stage," he said.

ЦитироватьOn the GSLV Mk III, which is being conceived and designed to make Isro fully self-reliant in launching 4 tonne-plus weighing communication satellites of INSAT-4 class, he said static testing is currently on which would continue till 2012.

ЦитироватьА последний 12КРБ полетит? Что-то тишина по результатам расследований...

ЦитироватьОн должен был лететь то ли в пред-предыдущий, то ли в пред-пред-предыдущий раз.

ЦитироватьAdding to this, The Indian Space Research Organization (ISRO) has planned to set up a rocket sub-systems integration facility near the spaceport of Sriharikota in coastal Andhra Pradesh. Also ISRO would set up a multi-mission ground segment for earth-observation satellites and a national database for the nation's emergency management, at Shadnagar near Hyderabad. A thrust chamber testing facility for high-thrust cryogenic engines will be set up at Mahendragiri as well.

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ЦитироватьА последний 12КРБ полетит? Что-то тишина по результатам расследований...

Так он же уроненный. Лично я бы вообще на нем ничего не пускал бы.

ЦитироватьХоссспадя, они бомбу роняли в 74-м году при сборке. Взорвали.

Цитировать

ЦитироватьХоссспадя, они бомбу роняли в 74-м году при сборке. Взорвали.

Сразу или потом? :)

ЦитироватьThe group traced the loss of GSLV-F06 to a failure of the composite shroud on the vehicle's Russian cryogenic engine. "The problem with GSLV is of a minor nature and it does not call for major changes," Nair says. Discussions have begun with Russia regarding the shroud issue.

ЦитироватьСостоялась встреча главы Роскосмоса с послом Индии[/size]
:: 09.06.2011

9 июня состоялась  протокольная встреча руководителя Федерального космического агентства Владимира Поповкина с вновь назначенным послом Индии Аджаем Мальхотрой.
Стороны обсудили состояние и перспективы российско-индийского сотрудничества по всем направлениям космической деятельности.

 http://www.federalspace.ru/main.php?id=2&nid=17304

Пресс-служба Роскосмоса

ЦитироватьВ 2-х словах при сборке на полигоне уронили на землю одну из взрывных линз(такая здоровенная фигня из взрывчатки в форме приблизительно дольки арбуза).  

ЦитироватьНейтронный активатор (шарик с полонием внутри) был уже установлен к этому моменту.

ЦитироватьТак что уронили-то? Взрывную линзу или всю боньбу в сборе?

ЦитироватьMonday, September 12, 2011
S200 Booster Tested at SDSC

Here's video of ISRO's recent test of the S200 solid rocket booster, at Satish Dhawan Space Centre. Meant for use in the upcoming GSLV-MkIII, the S200 is the world's 3rd largest booster of its kind, after the ones used by Ariane-5 and the Space Shuttle (well, since the Space Shuttle is now retired, I guess that would make this the 2nd-largest such booster). China and Russia use purely liquid-fuel technology. Solid rocket boosters offer superior thrust performance in comparison to liquid boosters, but cannot be throttled during flight.

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ЦитироватьSpaceR пишет:

 Если лететь из Шрихарикоты строго на юг, пролетят аккурат над многомиллиардным Мадрасом. Если ещё западнее заворачивать - ещё больше густонаселенных территорий. [Печально]
То ж самое касается и самой южной точки. При их плотности малозаселённость острова Шрихарикота вообще подарок судьбы.

Старый пишет:

Да, блин, с Мадрасом они не угадали. Южнее нада было строить... [Печально]

Дмитрий В. пишет:

Вот кому морской старт нужен!

ЦитироватьNew Delhi, September 11, 2011
India to have one more satellite launch site
PTI

Amid requests from various countries for launch of their satellites, India has decided to set up one more launch site to expand its capacity in this aspect.

At a meeting held by the Prime Minister's Principal Secretary T.K.A. Nair here to review performance of the Department of Space, it was decided that a feasibility study would be conducted for a new site, sources said.

The decision to find a new site was taken after the meeting was told that ISRO has only two satellite launch pads, both of which are affected during the cyclone season, the sources said.

The two launch pads are located at Sriharikota High Altitude Range (SHAR).

During recent years, there have been requests from a number of countries for launching their satellites in India.

ЦитироватьIndia Successfully Repeats Test Of Asia's Largest Solid Rocket Booster, The S-200

By Srinivas Laxman
September 14, 2011

India's ISRO successfully carried out the second test of the S-200 solid rocket booster, which will form the strap-on stage for the Geosynchronous Satellite Launch Vehicle Mark 32s maiden flight in 2012/2013.

(https://img.novosti-kosmonavtiki.ru/20130.jpg)
AsianScientist (Sep. 14, 2011) – India's space program crossed an important milestone on September 4 this month, when the Indian Space Research Organization (ISRO) successfully carried out the second test of the strap-on S-200 solid rocket booster, stated to be the biggest in Asia and the third largest in the world after the ones flown on NASA's space shuttle and Arianespace's Ariane 5 rocket.

The primary function of the strap-ons is to provide an initial boost to the rocket.

The success of the test assumes significance because the S-200s will form the strap-on stage for a new rocket known as the Geosynchronous Satellite Launch Vehicle (GSLV) Mark 3 version which is now in an advanced stage of development. There will be two strap-ons in the rocket.

This vehicle, slated to make its maiden flight either towards the end of 2012 or early 2013, will fly communication satellites weighing four tons. In contrast, the present version of GSLV's can carry communication satellites weighing only up to two tons.

Once the GSLV Mark 3 becomes operational, ISRO's dependence on Arianespace – the European rocket organization – to carry its four-ton class of communication satellites will be drastically reduced.

In the recent test which was conducted at the Satish Dhawan Space Center, Sriharikota, the S-200 fired for 130 seconds without any problems. Containing 200 tons of solid propellants, the length of the stage is 21.9 meters and its diameter is 3.2 meters. The S-200 was first tested on January 24, 2010.

For its maiden flight, the rocket will lift off with the simultaneous ignition of both the stages which will burn for about 130 seconds and separate at 149.3 seconds into the flight.

ЦитироватьQ&A: K Radhakrishnan, Chairman, ISRO
'We need more launch pads and transponders'
Praveen Bose / September 14, 2011, 0:27 IST

K RADHAKRISHNAN The Indian Space Research Organisation (Isro) has had a challenging time in recent years and chairman K Radhakrishnan talks to Praveen Bose about some of this. Edited excerpts:

You have been increasing the frequency of launches. What are you doing to increase the launch capacity?

We are planning a third launch pad at SHAR (the Satish Dhawan Space Centre, at Sriharikota island, off the Andhra coast). A launch blocks the pad for nearly 60 days. To increase the frequency, we need more launch pads. We are seeing what the requirements are.

It is not just for the GSLV Mark-III (the new launch vehicle being planned) alone that we are in need of a launch pad. We are also planning a unified configuration launch vehicle. It is a semi-cryogenic and cryogenic stage-I. Unified configuration has the growth potential. The third launch pad will take care of this requirement. It may also be used in possible human flights. All the launch pads should be such that we should be able to use the common facilities. We are planning such an infrastructure at Sriharikota. Meanwhile, we are also considering a second launch site. We are now talking of a feasibility study of this.

What kind of technologies are you developing and how are you planning to expand the infrastructure?

We have developed a flex nozzle that's used even in the PSLV, due to which the vehicle can be controlled remotely. But, it's a small one. In GSLV Mark-III, the requirement is enormous. The development of the vehicle is on and infrastructure at the Vikram Sarabhai Space Centre and at SHAR are being enhanced for this.

Isro can today launch a four tonne-class geostationary satellite. If it is in the low-earth orbit, then we can go up to 10 tonnes. In the GSLV, 50 per cent of the velocity will be provided by the cryogenic stage. All studies, though, are to be done. Solid motors and boosters are not flexible. However, they're now steerable because of the flexible technology. We have the actuator requirement and the ability to have materials that can withstand very high temperatures.

What is the transponder shortage for India? How do you intend to make up?

There is gap of about 200 transponders in the country. We have had to take transponders on lease. Isro is trying to find if a satellite can be moved to the Indian orbital slot. In addition to hiring transponders, we will repeat GSAT-8 and GSAT-10 types of satellites and increase capacity. But, this will happen during the second half of 2012. We have been working to get transponders from abroad. We have got good proposals. We have to finalise on the need. Commercial evaluation is on. It is in the right direction. Isro is exploring possibilities of taking on rent a foreign satellite for a couple of years and acquiring more foreign transponders on lease.

What is the progress on the attempt to augment transponder capacity?

We have 86.5 transponders on lease. We facilitate the process. In the next few months, we will get some more on lease. Earlier, we had 151 transponders. With the GSAT-8 and GSAT-12, we will have 36 more transponders with the launch of GSAT-10 in the second quarter of 2012. It will be launched on board Ariane-5 (the rockets made by the European Space Agency, used to launch payloads into low Earth orbit).

We are getting ready to have a contract with Ariane. The GSAT-10 will have three types of transponders, in the Ku, C and extended-C bands. We will also repeat the GSAT-8 and GSAT-10. The satellites will be 3.3-3.4 tonne class of satellites. At the end of the 11th five-year Plan (March 2012), we will have 251 transponders; the target was 500. Several satellites failed. Insat-4B had a partial failure. Then, the capacity fell to 152. Then, we added Insat-4CR.

You are lately encouraging students and universities to build small satellites. How does it help Isro?

The student satellites are Isro's programme for the academic community. Here, students and faculty learn about all systems — engineering and other aspects of a satellite. They get a feel of the whole process for building one. Plus, we get data, and we analyse it. It helps Isro. We are developing people who are interested. We are able to get projects like Anusat, which is a small satellite with good instruments. We want to promote such endeavours. We have a template for this. Some IITs want to develop basic instruments for satellites.

ЦитироватьNext step with indigenous engine
Sriharikota, Oct 12 DHNS:

Buoyed by a string of successful 'PSLV' launches, the Indian Space Research Organization (Isro) has fully geared up for the next higher level flight of its 'Geosynchronous Satellite Launch Vehicle (GSLV)' by mid-2012.

Disclosing this to reporters at the 'Satish Dhawan Space Centre' here on Wednesday, Isro Chairman K Radhakrishnan said the next GSLV flight would be with an indigenously built cryogenic stage engine and all groundwork for it were on in full swing. He also inaugurated a new 'Media Centre' in the campus.

Before the GSLV flight, there will be two more launches of the 'Polar Satellite Launch Vehicle (PSLV)' from here, namely PSLV-C19, that will carry a microwave remote sensing satellite (RiSat) and 'PSLV-C20', which will put into orbit another Indo-French satellite- 'Saral'-for ocean studies, he said. The launch of GSLV with indigenous cryogenic engine has been Isro's biggest challenge on date. Having learnt from its earlier GSLV crash, two Isro scientists Dr Veeraraghavan and Dr Ramakrishnan added that the debacle had been traced to a basic failure in the 'fuel booster turbo pump' in December 2010.

Now, the booster pump had been redesigned and tests on the pump had been successful , they said. The 'flight engine assembly' of the cryogenic stage engine was now going on, and one more 'long duration test' for the booster pump would be carried out by October-end, they added.

ЦитироватьQueried about the status of indigenous cryogenic engine that would power ISRO's heavier rocket geosynchronous satellite launch vehicle (GSLV) S.Ramakrishnan, director of ISRO's Liquid Propulsion Systems Centre (LPSC) said the agency had identified the reasons for the failure of the first engine during a flight.

"We have studied the design of booster pumps and redesigned it. The computer simulation was done and validated. One more long duration test of the cryogenic engine will be made by the end of this month," he said.

"The next GSLV will be launched with an indigenous cryogenic engine," added P.S.Veeraraghavan, director of the Vikram Sarabhai Space Centre in Thiruvananthapuram.

Queried about the one remaining Russian cryogenic engine, Radhakrishnan said one of its component has to be corrected by the suppliers before it could be used.

ЦитироватьThe organization is working on the development of an indigenous cryogenic engine for the GSLV MK-III, also called C25. "We have a completely indigenous design for C25 but the development is complex will need more time," said Ramakrishnan.

ЦитироватьNow under development, GSLV-MK III is designed to make India fully self-reliant in launching heavier communication satellites weighing 4,500-5,000 kg (9,900-11,000 lb.), boosting its status as a key player in the global commercial launch market. According to a senior ISRO official, GSLV-MK III is being designed to place a 4-ton-class satellite into a geostationary transfer orbit.

S. Ramakrishnan, director of ISRO's Liquid Propulsion Systems Center, says the agency has identified the issues with the GSLV upper-stage engine. "We have studied the design of booster pumps and redesigned it. The computer simulation was done and validated. One more long-duration test of the cryogenic engine will be made by the end of this month," he says.

Цитироватьinstml пишет:

Acoustic/vibrational tests have been completed on the payload faring for the GSLV Mark-III:

http://tarmak007.blogspot.in/2012/03/gslv-mk-iii-payload-fairing-completes.html
http://forum.nasaspaceflight.com/index.php?topic=28334.msg872507#msg872507

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(https://img.novosti-kosmonavtiki.ru/23322.jpg)

(https://img.novosti-kosmonavtiki.ru/23323.jpg)

ЦитироватьA test flight of India's third-generation GSLV, called the GSLV Mk.3, has been set for early 2013, Radhakrishnan said.

"GSLV Mk.3 has crossed several major milestones," Radhakrishnan said. "The lower stages have been qualified, and we will be undertaking an experimental flight of GSLV Mk.3 in a year from Sriharikota essentially to understand the behavior of the vehicle in the atmospheric stage of flight."

Propelled by two solid rocket boosters and a liquid-fueled two-engine core stage, the suborbital test flight will lift off from the Satish Dhawan Space Center on India's east coast.

Each booster will generate 1.1 million pounds of thrust, making it the third most powerful solid rocket motor in the world after the boosters used on the space shuttle and Ariane 5 launcher.

The S200 strap-on boosters and L110 liquid-fueled core will accelerate the GSLV Mk.3 several thousand miles from the Sriharikota launch pad.

The GSLV Mk.3 is designed to launch communications satellites weighing more than four metric tons - about 8,800 pounds - once it begins orbital flights in 2014. The launcher will be able to deliver more than 10 metric tons - 22,000 pounds - into low Earth orbit.

Orbital flights of GSLV Mk.3, which require a 25-ton cryogenic upper stage, likely will not begin until 2014.
     
(https://img.novosti-kosmonavtiki.ru/24471.jpg)
Artist's concept of the GSLV Mk.3 launch vehicle. Credit: ISRO

(https://img.novosti-kosmonavtiki.ru/24472.jpg)
File photo of static fire testing of the GSLV Mk.3 liquid-fueled core stage's Vikas engines. Credit: ISRO

ЦитироватьIndigenous space engine test Saturday
IANS | May 11, 2012, 11.08PM IST

BANGALORE: The Indian space agency will Saturday conduct a crucial test on an indigenously built cryogenic engine for launching its heavier rockets from its spaceport, a top official said Friday.

"The cryogenic acceptance test will take place Saturday in our Liquid Propulsion Systems Centre at Mahendragiri in Tamil Nadu. If it succeeds, we will use the cryogenic stage in the geostationary satellite launch vehicle (GSLV) rocket later this year," state-run Indian Space Research Organisation (ISRO) chairman K. Radhakrishnan told reporters here.

Th espace agency's attempt to use its first cryogenic engine April 15, 2010 to launch a communication satellite on board a GSLV was aborted as the heavy rocket plunged into the sea within minutes after blast-off from its Sriharikota spaceport, about 80 km north-east of Chennai.

"We have learnt a lot from the previous attempt and rectified the errors that caused the failure two years ago," Radhakrishnan admitted.

A cryogenic engine is a rocket motor that is fired by a mixture of liquid fuels (oxidiser) such as hydrogen and oxygen at very low temperatures of 20 degrees Kelvin and 90 degree Kelvin.

Buoyed by the success of its polar satellite launch vehicle (PSLV-C19) putting into a higher orbit its microwave radar imaging satellite (Risat-1) April 26, the space agency has drawn up an ambitious plan to launch a series of space missions over the next two years using a combination of lighter (PSLV) and heavier (GSLV) rockets, including an experimental flight of GSLV-Mark III.

"We have designed GSLV-Mark III to be self-reliant in launching four-five tonne communication satellites in the INSAT-4 series. The next generation rocket will also enhance our capability to be a competitive player in the multi-billion dollar commercial launch market," Radhakrishnan asserted on the occasion of the space agency's satellite centre (ISAC) herecompleting four decades (Ruby Year) of service.

The advanced rocket will have a multi-mission launch capability for geo-synchronous transfer orbit (GTO), low earth orbit (lEO), polar and intermediate circular orbits.

ЦитироватьISRO successfully tests indigenous cryogenic engine
Published: Saturday, May 12, 2012, 21:23 IST
Place: Chennai | Agency: PTI

In a major step, ISRO today successfully tested the indigenous cryogenic engine to be used to propel the country's Geosynchronous Satellite Launch Vehicle.

The test was conducted at the Liquid Propulsion Systems Centre at Mahendragiri in Tamil Nadu's Tirunelveli district.

"The acceptance test of the indigenous cryogenic engine for the forthcoming GSLV-D5 flight was conducted successfully for 200 seconds at 17:10 hrs...," an ISRO statement said.

"The performance of the engine was as predicted," it said.

The maiden flight test of the indigenous cryogenic stage onboard GSLV-D3 failed in May 2010 after it developed a snag and the rocket plunged into the sea minutes after lift-off.

ISRO chief K Radhakrishnan had said last month that GSLV would undergo two more tests at the Mahendragiri facility.

He had also said ISRO was planning a GSLV launch with Indian cryogenic engine during September-October.

ISRO plans to fly two GSLV rockets at an interval of six months with the third one meant for the Chandrayaan-2 moon mission.

ЦитироватьAn experimental flight of GSLV Mark III (without the active cryogenic stage), for launching communication satellites of 4 tonne (compared to GSLV's 2.2 tonne capacity), is scheduled for the second quarter of 2013.

Цитироватьantriksh пишет:

(http://img846.imageshack.us/img846/1624/gslvmk3.jpg)

ЦитироватьSalo пишет:
Думаешь собрали за полгода до пуска?

ЦитироватьGSLV-Mk III experimental flight in 2014: ISRO chairman Radhakrishnan
India, Posted on Apr 03, 2013 at 11:24pm IST
Press Trust of India

New Delhi: India plans to launch a next generation rocket to put heavier satellites and more astronauts into outer space within a year, a top official said on Wednesday. "The first experimental flight of the GSLV Mark III will take place one year from now," K Radhakrishnan, Chairman, Indian Space Research Organisation told the Annual General Meeting of the Confederation of Indian Industry in New Delhi.

The new rocket, which can put a four tonne satellite in orbit, will help Antrix Corporation, ISRO's commercial arm, to offer cheapest space launches in the niche market. The regular GSLV can put 2.2 tonne satellites in orbit.

The GSLV Mark III will enable ISRO launch heavier satellites, an activity for which it has to turn to foreign launch vehicles like Arianspace, based in Kourou in French Guiana. The GSLV Mark III will also help ISRO put more Indians in space at one go.

GSLV Mark III is designed to be a three-stage 42.4 m tall vehicle, with a lift off weight of 630 tonnes. First stage comprises two identical S200 Large Solid Booster with 200 tonne solid propellant, that are strapped on to the second stage, the L110 re-startable liquid stage.

The third stage is the cryogenic upper stage loaded with 25 tonnes of propellant. The large payload fairing measures five meters in diameter and can accommodate a payload volume of 100 cubic meters.

ЦитироватьIndia to test fly heaviest rocket next year: ISRO

India's heaviest rocket ever is expected to take to the sky next January on an experimental flight whose later versions could be used to send humans on space missions.

The mainstay of the Geosynchronous Satellite Launch Vehicle-Mark III (GSLV-Mk III) would be to put in orbit communication satellites weighing between four and five tonnes, thus packing more transponders per launch.

"We are targetting an experimental flight of GSLV-Mk III in January 2014," Indian Space Research Organisation (ISRO) Chairman K Radhakrishnan told reporters after a public lecture at the Indian National Science Academy (INSA) here.

This will also be a first time that ISRO scientists would undertake an experimental flight of a launch vehicle which would fall into the sea after reaching a height of 120 km.

"We have been simulating the flight using computers. But there are certain tests that cannot be carried out on the ground. We will test the rocket in a cost effective manner," GSLV-Mk III's project director S Somnath said.

He said ISRO engineers have planned to take some 2,000 measurements during the experimental flight of the GSLV-Mk III, which would weigh 640 tonnes at lift-off, making it the heaviest rocket built in the country.

"All the 2000 measurements during the flight would be telemetered down to the ground station. We will analyse them. This will enable us to have full knowledge of the flight," Somnath said.

The new rocket, which can put a four tonne satellite in orbit, will help Antrix Corporation, ISRO's commercial arm, to offer cheapest space launches in the niche market.

ЦитироватьIndia's first manned space flight trial in 2015
New Delhi, April 9, 2013, DHNS:

The first flight of ISRO's new and powerful rocket that will be able to carry an Indian to space, is expected to take place by the middle of 2015.

Known as the Geostationary satellite launch vehicle (GSLV) Mark-III, this is the heavy-duty rocket, which Indian Space Research Organisation (ISRO) will use to send an Indian astronaut to the space. Doing the same with commercial foreign rockets, would be very expensive.

"GSLV Mk-III will have a payload of 6-10 tonnes and can take an Indian astronaut to a low earth orbit," ISRO chairman K Radhakrishnan said at the Indian National Science Academy here on Tuesday.

Sending a man to the moon is not on ISRO's immediate agenda because the rocket has to carry a load of 35 tonnes up to the lunar orbit.

"For comparison, Chandrayan-I weighs only 1.8 tonnes. Such kind of up-scaling in rocket's capability is needed. The cost for such a mission will be very high," he said.
But a manned space flight to a low earth orbit (upwards of 160 km to few hundreds of km) is on the space agency's radar. Except USA'a Apollo missions to moon, all other manned space flights took place in these zones. The international space station moves at an altitude between 330 and 435 km.

However, because of a series of failure in the GSLV flights, space scientists have now planned to do an experimental test flight of the GSLV Mk-III in, January 2014 without the crucial cryogenic upper stage, which is being developed indigenously.
The experimental flight will have a full-fledged GSLV with strap on boosters without the cryogenic engine.

It will fly up to an altitude of 120 km after which it will take a parabolic path and dive in the Bay of Bengal.

The flight will generate crucial aerodynamics data which ISRO scientists will use while designing the rocket for first manned space flight.

"We have received permissions from the government for two developmental flights of GSLV with indigenous cryogenic engine. The first developmental flight is expected in 18 months after the experimental flight in January, 2014," said S Somnath, project director of GSLV Mk-III programme at Vikram Sarabhai Space Centre, Thiruvananthapuram.

The indigenous cryogenic engine, which failed in its first flight in 2010, will now be put to test again in July, when an older generation GSLV (Mk-II) is scheduled to be launched. Capable of carrying a payload up to 2.5 tonnes, GSLV Mk-II can reduce India's reliance on French ArianeSpace rockets to take INSAT class satellites to the 36,000 km orbit.

"GLSV Mk-III has a completely different architecture than Mk-II. It carries twice as much fuel and the thrust is double than that of Mk-II. We need both versions of GSLV to save our foreign exchange," Somnath told Deccan Herald.

ЦитироватьI am guessing that the large core is kerosene powered, and there is a small LH2 powered upper stage. If it's the reverse, that would be sad.

ЦитироватьI heard that it will be a passive flight of GSLV–Mark III. What is a passive flight?

Radhakrishnan:
It will be a passive cryo. You have the configuration of GSLV–Mark III, which comprises two solid strap-ons, S-200 with a propellant loading of 200 tonnes each; the liquid core stage which has a dual engine; and the high-thrust cryogenic stage [above it]. We call it C-25. That is, it will carry 25 tonnes of cryogenic propellants. The S-200 solid stage has already been qualified. One of the critical requirements is that the performance of the two strap-ons should be identical. The liquid stage has been qualified on the ground. Avionics and other sub-systems are ready. We are waiting for the completion of the development of the cryogenic engine and the stage.
 One of the essential requirements is the atmospheric characterisation of this launch vehicle configuration. So without waiting for the cryogenic engine and the stage to be ready, we are going ahead with this experimental mission where we will have S-200 strap-ons and the L-110 [110 tonnes of liquid propellants] stages and the cryogenic stage which [the cryogenic engine] will not ignite. It will not give any acceleration to the vehicle. We will get nearly 5 km per second provided by the solid and liquid stages. It will be a sub-orbital flight. The most important part of it is that it will go through the atmospheric phase and we will make all the measurements in flight required to characterise the vehicle and its performance. This is scheduled for January 2014. This is going to be a major milestone in the GSLV–Mark III development.
...
 The immediate task on hand is the development of GSLV–Mark III. Its experimental mission with a passive cryogenic stage will be in January 2014. After three years, a developmental flight with an active cryogenic stage will take place.

 So the first GSLV–Mark III flight will be in 2017.

Radhakrishnan:
Yes. We should have the testing of the engine and the stage conducted.

ЦитироватьFriday, June 15, 2012
ISROs SAGA (Supercomputer for Aerospace with GPU Architecture)

(https://img.novosti-kosmonavtiki.ru/87731.jpg)
Figure 1. SAGA facility, source [1].

 

A GPU based supercomputer, SAGA (Supercomputer for Aerospace with GPU Architecture) is developed in VSSC, ISRO. SAGA is based on Intel Xeon processors and nVIDIA GPUs. The supercomputer has a theoretical peak performance of 448 TFLOPS (DP). A GPU based Computational Fluid Dynamics (CFD) software  PARAS-3D has been developed in VSSC. PARAS-3D is a major application software running on SAGA, which is used for CFD analysis of launch vehicles (for example, Fig. 2 and 3). The cluster and infrastructure design was carried out in VSSC. Operating system, job scheduler, automated resource and  power manager are also developed in-house. The supercomputer consists of 736 numbers of Intel Xeon processors 736nVIDIA Tesla GPUs. SAGA uses in-house configured Linux Operating System. The 64-bit Linux operating system (OS)for SAGA is configured using LFS (Linux from Scratch) with support for GPUs and InfiniBand. 

(https://img.novosti-kosmonavtiki.ru/87732.jpg)
Figure 2. Geometry and Grids for a typical problem. [1]
 
(https://img.novosti-kosmonavtiki.ru/87733.jpg)
Figure 3. Pressure contour solution for LVM3 using PARAS-3D, source [1].
 
 

PARAS-3D is a 

Cartesian

 grid based CFD code

 that has been developed for SAGA. The CFD code was 

written for GPUs using CUDA programming model provided by 

nVIDIA. PARAS-3D has about 2.5 lakhs lines of C-code and is 

one of the most complex applications running on GPUs. The 

code is extensively used by ISRO and other aerospace 

organizations in the country. The advantages of PARAS-3D 

includes fully automatic grid generation, ability to handle 

complex geometries, interface for CAD geometries, adaptive grid 

refinement etc.

 [1] SUDHAKARAN.G, THOMAS.C.BABU, ASHOK.V, " A GPU COMPUTING PLATFORM (SAGA) AND A CFD CODE ON GPU FOR AEROSPACE APPLICATIONS".

ЦитироватьMonday, January 7, 2013
ISRO Human Space Flight Program (HSP)
 
 

As a natural progression of its endeavors, ISRO has decided to start a Human Space flight program. It has been decided that the entire program will be split into following three different phases:

[/li]
• First phase: design, development and performance demonstration of critical technologies leading to manned space missions.
  
• Second phase and third phase would establish the necessary infrastructure, do qualification tests including flight testing with test vehicles, PSLV, GSLV and GSLV Mk III and finally demonstrate the first Indian Human Spaceflight.
  

In the first phase, during the 12th plan period (2012-2018 ), ISRO has proposed to develop and demonstrate all the major technologies and infrastructure critical for Human Spaceflight Program (HSP) including pad abort test, Orbital Vehicle (OV), Crew Escape System (CES), Environmental Control and Life Support Systems (ECLSS) & Flight Suit, Human rating of Launch Vehicle (LVM3) and realizing essential facilities including third launch pad for the development and flight testing of these systems. Mission and configuration studies and technical developmental activities will also be initiated for the Human Lunar Missions.
 
 

The first major-milestone activity is "pad abort test" that is planned to demonstrate the performance of crew escape system (CES). This test will play a vital role in establishing the critical

abort maneuver of the CES which has to take the crew module (CM) to an altitude of about 2 km and range of about 2 km from the launch pad. The objectives of this pad abort test are:

[/li]
• Verify the performance / functioning of various motors / systems of CES.
  
• Verify the capability of CES to take CM to the required altitude (~ 2 km) & range (~ 2 km).
  
• Demonstrate the deceleration & floatation capability of parachute and Crew Module.
  
• Validate the crew module recovery from sea.
  

Work on the Orbital vehicle is progressing well. ISRO has built an  ergonomic model of crew module for study and is conducting plasma wind tunnel tests on scaled crew module models. ISRO has decided to convert the PSLV PS4 (4th stage) into a service module for the OV. 
 
(https://img.novosti-kosmonavtiki.ru/87734.jpg)

Ergonomic model of ISRO crew module.

For meeting the requirements of HSP, human rating of GSLV MK III or LVM3 will also be initiated in the 12th plan period. The work will involve the following:

[/li]
• Redesign of vehicle structures including propellant tanks and motor cases if necessary.
  
• Re-qualification tests including stage functional tests of S200, L110 and C25.
  
• Intelligent systems to monitor and identify the imminent failure of systems are to be developed.
  
• Redundancy schemes in all the avionics, control systems, pyro systems and mechanisms are to be re-looked and re-qualified.
  
• Additional facilities for structural test are to be developed for conducting these tests.
  

(https://img.novosti-kosmonavtiki.ru/87735.jpg)
Artist concept of manned LVM3.

ЦитироватьSaturday, January 26, 2013
ISRO LVM3 (GSLV MK3) Images

(https://img.novosti-kosmonavtiki.ru/87736.jpg)
LVM3 on launch pad (credit ISRO)

(https://img.novosti-kosmonavtiki.ru/87737.jpg)
LVM3 acoustics suppression system (credit: ISRO)

(https://img.novosti-kosmonavtiki.ru/87738.jpg)
LVM3 on mobile launch pad (credit: ISRO)

(https://img.novosti-kosmonavtiki.ru/87739.jpg)
LVM3 wind tunnel model (credit: NAL)
 
(https://img.novosti-kosmonavtiki.ru/87740.jpg)
LVM3 S200 solid boosters (credit: ISRO)
 
(https://img.novosti-kosmonavtiki.ru/87741.jpg)
LVM3 wind tunnel test (credit: NAL)

ЦитироватьWednesday, June 12, 2013
LVM3 Update: Vehicle subsytem status

(https://img.novosti-kosmonavtiki.ru/87742.jpg)

ЦитироватьWhat makes the launch crucial for the nation is the use of an indigenous (http://timesofindia.indiatimes.com/topic/Indigenous-(musician))cryogenic engine (http://timesofindia.indiatimes.com/topic/cryogenic-engine) as the upper stage. The first attempt to use an indigenous cryogenic engine on April 15, 2010 to power GSLV-D3 was a failure. With only one more Russian cryogenic engine left in the Isro (http://timesofindia.indiatimes.com/topic/Isro) arsenal, success of the indigenous technology using oxygen and hydrogen in extreme low temperatures as the fuel will propel several big ticket future missions including a manned project to space.
 
 Isro senior scientists led by chairman K Radhakrishnan are monitoring GSLV-D5, whose strap-boosters started getting fuelled soon after the countdown. Liquid propellants are being filled into the second stage. Liquid hydrogen and liquid oxygen, which fuel the cryogenic engine will be filled around 9am on Monday. Scientists at the Satish Dhawan Space Centre told TOI that the rocket's health and weather conditions were fine.
 
 India needs cryogenic engines to launch GSLVs that can carry payloads weighing more than three tonnes, which hold the key to future of telecommunication and space exploration. GSLV-D5 (http://timesofindia.indiatimes.com/topic/GSLV-D5) weighs 414 tonnes.

ЦитироватьNow, ISRO Well on Course to Test Giant Rocket GSLV Mk-III  
 
 By Tiki Rajwi - THIRUVANANTHAPURAM
 Published: 30th January 2014 08:24 AM
 Last Updated: 30th January 2014 08:24 AM

Work on India's most powerful rocket to date, scheduled for an experimental flight in April, is progressing fast. The first stage of the hefty Geosynchronous Satellite Launch Vehicle Mk-III (GSLV Mk-III) is ready, officials of Vikram Sarabhai Space Centre (VSSC) here said. Two S-200 boosters, which use solid fuel, comprise the first stage of Mk-III. This stage will burn for 130 seconds. ''The stage is ready. Work is now progressing on the second stage at the Liquid Propulsion Systems Centre (LPSC) in Mahendragiri,'' VSSC director S Ramakrishnan said. The GSLV Mk-III has three 'stages' in all.

The second stage uses liquid fuel - Unsymmetrical Dimethylhydrazine (UDMH) with Dinitrogen Tetroxide. This stage - L 110 - has two advanced Vikas engines and will burn for 200 seconds. The upper, third stage uses a more powerful version of the cryogenic engine used on the recent GSLV D-5 mission. The engine has been designated CE-2O and uses Liquid Oxygen and Liquid Hydrogen as fuel. Theoretically, this stage will burn for 580 seconds, but the April flight being an experimental one, the cryo stage won't be carrying propellant.

Tests are currently progressing on the engine at present, LPSC director M C Dathan said on the sidelines of a reception given to ISRO scientists here on Monday. ''The third test has been conducted successfully,'' he said. At 42.4 metres, Mk-III is shorter than the regular GSLV, but it has a lift-off weight of around 630 tonnes compared to the latter's 400 tonnes. Mk-III can place satellites weighing up to four tonnes in the geostationary transfer orbit, giving ISRO an edge in the market. If everything goes according to plan, the assembly of the rocket will begin at the Satish Dhawan Space Centre, Sriharikota, in February.

 ''The GSLV Mk-III will have a sub-orbital flight in April. It will have as payload a prototype of the crew module meant for the manned mission,'' Ramakrishnan said. Mk-III will lift off from the second launchpad at Sriharikota, the same one the

GSLV D-5 used on January 5. No modifications will be needed to the launchpad as it can accommodate the bigger GSLV, Ramakrishnan said. A regular flight of the Mk-III version is expected only by 2016.

ЦитироватьPrint edition : February 7, 2014 Interview: K. Radhakrishnan
GSLV MkIII, the next milestone
(https://img.novosti-kosmonavtiki.ru/92090.jpg)
 K. BHAGYA PRAKASH K. Radhakrishnan , Chairman of Indian Space Research Organisation (ISRO).

Interview with K. Radhakrishnan, Chairman, Indian Space Research Organisation. By R. RAMACHANDRAN

FOLLOWING THE SUCCESSFUL LAUNCH OF GSLV D5/GSAT-14, Frontline caught up with K. Radhakrishnan, Chairman, ISRO, on January 10 in New Delhi. In the conversation, Radhakrishnan discussed the various problems faced in the development of cryogenic systems and how these were overcome to prepare the organisation for its next big challenge, a success with GSLV MkIII, which will be powered by an entirely indigenous cryogenic engine and stage, and is targeted for 2015. Excerpts:

What elements of the Mark II cryogenic engine and stage, which fired GSLV-D5, still retain the legacy of Russian engine technology and design? How much of it is truly indigenous and how much of it relies on the Russian heritage?

Basically, both engines use the "staged combustion cycle". That is one approach compared with gas generator cycle, which we are using for the C20 engine to be used in GSLV MkIII. There are several other differences, conceptually also, especially the igniter system that we are using, which is totally different from what has been used in the Russian engine. [In MkII liquid oxygen (LOX) and gaseous hydrogen (GH2) are ignited by pyrogen-type igniters in the pre-burner as well as in the main and steering engines during initial stages, as against pyrotechnic ignition in the Russian engine.] But in the staged combustion cycle, similarities can be found in the way the engine is started and the steering engines are used for controllability.

But the staged combustion cycle itself is quite complex.

The staged combustion cycle is complex but it gives slightly improved performance in terms of the specific impulse [Isp]. But in the gas generator cycle, you have the ability to test the individual elements. So if you look at the reliability aspects—establishing a reliable system and the time required for that—we can work in parallel. The issue is relevant in the context of GSLV MkIII, for which we were working on the engine and stage elements in parallel. The turbo pump, which has something like 5 megawatt of power, has already been tested and it has logged about 1,400 seconds on the ground. We have tested the thrust chamber along with the injector, igniter and the nozzle. We did two tests, and the third test is being done today [January 10]. [This test, which lasted for 50 seconds, was as predicted and was successful.] Now, when we have sufficient knowledge about the ignition characteristics, the combustion instability aspects and performance in different regimes of [LOX+liquid hydrogen, or LH2] mixture ratio, then we can start with engine test and then the stage test. So the time required from now to qualifying the stage becomes less. This is the main advantage. The flexibility that is available in a gas generator cycle is much more because individual systems can be tested from the input/output point of view and they can be qualified in parallel. In the previous situation, the stage process was started after the engine qualification.

 The second aspect of the GSLV MkIII engine is that we are gimballing the nozzle for thrust vector control [and not the two using vernier (steering) engines as in the Russian engine and the cryogenic upper stage (CUS) of the indigenised MkII]. So we are only concerned about two ignitions, that is, the main engine and the gas generator. In the case of GSLV MKII's CUS, the two steering engines have to ignite before the main engine ignites and that feed has to come from the main line. Unless the right temperature and pressure conditions are there at the beginning of that process, the steering engines will not function. In fact, in some of the ground tests, we noticed the problem of a two-phased flow. The most important part of the cryogenic engine is the sustained ignition and the termination of the turbo pumps. It should not give any undue rate for the spacecraft. So in this launch, the engine start was as predicted; the four ignitions were as predicted; similarly, the termination was also as predicted. If you look at the performance of the subsystems, the turbo pumps—the main turbo pump, the oxidiser turbo pump and the fuel booster turbo pump—in both the regimes—the uprated regime and the nominal regime—plus the temperatures, all have been well within the specifications. All the components that it employs, too, have performed well.

In retrospect, considering that it has taken such a long time, could we not have used the gas generator cycle?

No. At that time, before 1992, we were working with a one-tonne engine. We were learning cryo at that time; the learning started in 1982. If you trace the history, in the early 1970s, when the Space Science and Technology Centre was there in Thiruvananthapuram, in the pre-SLV3 stage, we were trying to understand all these propulsion systems, including hyper-propulsion, semi-cryogenic propulsion, and cryogenic propulsion. But then the essential focus was on the SLV-3 programme, which had solid propulsion in all the four stages. And that was essential for the programme. So, in 1992, the approach was technology acquisition. We followed a path and we continued with that.

What is the gain in Isp in the staged combustion cycle?

It is only of the order of 10 seconds.

The one-tonne engine and the subsequent indigenous work were all based on the gas generator cycle. So it would seem that just for that little gain we seem to have embarked on a highly complex technology that has taken such a long time to absorb.

It was complex but at that time it was the only one that was available. We now know that the flexibility available in the gas generator cycle is enormous. It is a learning process.

The GSLV has seen several failures and there must have been a lesson to be learnt from each one of them.

 If you look at the first flight [GSLV-D1], essentially it was related to the mixture ratio used for the Russian cryogenic stage as far as the vehicle was concerned. In the aborted launch that took place [three weeks] earlier [March 28, 2001], essentially it was because of the blockage in one of the feed lines [by a lump of lead in the NO (dinitrogen tetroxide) feed line of the strap-on (S3) liquid engine L-40's gas generator]. The latter called for tightening of the assembly and inspection processes. In the second [GSLV-D2] and the third [GSLV-F01] launches, there were no issues. In the next launch [GSLV-F02], there was again a fabrication issue. A dimension was not inspected during the manufacturing process. When that component [of the strap-on S4] was tested, a deviation was seen but that was taken as a wild point, something to do with the facility. It was too abnormal because we got a flow rate almost nine times what was expected. It was an annular gap which was supposed to be 0.5 mm. Something which was to be 17 mm was made 16 mm, and because of this dimensional change, what was to be 0.5 mm became 1.5 mm, resulting in an increase in the area [3x3] and hence the flow rate. That's what happened.

If you look at the PSLV's first flight, which failed, when we did the simulation on the ground, there was a wild point even at that time. Only one out of some 1,000-plus simulations, but it was taken as a wild point and ignored. So the lesson that we learnt is that wild points are not to be ignored but to be studied. They are an indication of something else that is happening. In F04, the control system of a strap-on stage failed because a gas motor stopped. This has again to do with the component and has nothing to do with the vehicle design. In GSLV-D3, it was again a component problem. All four ignitions started, but it was a pump [fuel booster turbo pump] that stopped. Why did the pump stop? We looked at three scenarios and the contamination theory was the most likely because we found the source of that contamination. It was a propellant acquisition system [PAS], which is basically a filter that ensures that the propellant gets into the outlet.

The initial theory was that there are three bearings, and a normally assembled motor is tested under standard room conditions and not in cryogenic conditions. And when the pump goes into cryogenic temperatures, there will be contraction. Since there are different materials, there would be dissimilar contractions. So tolerances are provided so that the bearing will not stop. But we found that the calculation might not have been done accurately. But the issue is, if it touches [something],will it stop, because there is a lot of power given to it? So we decided to test this in cryogenic conditions. A test facility was created. We did not take [the theory] for granted.

The second scenario is that a welding could have failed and the casing could have come out. We would have had a similar condition then. The possibility of a casing coming out was, however, very remote. But still we redesigned it. We made a casting.

 The third scenario was contamination. We did not want to get locked on to the contamination theory because then we may not see the other things. The PAS is imported and is kept in a sealed cover. When we vibrated it, we found foreign particles coming out. Then we had to do a lot of cleaning and so that was the reason. So we decided to redesign it and that is what we used in D5. Otherwise, the liquid hydrogen tank itself could provide that contamination. All these three issues that we came across have been corrected. So it is a component-level problem and a not system problem. In F06, it was an inspection problem. The cryo-stage shroud, which is expected to move a little bit during the vehicle movement, is supposed to be provided with a lanyard of about 15 mm. But it was almost not there. It was only about 1-2 mm, resulting in greater tension. Two connectors are provided. But both connectors came out. And then we lost the signal from top to bottom. This is what happened actually.

The question is what did we do to address these. Compared with the PSLV, in the GSLV we have a large number of fluid components that have to work in flight. So we make the system, test it and use it and then after some time fly it. In this process, the leak rate would increase sometimes if there are very small defects. So getting a component assembled and tested properly becomes very important. We have tightened that now. In the recent PSLVs also, we have a good record in this area. We have introduced a zero-defect delivery system, which essentially boils down to the person who assembles the component. The technician who assembles the component should be aware of the impact of even a small scratch on a sheet or a dust particle coming into the system or something he might miss during the assembly. We introduced training about one and a half years ago and it is given in situ at the work spot in the local language with examples. When we say that the components have all performed to specifications during the entire campaign, it is actually the result of this. So this is the lesson from the GSLV. Otherwise, the GSLV per se, compared with the PSLV, is a better vehicle. Cryo is complex. Leave that part. If you take the bottom stages, the number of propulsion systems and control systems that come into the picture is far smaller. The only issue there is the solid motor hardware, which will have to be carried for nearly 40 seconds by the strap-ons because that does not separate. The advantage is that proven stages are being used here.

What is the next important milestone for the GSLV?

The immediate thing is GSLV MkIII, the experimental mission with the passive cryo stage.

What do you mean by passive cryo?

No engine will be burnt in the third stage. Actually, if you look at the GSLV, 50 per cent of the velocity is given by the non-cryo portion. So we will get about 5 km/s velocity, and it will be a suborbital flight. But what we want to test here is the atmospheric phase of the flight. While it is coming down, we will use it to characterise the crew module. We can measure the thermal stress when it is coming down. As far as the vehicle is concerned, its exterior will be ditto. Internally, the cryo will be passive.

ЦитироватьCHENNAI,  March 28, 2014  
Updated: March 28, 2014 22:10 IST
GSLV Mark III ready for mission T. S. Subramanian
 
(https://img.novosti-kosmonavtiki.ru/234996.jpg)   
The core second stage of GSLV-Mk III, with 110 tonnes of liquid propellants, just before it was flagged off on Friday from the Liquid Propulsion Systems Centre (LPSC), Mahendragiri, Tamil Nadu. Photo: LSPC, ISRO     
 
 A forerunner to the Human Space Flight programme
 
 India took the first step on Friday towards the liftoff of the experimental mission of its gigantic Geo-synchronous Satellite Launch Vehicle-Mark III when the rocket's core stage, weighing more than 110 tonnes, was flagged off from the Liquid Propulsion Systems Centre, Mahendragiri, near Nagercoil, Tamil Nadu, to Sriharikota in Andhra Pradesh. The significance of the mission is that it will be a forerunner to India sending its astronauts to space. For, the GSLV-Mk III in this flight will carry a crew capsule without astronauts. The capsule will return to earth with the help of parachutes. The mission will take place in June or first week of July.
 The Indian Space Research Organisation calls its mission to send Indian astronauts to space the Human Space Flight (HSF) programme.
K. Radhakrishnan, Chairman, ISRO, said the crew capsule will weigh 3.5 tonnes. It will carry no astronauts, he stressed. It was a replica of the crew module that would be put into orbit in a real mission. "The module is undergoing structural engineering tests" at the Vikram Sarabhai Space Centre, Dr. Radhakrishnan said.
 M.C. Dathan, Director, LPSC, emphasised that it will be an experimental mission. The rocket will do a sub-orbital flight, that is, reach an altitude of less than 100 km. Its upper cryogenic stage will not fire. It is "a passive flight," Mr. Dathan said. Instead of cryogenic propellants, the cryogenic stage would carry liquid nitrogen, which would be inert.
GSLV-Mk III is the "muscular sibling" of GSLV-Mk II which has an indigenous cryogenic engine. GSLV-Mk III can put a communication satellite weighing four tonnes into geo-synchronous transfer orbit or a 10-tonne satellite into low-earth orbit.
Mr. Dathan said GSLV-Mk III's core stage was flagged off from Mahendragiri on Friday. It would reach Sriharikota on Sunday evening. It will be married up with the other stages there.
"The assembling of one booster stage, weighing more than 200 tonnes, has already been completed at Sriharikota. The assembly of another booster stage is under way."

Цитироватьantriksh пишет:
Crew Module structural assembly ready for LVM3 X1 mission

 (https://forum.novosti-kosmonavtiki.ru/forum/file/33339)

ЦитироватьSRIHARIKOTA,  April 5, 2014  
Updated: April 5, 2014 03:58 IST
GSLV to soar into sky with crew capsule in June  T. S. Subramanian
 
 (https://img.novosti-kosmonavtiki.ru/234997.jpg)   
 
  ISRO Chairman K. Radhakrishnan (centre) with S. Ramakrishnan, Director, VSSC, Thiruvananthapuram (left), P. Kunhikrishnan, Mission Director, PSLV - C24 (second from left), M. Nageswara Rao, Project Director, IRNSS (second from right), and A.S. Kiran Kumar, Director, Space Application Centre, Ahmedabad (right), after the successful launch of IRNSS-1B from Sriharikota on Friday. Photo: K. V. Srinivasan  
 India's huge Geo-synchronous Satellite Launch Vehicle (GSLV- Mark III) will soar into the sky with a crew capsule from Sriharikota in June, signalling that the country is getting ready to send its own astronauts into space. It will be an experimental mission and it will carry no astronauts. This crew capsule will return to the earth with parachutes.
It would be identical to the "final crew capsule in structural and thermo-structural parts," said S. Ramakrishnan, Director, Vikram Sarabhai Space Centre, Thiruvananthapuram. "We will take it beyond the atmosphere, make it re-enter the earth's atmosphere, decelerate it and make a soft touchdown in the Bay of Bengal off the Andaman coast. We will make efforts to recover it."
The VSSC Director was speaking to reporters here after the Polar Satellite Launch Vehicle (PSLV-C24) put into orbit India's second navigation satellite, the Indian Regional Navigation Satellite System (IRNSS-1B).
Mr. Ramakrishnan said the Indian Space Research Organisation would evaluate the structural and thermal protection systems to withstand the re-entry load, and thermo-dynamic heating.
This crew capsule will not contain the life-support systems which will be required when actual astronauts fly in the crew capsule. "We will be measuring the environment inside the capsule which will give inputs on the validation of the astronauts' life-support systems in terms of temperature, vibration and shock which will be experienced inside the crew capsule. This will help us in designing the life-support systems when we actually fly the astronauts into space."
 No astronauts would be aboard the crew capsule in the GSLV-MkIII mission, he stressed.
K. Radhakrishnan, ISRO Chairman, said the June mission would be a passive flight. Its massive cryogenic engine would not fire.
The GSLV-MkIII was getting assembled at Sriharikota, Dr. Radhakrishnan said. Its two strap-on motors had arrived at the spaceport. . The cryogenic stage is getting ready in the ISRO Propulsion Complex at Mahendragiri, Tamil Nadu.
Dr. Radhakrishnan said the PSLV would put into orbit in June the French SPOT-7 satellite and four other satellites from abroad.

ЦитироватьMr. Modi saw the fully assembled four-stage PSLV-C23 and visited the VAB of the second launch pad where the integration of the gigantic GSLV-Mark III (Geo-synchronous Satellite Launch Vehicle) is under way. An experimental flight of the GSLV-MKIII is scheduled for August.
...
In the VAB of the second launch pad, Mr. Radhakrishnan explained the salient features of the GSLV-MkIII experimental mission. In the VAB, the Prime Minister saw the fully assembled two strap-on booster motors of the GSLV-MkIII, each weighing 200 tonnes.

ЦитироватьGSLV MkIII to launch Isro's next mission
Vanita Srivastava, Hindustan Times  New Delhi, July 01, 2014
First Published: 00:43 IST(1/7/2014)

After the successful launch of PSLV-C23 carrying five foreign satellites on Monday, the next major launch lined up by the Indian Space Research Organisation (Isro) is GSLV MkIII experimental mission carrying the crew module, a senior Isro official said.

"For the manned mission, we need a crew module in which the astronauts will be housed. This will orbit and can then be recovered. We are planning an experimental flight of GSLV Mk III with passive cryogenic stage in August this year to validate the vehicle performance during the atmospheric phase of the flight. The first developmental flight of GSLV-Mk III is targeted for 2016," he said.

 India's attempt to develop a heavy lift launch vehicle has reached a significant milestone with GSLV-Mk III, which is capable of launching 4 tonne class of communication satellites to Geo-synchronous Transfer Orbit (GTO), he said adding: "This vehicle has two 200 tonne solid booster (S-200) stage and L-110 tonne liquid core stage. Realisation of GSLV Mk-III will help Isro to put heavier satellites into orbit."

Regarding the preparedness of Isro for the human space flight he said: "The program is yet to be approved. Isro is developing certain critical technologies to fit the same. The crew module that will be launched by GSLV MkIII experimental mission is one such development."

ЦитироватьGSLV Mark 3 gets Rs 161 crore boost
Jul 11, 2014, 07.25 AM IST

The first budget of the Narendra Modi government has given a powerful boost to the GSLV Mark 3 rocket programme with its budgetary allocation rocketing from Rs 10 crore to Rs 171 crore.

The Mark 3 is an advanced version of the current GSLV (Geosynchronous Satellite Launch Vehicle) rocket, with a capacity to place four-tonne class of communication satellites in the geostationary transfer orbit. Once this launch vehicle becomes operational, India need not depend upon European space consortium Arianespace to carry its four-tonne class of Insat communication satellites. This rocket will also be used to fly astronauts from Sriharikota.

The massive hike for this much-delayed project assumes significance in the context of Prime Minister Narendra Modi assuring Isro at the launch of PSLV-C-23 on June 30 that his government would fully support India's space programme. The PM had said that "continued progress in space must remain a national mission. We must keep enhancing our space capabilities."

An Isro official told TOI that provisionally the GSLV Mark 3 was set to make its maiden flight towards the end of August with a passive cryogenic engine. This means the cryogenic stage will not be operational. The significance of the flight is that it will test the crew compartment as it re-enters and splashes into the Bay of Bengal.

The amount earmarked for the human space flight programme has also gone up: from Rs 9.19 crore to Rs 17.05 crore. This project, too, has been considerably delayed and Isro officials hope the new government will give its green signal at the earliest.

The Isro Propulsion Complex at Mahendragiri in Tamil Nadu has been allotted Rs 100 crore.

The budget document, however goofed up with regards to the Mars Orbiter Mission. In a note at the end of the document, it said: "Mars orbiter will be placed in an orbit of 500 X 80,000 km around Mars and will have a provision for carrying nearly 25 kg of scientific payloads on board.'' The orbit of the spacecraft will be 377 X 80,000 km and it is carrying 15 kg of payloads.

ЦитироватьNow, Gupta works on the next generation Geostationary Launch Vehicle (GSLV), the heavy lifter that ISRO is developing for launch next year, and sits in its design review committee.

ЦитироватьThiruvananthapuram: India does not need to rely on foreign countries for launching heavier communication satellites once its experimental mission of GSLV Mark III tasted success, Vikram Sarabhai Space Centre (VSSC) Director M Chandra Dathan on Saturday said.
"The GSLV Mark III, scheduled to be launched in November first week, will carry four tonne class of communication satellites and it will help India achieve self-reliance in this," he said.

ЦитироватьISRO Logs Milestone with Cryo Engine  
 
 By Tiki Rajwi
 Published: 22nd October 2014 03:17 AM
 
THIRUVANANTHAPURAM : Taking a big step forward in the development of bigger and more powerful locally-built rocket engines, the Liquid Propulsion Systems Centre (LPSC) on Monday successfully conducted the first 'cold flow test' on the CE-20 cryogenic engine, which will power the upper stage of the Geosynchronous Satellite Launch Vehicle-Mk III (GSLV-Mk III).
 "It's a milestone," LPSC director Dr K Sivan told 'Express' here on Tuesday, confirming that the test had gone as planned at the LPSC facility in Mahendragiri, Tamil Nadu. The first 'hot test' - where the engine will be fired for a few seconds- will be performed in three weeks' time, Sivan said. In a cold test, the propellants are not ignited. Cryogenic engines were back in the news with the Kerala High Court making a reference to it on Monday while passing a directive on the infamous ISRO spy case of 1994. The spy case had delayed its development and the ISRO could conduct the first successful flight test aboard the GSLV-Mk II type launch vehicle (GSLV-D5) only on January 5, 2014.
CE-20 is a mightier version of the CE-7.5 engine used in the GSLV-D5 mission. Cryogenic technology is highly complex as the propellants must be stored at extremely low temperatures. The work is progressing on another CE-7.5 engine, which will power the upper stage of the GSLV-D6, a ditto version of the GSLV-D5, expected to be flown in March-April 2015. This flight is very crucial for ISRO to prove that the cryo stage is reliable.
 "The work on the engine is in an advanced stage," said N R Vishnu Kartha, LPSC associate director and GSLV Cryogenic Upper Stage Project director.
The CE-20 will make isro self-reliant
The success of the CE-20 engine is crucial for the GSLV Mk-III launch vehicle project. This Mk-III rocket will make ISRO self-reliant in the launch of heavier communication satellites in the 4000-plus kg class. The rocket will give ISRO an edge in the international satellite launch market.

ЦитироватьISRO successfully tests its GSLV Mk III cryogenic engine
(https://img.novosti-kosmonavtiki.ru/234609.jpg)
The GSLV Mk III booster at Satish Dhawan Space Centre, Andhra Pradesh, India. Photo Credit: ISRO         
             
Tomasz Nowakowski
March 16th, 2015          
                                 
The Indian Space Research Organisation (ISRO (http://isro.gov.in/) ) successfully conducted a test on Saturday Mar. 14 to check the GSLV Mk III launch vehicle's indigenous cryogenic CE-20 engine at ISRO Propulsion Complex (IPRC) in Mahendragiri, Tirunelveli district. The test is just the latest step toward providing the ISRO with the capability of sending astronauts to low-Earth orbit (LEO).
"It is yet another milestone achievement on the road map of developing a bigger and more powerful indigenously-built high thrust cryogenic upper stage for GSLV Mk III (http://www.nasaspaceflight.com/2014/12/india-gslv-mk-iii-prototype-crew-capsule/) rocket for the Indian Space Program," said IPRC Director D. Karthikesan. IPRC is called the "Jet Propulsion Laboratory of India" as all stage and engine related tests of ISRO's launch vehicles and satellites are carried out there.
The CE-20 was ignited and was tested for 20 seconds to study the flight characteristics of the engine. All the major parameters of CE-20 were normal and further tests are planned in the coming months.
Various subsystems of CE-20, such as the injector, thrust chamber, gas generator, liquid oxygen and liquid hydrogen turbo pumps were tested earlier at IPRC.
(https://img.novosti-kosmonavtiki.ru/234612.jpg) (https://img.novosti-kosmonavtiki.ru/234612.jpg)
GSLV Mk III launch on Dec. 18, 2014. Credit: ISRO
 
The GSLV Mk III launch vehicle is designed to be capable of sending satellites into geostationary orbit and will also be used as a launcher for an Indian crewed vehicle. The booster is meant to help the country carry out major scientific missions in space.
"The GSLV Mk III rocket has a payload capacity of four tons which would enable to carry out space missions successfully. Besides, there is also a billion-dollar satellite market that could be tapped for the commercial benefit of the country," said former ISRO director Suresh Naik.
Weighing approximately 630 tons, the GSLV Mk III is a new-generation launch vehicle, one which measures an estimated 43 meters (142 ft) long. The cryogenic upper stage C 25 will be powered by the CE-20 engine burning liquid oxygen and liquid hydrogen, producing 186 kilonewtons (19.0 tf) of thrust. The C 25 will be 13 feet (4 meters) in diameter and 44 feet (13.5 meters) long. Fully fueled, the rocket should carry some 27 tons of propellant.
A suborbital flight test of the GSLV Mk III launcher, with a passive cryogenic third stage, was successfully carried out on Dec. 18, 2014. This flight was used to test out the Crew Module Atmospheric Re-entry Experiment (CARE) on a suborbital trajectory.
"The GSLV will also be useful for carrying out Indian human space missions through Chandrayaan-3. In the recent years, India has been successful in reducing dependency on other countries to launch satellites, while many nations are carrying out the process from India due to cost effectiveness and reliability," Naik said.
The next launch of GSLV Mk III is planned to take place in early 2017. That mission will put in the GSAT-19E communication satellite into orbit.

Цитироватьche wi пишет:
Isro successfully tests indigenous cryogenic engine with four-tonne capacity
 http://www.livemint.com/Politics/dFq7NvUyKp7EMxD67udqPP/Isro-successfully-tests-indigenous-cryogenic-engine-with-fou.html

ЦитироватьNew Delhi: The Indian Space Research Organisation (Isro) successfully tested an indigenous cryogenic engine on Tuesday which will allow launch vehicles to carry satellites of up to four tonnes.

Congratulating the scientists on the successful testing, Prime Minister Narendra Modi said on Twitter, "The engine tested today will enable us to put satellites of up to 4 tons in geostationary orbit. A proud accomplishment."

Although the Geosynchronous Satellite Launch Vehicle (GSLV Mark III) successfully launched an unmanned capsule that could be used for manned missions in December, it had a passive cryogenic stage. While GSLV Mark III is India's largest launch vehicle, carrying up to four-tonne vehicles will only be possible with a cryogenic engine with the capacity.

India has till now been dependent on foreign launch vehicles to send heavier satellites to the required orbits. "There was a special test set up in Mahendragiri to see if the engine developed the exact thrust required to launch payloads of that weight. It succeeded," an Isro spokesperson told Mint on the phone.

"Now we'll have to prove if this engine can be used in a launch vehicle," the spokesperson added. Mahendragiri in Tamil Nadu is home to the Isro Propulsion Complex, where cryogenic engines are tested.

India has been on a long arduous journey to develop an operational indigenous cryogenic engine which began around 30 years ago. The first success came in January last year, when India successfully launched GSLV-D5, marking the first successful launch of a vehicle with an indigenous cryogenic engine. But India at present can only launch satellites of up to two tonnes.

ЦитироватьSuccessful testing of High Thrust Cryogenic Engine

A major milestone in the development of ISRO's next generation launch vehicle, GSLV MkIII, was achieved on successful long duration hot test (635 seconds) of high thrust cryogenic engine (CE20) on 28-04-2015 at ISRO Propulsion Complex, Mahendragiri, Tamil Nadu. The CE20 cryogenic engine is being indigenously developed by ISRO to power the cryogenic stage of GSLV MkIII launch vehicle.
 The completion of successful long duration hot test has once again proved ISRO's capability in mastering the complex cryogenic technology. All subsystems of this engine such as Thrust Chamber, Injector, Gas Generator, LOX & LH2 Turbopumps, Control Components, Pyro systems etc., and the ground Test Facility systems performed very well and the parameters are well within the prediction.
 A series of development tests on this engine are being carried out to validate the performance and to prove the design of the engine. Two cold start tests and four short duration hot tests were already carried out on this engine at IPRC, Mahendragiri.

ЦитироватьHigh Thrust Cryogenic Engine (CE20) Development
 (https://forum.novosti-kosmonavtiki.ru/forum/file/54582)
ISRO is developing a high thrust cryogenic engine to be used for the upper stage of its heavy lift launch vehicle GSLV Mk-III. This high thrust cryogenic engine produces a nominal thrust of 196.5 kN in vacuum with a specific impulse of 434 seconds. The engine works on "Gas Generator Cycle" which has flexibility for independent development of each sub-system before the integrated engine test, thus minimising uncertainty in the final developmental phase and reducing development time. This engine generates nearly 2 MW power as compared to 1 MW generated by the engine of Cryogenic Upper Stage (CUS) engine of GSLV. The high thrust cryogenic engine is one of the most powerful cryogenic engines of upper stages in the world.
ISRO has achieved a major milestone by successfully conducting the ground test of Indigenous High Thrust Cryogenic Engine at ISRO Propulsion Complex at Mahendragiri on April 28, 2015 at 1657 Hrs for a duration of 635 seconds.  All the propulsion parameters during the tests were found satisfactory and closely matched with predictions. This ground test was preceded in the last few weeks, by four short duration tests of 5.5, 7.5, 20 and 30 seconds.
The high thrust cryogenic engine is designed and realised by Liquid Propulsion Systems Centre (LPSC) at Valiamala with the support of Vikram Sarabhai Space Centre (VSSC) at Thiruvananthapuram. The engine assembly, integration and testing is carried out by ISRO Propulsion Complex (IPRC) at Mahendragiri. Indian Industries have significantly contributed in the realization of the cryogenic engine.
While ground tests conducted so far validate this the design adequacy and performance of the integrated engine, further demonstration tests are planned at engine and stage level to characterise the different performance parameters under various operating conditions. After completion of the tests, the indigenous high thrust cryogenic engine and stage are planned to be flight tested in GSLV Mk- III-D1 mission.

ЦитироватьLVM3
       
About the Launch Vehicle          
LVM 3 is a heavy launch capability launcher being developed by ISRO. It will allow India to achieve complete self reliance in launching satellites as it will be capable of placing 4 tonne class Geosynchronous satellites into orbit. The LVM3 will have an India built cryogenic stage with higher capacity than GSLV. The first experimental flight of LVM3, the LVM3-X/CARE mission lifted off from Sriharikota on December 18, 2014 and successfully tested the atmospheric phase of flight. Crew module Atmospheric Reentry Experiment was also carried out in this flight. The module reentered, deployed its parachutes as planned and splashed down in the Bay of Bengal.
          
          Vehicle Specifications          

Height	: 43.43 m
Vehicle Diameter	: 4.0 m
Heat Shield Diameter	: 5.0 m
Number of Stages	: 3
Lift Off Mass	: 640 tonnes

      
    (https://img.novosti-kosmonavtiki.ru/230434.png)      
              
          
          TECHNICAL SPECIFICATIONS    
             
(https://img.novosti-kosmonavtiki.ru/230430.png)
Payload to GTO: 4,000 kg
LVM3 will be capable of placing the 4 tonne class satellites of the GSAT series into Geosynchronous Transfer Orbits.
             
(https://img.novosti-kosmonavtiki.ru/230431.png)
Payload to LEO: 8,000 kg
The powerful cryogenic stage of LVM3 enables it to place heavy payloads into Low Earth Orbits of 600 km altitude.
             
(https://img.novosti-kosmonavtiki.ru/230432.png)
Cryogenic Upper Stage : C25
The C25 is powered by CE-20, India's largest cryogenic engine, designed and developed by the Liquid Propulsion Systems Centre of ISRO located at Thiruvananthapuram.
             

Cryo Stage Height	: 13.5 m
Cryo Stage Diameter	: 4.0 m
Engine	: CE-20
Fuel	: 27 tonnes of LOX + LH2
Thrust	: 186 kN

            
(https://img.novosti-kosmonavtiki.ru/230435.png)
Solid Rocket Boosters : S200
LVM3 uses two S200 solid rocket boosters to provide the huge amount of thrust required for lift off. The S200 was developed at Vikram Sarabhai Space Centre.
             

Booster Height	: 25 m
Booster Diameter	: 3.2 m
Fuel	: 207 tonnes of HTPB (nominal)
Thrust	: 9316 kN
Vacuum Isp	: 274.5 sec
Burntime	: 130 sec

                      
(https://img.novosti-kosmonavtiki.ru/230433.png)
Core Stage : L110 Liquid Stage
The L110 liquid stage is powered by two Vikas engines designed and developed at the Liquid Propulsion Systems Centre.
             

Stage Height	: 17 m
Stage Diameter	: 4 m
Engine	: 2 x Vikas
Fuel	: 110 tonnes of UDMH + N2O4
Thrust	: 1598 kN
Vacuum Isp	: 293 sec
Burntime	: 200 sec

ЦитироватьThe Indian Space Research Organisation (ISRO) successfully conducted the much-awaited 'full endurance test' of the Geosynchronous Satellite Launch Vehicle Mk III's indigenous cryogenic CE-20 engine at ISRO Propulsion Complex (IPRC) in Mahendragiri in the district on Thursday.

The CE-20 was ignited and tested for 800 seconds from 5 p.m. to study the performance of the engine though the actual required duration was only 635 seconds.

During the actual flight of the GSLV, the engine will be ignited for only 635 seconds.

Parameters normal

"All major parameters of CE-20 were normal and the test comfortably met all predetermined results," D. Karthikesan, Director, IPRC, Mahendragiri, who witnessed the test along with his colleagues, told The Hindu on Thursday evening.

An elated Mr. Karthikesan termed the successful conduct of 'full endurance test' yet another milestone in developing a bigger and more powerful indigenously built high thrust cryogenic upper stage for the 43-metre-tall GSLV Mk III that would position heavier payloads (satellites weighing about 4,000 kg) in the geostationary orbit.

He said that the subsystems of CE-20 such as injector, thrust chamber, gas generator, liquid oxygen and liquid hydrogen turbo pumps were tested at the IPRC, known among the ISRO scientists as the 'Jet Propulsion Laboratory of India', as every parameter of ISRO's launch vehicles are tested only here.

A suborbital flight test of GSLV Mk III launcher, with a passive cryogenic third stage, was successfully carried out on December 18, 2014, and was used to test a Crew Module Atmospheric Re-entry Experiment (CARE) on a suborbital trajectory.

A morale booster

Since the ISRO has planned to go in for the next launch of GSLV Mk III within next 18 months, the successful 'full endurance test' for 800 seconds has come as a morale booster for its scientists at IPRC.

The mission will put in the GSAT-19E communication satellite into orbit.

Цитировать(https://img.novosti-kosmonavtiki.ru/158342.jpg)
  (https://img.novosti-kosmonavtiki.ru/69464.jpg) ISRO ‏@isro  (https://twitter.com/isro) 10 мая (https://twitter.com/isro/status/729896352063225856)
Nozzle Testing Laboratories established at VSSC http://www.isro.gov.in/nozzle-testing-laboratories-established-vssc ... (https://t.co/VMPuBoHB8g)

ЦитироватьNozzle Testing Laboratories established at VSSC
(http://www.isro.gov.in/sites/default/files/article-files/node/4109/nozzle.jpg)

Performance improvement in propulsion systems is essential towards achieving cost effective launch vehicles. Apart from propellant energetics, the nozzle plays a vital role in improving propulsion system performance. Therefore by improving performance of existing nozzles and by developing new nozzle concepts, which can operate at both low and high altitude regimes, it is possible to obtain significant gains in the delivered specific impulse of rockets. With these objectives, ISRO has established Nozzle Testing Laboratories (NTL) at Vikram Sarabhai Space Centre (VSSC), Thiruvananthapuram.
 
The NTL consists of a Nitrogen gas generation and storage system, a graphite cored induction heater (for heating nitrogen), a test chamber, a diffuser system and heat exchanger, coolant system and power supply systems. The facility utilizes the available 6600 m3 capacity vacuum vessel of the Hypersonic Wind Tunnel (HWT) for simulation of altitude pressure. For nozzle performance evaluation, heated nitrogen gas is allowed to expand in nozzles kept in the test chamber having simulated altitude pressure.  Gaseous nitrogen admitted to the storage heater from the top exits the heater at the required temperature. The facility utilises fast response pressure transducers and instrumentation to study nozzle phenomena. Nozzles up to Area Ratio (AR) 300 and more can be tested in the facility.
 
The NTL has the capability to cater to a wide range of studies related to nozzles such as:
 

[/li]
•      Contour optimization for large AR nozzles
•      Flow separation, techniques for flow separation control
•      Nozzle wall heat transfer
•      Regenerative cooling
•      Supersonic film cooling
•      Evaluation of new nozzle concepts
  

Experimental validation of flow separation control devices with minimal modifications in the existing contour nozzles enabling high AR operation can be carried out. Specific tests can be devised and carried out to validate Computational Fluid Dynamics (CFD) predictions. The facility can also be used to carry out open jet heat transfer studies.
 
The Nozzle Testing Laboratories was inaugurated recently by Chairman, ISRO which is a unique facility established for the first time in the country towards carrying out advanced R&D in the area of rocket nozzle. 
 
(http://www.isro.gov.in/sites/default/files/article-files/node/4109/inside_view_of_ntl.jpg)
Inside view of NTL
 
(http://www.isro.gov.in/sites/default/files/article-files/node/4109/typical_100_ar_nozzle.jpg)
A typical 100 AR nozzle developed for tests in the facility

(http://www.isro.gov.in/sites/default/files/article-files/node/4109/nozzle_testing_laboratories.jpg)
Nozzle Testing Laboratories (NTL) Building at VSSC

ЦитироватьAndrey Samoilov пишет:
Индия в рамках проекта Two Stage To Orbit разрабатывает многоразовую первую ступень, как у SpaceX

ЦитироватьComing to a commercial market near you: India's GSLV Mark 3
On the heels of the PSLV is India's GSLV Mark 3 rocket, designed to carry satellites weighing up to 4,000 kilograms into geostationary transfer orbit, the destination of most telecommunications satellites.
As is the case with start-up U.S. rockets, the GSLV is far behind schedule but is moving inexorably toward operations. A 50-second test of its CS 25 cryogenic upper-stage engine on Jan. 25 was declared a success.
ISRO Chairman A.S. Kiran Kumar said after the PSLV launch that a flight-duration test of the engine, lasting 640 seconds, was scheduled for Feb. 17.

ЦитироватьИндия успешно испытала собственный криогенный двигатель для тяжелой ракеты-носителя
НЬЮ-ДЕЛИ, 18 февраля. /Корр. ТАСС Евгений Пахомов/. Индийская организация космических исследований провела успешное испытание криогенного двигателя собственной разработки, предназначенного для тяжелой ракеты-носителя нового поколения. Как сообщает телеканал NDTV (http://www.ndtv.com/india-news/isro-tests-indias-largest-cryogenic-engine-for-400-ton-rocket-1660935?pfrom=home-lateststories), силовой агрегат проработал полные 10 минут.
Испытания состоялись днем ранее на территории двигателестроительного комплекса в Махендрагири на юге страны. Силовой агрегат предназначен для установки на новой индийской ракете-носителе GSLV Mark III  высотой около 50 м и весом более 414 тонн. Эти испытания стали последними перед запуском ракеты, который может состоятся в этом году, указывает телеканал.
Новый мощный носитель GSLV Mark III сможет выводить грузы до 10 тонн на низкую околоземную орбиту и до 4 тонн - на геосинхронную орбиту. Планируется также, что он может быть использован для выведения на орбиту первого индийского космического корабля с людьми на борту. В перспективе GSLV Mark III также предназначается для запуска межпланетных автоматических станций.
Как указывает NDTV, разработка нового двигателя потребовала почти 20 лет, поскольку в 1990-е годы Россия под давлением США была вынуждена отказаться от передачи индийской стороне технологий производства криогенных силовых установок. Создание такого двигателя - очень сложная задача, ее смогли решить только РФ, США, Франция, Китай, Япония и Индия, отмечает телеканал.

ЦитироватьIndia to launch GSLV Mark-III in another two months: ISRO space scientist
 ISRO scientist TGK Murthy says India will also launch a satellite to study the sun and global climate change named Aditya-L1 weighing 400 kg
PTI (http://www.livemint.com/Search/Link/Author/PTI)
(https://img.novosti-kosmonavtiki.ru/230996.jpg)
ISRO has been successful in testing high-thrust cryogenic technology for use in the launch vehicle, GSLV Mark-III, said ISRO's TGK Murthy. Photo: Wikimedia commons

Kolkata: India is going to launch GSLV Mark-III, the country's most powerful launch vehicle, in another two months, senior space scientist and ex-programme director of ISRO professor T.G.K. Murthy said on Friday.
"In another two months, we are going to launch GSLV Mark-III. We are going to launch four satellites from the Indian soil in the near future," Murthy told PTI on the sidelines of a three-day international conference on 'Advances in Science and Technology' in Kolkata.
ISRO has been successful in testing the high-thrust cryogenic technology for use in the launch vehicle, GSLV Mark-III, the space scientist said.

ЦитироватьThe vehicle is designed to take a payload of four tonnes, but it would still not be enough for some of Isro's future requirements.

"Satellites are getting heavier and heavier," says K Sivan, director of the Vikram Sarabhai Space Centre (VSSC) in Thiruvananthapuram. "So we have to increase the capacity of the vehicle."

GSLV Mark III can be tweaked to later to carry more than six tonnes of payload into a geostationary orbit, by replacing the core liquid stage with a semi-cryogenic engine. This engine is under development, and might take three to four years. After its development, India would be able to put six to seven tonne-class of satellites into a geostationary orbit, and stop using expensive overseas facilities for launching its communication satellites.

Цитировать'Baahubali' rocket GSLV Mk-III has perfect launch
U Tejonmayam | Jun 6, 2017, 04.23 AM IST
ISRO's heaviest rocket GSLV Mk-III was launched successfully
(https://img.novosti-kosmonavtiki.ru/221358.jpg)
 SRIHARIKOTA: The country took another step towards establishing itself in the global heavy payload market, successfully launching its most powerful rocket, GSLV Mk III, on Monday .
 
 After the rocket, nicknamed "Fat Boy", fired by a high-thrust indigenous cryogenic engine, lifted off at 5.28pm fr om the second launch pad at the Satish Dhawan Space Centre (http://timesofindia.indiatimes.com/topic/Satish-Dhawan-Space-Centre) in Sriharikota, a fourtonne communications satellite, GSAT 19, the country's heaviest, was placed in geosynchronous transfer orbit 15.53 minutes later, a few seconds earlier than scheduled.
 
 The Indian Space Research Organisation (Isro) has now demonstrated its mastery in developing a cryogenic engine, a technology denied to it years ago. The launch also proves the homegrown launch vehicle's capability of hurling up to four payloads into higher orbits. Isro (http://timesofindia.indiatimes.com/topic/Isro) chairman A S Kiran Kumar (http://timesofindia.indiatimes.com/topic/Kiran-Kumar) said, "The GSLV Mk III needs just one more developmental flight, planned in a year, before it can be declared operational."
 
 The boosters of satellite GSAT 19 would be fired at 9.30am on Tuesday to make a series of manoeuvres in the next two days so that it would be placed in its orbital slot in two weeks, he said.
 
 The launch demonstrated an indigenous cryogenic engine, in the works since 2002, a strong foundation for ambitious future projects, including Chandraayan II, scheduled for the first quarter of 2018, and a manned mission. It also showed the capability to make a next-generation satellite with a high reach. The satellite contains 50 new technologies which will be its mainstay in the next decade.
 
 The mood was upbeat at mission control wh ere scientists burst into applause when the cryogenic stage started to burn. On its maiden flight, the CE-20 engine was operational for 640 seconds. Congratulating the scientists and others involved in the mission, Kiran Kumar said it was a historic day . "The entire team has worked since 2002. The vehicle carried the next-generation satellite."
 
 Dr K Sivan, Vikram Sarabhai Space Centre director, said it was the commencement of complex technologies -a vehicle that can carry twice the payload weight and a high throughput satellite. "It is the continued efforts of the team and industry contribution."
 
 Satish Dhawan Space Centre director P Kunhikrishnan said Isro had made two new technologies for GSLV MkIII at the launch pad. "We made an acoustic suppression unit, which is a tower containing 600 tonnes of water, and a solid propellant plant to prepare the 200 tonnes each of propellant loaded in each of the motors. The suppression unit splashed the water on the rocket when it lifted off." Satish Dhawan Space CenS tre director P Kunhikrish nan said integration for the next launch of PSLV C38 was on simultaneously at the first launch pad. "It is planned for the next half of the month.The next GSLV Mk III will be integrated in the new vehicle assembly , which will be three times bigger," he said.
 
 GSAT-19 carried transponders and a geostationary radiation spectrometer which will monitor and study the nature of charged particles and the influence of space radiation on satellites and their electronic components.

 Kiran Kumar said the immediate requirement was to improve the launch frequency of PSLVs and undertake at least two GSLV MkII launches per year. "NASA 's synthetic aperture radar will be launched using a MkII rocket.The cost of doing the launches in India is cheaper than going abroad. At the cost of hiring a launch vehicle abroad, we can make a launch vehicle and satellite here," he said.
 
 Commenting on commercialisation of the GSLV launch, he said "with every launch credibility will go up and customers will have confidence, and it will also bring down the insurance premium". On whether India would go abroad for future launches, he said the country had not used foreign launch vehicles to put satellites in lower Earth orbit since 1995.

ЦитироватьThe Indian Space Research Organisation (ISRO) has progressed to the testing of subsystems in the development of a semi-cryogenic engine for rockets with heavier payload capacity.

The testing facilities at the ISRO Propulsion Complex, Mahendragiri, are being augmented for the engine being developed by the Liquid Propulsion Systems Centre here under a project codenamed SCE 200. Three of the four turbo pumps of the new engine have been tested and the pre-burner and thrust chamber are being readied for testing, LPSC Director S. Somanath told The Hindu.

The semi-cryogenic engine uses a combination of liquid oxygen (LOX) and refined kerosene (Isrosene) as propellants.

ISRO scientists have simultaneously begun work on the stage configuration. ''We hope to complete the development of the engine by 2019. The stage test is expected to take place by 2020, followed by the first flight test in 2021,'' he said.

One of the options before ISRO is to replace the liquid core (L110) engine of the GSLV Mark 3 with the SCE-200 to boost the payload capacity of the rocket from four to six tonnes. ''That could be one of the immediate applications of the new engine, though the objective is to power the future heavy lift launch vehicles and reusable launch vehicles as well as human spaceflight missions,'' K. Sivan, Director, Vikram Sarabhai Space Centre, said.

Mindful of the fact that the standard size of satellites is expected to go up in the near future, ISRO is already looking much ahead. On the cards is a proposal to develop a bigger semi cryogenic engine with a cluster of four or five engines that could generate a lift of eight to 10 tonnes.

A clustered semi cryogenic booster with a more powerful cryogenic upper stage is another possibility. ''Once we have mastered the technology, we could possibly go on to modular development of rockets with different configurations,'' Mr. Somanath said.

But before that, ISRO needs to ensure that critical technologies such as special materials and coatings, brazing process, kerosene refinement, combustion instability and control components are mastered and the necessary infrastructure is in place.

ЦитироватьThe semi-cryogenic engine uses a combination of liquid oxygen (LOX) and refined kerosene (Isrosene) as propellants.

ЦитироватьAccording to ISRO fully integrated SCE-200 will be delivered ready for testing by the end of year. A hot fire should take place between Jan-June 2018 depending on readiness of new testing facility.

ЦитироватьIsro gets nod for semi-cryogenic engine, will boost GSLV's lift capability by 1 tonneSurendra Singh (https://timesofindia.indiatimes.com/toireporter/author-Surendra-Singh-30991123.cms) | TNN | Jun 8, 2018, 06:27 IST

Highlights

[/li]
• Space Commission has given approval to Isro to develop a semi-croygenic engine, which will increase the lifting capability of its GSLV Mk III rocket by one tonne
• Satellites will track now production of 25 crops instead of eight: Isro chief
  

(https://img.novosti-kosmonavtiki.ru/194835.png)
NEW DELHI: The Space Commission (https://timesofindia.indiatimes.com/topic/Space-Commission) has given approval to Indian Space Research Organisation (Isro (https://timesofindia.indiatimes.com/topic/ISRO)) to develop a semi-croygenic engine, which will increase the lifting capability of its GSLV (https://timesofindia.indiatimes.com/topic/GSLV) Mk III rocket by one tonne.
 
Talking to TOI about the new project, Isro chairman K Sivan (https://timesofindia.indiatimes.com/topic/K-Sivan) said, "After a presentation before the Space Commission, Isro has got the approval for developing the semi-cryogenic rocket stage. The deadline to develop this stage is 29 months. Once the stage is ready, the carrying capability of GSLV Mk III will increase from the existing four tonnes to five tonnes."
 
Explaining the project, Sivan said, "A GSLV Mk III rocket comprises two strap-on boosters (to provide thrust during a launch), middle stage that carries liquid fuel nitrogen tetroxide and unsymmetrical dimethylhydrazine, and the second stage, which consists of a cryogenic engine. Once the semicryogenic stage is developed, we will simply replace the middle liquid fuel stage with it. The new stage is likely to be an exact fit and the rocket will look like the earlier one from outside."
 
He said, "The first launch of Isro's heaviest rocket GSLV Mk III DI last year carried 3.1 tonne weight. The second launch of Mk III D2, scheduled in July this year and which will carry Gsat-29 satellite, will have the load capability of 3.7 tonnes. We can easily raise the weight up to 4 tonne. With the semicryogenic stage, the same rocket will be able to carry the load up to five tonne. With the increased capability, we don't have to depend on foreign spaceports to launch our satellites weighing over 5 tonnes."

ЦитироватьSalo написал:
С одной стороны нет Протона-М,  а с другой GSLV Mk III скорее нужно сравнивать с Союзом-2-1Б/Фрегат.

ЦитироватьSalo написал:
С одной стороны нет Протона-М,

ЦитироватьСтарый написал:
Вобщето аналог Союза это PSLV. Максимум - GSLV-2.  

ЦитироватьTECHNICAL SPECIFICATIONS
Payload to SSPO: 1,750 kg

PSLV earned its title 'the Workhorse of ISRO' through consistently delivering various satellites to Low Earth Orbits, particularly the IRS series of satellites. It can take up to 1,750 kg of payload to Sun-Synchronous Polar Orbits of 600 km altitude.
Payload to Sub GTO: 1,425 kg

Due to its unmatched reliability, PSLV has also been used to launch various satellites into Geosynchronous and Geostationary orbits, like satellites from the IRNSS constellation.

ЦитироватьTECHNICAL SPECIFICATIONS
Payload to GTO: 2,500 kg

GSLV's primary payloads are INSAT class of communication satellites that operate from Geostationary orbits and hence are placed in Geosynchronous Transfer Orbits by GSLV.

Payload to LEO: 5,000 kg

Further, GSLV's capability of placing up to 5 tonnes in Low Earth Orbits broadens the scope of payloads from heavy satellites to multiple smaller satellites.

ЦитироватьTECHNICAL SPECIFICATIONS
Payload to GTO: 4,000 kg

GSLV Mk III will be capable of placing the 4 tonne class satellites of the GSAT series into Geosynchronous Transfer Orbits.

Payload to LEO: 8,000 kg

The powerful cryogenic stage of GSLV Mk III enables it to place heavy payloads into Low Earth Orbits of 600 km altitude.

ЦитироватьGSLV Flight Record

 DATE     VEHICLE      ID     PAYLOAD    MASS(t) SITE  ORBIT
-------------------------------------------------------------------------------------
04/18/01 GSLV          D01  GSAT 1           1.54    SR 1  [GTO-](1)
05/08/03 GSLV          D02  GSAT 2           1.80    SR 1  GTO
09/20/04 GSLV          F01  Edusat            2.00    SR 1  GTO
07/10/06 GSLV          F02  INSAT 4C        2.17    SR 2  [FTO](2)
09/02/07 GSLV          F04  INSAT 4CR      2.13    SR 2  [EEO](3)
04/15/10 GSLV Mk2   D03  GSAT 4           2.22   SR 2  [FTO](4)
12/25/10 GSLV          F06  GSAT-5P         2.31    SR 2  [FTO](5)
01/05/14 GSLV Mk2   D05  GSAT 14        1.98    SR 2  GTO (6)
08/27/15 GLSV Mk2   D06  GSAT 6          2.117  SR 2  GTO
09/08/16 GSLV Mk2   F05  INSAT 3DR     2.211  SR 2  GTO
05/05/17 GSLV Mk2   F09  GSAT 9          2.23    SR 2  GTO
03/29/18 GSLV Mk2   F08  GSAT 6A        2.14    SR 2  GTO
12/19/18 GSLV Mk2+ F11  GSAT 7A        2.25    SR 2  GTO+(7)
-------------------------------------------------------------------------------------
(1) Upper stage shut down early. Left GSAT-1 4,000 km short of planned GTO apogee.
(2) First stage liquid strap-on failed shortly after liftoff
(3) Launch vehicle placed INSAT-4CR in 168 x 31,786 km x 15.8 deg orbit, well
short of planned 170 x 35,975 km x 21.7 deg GTO. Guidance error.
(4) 3rd Stg failed at or near startup. First Indian Cryo Stage
(5) Control failed T+47 sec. RSO T+63 sec.
(6) ISRO's first indeginous cryo upper stage success.
(7) First indigenous CUS-15 upper stage.
============================================================

ЦитироватьGSLV Mk 3 Flight Record

    DATE    VEHICLE      ID     PAYLOAD      MASS(t)  SITE  ORBIT
-----------------------------------------------------------------------
12/18/14  LMV3-X       X1  CARE/Test Flt    3.735   SR 2  SUB [1]
06/05/17  GSLV Mk3   D1  GSAT 19E          3.136   SR 2  GTO [2]
11/14/18  GSLV Mk3   D2  GSAT 29            3.4       SR 2  GTO  
-----------------------------------------------------------------------
[1] Suborbital test with dummy Stage 3.  CARE crew module performed
    reentry and splashdown to test recovery systems.
[2] First GSLV Mk3 orbital launch.

Цитировать-------------------------------------------------------------------------------------
DATE                 VEHICLE           ID      PAYLOAD             MASS(t) SITE*      ORBIT**
-------------------------------------------------------------------------------------
01/28/17 Soyuz 2-1b/Fregat  VS16    Hispasat 36W-1   3.22   KO ELS      GTO
05/18/17 Soyuz 2.1a/Fregat  VS17    SES 15                 2.302  KO ELS     GTO+

ЦитироватьSalo написал:
Союз-СТА/Фрегат-М примерно соответствует GSLV Mk II,  а Союз-СТБ/Фрегат-МТ - GSLV Mk III.

ЦитироватьСтарый написал:
Разница между GSLV-2  и GSLV-3 примерно в два раза. Чтото я сомневаюсь что между СТ-А и СТ-Б такая разница.

ЦитироватьSalo написал:
 

ЦитироватьСтарый (//forum/user/13420/) написал:
Разница между GSLV-2  и GSLV-3 примерно в два раза. Чтото я сомневаюсь что между СТ-А и СТ-Б такая разница.

GSLV Mk III / GSLV Mk II = 4000 кг/2500 кг = 1.6 раза
СТБ / СТА = 3250 кг/2810 кг = 1.16 раза

ЦитироватьСтарый написал:
 

ЦитироватьSalo (//forum/user/14860/) написал:
С одной стороны нет Протона-М,  а с другой GSLV Mk III скорее нужно сравнивать с Союзом-2-1Б/Фрегат.

Вобщето аналог Союза это PSLV. Максимум - GSLV-2.  

ЦитироватьSalo написал:
C чего всё начиналось?
 

ЦитироватьСтарый (//forum/user/13420/) написал:
 

ЦитироватьSalo (//forum/user/14860/)  написал:
С одной стороны нет Протона-М,  а с другой GSLV Mk III скорее нужно сравнивать с Союзом-2-1Б/Фрегат.

Вобщето аналог Союза это PSLV. Максимум - GSLV-2.  

ЦитироватьСтарый написал:
Важно не путаться, мучатся и теряться в цифрах а правильно определить к какому классу относится ракета. Так вот, Союз и PSLV  это ракеты одного класса, а Протон и GSLV-3 - другого класса.  

ЦитироватьSalo написал:
Протон Экспресс-АМ6 массой 3358 кг почти на ГСО выводил?
А Экспресс-АМ5 массой 3200 кг прямо на ГСО.

ЦитироватьСоюз СТ-Б/Фрегат МТ / Hispasat 36W-1 - 3221 кг

ЦитироватьСтарый написал:

ЦитироватьСоюз СТ-Б/Фрегат МТ / Hispasat 36W-1 - 3221 кг

Погоди, погоди, погоди. 3.2 т на ГПО?  :oops:  

ЦитироватьСтарый написал:
Сергей, мне кажется ты продолжаешь блуждать в цифрах не в силах выявить систему и определить какая ракета является аналогом какой.  

ЦитироватьSalo написал:
 

ЦитироватьСтарый (//forum/user/13420/) написал:
Сергей, мне кажется ты продолжаешь блуждать в цифрах не в силах выявить систему и определить какая ракета является аналогом какой.  

Володь, а ты вопреки цифрам продолжаешь продвигать свою теорию классификации РН по стартовой массе, а не по ПН.

ЦитироватьСтарый написал:
 
Однако скажи: если правый край диапазона Союза и левый край диапазона GSLV-3 соприкасаются то значит ли это что эти РН аналогичны?  

ЦитироватьСтарый написал:

Однако скажи: если правый край диапазона Союза и левый край диапазона GSLV-3 соприкасаются то значит ли это что эти РН аналогичны?

ЦитироватьSalo написал:
Зенит-3SLБ тяжёлый геостационарный носитель?

ЦитироватьСтарый написал:
Я продвигаю теорию классификации РН по функциональности. "Универсальный носитель среднего класса", "тяжёлый геостационарный носитель" и т.д.

ЦитироватьСтарый написал:
Так вот PSLV  это универсальный средний носитель, ракета того же класса то и Ариана-1/4, Союз и CZ-2/4.
GSLV2 это  расширение PSLV вправо в область СКПГ путём навески "ускорителей".
А GSLV3 это тяжёлый геостационарный носитель.  

ЦитироватьSalo написал:
 Рокот универсальный средний носитель?

ЦитироватьА Протон-М, F9, H-2B и Ariane-5 это сверхтяжёлые геостационарные носители?

ЦитироватьApollo13 написал:
Я вообще предлагаю классифицировать РН по их сухой массе.

ЦитироватьСтарый написал:
 

ЦитироватьSalo (//forum/user/14860/) написал:
 Рокот универсальный средний носитель?

Рокот - лёгкий носитель.

ЦитироватьSalo написал:
 А в чём его отличие от PSLV?

ЦитироватьSalo написал:
Каких именно функций, характерных для PSLV, Рокот не выполняет?

ЦитироватьSalo написал:
 Рокот универсальный средний носитель?

ЦитироватьSalo написал:
А что PSLV запустила на ГСО и навстар?

ЦитироватьСтарый написал:
 

ЦитироватьSalo (//forum/user/14860/) написал:
Зенит-3SLБ тяжёлый геостационарный носитель?

Зенит это СКПГ. "Средний класс повышенной грузоподъёмности".
...
Повторяю: Зенит - универсальный носитель, он запускал и спутники РТР, и фоторазведки, и ДЗЗ на ССО, и спутники на ГСО.

Так понятнее что к какому классу относится?

ЦитироватьСтарый написал:
GSLV2 это  расширение PSLV вправо в область СКПГ путём навески "ускорителей".

ЦитироватьSalo написал:
 А Delta-H, Протон и Ariane 5 тоже СКПГ? Или это Универсальные носители высокой грузоподъёмности, т.е. УНВГ?

ЦитироватьСтарый написал:
 

ЦитироватьSalo (//forum/user/14860/) написал:
 Рокот универсальный средний носитель?

Да, и ещё. Мне не интересны собеседники которые вместо обсуждения предложенной темы пускаются в примитивные попытки докопаться, уесть, поймать на слове. У тебя есть что сказать по предлагаемой классификации? Есть более подходящие на твой взгляд варианты? Тогда не утруждайся.
 Сообщения типа "Я вот не предлагаю своих вариантов классификаций, а ты как посмел???" меня не интересуют.  

ЦитироватьСтарый написал:
Если тебе интересно то во всех странах средний класс расширялся "вправо" вплоть до тяжёлого путём применения навесных ускорителей.Классика:  Ариана-1-4 в Европе, CZ-2-3-4 в Китае.  Ныне Атлас-5 от 401 до 551 в США.  В СССР такой практики не было, в СССР средний класс заполнили тремя отдельными носителями - Циклон-Союз-Зенит.

ЦитироватьСтарый написал:
На всякий случай повторяю что в основные классы "лёгкий носитель", "средний универсальный носитель" и "тяжёлый геостационарный носитель" входят понятия "лёгкий", "средний" и "тяжёлый". То есть стартовая масса имеет значение.

ЦитироватьСтарый написал:
 

ЦитироватьSalo (//forum/user/14860/) написал:
 А Delta-H, Протон и Ariane 5 тоже СКПГ? Или это Универсальные носители высокой грузоподъёмности, т.е. УНВГ?

А Хэви Дельта, Протон и Ариан-5 это тяжёлые геостационарные носители. Кажется я тебе это уже говорил?

ЦитироватьSalo написал:
 Они не работают на НОО, ССО, ВЭО, Навстар? Они не универсальны?

ЦитироватьSalo написал:
 Тяжёлый геостационарный носитель слишком узкий класс, не отражающий реалий.

ЦитироватьGSLV Mk III согласно твоей же классификации средний универсальный носитель, или с большой натяжкой СКПГ. Тяжёлым геостационарным носителем он не является от слова совсем.

ЦитироватьSalo написал:
Классификация геостационарных спутников по массе на ГПО согласно FAA:
  https://www.faa.gov/about/office_org/headquarters_offices/ast/media/2018_AST (https://www.faa.gov/about/office_org/headquarters_offices/ast/media/2018_AST) ­_Compendium.pdf  

ЦитироватьSalo написал:
Классификация геостационарных спутников по массе на ГПО согласно FAA:
  https://www.faa.gov/about/office_org/headquarters_offices/ast/media/2018_AST (https://www.faa.gov/about/office_org/headquarters_offices/ast/media/2018_AST) ­_Compendium.pdf  

ЦитироватьSalo написал:
Две трети коммерческих спутников имеют массу более 4200 кг.
Внимание, вопрос: может ли называться тяжёлым геостационарный носитель, который может выводить не все тяжёлые спутники, а точнее только четверть от общего числа коммерческих геостационарных спутников.

ЦитироватьSalo написал:
может ли называться тяжёлым геостационарный носитель,

ЦитироватьСтарый написал:
 

ЦитироватьSalo (//forum/user/14860/) написал:
Две трети коммерческих спутников имеют массу более 4200 кг.
Внимание, вопрос: может ли называться тяжёлым геостационарный носитель, который может выводить не все тяжёлые спутники, а точнее только четверть от общего числа коммерческих геостационарных спутников.

