为了满足导弹大落角攻击要求,提出一种适用于鸭/尾舵复合控制导弹的带落角约束制导控制一体化系统方法,解决了导弹末端攻击时单舵控制时的舵偏饱和问题。首先,建立了鸭/尾舵复合控制导弹一体化模型,采用滑模变结构控制方法,构建带落角约束的滑模面,并利用指数趋近律用以解决滑模抖颤问题。仿真结果表明,文中所设计的制导控制一体化方法能同时满足脫靶量和落角约束的要求。

To satisfy the attack requirements of large falling angle of missile, a guidance and control integration system method for canard/ tail vane composite control missile with falling angle constraint was proposed which could solve the rudder partial saturation problem when the missile terminal attacked and it controlled by single rudder. The integrated model of canard/tail vane composite control missile was built, the sliding mode surface with falling angle constraint was constructed by using sliding mode variable structure control method. And the exponential approach law was used to solve the chattering problem of sliding mode. The simulation results showed that the designed guidance and control integration could satisfy the requirements of miss distance and falling angle constraint at the same time.