Indian Space Research Organisation (ISRO) has set an ambitious goal of achieving self-reliance in launching spacecrafts into near earth orbit and in geosynchronous orbits. The first major milestone was achieved through the launch of 40 kg spacecraft Rohini into 400 km orbit by SLV-3. Further, using SLV-3 modules, 180 kg spacecraft was orbited by the Augmented Satellite Launch Vehicle ASLV. Latest in this series of launch vehicles is the Polar Satellite Launch Vehicle PSLV which has become an operational launch vehicle system Oxidizers and fuels, storable as liquids at room temperature conditions, are used in the liquid propellant rocket engines in the above launch vehicles. They produce specific impulse into the range of 220 to 310 s. When hydrogen and oxygen are used, as high as 460 5 could be achieved. However, the hydrogen and oxygen are to be maintained in liquid form in the temperature range of 20 K to 90 K. Development of rocket system using oxygen and hydrogen stored at cryogenic temperatures poses a number of technology challenges. These are in the areas of thermal management, propellant supply, materials of construction and fabrication techniques. Dedicated facilities are required for storage and handling of the cryogenic fluids and for the testing of components and engine. These have been established in the Liquid Propulsion Systems Centre. Developmental hardware have also been fabricated and test-fired. These aspects are brought out in this paper.
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