LVM3 (GSLV Mark III) -- ИНДИЙСКАЯ PAKETA

[Дмитрий В.]

До 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.

Потому что они пока ориентированы на внутренний рынок.

[Salo]

Собирались в этом году пустить шесть ракет. Сохраняются шансы, что запустят четыре. Полезные нагрузки уже стоят в очереди.

[SpaceR]

До 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.

В целом согласен.
Такая грузоподъемность соответствует только платформе Orbital STAR-2 и спутникам самой Индии. В принципе, опрокинуть рынок это не даст, но чуток расшевелит. Есть шансы отобрать некоторые КА у Ариана 5 (вторичные) и Союза-2ST и повлиять на общемировое ценообразование.
А с выходом на коммерцию GSLV Mk.III у них уже есть реальная возможность серьезнее потеснить Ариан 5 и Зенит-3SLБ.
Конечно, это зависит от реально достижимого темпа запусков.

[Bell]

Вот 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.

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

[SpaceR]

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

Далеко, дорого и неудобно. Да ещё платить кому-то.
Выигрыш по энергетике это всё не окупит.
А тут - грандиозный технопарк на своей земле. Нужный и полезный, кроме космических, и для других задач. Делай что хочешь и распоряжайся как хочешь.

Много ли стран построили космодром на чужой земле и используют его до сих пор?

[Salo]

http://www.brahmand.com/news/ISRO-to-conduct-key-test-for-GSLV-Mk-III-rocket-next-week/4813/3/13.html

ISRO 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.

[Salo]

http://www.indiadaily.com/editorial/21641.asp

ISRO 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.

[Salo]

http://www.rian.ru/science/20100908/273721029.html

Индия 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.

[Salo]

Насчёт С-25 РИАН поторопился. :roll:

[Salo]

http://www.isro.org/pressrelease/scripts/pressreleasein.aspx?Sep08_2010
http://www.thehindubusinessline.com/2010/09/09/stories/2010090951630400.htm
http://www.thehindu.com/sci-tech/article621253.ece

[Salo]

http://expressbuzz.com/nation/isro-plan-to-launch-8-spacecraft-a-year/206898.html

ISRO 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."

[Salo]

http://www.spaceflightnow.com/news/n1010/12gslv/

India 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.


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.


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.

[Sаlyutman]

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

[Дмитрий В.]

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

Разуверились в своих силах? "А как дысал, как дысал!" :lol:

[Salo]

Т.е. 15КРБ так и остался в мечтах?

[Salo]

http://www.spaceflightnow.com/news/n1010/12gslv/

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.

А что с этим девайсом?

Frigate пишет:

ИМХО похоже полетит "самостийний" индийский:
CE-20 Engine

The 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   .
Вот картинка с выставки Aero India 2009 (проходила в феврале этого года):

Дмитрий 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)

[Дмитрий В.]

Т.е. 15КРБ так и остался в мечтах?

Он же, вроде, уже поставлялся, хоть и под маркой 12КРБ :roll:

[Salo]

Два двигателя КВД-1А тягой 9,5 тс поставили, но был ли там увеличен РЗТ до 15т?

[Salo]

http://www.indiandefence.com/forums/f9/isro-s-success-wins-india-orders-launch-eight-foreign-satellites-1038/#post8347

Arjun 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.

[Salo]

А возятся с CE-20 уже давно- с 2006 года:

http://nal-ir.nal.res.in/8890/

CASCADE 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)

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.

http://nal-ir.nal.res.in/8891/

CASCADE 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)

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.