Method and system for controlling solid propellant thrust
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United States of America Patent
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Nov 19, 2013
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N/A
app pub date -
Sep 16, 2009
filing date -
Sep 16, 2008
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Abstract
The present invention relates to a solid rocket motor control system that uses state of the art electrically ignited, extinguishable and throttleable propellants. In embodiments, the control system is implemented by a software algorithm embedded in missile flight controllers and contains all control system elements and control compensation that performs thrust control for many defense and space rocket motor applications, for example.
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