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

Report Date:

1971-07-01

Pagination or Media Count:

48.0

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 0F 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.

Subject Categories:

  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE