在固体火箭发动机的设计过程中,仅仅对发动机自身参数进行优化,难以得到最优的飞行器总体设计结果。为提升优化效果文中综合了发动机内弹道与飞行器外弹道设计,建立内外弹道联合仿真流程,直接从飞行器总体性能的角度选择发动机设计参数,建立了与内外弹道同时匹配的发动机优化设计方案。此优化设计方法避免了发动机内弹道和飞行器外弹道两个设计间的多次输入输出迭代,缩短了设计周期。

In order to solve the difficulty of obtaining the overall tactical performance indicators of the aircraft through one optimal process in the solid rocket motor (SRM) design, and comprehensively considering the solid propulsion and the external trajectory, the two traditional optimal processes which are the optimization of scheme and the optimization of parameters of the SRM were combined to one design optimization program here. From the point of the overall tactical performance of the aircraft, the process of the integrated simulation of internal and external trajectory was established to get the parameters of the relevant parameters of the SRM. And the design optimization program which matches both the internal and external trajectory well was set up. Based on the integrated simulation of internal and external trajectory, The design of the SRM was optimized to avoid the multiple iterations and coordination of the two traditional optimal processes, so the design cost and period decrease.