摘要
针对导弹在气动参数变化剧烈且控制精度要求较高的情况下,控制参数难以确定的问题,提出了采用飞行全包络动态控制的方法。文中首先通过遗传算法来求解不同飞行状态和飞行环境下的控制参数的优化解,从而得出飞行包络参数表,然后通过插值查询得出在实时飞行状态下所需控制参数,以此实现动态控制,使得导弹在不同的飞行阶段都有对应的精确控制参数。文中以某防空导弹的六自由度模型为对象进行仿真研究,结果表明了该方法的可行性及良好的控制效果。
In view of difficult determination of control parameters in case of dramatic change of aerodynamic parameters and high requirement for control accuracy,a dynamic control method with full flight envelopes was proposed. In this paper,the optimization solution of control parameters in different flight states and environment was obtained by adopting genetic algorithm,and then through interpolation query,the needed control parameters were got under real-time flight state. Therefore,the dynamic control method was implemented,and the missile’s precise control parameters in different flight moment were achieved. Based on simulation of a six-degree-of-freedom model of certain antiaircraft missile,the result shows that the method is feasible and can achieve good control effect.
出处
《弹箭与制导学报》
CSCD
北大核心
2014年第5期33-36,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
航天支撑技术基金(2011-HT-GFKD
2012-HT-GFKD)资助
关键词
遗传算法
控制系统
仿真
飞行包络
genetic algorithm
control system
simulation
flight envelope
