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Higher-performance Solid Motor for PSLV Successfully Ground Tested
Bangalore - Apr 2, 2002 An optimized version of solid motor for third stage of PSLV was successfully ground tested yesterday (March 30, 2002) at ISRO's SHAR Centre, Sriharikota. The performance parameters of the motor during the test were normal. The major improvements in the 2-meter diameter composite third stage motor include optimization of motor case and nozzle and increased propellant loading. With the present test, the motor with the improvement has been successfully evaluated consecutively in two ground tests. During the firing of the motor, about 270 parameters like pressure, strain, temperature, displacement, vibration etc., were monitored and recorded. The motor has a nominal burn time of 112 seconds and a maximum sea level thrust of 19 tonnes. Vikram Sarabhai Space Centre, Thiruvananthapuram, the lead centre for the launch vehicle systems is responsible for the design and development of high performance solid motor, and SHAR Centre is responsible for activities related to propellant casting, motor assembly and static testing. This high performance motor is planned to be used in the next PSLV flight (PSLV-C4) for Geo-Synchronous Transfer Orbit (GTO) mission and is expected to increase the payload capability of PSLV in this orbit by about 70 kg. Meanwhile, development of Cryogenic Upper Stage for Geo-synchronous Satellite Launch Vehicle (GSLV) crossed one more milestone last week with the successful test firing of the indigenous cryogenic engine for a duration of 12 minutes. The test was carried out at the Liquid Propulsion Systems Centre (LPSC) Test complex at Mahendragiri in Tamil Nadu. This hot test was preceded, in the last few weeks, by four shorter duration tests of 10, 40, 40 and 200 seconds. This turbo-pump fed regeneratively cooled engine produces a nominal thrust of 7.0 tonne in vacuum. The required test facilities were established specifically to test the cryogenic engine consisting of feed systems for handling liquid oxygen and liquid hydrogen, instrumentation and data acquisition system with attendant safety devices. Number of chill-down trials and simulation tests were conducted before the actual hot firing of this engine. The cryogenic engine development has been a challenging task with breakthroughs needed with respect to many disciplines including analytical tools, material characterization, fabrication processes, test facility establishment, handling of cryogenic fluids and finalization of test sequence. LPSC, the lead centre for the liquid propulsion systems is responsible for the realization of the engine and stage, fluid system and associated test facilities. The Vikram Sarabhai Space Centre (VSSC), Thiruvananthapuram, is responsible for the development of pyrogen ignitors, pyrotechnic devices and analysis software. Indian industries have significantly contributed in the realization of the cryogenic engine. Community Email This Article Comment On This Article Related Links Indian Space Research Organisation SpaceDaily Search SpaceDaily Subscribe To SpaceDaily Express Rocket Science News at Space-Travel.Com
Successful First Test For Vega's Zefiro 9 Engine
Paris, France(ESA) Dec 28, 2005Flames, smoke and a deafening noise accompanied the first firing test of Vega's Zefiro 9 third-stage solid rocket motor. A first examination of the data indicates that everything went well at the test carried out yesterday at Salto de Quirra in southeast Sardinia. |
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