Development and Testing of Ablative Rocket Engine with Selected 7.62-Centimeter (3.0 IN.) Diameter Throat Inserts.
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER
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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.
- Rocket Engines