Indian Space Capabilities

[S-DUCT]

Updates on programme from ISRO annual report:

1) GSLV: All the
recommendations from Failure Analysis Committees of GSLV-F06 and GSLV-D3 have been incorporated and implemented. Modifications in Fuel Booster Turbo Pump (FBTP) and Oxidiser Booster Turbo Pump (OBTP) were carried out along with improvements in Cryogenic Upper Stage (CUS) elements.The CUS lower shroud was redesigned and strengthened. Wind tunnel configuration was modified by extending its length. The lanyard connector mounting bracket was relocated from the lower shroud to truss member.

All the motor segments of S139 stage were realised and cleared for flight. All the four L40 stages are positioned at SDSC, SHAR.GS2 stage is under preparation at LPSC Mahendragiri Facility (LMF). Assembly of cryogenic flight stage is in advanced stage of completion after successful completion of acceptance test and post test inspection of flight engine at LPSC Mahendragiri. To emonstrate cryogenic engine ignition under vacuum condition,preparation for the test in High Altitude Test (HAT) facility at LPSC Mahendragiri is progressing well. In parallel, assembly of GSLV-D5 at Vehicle assembly building of Second Launch Pad commenced on January 31, 2013 and the launch is targeted for June 2013.

2) GSLV MK3: The first experimental flight with passive cryogenic stage (GSLV-MkIII-X flight) is targeted in the last quarter of 2013. Towards this mission, all six segments of two S200 flight motor have been cast and are stored in magazines. All flight hardware of L-110 is positioned at LPSC, Mahendragiri and flight stage integration is in progress. For passive C25 stage, propellant tanks for the flight stage have been realised and stage integration activities have been initiated.

3) SEMI-CRYOGENIC PROJECT: Design of single element thrust chamber was completed and single element thrust chamber injector elements realised and cold flow tested. A rubber composition resistant to ISROSENE was also qualified. Rectangular rings, gaskets and O-rings for control components and turbo pump of semi cryogenic engine
as well as Tri-ethyl aluminum (TEA) based hypergolic igniter have also been developed. Hot test was carried out with LOX step injection mode on semi cryogenic pre-burner injector at high pressure after completing cold flow trials and sequence validation tests. Further tests with step injection for ISROSENE and LOX are planned.

3) Reusable Launch Vehicle–Technology Demonstrator (RLV-TD):A winged Re-usable Launch Vehicle Technology Demonstrator (RLV-TD) has been configured to act as a
flying test bed to evaluate various technologies, namely, hypersonic flight, autonomous landing, powered cruise flight and hypersonic flight using air breathing propulsion towards realising a Two Stage to Orbit (TSTO) fully re-usable launch vehicle.Technology Demonstrator Vehicle (TDV) structural model was realised. Fuselage and inter stage assemblies are realised for structural testing. Flush Air Data System (FADS) test article realised and integration procedure, FADS algorithm, avionics and leak tightness for pressure pick up assembly were validated through 1:1 FADS wind tunnel test at IIT, Kanpur.Qualification model of Radar Altimeter was realised and balloon test conducted at TIFR, Hyderabad. Carbon-carbon (C/C) laminates for nose cap were realised through a new route.Functional qualification test of Launch Hold and Release System (LHRS) with dual pyro initiation carried out with simulated interfaces. The testing of HS9 booster stage separation system along with hydraulic line separation system was completed successfully. High altitude test of the 2 kN retro rocket developed for jettisoning spent HS9 motor was successfully conducted at SDSC SHAR.
The Integrated Technical Review (ITR) of RLV-TD by the National Review Committee in October 2012 has concluded that launch of RLV-TD HEX-01 mission in September 2013 is feasible.

 

[kurup]

 

[S-DUCT]

HEX-01 FLIGHT PROFILE

 

[RPK]

 

[S-DUCT]

@BlueDot_in_Space:

What's purpose of fitting ABP(air breathing propulsion) on RLV-TSTO and hence objective of SPEX experiment.AFAIK TSTO will take of vertically using Semicryogenic Booster stage and at an altitude of 100KM, Orbitor will separate from winged body and using its cryogenic stage(Orbitor) it will place Payload and re-enter atmosphere land using Air-bags.Winged body willt then conventionally lands on Air-strip.

 

[Genesis]

Indian space technology is impressive. I understand a Mars mission is either in the works or done? Man space flight is next and so on so forth.

