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HYDROXY AMINE BASED STAGED COMBUSTION HYBRID ROCKET MOTOR
HYDROXY AMINE BASED STAGED COMBUSTION HYBRID ROCKET MOTOR
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机译:基于羟基胺的分级燃烧混合火箭发动机
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摘要
A new rocket motor assembly configuration is disclosed. Amine based oxidizer is decomposed in the presence of a metallic catalyst to generate an oxygen rich hot gas stream. The hot gas stream is used to trigger a Magnesium based solid fuel in the combustion chamber. The thrust of the rocket motor may be regulated at multiple points. This design thus offers an IM compliant, thrust-adjustable rocket motor that is of a low hazard classification without compromising its performance.
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