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CFRP PLF Functional Test
Indigenously developed Advanced Mission Computer (AMC) packages, RESINS Mk IV package, Composite 4m payload fairings, Piston type EGC actuators for L40s and Advanced Telemetry System (ATS) packages will be inducted in the vehicle systems in GSLV-D3 flight.
The flight stage integration of the indigenous cryogenic upper stage is in the final stage and the maiden launch of GSLV with indigenous cryo stage is planned in 2009.
Cryogenic Upper Stage Project
The indigenous Cryogenic Upper Stage (CUS) which has been realised, will be flight tested in GSLV-D3 Mission. The full duration (720 s) stage level hot test was successfully completed on November 15, 2007.
The Flight Acceptance Hot Test of Indigenous Cryogenic Engine was successfully conducted at Liquid Propulsion Systems Centre’s (LPSC) Mahendragiri facilities on December 18, 2008.
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.
The indigenous Cryogenic Engine is being integrated with propellant tanks, stage structures and associated feed lines to realise the first fully integrated indigenous flight Cryogenic 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-Mk III programme is presently in the hardware testing and qualification phase. Subsystem level development tests have been completed in most of the areas. The Project is entering into the phase of stage level tests for propulsion modules and vehicle level tests like Ground Resonance Test (GRT).
For C25, subsystem level tests are nearing completion and engine tests are planned during 2010. Majority of the facility realisation across different launch vehicle centers and industries have been completed.
Some of the major accomplishments include Solid Propellant Plant (SPP) commissioning, S200 Flex Nozzle Control (FNC) system integrated tests, L110 engine qualification, Cryo Engine subsystem tests and sub assembly acoustic tests.
Indigenously developed Advanced Mission Computer (AMC) packages, RESINS Mk IV package, Composite 4m payload fairings, Piston type EGC actuators for L40s and Advanced Telemetry System (ATS) packages will be inducted in the vehicle systems in GSLV-D3 flight.
The flight stage integration of the indigenous cryogenic upper stage is in the final stage and the maiden launch of GSLV with indigenous cryo stage is planned in 2009.
Cryogenic Upper Stage Project
The indigenous Cryogenic Upper Stage (CUS) which has been realised, will be flight tested in GSLV-D3 Mission. The full duration (720 s) stage level hot test was successfully completed on November 15, 2007.
The Flight Acceptance Hot Test of Indigenous Cryogenic Engine was successfully conducted at Liquid Propulsion Systems Centre’s (LPSC) Mahendragiri facilities on December 18, 2008.
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.
The indigenous Cryogenic Engine is being integrated with propellant tanks, stage structures and associated feed lines to realise the first fully integrated indigenous flight Cryogenic 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.
L-110 engine test at liquid propulsion test facilities, Mahendragiri
Efforts to develop various subsystems are progressing satisfactorily with the establishment of necessary infrastructure at ISRO centres such as the propellant casting facility for 200 t solid boosters etc. GSLV-Mk III uses new propulsion stages such as 200 tonne solid boosters, 110 tonne liquid stage and 25 tonne cryogenic upper stage. The launch of GSLV-Mk III is scheduled during 2009-10. A Solid Propellant Plant (SPP) for manufacturing S-200 solid boosters for GSLV-Mk III was successfully commissioned at SDSC SHAR. Casting and curing of one of the live S-200 segments was completed successfully achieving excellent propellant properties. The facilities have undergone rigorous test and evaluation at various levels and many trials were carried out using inert propellant to obtain safety clearance from the review committees. The new S-200 SPP is provided with automation and remote operation features to reduce manpower and improve safety. GSLV-Mk III programme is presently in the hardware testing and qualification phase. Subsystem level development tests have been completed in most of the areas. The Project is entering into the phase of stage level tests for propulsion modules and vehicle level tests like Ground Resonance Test (GRT).
For C25, subsystem level tests are nearing completion and engine tests are planned during 2010. Majority of the facility realisation across different launch vehicle centers and industries have been completed.
Some of the major accomplishments include Solid Propellant Plant (SPP) commissioning, S200 Flex Nozzle Control (FNC) system integrated tests, L110 engine qualification, Cryo Engine subsystem tests and sub assembly acoustic tests.