火箭弹推力方案的优化设计

Optimization Design for Thrust Project of MLRS

提出了一种基于M atlab/S im u link和iS IGHT软件平台,以火箭弹规定的射程为约束,以火箭弹飞行过程中的最大马赫数最小为优化目标的火箭弹推力方案优化设计方法。在M atlab/S im u link软件下建立火箭弹飞行的六自由度弹道仿真模型,推力模型依所选推力方案而变化,利用iS IGHT软件的优化功能充分挖掘每一种推力方案的潜能。经过大量的优化计算,可以得到每一种推力方案下的最优结果。文中还对每一种推力方案下所需要的火箭发动机总冲进行了分析。

An optimization method is proposed based on Matlab/Simuling and iSIGHT platform, in which the range of multiple launch rocket system （MLRS） is a constraint condition and the minimization of maximum mach during the period of flying is the object. Asix-freedom trajectory simulation model is set up in Matlab/Simulink and the thrust model varies with the project. And the optimization function of iSIGHT is used to find the potential ability of each project. The optimum results for each thrust project are obtained through a series of optimizing calculation. The total impulse needed for each thrust project is also analyzed in this paper.