Accession Number : AD0509090

Title :   Minimum-Cost Design Booster Program.

Descriptive Note : Final rept. 1 Sep 68-10 Jan 70,

Corporate Author : ROCKETDYNE CANOGA PARK CALIF

Personal Author(s) : Dennies,P. C. ; Eberle,E. E. ; Hawkinson,E. L.

Report Date : APR 1970

Pagination or Media Count : 415

Abstract : A program to evaluate the performance and stability characteristics of minimum cost, low chamber pressure (300 psia) thrust chambers and injectors was conducted jointly by AFRPL and Rocketdyne. Rocketdyne designed and had fabricated all test hardware and AFRPL conducted the major portion of the test program. Rocketdyne designed an injector concept consisting of groups of modules (7 at the 250,000-pound-thrust level) that would be scaled to larger thrust levels by increasing the number of modules. The program was divided into three phases: Phase I evaluated the performance and stability of a single module, Phase II evaluated the operating characteristics of short-duration heat sink hardware at full thrust, and Phase III evaluated long-duration (up to 140 seconds), ablative-lined hardware. The performance requirement of 90 percent was bettered in both long- and short-duration tests and stability and integrity were demonstrated over the operating range. This report covers the work performed during the course of the program. Presented are design analysis, fabrication history, test results, data correlation, scaling considerations, and program conclusions.

Descriptors :   (*BOOSTER ROCKETS, PERFORMANCE(ENGINEERING)), FUEL INJECTORS, COMBUSTION CHAMBERS, PRESSURE, INTERIOR BALLISTICS, THRUST, COMBUSTION CHAMBER LINERS, ABLATION, HEAT SINKS, LIQUID PROPELLANT ROCKET ENGINES, EFFICIENCY, COSTS, OPERATION, DESIGN, STABILITY, FUEL SPRAYS, SCALE, MODEL THEORY (U) CONICAL NOZZLES

Subject Categories : Liquid Propellant Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE