摘要
在内部装填物参数给定的情况下,减小再入飞行器的质量和雷达截面具有重要意义。本文以再入飞行器的质量和雷达截面为目标函数进行多目标优化。本文的理论和计算方法可用于再入飞行器总体设计的方案论证阶段。
A suitable mathematical model and an optimum method of system design of the reentry vehicle have been established. The paper herein optimizes the objectives of the mass and the RCS of the reentry vehicle, and makes the objectives smallest.
出处
《导弹与航天运载技术》
1993年第1期49-55,共7页
Missiles and Space Vehicles
关键词
再入飞行器
头锥
最佳设计
Reentry vehicle, Nose cone, Optimum design.
