Accession Number : AD0505452
Title : Trimode Rocket Propulsion Feasibility Program.
Descriptive Note : Final rept. 3 Jan 67-30 Jun 69,
Corporate Author : BELL AEROSYSTEMS CO BUFFALO N Y
Personal Author(s) : Safeer,Neil I. ; Drexhage,Martin G.
Report Date : 01 NOV 1969
Pagination or Media Count : 261
Abstract : This document is the final report on the work accomplished on the Trimode Engine Feasibility Program. This engine employes a fuel, hydrazine, and an oxidizer, hydrogen peroxide, which individually are energetic monopropellants. Both propellants are decomposed in catalyst beds and the hot gas decomposition products injected and combusted in a second stage combustor. The development work on integrated gas generators with hot gas injectors is described. In addition, the development of a 100 lb thrust flight configuration demonstration engine is detailed. Critical experiments on hot gas injection, ignition, and combustion are discussed. Performance, start characteristics, and operating behavior in all three engine combustion performance, heat rejection characteristics, and start response determined for the engine. The engine demonstrated delivered steady-state performance values, hot start response, and heat rejection characteristics, which were competitive with conventional bipropellant reaction control engines. However, excessive heat soakback and delayed cold starts were found to be areas of technology needing further exploration, before the full potential of the engine can be exploited. (Author)
Descriptors : (*LIQUID PROPELLANT ROCKET ENGINES, PERFORMANCE(ENGINEERING)), LIQUID ROCKET PROPELLANTS, HYDRAZINE, LIQUID ROCKET OXIDIZERS, HYDROGEN PEROXIDE, MONOPROPELLANTS, DECOMPOSITION, BIPROPELLANTS, COMBUSTION CHAMBERS, GAS GENERATING SYSTEMS, IGNITION, FUEL INJECTORS, CATALYSTS, FLUIDIZED BED PROCESSES, COMBUSTION, COOLING, FILMS (U) O RINGS, METAL COATINGS, NICKEL
Subject Categories : Liquid Propellant Rocket Engines
Liquid Rocket Propellants
Distribution Statement : APPROVED FOR PUBLIC RELEASE