多约束下考虑控制饱和的自适应末制导方法

Adaptive Terminal Guidance with Control Saturation under Multiple Constraints

对地攻击飞行器在末制导过程中需满足导引头视场、攻角、落角等多种约束。针对这一问题提出一种多约束下的制导方法。将多约束下的制导问题转化为具有控制饱和的线性系统的镇定问题。针对该问题,利用基于参量Lyapunov方程的低增益反馈设计方法,推导带低增益参数的纵向制导律。借助Lambert W函数,研究闭环系统状态收敛特性与低增益参数的关系,给出低增益参数的自适应整定方法。通过该方法在线调整参数,使各约束条件得到满足。通过数值仿真对提出的制导方法进行校验。仿真结果表明,提出的制导方法满足约束条件且获得较高的制导精度。

The seeker＇s field-of-view, attack angle, and impact angle are constrained in terminal guidance against a ground target. A guidance method is presented in the consideration of the above constraints. The guidance problem is transformed to a stabilization problem of a linear system subject to control saturation. A longitudinal guidance law with a low-gain parameter is derived by using the parametric Lyapunov equation-based low-gain feedback design. The relationship between the low-gain parameter and the convergence of the closed-loop system is investigated by using the Lambert W function. An adaptive tuning method is proposed to adjust the low-gain parameter. All the constraints can be observed by tuning the parameter online. The proposed guidance method is demonstrated by numerical simulation. Simulation results suggest that the proposed method satisfies all the constraints and achieves high guidance accuracy.