BERYLLIUM EROSION CORROSION INVESTIGATION FOR SOLID ROCKET NOZZLES
Technical progress rept. no. 2, 1 Oct 1965-15 Mar 1966
PHILCO NEWPORT BEACH CA AERONUTRONIC DIV
Pagination or Media Count:
The mechanisms of corrosion and erosion of graphite, tungsten, and ablative plastic materials in beryllium propellants are studied. Propellants, grain designs, motor-nozzle configurations, and materials have been selected for 22 small motor tests using 100-lb grains. Four aluminum analog tests are included to provide direct comparisons of the two propellant systems. The grain design and double base propellants were selected for five 500-lb development motor tests. Graphite and tungsten inserts will be used with two submerged nozzle configurations. Results of the first seven small motor tests are presented. Four beryllium and three aluminum analog propellants were tested as remotely located end burners. The edge grain pyrolytic graphite throat heat sink is common to all tests together with asbestos phenolic insulation and ATJ graphite nozzle inlet and exit cones. Detailed laboratory post-test analyses were performed on the hardware, deposit, and exhaust particle samples. Ballistic data were reduced to provide throat deposition histories and propellant performance. These data and the thermocouple measurements were used to characterize nozzle thermal history and exhaust convection and radiation heat transfer coefficients. Measured corrosion, heat transfer, and deposition are discussed in terms of physical and analytical models. The test results tend to confirm predicted similarities in beryllium and aluminum propellant behavior. Deposition and combustion problems may be primarily responsible for materials problems with beryllium propellants.
- Solid Propellant Rocket Engines