【摘要】 给出了一种理论模型和基本计算方法。采用有限元法对某固体火箭发动机喉衬结构的烧蚀量、瞬态温度场和应力场进行了理论计算,计算结果与实测值比较一致,喉部直径实测值与计算值相对误差约为 2%。更多还原

【Abstract】 A theoretical model and fundamental calculation method were developed. By using finite element method,the erosion, instantaneous temperature field and stress field for the throat-insert of a solid rocket motor nozzle were calculated theoretically. The calculation results of the erosion accord with actual measurement value. The relative error between the actual measurement value of throat diameter and the calculation value is about 2%.更多还原