摘要
针对导弹倾彻攻击时对弹着角控制的要求,研究了带末端落角约束的反演变结构控制律。仿真结果表明,该控制律能满足导弹在攻击固定或低速运动目标时对脱靶量和弹着角的双重要求,并具有一定的鲁棒性。
According to requirement that the missile terminal angle should be controlled, the variable structure guidance law with impact angle wais studied based on the inverse control theory. Simulation results show that the guidance law can meet the requirements of both precision and angle constraint when the missile attacks a fixed or low speed target, and shows a good robustness.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第4期47-50,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
反演
变结构
落角约束
制导律
inversion
variable structure
terminal angle constraint
guidance law
