以某型发动机为例,采用6△s统计及DOE试验设计方法对喉衬进行优化设计,通过多轮比较和大量仿真计算分析,发现喉衬轴向承力面与内型面的夹角是影响喉衬受力状态的主要因素,同时,模拟验证试验验证了角度的改变对喉衬最大应力有显著影响,且当角度为90°时喉衬的受力状态达到最佳,最大应力值从优化前的77.54MPa降低到48.41MPa,能够保证喉衬在发动机工作过程中保持结构完整,满足发动机的使用要求。

Based on a certain type of solid rocket motor, in this article, the structure of nozzle insert was optimized by six sigma statistics a-nalysis method and design of experiment method. Through lots of comparative studies and imitation analysis, the angle between the axial contact surface and the nozzle wall was chosen as the main factor of the stress distribution in the nozzle insert. Meanwhile, simulation ex-periment proved that the angle affects the stress of nozzle insert obviously. Research shows that the nozzle inserts will be in the best favora-ble stress state as while the angle reaches 90 degrees, and the maximum stress value is reduced from 77.54 MPa to 48.41 MPa to ensure the nozzle insert maintains structure integrity and satisfies the requirements of the certain type of solid rocket motor.