Accession Number : ADA091078
Title : Low-Thrust Bipropellant Engine Technology.
Descriptive Note : Final technical rept. Sep 77-Jul 80,
Corporate Author : AEROJET LIQUID ROCKET CO SACRAMENTO CA
Personal Author(s) : Schoenman,L ; Friedman,R L
Report Date : Aug 1980
Pagination or Media Count : 428
Abstract : 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 mission/system 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.
Descriptors : *LIQUID PROPELLANT ROCKET ENGINES , *THRUST , *BIPROPELLANTS , STATE OF THE ART , EXPERIMENTAL DESIGN , TEST METHODS , FABRICATION , LOW LEVEL , TRADE OFF ANALYSIS , INJECTORS , SPECIFIC IMPULSE , NITRATES , LIQUID ROCKET OXIDIZERS
Subject Categories : Liquid Propellant Rocket Engines
Liquid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE