S-DUCT
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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 VehicleTechnology 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.
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 VehicleTechnology 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.