COMBUSTION STABILITY OF METALLIZED GELLED PROPELLANTS.
Quarterly progress rept. no. 3, 1 Oct-31 Dec 66,
ROCKETDYNE CANOGA PARK CA
Pagination or Media Count:
Work conducted during the third quarter of a 12-month exploratory development program concerning the combustion stability of metallized gelled propellants is reported. Results obtained to date from 36 hot firings using a 10,000-pound-thrust, 150-psig chamber pressure rocket combustor and an N2O4gelled N2H4 propellant combination are presented. Various sizes and amounts of aluminum and Al2O3 particles have been added to the gelled hydrazine. The response of the combustion process to pulse gun-initiated disturbances was determined. The feasibility of controlling the stability of the motor by the addition of aluminum and Al2O3 particles to the gelled fuel was established and the means through which the stability increase is manifested were also determined. Using a particle size distribution experimentally determined from samples collected in the exhaust plume, a preliminary analysis of the test results indicates that the improvement in stability is due predominantly to increased acoustic damping particulate damping within the combustion products rather than reduced driving in the combustion process itself. Author
- Liquid Rocket Propellants