Может. Особенно с новым центральным блоком.  

ЦитироватьSalo написал:
PSLV XL выводит на НОО 3800 кг и 1450 кг на ВЭО с высотой апогея ~22000 км с наклонением 19 градусов. Можно ли её называть средней ракетой ? 

ЦитироватьАнгара-А1.2 средняя ракета?

ЦитироватьСтарый написал:
 

ЦитироватьSalo (//forum/user/14860/) написал:
PSLV XL выводит на НОО 3800 кг и 1450 кг на ВЭО с высотой апогея ~22000 км с наклонением 19 градусов. Можно ли её называть средней ракетой ?

Да. Аналог Арианы-1 Не забывай что PSLV XL  это лёгкий вариант данной ракеты, тяжёлый вариант - GSLV-2.

ЦитироватьСтарый написал:
Я рассматриваю два варианта формальной классификации по стартовой массе:
1. С модулем "3"
-сверхлёгкий - до 50 т
-лёгкий - 50-150 т
-средний -150-450 т
-тяжёлый - 450-1400 т
-сверхтяжёлый - более 1400 т

2. С модулем "4"
-сверхлёгкий - до 30 т
-лёгкий - 30-120 т
-средний -120-500 т
-тяжёлый - 500-2000 т
-сверхтяжёлый - более 2000 т

Второй мне нравится больше, только граница между тяжёлым и сверхтяжёлым классом проходящая по 2000 т кажется великовата.  

ЦитироватьSalo написал:
 

ЦитироватьСтарый (//forum/user/13420/) написал:
2. С модулем "4"
-сверхлёгкий - до 30 т
-лёгкий - 30-120 т
-средний -120-500 т
Второй мне нравится больше, только граница между тяжёлым и сверхтяжёлым классом проходящая по 2000 т кажется великовата.  

Vega у тебя гуляет между лёгкой и средней, а Vega C попадает в средний класс.

ЦитироватьSalo написал:
Старт-1 у тебя в лёгком классе, "Штиль" болтается между.

ЦитироватьСтарый написал:
 

ЦитироватьSalo (//forum/user/14860/) написал:
Старт-1 у тебя в лёгком классе, "Штиль" болтается между.

Не знаю такой РН "Штиль"  

ЦитироватьSalo написал:
Falcon Heavy во втором варианте в сверхтяжи не попадает.

ЦитироватьДмитрий В. написал:
 

ЦитироватьСтарый (//forum/user/13420/) написал:
 

ЦитироватьSalo (//forum/user/14860/)  написал:
Старт-1 у тебя в лёгком классе, "Штиль" болтается между.

Не знаю такой РН "Штиль"  

Век живи - век учись, .........
 http://www.makeyev.ru/activities/space-and-rocket-research/1/ (http://www.makeyev.ru/activities/space-and-rocket-research/1/)

ЦитироватьSalo написал:
C младшей OmegA тоже могут быть проблемы.

ЦитироватьСтарый написал:
 

ЦитироватьSalo (//forum/user/14860/) написал:
Falcon Heavy во втором варианте в сверхтяжи не попадает.

Я его отношу к тяжёлым геостационарным.  

ЦитироватьSalo написал:
 

ЦитироватьСтарый (//forum/user/13420/) написал:
 

ЦитироватьSalo (//forum/user/14860/)  написал:
Falcon Heavy во втором варианте в сверхтяжи не попадает.

Я его отношу к тяжёлым геостационарным.  

Вместе с GSLV Mk III.

ЦитироватьСтарый написал:
Флакон-9 был создан как классический универсальный средний носитель, затем проэволюционировал в СКПГ. Тяжёлый геостационарный носитель это Флакон Хэви.  

ЦитироватьSalo написал:
 

ЦитироватьСтарый (//forum/user/13420/) написал:
Тяжёлый геостационарный носитель это Флакон Хэви.  

A Mk III тяжёлый.

ЦитироватьСтарый написал:
Да. В модуль "4" входит.  

ЦитироватьSalo написал:
 Он у тебя и в модуль 4 входит. А вот F9FT почему-то нет.

ЦитироватьСтарый написал:
Правый край среднего класса слегка перекрывается с левым краем тяжёлого класса. Докопаться до этого может только тот кто не отличает "право" от "лево".  

ЦитироватьСтарый написал:
 

ЦитироватьSalo (//forum/user/14860/) написал:
 Он у тебя и в модуль 4 входит. А вот F9FT почему-то нет.

Невозможно так провести границы чтобы всё влазило строго. Некоторые варианты ракет разных классов слегка перекрываются. Самые тяжёлые варианты СКПГ (Атлас-552, F9FT) слегка вылазят вправо в область ТГН. Надо просто понимать что это тяжёлые варианты СКПГ а не отдельные РН.  

ЦитироватьДмитрий В. написал:
 Эти "пересечения" делают бессмысленной любую классификацию РН по трудноформализуемым признакам.

ЦитироватьСтарый написал:
 

ЦитироватьДмитрий В. (//forum/user/14022/) написал:
 Эти "пересечения" делают бессмысленной любую классификацию РН по трудноформализуемым признакам.

Отнюдь.
Пересечения по массе ПН "почемуто" не вызывают у тебя отрицания этого параметра классификации.
 Кстати, стартовая масса это самый конкретный и легко формализуемый параметр в отличие от например массы ПН.  

ЦитироватьSalo написал:
Но Титан-3С у тебя тяжёлая ракета, а не СКПГ Титана-II.

ЦитироватьСтарый написал:
Если например одна РН в разных вариантах имеет стартовую массу 200-520 т а другая - 480-1200 т то легко заметить что это две разных ракеты двух разных классов. И наличие пересечения в области 480-520 т не делает их ракетами одного класса. Докопаться до этого пересечения может не просто тот кто не отличает "лево" от "право" а тот кто очень хочет докопаться но не знает до чего.

ЦитироватьIndia Can Fill The Slot In Global Commercial Satellite Launch Market: ISRO Chairman
By OMMCOM NEWS On Oct 22, 2022

Chennai: With a shortage of rockets to launch satellites, India with its LVM3 or GSLV Mk3 rocket now has a slot in the global commercial satellite launch market, said S.Somanath, Secretary, Department of Space and Chairman, Indian Space Research Organisation (ISRO).
He also said India is planning to ramp up production of the LVM3 rocket.
"There is a shortage of commercial satellite launch vehicles for putting into orbit multiple satellites to form a constellation. The Russian rockets are not in consideration now. Further the Ariane 6 rocket of Arianespace got delayed. The commercial potential of Chinese rockets is not accepted by the West. Hence India has a slot now," Somanath told IANS.
It was IANS which first said that India has an opportunity in the global commercial satellite launch market soon after the US and Europe's economic sanctions against Russia for its military action.
"All those countries feeling the pinch due to the absence of Russian rockets for satellite launches may look at alternatives. While the bulk of the satellite launch contracts will be taken by the US and Europe, there will be others who may look at other options. India's neutrality has created a new market segment," Chaitanya Giri, Founder, DAWON Advisory & Intelligence, had told IANS.
Space sector exports had told IANS that to cash in on the opportunities, India should accelerate its satellite launch capabilities, and announce productivity-linked incentive (PLI) schemes for the aerospace sector.
"A plan is being made to ramp up LVM3 production to four or five per year after one to two years. And investments are needed for that. NewSpace India Ltd (NAIL-commercial arm of ISRO) will look into how to do this," Somanath said.
Starting in 1999, ISRO has put into orbit 345 small foreign satellites till date using its rocket called Polar Satellite Launch Vehicle (PSLV).
For the first time ISRO is introducing its heavy lift rocket Geosynchronous Satellite Launch Vehicle-MkIII (GSLV-MkIII) into the global commercial launch market renaming it as LVM3.
Normally, the GSLV rocket is used for launching India's geostationary communication satellites. And hence it was named as GeoSynchronous Satellite Launch Vehicle (GSLV). The GSLV MkIII refers to the third generation rocket.
As the rocket that will fly on Sunday morning will be orbiting the OneWeb satellites in Low Earth Orbit (LEO), ISRO has renamed GSLV MkIII as LVM3 M2 (Launch Vehicle MkIII).
On Sunday at 12.07 a.m. the LVM3 will fly with 36 small satellites of Network Access Associated Ltd (OneWeb) in LEO.
OneWeb, is a joint venture between India Bharti Global and the UK government.
The satellite company plans to have a constellation of about 650 satellites in low earth orbit (LEO) to offer communication services.
The LVM3 M2 is a three stage rocket with the first stage fired with liquid fuel, the two strap on motors powered by solid fuel, the second by liquid fuel and the third is the cryogenic engine.
The ISRO's heavy lift rocket has a carrying capacity of 10 ton to the LEO and four ton to the Geo Transfer Orbit (GTO).
The total launch mass of OneWeb satellites will be 5,796 kg, said ISRO.
"We have contracted for one more launch of 36 OneWeb satellites. More launches may come based on our performance," Somanath remarked.
The Indian space agency's other rocket PSLV has a carrying capacity, of 3.2 ton to 3.8 ton to LEO orbit depending on the variant.
With LVM3, ISRO can offer two rockets for the global commercial launch market.
Queried about the small satellite market Somanath said: "There are too many predictions based on different approaches. Primarily by the LEO communication network and small satellite imaging services. However it will be a few thousands per year."
He said NSIL is offering PSLV and will also take up the Small Satellite Launch Vehicle (SSLV) to tap this market in the next few years.
The SSLV has a carrying capacity of 500 kg to LEO.
The ISRO Chairman said GSLV rocket will be launched up to two per year to meet the NavIC (India's navigation satellite system) and other scheduled missions.
"The GSLV rocket will be for internal (domestic) demand. Only PSLV and LVM3 are into commercial service now," Somanath said.
"We need to make industries ready to produce PSLV, SSLV and LVM3 in bulk on their own. Otherwise, large scale launch service is difficult. This can also be modulated by geopolitical conditions evolving," Somanath remarked.
The first step towards sourcing PSLV rockets by NSIL has been taken with the award of Rs.860 crore contract to make five rockets to HAL-L&T consortium.[/b]

ЦитироватьISRO renames GSLV Mark-III as LVM-3
PTI
New Delhi October 23, 2022 18:55 IST
Updated: October 24, 2022 17:15 IST
(https://img.novosti-kosmonavtiki.ru/334199.jpg)
GSLV Mark-III. File. | Photo Credit: M. Prabhu

The LVM-3 rocket will also be used for India's maiden human space flight tentatively scheduled for late 2024

The Indian Space Research Organisation (ISRO) has renamed the Geosynchronous Satellite Launch Vehicle (GSLV) Mark -III as Launch Vehicle Mark-III, mainly to identify its task of placing satellites into a variety of orbits.

The LVM-3 rocket will also be used for India's maiden human space flight tentatively scheduled for late 2024 and is also emerging as a favourite for ISRO's commercial launches after the successful placing in orbits of 36 OneWeb satellites on Sunday.

"Earlier, the launch vehicles were named for a specific purpose, such as PSLV for putting polar satellites in orbit or GSLV for geostationary satellites," a senior ISRO official said.
"The rocket no longer goes only to the geosynchronous orbit. A rocket can go anywhere, it does not have a fixed orbit to go anywhere—GEO (Geosynchronous Earth Orbit), MEO (Medium Earth Orbit), LEO (Low Earth Orbit)," the official said.
The decision to rename the rocket was to remove the confusion regarding the type of orbits identified for launch.

"A GSLV – for the GEO orbit – will continue to be called so, but the GSLV-Mark III has been renamed as LVM3. The LVM3 will go everywhere —GEO, MEO, LEO, missions to the moon, sun," the official said.
GSLV Mark-III or LVM3 was used to launch the Chandrayaan-2 mission to the moon in 2019, which was the first operational flight of the rocket.
LVM3 was used to put 36 OneWeb satellites into orbit on Sunday and will also be used for a similar mission next year.

ЦитироватьВ Индии завершили испытания ракетного двигателя для будущей пилотируемой миссии
НЬЮ-ДЕЛИ, 21 февраля. /ТАСС/. Индийская организация космических исследований (ISRO) успешно завершила испытания криогенного двигателя для будущей первой пилотируемой миссии страны. Об этом ISRO сообщила в пресс-релизе.

"ISRO достигла значительной вехи в адаптации криогенного двигателя CE20 для пилотируемой ракеты-носителя LVM3 в рамках миссии "Гаганьян", заключительный раунд наземных испытаний состоялся 13 февраля", - говорится в сообщении ведомства.

Испытания прошли в штате Одиша на полигоне на горе Махендрагири. Они включали разные компоненты, в том числе демонстрационный тест, проверку работы на продолжительной нагрузке как в штатных условиях, так и в нештатных. "Все наземные испытания двигателя CE20 для миссии "Гаганьян" успешно завершены", - добавили в ISRO.

В общей сложности двигательная установка проработала в тестовом режиме около 4 часов. "ISRO успешно выполнила приемо-сдаточные испытания ракетного двигателя, выбранного для первой непилотируемой миссии G1, которая предварительно запланирована на второй квартал 2024 года. Этот двигатель станет верхней ступенью для пилотируемой ракеты LVM3", - добавили в организации.

Если первый полет ракеты LVM3 без экипажа запланирован на второй квартал 2024 года, то запуск пилотируемой миссии планируется к концу 2025 года, об этом ранее говорил глава ISRO Шридхара Паникер Сомнатх.

В августе 2018 года премьер-министр Индии Нарендра Моди официально объявил, что его страна отправит на орбиту первый национальный космический экипаж к августу 2022 года, когда Индия планировала отмечать 75 лет освобождения от британского колониального господства. Название проекта "Гаганьян" (от санскритского "гагана" - небеса) означает "небесный корабль". Однако из-за пандемии коронавирусной инфекции, остановившей в марте 2020 года большинство работ по проекту, отправка на орбиту миссии "Гаганьян" отложена. Четверо индийских астронавтов уже прошли подготовку в российском Звездном городке.