When the manned mission is done, India would be the fourth nation to do so? Asian countries leading the way. Maybe one day Asian countries can work together and work faster and achieve better results. One can hope.

Finally unlocking the Mysteries of Mars and perhaps even manned missions or unmanned missions outside of Solar system?

 

[karan21]

Indian space technology is impressive. I understand a Mars mission is either in the works or done? Man space flight is next and so on so forth.

When the manned mission is done, India would be the fourth nation to do so? Asian countries leading the way. Maybe one day Asian countries can work together and work faster and achieve better results. One can hope.

Finally unlocking the Mysteries of Mars and perhaps even manned missions or unmanned missions outside of Solar system?

First of all the work on manned mission is going on quietly, but it is stuck in approvals by the govt.

The problem is that India currently has no rocket that can take maned capsules in space. India was supposed to get the clearance for the manned mission in 2010 but Mk2 failed twice that year. Since then there has been no progrss. Gslv mk2 has a payload capacity of upto 5000 to 6000kg to leo but has failed 4 times. Next launch is in july. If its a success we are back on track.

Now coming to the Gslv mk3 with payload of 10000 to 15000 kg to leo, its first launch is in 2013 as well in sept, if its a success then Isro can finally claim the approval for the manned mission with full confidence. \

Just to let you know the Planning commision of India has already approved the manned mission just the central govt approval is required.



Indian perspective on Manned Space Missions - reasons & necessary Technologies [Aero India 2011] - YouTube

 

[BlueDot_in_Space]

@BlueDot_in_Space:

What's purpose of fitting ABP(air breathing propulsion) on RLV-TSTO and hence objective of SPEX experiment.AFAIK TSTO will take of vertically using Semicryogenic Booster stage and at an altitude of 100KM, Orbitor will separate from winged body and using its cryogenic stage(Orbitor) it will place Payload and re-enter atmosphere land using Air-bags.Winged body willt then conventionally lands on Air-strip.

There are two parts to achieving low cost of access to space:

1) A reusable launch vehicle: the hardware contributes a major chunk (70-80 % that includes manufacturing + materials) to the cost of a launch vehicle that is expended after one use in present launch vehicles. By reusing the same hardware for multiple launches, a major cost saving can be achieved and thus launch cost can be reduced.

To achieve this ISRO is developing reusable technologies through RLV-TD and SRE programs.

2) Air breathing propulsion: A major fraction of launcher mass are propellants. A major part of propellants is oxidizer. ABP precludes the need to carry all of the oxidizer as air is used for the purpose after a certain point in the flight profile. This cuts cost and also improves payload fraction of launch vehicles.

To achieve this ISRO is developing duel mode ramjet-scramjet engine. The engine technology will first be demonstrated on advance technology vehicle (ATV is a sounding rocket, ATV D2 will feature active scramjet engine and is under construction) and ones the engine matures, which will take a long time, its bigger version will be tested on RLV-TD vehicle. SPEX is all about testing matured ABP engine on a RLV TD sized vehicle.


As far as use of ABP goes, The RLV-TSTO wont have ABP and will consists of stages as you have described. Its the SSTO or AVATAR that will feature ABP.

 

[S-DUCT]

There are two parts to achieving low cost of access to space:

1) A reusable launch vehicle: the hardware contributes a major chunk (70-80 % that includes manufacturing + materials) to the cost of a launch vehicle that is expended after one use in present launch vehicles. By reusing the same hardware for multiple launches, a major cost saving can be achieved and thus launch cost can be reduced.

To achieve this ISRO is developing reusable technologies through RLV-TD and SRE programs.

2) Air breathing propulsion: A major fraction of launcher mass are propellants. A major part of propellants is oxidizer. ABP precludes the need to carry all of the oxidizer as air is used for the purpose after a certain point in the flight profile. This cuts cost and also improves payload fraction of launch vehicles.

To achieve this ISRO is developing duel mode ramjet-scramjet engine. The engine technology will first be demonstrated on advance technology vehicle (ATV is a sounding rocket, ATV D2 will feature active scramjet engine and is under construction) and ones the engine matures, which will take a long time, its bigger version will be tested on RLV-TD vehicle. SPEX is all about testing matured ABP engine on a RLV TD sized vehicle.


As far as use of ABP goes, The RLV-TSTO wont have ABP and will consists of stages as you have described. Its the SSTO or AVATAR that will feature ABP.

