摘要
针对助推-滑翔式弹道导弹,提出一种主被动段弹道联合优化设计方法,并以多目标约束下的最大射程弹道设计为例,讨论了联合优化设计过程中所需解决的一些关键问题。仿真结果表明,相比于分段优化设计方法,联合优化方法所设计出弹道性能指标有明显提高。
An united optimization method subjected to multiple goal constraint is presented to design the boost-glide missile. Based on the example of the design of maximal range trajectory under multiple goal restraint, some crucial aspects of the united optimum method have been discussed. The simulation results indicate that united optimization method offers much more superior trajectory parameters than traditional method.
出处
《导弹与航天运载技术》
北大核心
2009年第5期1-5,共5页
Missiles and Space Vehicles
关键词
联合优化
滑翔机动
弹道设计
多目标约束
United optimization
Gliding maneuver
Trajectory design
Multiple goal restraint
