高速旋转火箭发动机采用单孔管状装药时,由于火箭发动机自身高速旋转产生的离心惯性力很大,火箭发动机在工作后期将会出现二次压力峰,给火箭发动机装药强度和壁厚强度设计带来十分不利的影响。本文将介绍一种新型的管状装药设计方法,使通过本方法设计成的装药能够消除火箭发动机因自身高速旋转所生成的二次压力峰,为旋转火箭发动机的装药设计补充一种新的装药设计方法。 When single-hole tubular charge is adopted in high-speed rotating rocket engine, centrifugal force generated by high-speed rotation of rocket engine is very large. Secondary rocket engine will appear secondary pressure peak in the later stage of operation, which gives the design of rocket motor charge strength and wall thickness strength Has a very negative impact. This article will introduce a new type of tubular charge design method that allows the charge designed by this method to eliminate the secondary pressure peaks generated by the rocket motor due to its own high speed rotation and complement a new charge design for the rotary rocket motor Charge design method.