Accession Number : ADA305315

Title :   Development and Testing of Ablative Rocket Engine with Selected 7.62-Centimeter (3.0 IN.) Diameter Throat Inserts.

Descriptive Note : Technical memo.,

Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER

Personal Author(s) : Winter, Jerry M. ; Peterson, Donald A. ; Shinn, Arthur M., Jr. ; Pavli, Albert J.

PDF Url : ADA305315

Report Date : JUL 1971

Pagination or Media Count : 48

Abstract : Five injector configurations were designed and the performance evaluated in a nitrogen tetroxide - 50-percent blend of unsymmetrical dimethyl-hydrazine and hydrazine propellant rocket engine. A triplet injector modified for 0/F zoning provided combustion efficiency of over 95 percent. Selected throat inserts (7. 62 cm (3. 0 in.) in diameter) were tested to demonstrate long-term firing duration and restart capability. The duty cycle chosen was an initial 300-second firing, five 20-second firings and a final 300-second firing. The best throat insert material tested was zirconia reinforced with tungsten-rhenium wire. Scale-up to larger throat sizes is discussed.

Descriptors :   *ROCKET ENGINES, *THROATS(EQUIPMENT), *INSERTS, ABLATION, SIZES(DIMENSIONS), HYDRAZINES, FIRING TESTS(ORDNANCE), WIRE, EFFICIENCY, PROPELLANTS, COMBUSTION, CONFIGURATIONS, NICKEL ALLOYS, NITROGEN OXIDES, RESTARTING, INJECTORS, ZIRCONIUM OXIDES, TETROXIDES, RHENIUM ALLOYS.

Subject Categories : Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE