Current nozzle materials used in small diameter tactical rocket motor applications experience significant erosion at the throat during service. Several feasible nozzle throat materials/design concepts were developed in Phase I which offer significant reductions in throat erosion and reduced weight when compared to current materials. The objectives of the proposed Phase 11 program are to: (J) fabricate and demonstrate via experimentation the performance of the nozzle throat material/design concepts; (2) corroborate material models analyses and analytical tools using the results of a three phase experimental program; and (3) optimize the materials/design concepts. Performance data for several individual material concepts will be obtained as well as for full-scale nozzle configurations representative of a state-of-the-art, high performance tactical rocket motor. Phase Ill commercialization of the non-eroding nozzle technology has potential applications for both current and future missile systems. BENFITS: The benefits derived from the proposed research are directly applicable to high performance small diameter rocket motors. The Phase II results can also be applied to commercial applications such as satellite motors, jet engines, turbine engines, electricalpower generation~plant5 and processing of materials using high temperature gases.
Keywords: NOZZLE GRAPHITE THROAT EROSION CARBON-CARBON ROCKET MOTORS COATINGS THROAT INSERTS REFRACTORY METALS
