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介绍了采用缩小喷管喉径的方法，对固体火箭发动机燃烧室压强和推力进行补偿，以达到延长发动机使用寿命的目的。
The method of reducing the throat diameter of the nozzle is introduced in order to compensate the pressure and thrust of the combustion chamber of a solid rocket engine so as to prolong the service life of the engine.