LVM3 (GSLV Mark III) -- ИНДИЙСКАЯ PAKETA

[Salo]

http://forums.bharat-rakshak.com/viewtopic.php?p=747266&sid=3f1bb16f911508da9135df29b349aa4e#p747266

The 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.

[Salo]

http://www.thehindubusinessline.com/2010/04/16/stories/2010041657870100.htm

India-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]

[Salo]

http://indianspaceweb.blogspot.com/2010/01/l110-test-to-follow-s200.html

L110 test to follow S200


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

И далее в комментариях:

January 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.

[Salo]

http://www.dare.co.in/news/others/semi-cryogenic-engine-technology-for-future-space-transportation-systems.htm

Semi 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.

[Salo]

http://indianspaceweb.blogspot.com/2010/07/pictures-indian-space-transportation.html

PICTURES: 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

Сама презентация:
http://picasaweb.google.com/crgkc.r/IndianSpaceTransportationSystem?feat=flashalbum#5491570113696502402

[Salo]

http://picasaweb.google.com/crgkc.r/IndianSpaceTransportationSystem?feat=flashalbum#5491570113696502402

[Salo]

http://indianspaceweb.blogspot.com/p/pslv.html

PSLV

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.

http://indianspaceweb.blogspot.com/2010/05/pslv-variants.html

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

comments 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.

[Salo]

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

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.

[Луноход]

http://www.scientiamag.com/2010/04/isro-roadmap-for-missions-and-launch.html

[Salo]

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

GSLV 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.

http://www.deccanchronicle.com/hyderabad/gslv-rocket-all-set-launch-976

The 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.

[SpaceR]

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

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.[/color]

А на постере всё равно изобразили 3,4-метровый ГО

[Salo]

А так:


GSLV-F06.

[Salo]

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

The 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.

[TestPilot]

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

[SpaceR]

А так:
img / img

Вот-вот, и я о том же.
Разница очевидна.
Кстати, впервые 4-метровый индийский ГО слетал ещё на PSLV.  Где-то года два назад.

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

The 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.

Приятный, 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.

[SpaceR]

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

Так быстро не получится. Нужно не сколько устранить причину, сколько убедиться, что доработанный вариант надежно выполнит свою задачу - за два прокола подряд последствия будут посерьёзнее.
Напоминаю, что данный индийский КРБ ещё ни разу успешно в космосе не работал, а при наземных тестах испытаний на запуск в невесомости не проходил.

Да, действительно, руководитель ISRO сразу (вскоре) после аварии заявил, что следующую попытку индийский блок сделает через год, а пока будут летать на оставшихся российских.
Этот пуск, кстати, тогда планировался на октябрь (емнип).

[Salo]

Приятный, 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.

http://www.novosti-kosmonavtiki.ru/content/numbers/238/22.shtml

[ronatu]

Вторая попытка Индии запустить ракету-носитель GSLV со спутником связи GSAT-5P прошла неудачно, передает Times of India. Спустя несколько секунд после старта ракета взорвалась в воздухе. Предварительной причиной аварии назвали некие технические неисправности.
Ракета стартовала с космодрома на Шрихарикате (штат Андхра-Прадеш). Планировалось, что телекоммуникационный спутник GSAT-5P сменит на орбите спутник INSAT-2E, запущенный в 1999 году. GSAT-5P весит более двух тонн, его срок службы - 13 лет.

Первая попытка запустить спутник, состоявшаяся в апреле 2010 года, также завершилась неудачей. Примечательно, что тогда Индийское космическое агентство решило использовать для вывода аппарата на орбиту ракету с криогенным двигателем собственного производства. После неудачи было решено до устранения технических неполадок вновь использовать российские криогенные двигатели "12 КРБ".

[ronatu]

http://timesofindia.indiatimes.com/india/GSAT-5P-launch-fails-satellite-vehicle-explodes-mid-air/articleshow/7162634.cms

[ronatu]

http://timesofindia.indiatimes.com/india/GSAT-5P-launch-fails-satellite-vehicle-explodes-mid-air/articleshow/7162634.cms