The objective of this conceptual design study is to verify that the Cosmic Background Explorer (COBE) Hydrazine Propulsion Subsystem (HPS) Rocket Engine Assembly (REA) will satisfy the Tropical Rainfall Measuring Mission (TRMM) requirements and to develop a preliminary thruster module design using the existing REAs. The performance of the COBE HPS 5 lbf thrusters meet the TRMM mission requirements. The preliminary design consists of a single 5 lbf REA REM which is isolation mounted to a spacecraft interface angle bracket (5 or 10 deg angle). The REM incorporates a catalyst bed heater and sensor assembly, and propellant thermal control is achieved by thermostatically controlled heaters on the thruster valves. A ROM cost of approx. $950 K has been estimated for the phase 2 program to finalize the design, fabricate, and test the hardware using mechanical thermostats for thermal control. In the event that solid state thermostats are used, the cost is estimated to be $160 K higher. A ROM cost is approx. $145 K is estimated to study the effects of using Japanese manufactured hydrazine for the TRMM mission.
Conceptual Design Study for the Use of COBE Rocket Engines on the Tropical Rainfall Measuring Mission
1992
243 pages
Report
Keine Angabe
Englisch
Meteorological Instruments & Instrument Platforms , Physical Meteorology , Rocket Engines & Motors , Cosmic background explorer satellite , Propulsion system performance , Rocket engines , Catalysts , Hydrazines , Temperature control , Cost analysis , Fabrication , Mission planning , Propellants , Solid state , Thermostats , Rainfall
Tropical rainfall measuring mission (TRMM)
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