Accession Number : AD0378294

Title :   ADVANCED CRYOGENIC ROCKET ENGINE PROGRAM, AEROSPIKE NOZZLE CONCEPT.

Descriptive Note : Quarterly progress rept. no. 3, 1 Sep-30 Nov 66,

Corporate Author : ROCKETDYNE CANOGA PARK CALIF

Personal Author(s) : Lary,F. B.

Report Date : DEC 1966

Pagination or Media Count : 200

Abstract : Program status and technical results obtained at the end of the report period are described for the Advanced Development Program, Aerospike. This program includes analysis and preliminary design of an advanced rocket engine using an Aerospike nozzle and experimental evaluation of critical technology related to the Aerospike concept. Component and system features, arrangement, and design parameters have been established for an optimum demonstrator engine. Studies of application of a flight engine to certain vehicles are in work. Experimental injector performance investigations on a segment chamber have been completed. Experimental cooling investigations on segment chambers and material studies are near completion. Fabrication of full-scale, cooled thrust chambers for performance demonstrations is under way. Fabrication of segments for structural and cooling evaluations is also in progress. (Author)

Descriptors :   (*ROCKET NOZZLES, DESIGN), (*SPIKES, AERODYNAMIC CHARACTERISTICS), SECONDARY FLOW, COLD FLOW, WEIGHT, HEAT TRANSFER, BASE PRESSURE, FLOW FIELDS, VISCOSITY, AERODYNAMIC CONFIGURATIONS, COMBUSTION CHAMBERS, OPTIMIZATION (U) LIQUID PROPELLANT ROCKET ENGINES, PLUG NOZZLES, VARIABLE AREA NOZZLES, CRYOGENIC PROPELLANTS, STARTING, THRUST, REGENERATIVE COOLING, COOLING

Subject Categories : Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE