gslv mk3
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From the annual report.
Geosynchronous Satellite Launch Vehicle Mark III (GSLV-Mk III)
GSLV-Mk III is the next generation launch vehicle of ISRO capable of delivering 4 ton class spacecraft to Geosynchronous transfer orbit (GTO).
GSLV-Mk III is a three stage launch vehicle with three propulsion stages and has a lift-off weight of 630 tonnes and a height of 42.4 m. The GSLV-Mk III vehicle configuration is two Solid strap-on boosters Stages (S200), One Liquid Stage (L110) and One Cryogenic Stage (C25). The spacecraft is accommodated in a 5 metre diameter composite payload fairing of 110 m3 volume.
GSLV-Mk III is in the advanced stage of development with the completion of static firing of the S200 solid strap-on motor, stage testing of L110 liquid stage, completion of development tests of the engine subsystems of the C25 cryogenic upper stage and development and qualification tests of major sub-systems.
CE 20 Thrust Chamber Hot Test
The major development and qualification tests conducted during the year include structural and separation tests of payload fairing, acoustic test of Strap-on Base Shroud, Strap-on Nose Cone and S200 Flex Nozzle Control (FNC) tank, vibration tests of Proto Equipment Bay and Proto Strap-on Nose Cone, ground resonance test for the full vehicle configuration, system level functional test of satellite separation system and hot test of CE 20 thrust chamber. The Critical Design Reviews of S200 solid strap-on motor, L110 liquid stage and avionics systems have been completed.
L110 Flight Stage for X Mission
An experimental sub-orbital flight (LVM3-X) with passive cryogenic stage is targeted during the third quarter of 2014, to validate the entire vehicle configuration during the complex atmospheric regime of flight including its controllability. Towards this mission, two S200 flight motors, L110 flight stage, avionics packages, flight actuator and control electronics are ready for integration for the experimental flight. The passive cryogenic stage is in the final stages of assembly and integration and the vehicle avionics is undergoing system-level simulations.
Semi-cryogenic Project
The semi-cryogenic Project envisages the design and development of a 2000 kN semi-cryogenic engine for a future heavy-lift Unified Launch Vehicle (ULV) and Reusable Launch Vehicle (RLV). The semi-cryogenic engine uses a combination of Liquid Oxygen (LOX) and ISROSENE (propellant-grade kerosene), which are eco-friendly and cost-effective propellants.
Realisation of semi-cryogenic engine involves the development of performance-critical metallic and non-metallic materials and related processing technologies. 23 metallic materials and 6 non-metallic materials have been developed. Characterisation of injector elements and hypergolic slug igniters with different proportion of Tri-ethyl Aluminium and Tri-ethyl Boron has been completed. Sub-scale models of thrust chamber have been realised and ignition trials have been carried out successfully. Single element thrust chamber hot test in stage combustion cycle mode was also conducted successfully.
Establishment of test facilities like Cold Flow Test Facility and Integrated Engine Test Facility are under various stages of realisation. Fabrication drawings are realised for all sub-systems and fabrication of booster turbo-pump and pre-burner subsystem commenced.
Pre Project activities of Human Spaceflight Programme (HSP)
The objective of Human Spaceflight Programme is to undertake a human spaceflight mission to carry a crew of two to Low Earth Orbit (LEO) and return them safely to a predefined destination on earth. The programme is proposed to be implemented in defined phases. The pre project activities are progressing with a focus on the development of critical technologies for subsystems such as Crew Module (CM), Environmental control and Life Support System (ECLSS), Crew Escape System, etc., and performance demonstration of major systems through Crew Module Atmospheric Re-entry Experiment (CARE) and crew escape system through Pad Abort Test (PAT).
Preliminary design reviews for most of the systems pertaining to CARE for LVM3-X mission and PAT have been completed. Configuration, layout, and structural analysis of Crew Module for CARE mission have been completed. Design of re-entry trajectory for CARE mission corresponding to launch vehicle ascent trajectory has been carried out. Crew Module structure is in advance stage of realisation for flight test in GSLV-MkIII Experimental Mission.
Human Space flight Programme Crew Module undergoing a test
Functioning of newly developed Head-end Mounted Safe Arm (HMSA) for solid motors in Crew Escape System was successfully demonstrated. A parachute ejection test with Mortar was carried out at Terminal Ballistics Research Laboratory (TBRL), Chandigarh wherein sequential deployment of pilot parachute and drogue parachute was demonstrated. As part of deceleration system qualification, main and drogue parachutes, in modified and improved pack cover configuration, was drop tested at ADRDE, Agra. Parachute Reefing Line Cutter [RLC] of main parachute was realised and development tests were also carried out.
Gas analysers for environment monitoring of crew cabin, cabin lighting system with intensity control and MEMS based barometric sensor have been developed. Wind tunnel testing of Scale model of Crew escape system was completed in National Aerospace Laboratories, Bengaluru.
A unique state-of-the-art test facility – Environment Simulation Chamber (ESC) has been realised and commissioned at VSSC for stand-alone and integrated testing of Environmental Control & Life Support System (ECLSS) functional modules and Flight suit systems. A Variable length-to-diameter [L/D] Lithium Hydroxide (LiOH) proto-canister has been realised as part of air re-vitalisation system development. An integrated thermal performance test setup was realised for testing of crew cabin thermal and humidity control system and tests are in progress.
Air Breathing Propulsion Project (ABPP)
Air Breathing (AB) propulsion along with Reusable Launch Vehicle technology is the key for low cost access to Space. Unlike conventional rockets, Air Breathing Propulsion system makes use of atmospheric oxygen for combustion thus resulting in substantial improvement in payload fraction and reduction in overall cost.
ISRO has taken up a systematic R&D programme for demonstrating stable supersonic combustion through a series of ground tests on the Air-Breathing Propulsion Technology. The flight demonstration of this technology is planned with Advanced Technology Vehicle (ATV).
Towards Scramjet flight testing, mission studies have been carried out and feasibility established. Qualification and flight model of the Scramjet Engine Avionics Module with High Frequency Data Acquisition Units and its sub-systems were realised. Test and evaluation of these packages for flight were also successfully carried out.
Functional tests of the ignition system of scramjet with different mixture ratios of Gaseous Hydrogen – Gaseous Oxygen were carried out. High pressure gaseous hydrogen flow control module and a module for operating the start valves of Fuel Feed System for scramjet engine flight testing were realised.
The scramjet engine frame assembly for flight and the flow duct segments made out of super alloy Inconel-718 have been realised. Qualification test to demonstrate sliding capability of scramjet engine and vehicle interface was successfully carried out. The Scramjet Characterisation flight is targeted in 2014.
Space Capsule Recovery Experiment–2 (SRE-2)
SRE-2 Project was formed with the main objective of realising a fully recoverable capsule and to provide a platform to conduct microgravity experiments. SRE capsule has four major hardware, namely, Aero Thermo-structure (ATS), Spacecraft platform, Deceleration & Floatation system and Payloads.
ATS base structure has been realised. Six plasma wind tunnel tests were conducted to validate repair scheme of the silica tile. To qualify new elements mounted in the base region of SRE-2, an integrated test of annular deck was successfully completed. Carbon-Carbon cap has been processed as 4D composite through Hot Isostatic Pitch Impregnation and Carbonisation (HIPIC) route. Processing of Carbon-Carbon shell through 2D Pitch Impregnation and Carbonisation route is in progress. Interface design of Carbon-Carbon cap and shell was revisited based on the new thermo-mechanical properties. SiC coated Carbon-Carbon samples have been validated at plasma wind tunnel facility.
Aerothermo-structure of SRE-2
Geosynchronous Satellite Launch Vehicle Mark III (GSLV-Mk III)
GSLV-Mk III is the next generation launch vehicle of ISRO capable of delivering 4 ton class spacecraft to Geosynchronous transfer orbit (GTO).
GSLV-Mk III is a three stage launch vehicle with three propulsion stages and has a lift-off weight of 630 tonnes and a height of 42.4 m. The GSLV-Mk III vehicle configuration is two Solid strap-on boosters Stages (S200), One Liquid Stage (L110) and One Cryogenic Stage (C25). The spacecraft is accommodated in a 5 metre diameter composite payload fairing of 110 m3 volume.
GSLV-Mk III is in the advanced stage of development with the completion of static firing of the S200 solid strap-on motor, stage testing of L110 liquid stage, completion of development tests of the engine subsystems of the C25 cryogenic upper stage and development and qualification tests of major sub-systems.
CE 20 Thrust Chamber Hot Test
The major development and qualification tests conducted during the year include structural and separation tests of payload fairing, acoustic test of Strap-on Base Shroud, Strap-on Nose Cone and S200 Flex Nozzle Control (FNC) tank, vibration tests of Proto Equipment Bay and Proto Strap-on Nose Cone, ground resonance test for the full vehicle configuration, system level functional test of satellite separation system and hot test of CE 20 thrust chamber. The Critical Design Reviews of S200 solid strap-on motor, L110 liquid stage and avionics systems have been completed.
L110 Flight Stage for X Mission
An experimental sub-orbital flight (LVM3-X) with passive cryogenic stage is targeted during the third quarter of 2014, to validate the entire vehicle configuration during the complex atmospheric regime of flight including its controllability. Towards this mission, two S200 flight motors, L110 flight stage, avionics packages, flight actuator and control electronics are ready for integration for the experimental flight. The passive cryogenic stage is in the final stages of assembly and integration and the vehicle avionics is undergoing system-level simulations.
Semi-cryogenic Project
The semi-cryogenic Project envisages the design and development of a 2000 kN semi-cryogenic engine for a future heavy-lift Unified Launch Vehicle (ULV) and Reusable Launch Vehicle (RLV). The semi-cryogenic engine uses a combination of Liquid Oxygen (LOX) and ISROSENE (propellant-grade kerosene), which are eco-friendly and cost-effective propellants.
Realisation of semi-cryogenic engine involves the development of performance-critical metallic and non-metallic materials and related processing technologies. 23 metallic materials and 6 non-metallic materials have been developed. Characterisation of injector elements and hypergolic slug igniters with different proportion of Tri-ethyl Aluminium and Tri-ethyl Boron has been completed. Sub-scale models of thrust chamber have been realised and ignition trials have been carried out successfully. Single element thrust chamber hot test in stage combustion cycle mode was also conducted successfully.
Establishment of test facilities like Cold Flow Test Facility and Integrated Engine Test Facility are under various stages of realisation. Fabrication drawings are realised for all sub-systems and fabrication of booster turbo-pump and pre-burner subsystem commenced.
Pre Project activities of Human Spaceflight Programme (HSP)
The objective of Human Spaceflight Programme is to undertake a human spaceflight mission to carry a crew of two to Low Earth Orbit (LEO) and return them safely to a predefined destination on earth. The programme is proposed to be implemented in defined phases. The pre project activities are progressing with a focus on the development of critical technologies for subsystems such as Crew Module (CM), Environmental control and Life Support System (ECLSS), Crew Escape System, etc., and performance demonstration of major systems through Crew Module Atmospheric Re-entry Experiment (CARE) and crew escape system through Pad Abort Test (PAT).
Preliminary design reviews for most of the systems pertaining to CARE for LVM3-X mission and PAT have been completed. Configuration, layout, and structural analysis of Crew Module for CARE mission have been completed. Design of re-entry trajectory for CARE mission corresponding to launch vehicle ascent trajectory has been carried out. Crew Module structure is in advance stage of realisation for flight test in GSLV-MkIII Experimental Mission.
Human Space flight Programme Crew Module undergoing a test
Functioning of newly developed Head-end Mounted Safe Arm (HMSA) for solid motors in Crew Escape System was successfully demonstrated. A parachute ejection test with Mortar was carried out at Terminal Ballistics Research Laboratory (TBRL), Chandigarh wherein sequential deployment of pilot parachute and drogue parachute was demonstrated. As part of deceleration system qualification, main and drogue parachutes, in modified and improved pack cover configuration, was drop tested at ADRDE, Agra. Parachute Reefing Line Cutter [RLC] of main parachute was realised and development tests were also carried out.
Gas analysers for environment monitoring of crew cabin, cabin lighting system with intensity control and MEMS based barometric sensor have been developed. Wind tunnel testing of Scale model of Crew escape system was completed in National Aerospace Laboratories, Bengaluru.
A unique state-of-the-art test facility – Environment Simulation Chamber (ESC) has been realised and commissioned at VSSC for stand-alone and integrated testing of Environmental Control & Life Support System (ECLSS) functional modules and Flight suit systems. A Variable length-to-diameter [L/D] Lithium Hydroxide (LiOH) proto-canister has been realised as part of air re-vitalisation system development. An integrated thermal performance test setup was realised for testing of crew cabin thermal and humidity control system and tests are in progress.
Air Breathing Propulsion Project (ABPP)
Air Breathing (AB) propulsion along with Reusable Launch Vehicle technology is the key for low cost access to Space. Unlike conventional rockets, Air Breathing Propulsion system makes use of atmospheric oxygen for combustion thus resulting in substantial improvement in payload fraction and reduction in overall cost.
ISRO has taken up a systematic R&D programme for demonstrating stable supersonic combustion through a series of ground tests on the Air-Breathing Propulsion Technology. The flight demonstration of this technology is planned with Advanced Technology Vehicle (ATV).
Towards Scramjet flight testing, mission studies have been carried out and feasibility established. Qualification and flight model of the Scramjet Engine Avionics Module with High Frequency Data Acquisition Units and its sub-systems were realised. Test and evaluation of these packages for flight were also successfully carried out.
Functional tests of the ignition system of scramjet with different mixture ratios of Gaseous Hydrogen – Gaseous Oxygen were carried out. High pressure gaseous hydrogen flow control module and a module for operating the start valves of Fuel Feed System for scramjet engine flight testing were realised.
The scramjet engine frame assembly for flight and the flow duct segments made out of super alloy Inconel-718 have been realised. Qualification test to demonstrate sliding capability of scramjet engine and vehicle interface was successfully carried out. The Scramjet Characterisation flight is targeted in 2014.
Space Capsule Recovery Experiment–2 (SRE-2)
SRE-2 Project was formed with the main objective of realising a fully recoverable capsule and to provide a platform to conduct microgravity experiments. SRE capsule has four major hardware, namely, Aero Thermo-structure (ATS), Spacecraft platform, Deceleration & Floatation system and Payloads.
ATS base structure has been realised. Six plasma wind tunnel tests were conducted to validate repair scheme of the silica tile. To qualify new elements mounted in the base region of SRE-2, an integrated test of annular deck was successfully completed. Carbon-Carbon cap has been processed as 4D composite through Hot Isostatic Pitch Impregnation and Carbonisation (HIPIC) route. Processing of Carbon-Carbon shell through 2D Pitch Impregnation and Carbonisation route is in progress. Interface design of Carbon-Carbon cap and shell was revisited based on the new thermo-mechanical properties. SiC coated Carbon-Carbon samples have been validated at plasma wind tunnel facility.
Aerothermo-structure of SRE-2
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