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Rocket motor nozzle throat area control system and method
Rocket motor nozzle throat area control system and method
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机译:火箭发动机喷嘴喉部面积控制系统及方法
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摘要
A solid rocket motor including a combustion chamber, in which propellant is ignited to produce combustion gas, and a nozzle having a throat with an effective flow area, implements a system and method to inject gas into the nozzle throat to control its effective cross sectional flow area. Controlling the effective cross sectional flow area of the nozzle throat in turn controls combustion chamber pressure, thus the burn rate of the propellant in the combustion chamber, and thus the thrust generated thereby.
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