Accession Number : AD0373614

Title :   ADVANCED CRYOGENIC ROCKET ENGINE PROGRAM AEROSPIKE NOZZLE CONCEPT.

Descriptive Note : Quarterly progress rept. no. 1, 1 Mar-1 Jun 66.

Corporate Author : ROCKETDYNE CANOGA PARK CALIF

Report Date : 30 JUN 1966

Pagination or Media Count : 164

Abstract : Analysis and preliminary design of an advanced rocket engine using an aerospike nozzle and analysis, test hardware design, and test evaluation of thrust chamber performance and thrust chamber durability are described.

Descriptors :   (*LIQUID PROPELLANT ROCKET ENGINES, RESEARCH MANAGEMENT), (*ROCKET NOZZLES, LIQUID PROPELLANT ROCKET ENGINES), COMBUSTION CHAMBERS, CAPTIVE TESTS, PERFORMANCE(ENGINEERING), INJECTORS, FUEL INJECTORS, TURBOPUMPS, THROTTLING, MIXTURES, CRYOGENIC PROPELLANTS, HYDROGEN (U) ANNULAR NOZZLES, WATER, LIQUID COOLED, COMBUSTION, SPIKES, COPPER, FILM COOLING, PIPES, NICKEL, STAINLESS STEEL, REGENERATIVE COOLING, THERMAL STRESSES, FATIGUE(MECHANICS), LIFE EXPECTANCY, PROPELLANT CONTROL

Subject Categories : Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE