Hydroxyl amine based staged combustion hybrid rocket motor
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United States of America Patent
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Jun 28, 2011
Grant Date -
Aug 27, 2009
app pub date -
May 15, 2007
filing date -
May 15, 2007
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Abstract
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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