LVM3 (GSLV Mark III) -- ИНДИЙСКАЯ PAKETA

[Salo]

http://www.isro.org/Launchvehicles/GSLVMARKIII/mark3.aspx

The 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

http://knol.google.com/k/indian-space-projects#

GSLV Mk-3 (LVM3)


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).

[Salo]

[Alex_II]

Ого... MK-IV сколько должна на НОО тянуть - тонн 20?

[Salo]

[Salo]

На схеме выведения можно разобрать, что двигатели ЦБ (L-110 - вторая жидкостная ступень на вонючке) запускаются после отделения твердотопливных ускорителей S-200. Криогенная третья ступень С25 с двигателем СE-20 имеет два включения.

[Salo]

[Salo]

http://www.bharat-rakshak.com/media/AeroIndia2009/yashu/

[Salo]

http://www.thaindian.com/newsportal/sci-tech/india-to-test-worlds-third-largest-solid-rocket-booster_100285103.html

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

Насколько всё-таки индийские ТТУ несовершенны.  

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

[Salo]

http://www.domain-b.com/aero/space/spacemissions/20091127_isro.html

ISRO 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]

[Salo]

http://indianspaceweb.blogspot.com/2009/12/ground-firing-of-s200.html

Tuesday, 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.

[Monoceros]

Насколько всё-таки индийские ТТУ несовершенны.  

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

Что-то для шаттла запредельно много, а для индийской запредельно мало...

[Salo]

У 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?

[Salo]

Кстати у S200 непомерно высокое массовое совершенство 20/220=0,09.
При том, что у SRB Шаттла 60/500=0,12, а у Ariane 5 36/276=0,13.

[577]

И на какой из этих ракет индийцы собираются на Луну?

[Monoceros]

У 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.

[Дмитрий В.]

У 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.

Это больше похоже на правду.

[Salo]

У Норберта Брюгге http://www.b14643.de/Spacerockets_2/United_States_1/Space_Shuttle/Description/Frame.htm  
тоже масса топлива чуть больше 500 т. А вакууный УИ 265-269 с.
У ускорителя Ariane 5ECA MPS 240 http://www.b14643.de/Spacerockets_1/West_Europe/Ariane-5/Description/Frame.htm
вакуумный УИ ещё выше - 275 с.

[Salo]

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

[Monoceros]

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

Да ну... у Скаута на двухосновном топливе был на земле 230

upd: упс, 214 и смесевое, вухосновное на верхних.

[Salo]

Единственная цифра в которой можно сомневаться это тяга в 400 тс.
Масса топлива в 200т следует из названия ступени. Время работы в 103 с озвучено многократно.