and some more.
Quote: Geosynchronous Satellite Launch Vehicle (GSLV)
ISRO's Geosynchronous Satellite Launch Vehicle (GSLV), in its first operational flight (GSLV-F01), launched 1950 kg EDUSAT, India's first exclusive satellite for educational services, from Satish Dhawan Space Centre, SHAR, Sriharikota on September 20, 2004.
GSLV was declared operational after both its developmental test flights conducted in April 2001 and May 2003 were successful.
For the 49 metre tall, 414 tonne, GSLV first stage, GS1, comprises a core motor with 139 tonne of solid propellant and four strap-ons each with 40 tonne of hypergolic liquid propellants (UH25 and N204). The second stage has 39 tonne of the same hypergolic liquid propellants. The third stage (GS3) is a cryogenic stage with 12.5 tonne of Liquid Oxygen (LOX) and Liquid Hydrogen (LH2). The Composite Fibre Reinforced Plastic (CFRP) GSLV payload fairing is 4 m in diameter and is 8 m long.
All the GSLV Missions flown so far utilised cryogenic stage (CS) procured from Russia. The GSLV-D3 is the third developmental Mission of GSLV. The main significance of this mission is the usage of the indigenously developed Cryogenic Upper Stage (CUS) in place of bought out Cryogenic Stage (CS) from Russia.
[center]PAM-G stage undergoing hot test
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.
[center]L110 development stage[/center]
GSLV MkIII programme is presently in the hardware testing and qualification stage. The project has entered the phase of stage level tests for propulsion modules with the successful static test of S200 on January 24, 2010.
[center]CE20 Integrated Turbopump Hot Test in progress[/center] L110 development stage functional integration has been completed. Structural test facility for propellant tanks commissioned at SDSC, SHAR. Preparation and assembly of L110 stage for long duration hot test is progressing well at LPSC, Mahendragiri.
Indigenously developed turbo pump system of CE20 engine was successfully tested in integrated pressure fed mode for 60 seconds. First launch of GSLV Mk III is expected during 2011-12.
Space capsule Recovery Experiment (SRE-2)
SRE-2 is proposed to be launched onboard PSLV-C19 in of 2010 - 11. The main objective of this mission is to realise a fully recoverable capsule and provide a platform to conduct microgravity experiments.
SRE-2 carries six new payloads - Advanced Isothermal Heating Furnace (IHF) to study the effect of microgravity on liquid phase sintering of powder metallurgy products and processing Carbon nanotube, CCMB Bioreactor to study the effect of microgravity on gene expression of E-coli bacteria, Langmuir Probe for Electron density measurement, Dosimeter for orbital radiation measurement, JAXA payload for Cyanobacteria growth and Biopa payload to study growth and gene expression of seeds.
SRE-2 capsule has four major hardware: Aero Thermostructure (ATS), Spacecraft platform, deceleration and floatation system and six new payloads. New systems developed for SRE 2 include Carbon-Carbon Nose Cone, and indigenous Beacons.
Semi Cryogenic Engine Development (SCED)
Semi-Cryogenic Engine development envisages the development of a high thrust engine producing 2000 kN (Vacuum) thrust with Liquid Oxygen and kerosene propellant combination for the Common Liquid Core in Unified Launch Vehicle (ULV). As part of semi-cryo engine development pre-project activities, five designs of single element pre-burner injector were realised and tested. Semi-cryo Project Report was prepared and clearance obtained. Conceptual design of the semi cryo engine has been completed.
Advanced Technology Vehicles
Research and development activities in semi-cryogenic propulsion stages, air breathing propulsion and re-usable launch vehicle technology are also being pursued vigorously by the department in an effort towards reducing the cost of access to space.
Air Breathing Rocket Systems use atmospheric oxygen from the surroundings and burn it with the stored on-board fuel for producing the forward thrust in contrast to the conventional chemical rocket systems, which carry both the Oxygen and fuel on board. As a result, air-breathing systems become much lighter and more efficient leading to reduced overall costs.
Air Breathing Propulsion, along with Reusable Launch Vehicle Technology will lower cost of space access drastically. Scramjet engine with supersonic combustion is identified as the most critical element in Air Breathing propulsion technology.
As the Air-Breathing Systems have the capacity to operate only during the atmospheric phase of flight, they always have to be adopted along with conventional chemical rockets for meeting the final orbital velocity requirements. Air-Breathing engines like the turbojet engines used in aircraft have limitations of operating only upto a maximum of Mach number 3. To travel from Mach number 3 to 6, a RAMJET is used. Beyond Mach number 6, SCRAMJET propulsion is the only viable option.
The development of a SCRAMJET System is complex and it involves a number of technological challenges, especially those related to the mixing of very high speed air (velocity around 1.5 km/s) with fuel, achieving stable ignition and flame holding in addition to ensuring efficient combustion within the practical length of combustor. Supersonic combustion was successfully achieved in ground testing.
During the year, hypersonic air intake models were studied in wind tunnels simulating high flight velocities and supersonic combustor configuration was firmed up for first Scramjet flight. Full engine simulation with combustion was also carried out.
Advanced Technology Vehicle (ATV)
The two stage vehicle with RH560 M motor for first stage (Booster Stage), RH560M motor for the second stage (sustainer stage) with all associated structural systems and payload is having a total length of 10.3 meters with a take-off mass of 3 tonnes.
The first flight aims at vehicle characterisation and performance evaluation. Booster and sustainer motors, structures, separation and destruct system were realised during the year.
Reusable Launch Vehicle Technology Demonstrator
As a first step towards realising a Two Stage To Orbit (TSTO) fully re-usable launch vehicle, a series of technology demonstration missions have been conceived. For this purpose, a Winged Reusable Launch Vehicle technology Demonstrator (RLV-TD) has been configured.
The RLV-TD will act as a flying test bed to evaluate various technologies, viz., hypersonic flight, autonomous landing, powered cruise flight and hypersonic flight using air breathing propulsion. First in the series of demonstration trials is the hypersonic flight experiment (HEX).
[center]An artistââ¬â¢s view of RLV-TD[/center] During the year, aerodynamic characterisation of technology demonstration vehicle was completed at NAL, VSSC and IITK. Trajectory design and Closed Loop Guidance algorithm from lift off to touch down was also completed. Besides, aerodynamic characterisation of ascent and descent configuration, lift off aerodynamic studies at IIT Kanpur and control surface deflection studies at hypersonic Mach numbers by in-house wind tunnel tests were completed.
Engineering model of Airframe and simulation models of avionics packages were realised. HS9 motor static test completed.
Advanced R&D Projects
Aerodynamic characterisation of advanced space transportation system needs higher capacity facilities. Towards this, 1m diameter hypersonic wind tunnel and 1 m diameter shock tunnel are in advanced stage of realisation. During the year, vacuum system for Hypersonic Wind Tunnel Project facility was commissioned. Besides, a Higher capacity shaker system is being indigenously realised for environmental vibration testing of future launch vehicle subsystems. And, to simulate the plasma environment faced by reentry modules like SRE-II and HSP Crew module, current 1 MW Plasma tunnel is being enhanced to 6 MW Plasma Tunnel.
Launch infrastructure
SDSC SHAR supported two launches of Polar Satellite Launch Vehicle PSLV-C12 on April 20, 2009 for RISAT-2 and ANUSAT and PSLV-C14 on September 23, 2009 for launching Oceansat - 2.
[center]S200 at its test facility[/center] Fluid mockup trials on Indigenous CUS were completed using filling software developed in house.
State of the art S-200 Solid Propellant Plant (SPP) with built in automation and safety features has been commissioned successfully at SDSC SHAR. This includes full commissioning of facilities for Hardware Insulation and Lining, Raw Material Preparation, Premix, Mixing and Bowl cleaning, Casting, Curing and Post Curing like Propellant Machining, Inhibition and Tilting and NDT. Static Test of S200 motor, the third largest in the worls was conducted successfully on January 24, 2010. Vehicle Assembly and Test Facilities (VATF), Range Instrumentation and Computer Systems (RICS) and Propellant Servicing Facilities (PSF) required for GSLV-Mk III project are nearing completion.
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