双脉冲中程空空导弹弹道优化  

Trajectory Optimization of Dual-pulse Medium Range Air-to-air Missile

作　　者：李伟喆 陈万春[1] Li Weizhe;Chen Wanchun(School of Astronautics,Beihang University,Beijing 100083,China)

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《战术导弹技术》2018年第5期19-24,37,共7页Tactical Missile Technology

摘　　要：针对双脉冲中程空空导弹多次开关机且开关机时间不确定的弹道优化问题,以发动机开关机前后为分段条件,并考虑终端位置、速度以及舵偏角、动压等过程约束,建立了多段多约束的弹道优化模型,分别以最短时间和最大末速度为性能优化指标,使用hp自适应Radau伪谱法进行求解,获得了不同末速度、不同初始和终端高度情况下的最优弹道,并根据求解结果分析了飞行条件变化对导弹弹道的影响。结果表明,在初始高度相同的情况下,导弹末速度越大,飞行时间越长;而导弹的初始高度越高,其飞行时间就越短,末速度也越大。The optimization problem of dual-pulse medium range air-to-air missiles which are able to start and turn off for several times and have uncertain time delay is researched in this paper. The segmentation of the problem is based on engine switching time. Constrains on terminal position and speed, deflection angle and dynamic pressure are taken into account. The multi-stage and multi-constrained optimization model is built, of whom the objective function is chosen to be minimum flight time and maximum terminal velocity. The simulation is based on hp-adaptive Radau pseudospectral method, and optimal trajectories in different terminal velocity and initial or terminal altitude are obtained. The result shows that in the same initial altitude, the flight time increases as the terminal velocity increases. On the other hand, the higher altitude of launch position will end up with less flight time and higher final speed.

关 键 词：双脉冲 空空导弹 Radau伪谱法 弹道优化 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]