整体式固冲发动机空空导弹一体化设计

INTEGRAL DESIGN OF AIR-TO-AIR MISSILE WITH INTEGRATE ROCKET RAMJET

采用分步优化方法,研究了整体式固冲发动机中远程空空导弹的一体化设计问题。在质点弹道总体优化设计中,把导弹和整体式固冲发动机作为一个系统,优选了导弹和发动机的参数;在质点系优化设计中,对控制系统参数进行优选,满足导弹的命中精度要求。实例计算结果表明,采用分步优化方法具有较高的效率,便干工程应用。

Using the stepwise optimization, some questions about optimal design of air-to-air mediumlong missile propelled by integral rocket ramjet is studied. In the course of integrated design of particle trajectory, the combination of missile and integral rocket ramjet is regarded as a system, so the system optimum parameters were obtained. However, in the optimal design of the mass of particle system, the control parameters were optimized, which aims at meeting the requirement of targeting accuracy. The computed results of a real example indicated that it's fit to use stepwise optimization because of its high efficiency.