So duel mode ramjet-scramjet engine will suck air at hypersonic speed ,and separate and liquify oxygen at the same time.But incoming air would have temperature of around 1000 celsius and to liquify it will not be an easy task, Air condenser will increase engines weight.

One issue with the Liquid Air Cycle Engine system is that in order to appreciably reduce the mass of the oxygen carried at launch, a LACE vehicle needs to spend more time in the lower atmosphere to collect enough oxygen to supply the engines. This leads to greatly increased vehicle heating and drag losses, which therefore increases fuel consumption to offset the drag losses and the additional mass of the thermal protection system. This increased fuel consumption offsets somewhat the savings in oxidizer mass; these losses are in turn offset by the higher Isp (Specific impulse) of the air-breathing engine. Thus, the engineering trade-offs involved are quite complex, and highly sensitive to the design assumptions made.

1)Is there is any program parallel to ABP in the case ISRO fails to develope ABP (Like Precooled jet engineengines)?

2)Can you specify main difference between SABRE and ABP?

Thanks in advance.

 

[kurup]

 

[BlueDot_in_Space]

So duel mode ramjet-scramjet engine will suck air at hypersonic speed ,and separate and liquify oxygen at the same time.But incoming air would have temperature of around 1000 celsius and to liquify it will not be an easy task, Air condenser will increase engines weight.

There is no liquification in ramjet-scramjet.

1)Is there is any program parallel to ABP in the case ISRO fails to develope ABP (Like Precooled jet engineengines)?

2)Can you specify main difference between SABRE and ABP?

Thanks in advance.

1) There is no parallel program to ABP based on dual mode ramjet-scramjet in ISRO.

2) SABRE is a combined cycle or hybrid (pre-cooled ABP + rocket) engine. It either uses stored liquid oxygen or compressor fed gaseous air to burn the liquid hydrogen in the thrust chambers. No liquification takes place.

 

[BlueDot_in_Space]

 

[Guynextdoor2]

There is no liquification in ramjet-scramjet.



1) There is no parallel program to ABP based on dual mode ramjet-scramjet in ISRO.

2) SABRE is a combined cycle or hybrid (pre-cooled ABP + rocket) engine. It either uses stored liquid oxygen or compressor fed gaseous air to burn the liquid hydrogen in the thrust chambers. No liquification takes place.

Dude...when will you post the pics of the space suit...it's about time bro .

 

[S-DUCT]

There is no liquification in ramjet-scramjet.



1) There is no parallel program to ABP based on dual mode ramjet-scramjet in ISRO.

2) SABRE is a combined cycle or hybrid (pre-cooled ABP + rocket) engine. It either uses stored liquid oxygen or compressor fed gaseous air to burn the liquid hydrogen in the thrust chambers. No liquification takes place.

Mate am I right about operation of Avatar SSTO?

1)It would take-off horizontally using conventional turbo-rocket.After it has reached cruise speed of mach 1-1.2, vehicle would use DMRJ dual mode ramjet-scramjet engine to accelerate to mach 3-10.

2)During this cruising phase, an on-board system would collect air from the atmosphere, from which liquid oxygen would be separated and stored. The liquid oxygen collected then would be used in the final flight phase when the rocket engine(turbo-rocket) burns the collected liquid oxygen and the carried hydrogen to attain orbit.

 

[S-DUCT]

Ukraine is developing the engine for the Indian launch vehicle, the press service of the government of the country. "The implementation of the joint Ukrainian-Indian project" Jasmine ", which aims to develop a rocket engine for the Indian launch vehicle for space purposes," - said in a statement.

Prospects of cooperation in the space sector discussed the Deputy Minister of Economic Development and Trade of Ukraine Alexander Pinsky and chairman of the Indian Space Research Organization (ISRO) Sarvepalli Radhakrishnan.

The Indian side expressed its support for the holding in Kyiv in 2016. International Astronautical Congress. Head ISRO has confirmed that in the near future to complete the formation of the Indian bilateral working group on space, and Indian experts will focus on Ukraine to concretization of bilateral cooperation programs.

From 19 to 22 March, the Ukrainian delegation headed by A.Pinskim was in India as part of the second meeting of the working group on trade and economic cooperation in the Intergovernmental Ukrainian-Indian Commission on Trade, Economic, Scientific, Technical, Industrial and Cultural Cooperation.

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