Material Performance of Carbon Phenolic Ablators and Pyrolytic Graphite Coatings in Nozzles Subjected to Multiple Pulse Duty Cycles
AEROTHERM ACUREX CORP MOUNTAIN VIEW CA
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Measurements and analysis of the thermal and ablative response of five multiple pulse duty cycle rocket nozzles were performed. Nozzles were fired on a solid propellant simulator with a test stream composition, designated ANB-3066, which contained 16 percent aluminum. Nominal chamber pressure for each of the various firing pulses was 750 psia. Material temperature histories were recorded at several locations in each nozzle. Post-test measurements of surface recession, char penetration, and density versus depth, as well as thermocouple data are used for comparison with one and two-dimensional heat conduction and material ablation calculations.
- Ceramics, Refractories and Glass
- Coatings, Colorants and Finishes
- Rocket Engines