Low-Thrust Bipropellant Engine Technology.
Final technical rept. Sep 77-Jul 80,
AEROJET LIQUID ROCKET CO SACRAMENTO CA
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The design, fabrication and hotfire test of a low-thrust, 0.5 lbF class bipropellant rocket engine, capable of providing very small, precisely repeatible impulse bits and long, high-performance, steady-state burns, was undertaken in a three-phase program. Phase I, Analysis and Design, consisted of detailed studies and tradeoff analyses of general missionsystem requirements versus engine assembly parametrics and the development of the overall design approach. Phase II, Design Verification, consisted of component valve, injector and chamber fabrication and development testing for the demonstration point design. Phase III, Demonstration, consisted of engine fabrication and demonstration of the point design. While a 100 achievement of all contract goals was elusive within the resources provided, significant advancements in small engine technology were made that prove the feasibility of developing a 0.5 lbF class bipropellant engine. Steady-state durability of 8 hours of firing without failure has been demonstrated, along with a small impulse bit of less than 0.005 or - .0005 lbF sec. It is reasonable to predict that the same engine that ran 8 hours steady-state will be able to accomplish the 10 hour life goal based on its excellent postfire condition.
- Liquid Propellant Rocket Engines
- Liquid Rocket Propellants