Single-Chamber Stop/Start Solid Rocket Motor. Volume 2. Appendixes
Final rept. Apr 1968-Feb 1970
AEROJET SOLID PROPULSION CO SACRAMENTO CA
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This report deals with the technical effort conducted during the fulfillment of Contract F04611-68-C-0063, Single-Chamber StopStart Solid Rocket Motor. The program comprised five phases made up of preliminary design, propellant tailoring, component testing, lightweight motor design, and lightweight motor fabrication and testing. Although some problems were encountered in pintle nozzle and igniter function, the program yielded some very significant results. The basic design concepts of the motor were demonstrated to be sound and practical. The functional problems encountered are identified and solutions are presented to eliminate them. The program clearly demonstrated that a lightweight solid rocket motor can be repeatedly stopped and started at a simulated altitude of 60,000 ft and that a wide diversity of duty cycles can be attained to meet the spectrum of potential mission requirements.
- Solid Rocket Propellants