带有引诱角色的有限时间协同制导方法

Finite Time Cooperative Guidance Method with a Lure Role

为实现高价值飞行器的有效突防,采用突防飞行器携带一枚防御器的协同突防方案,在突防器作为引诱角色的情况下,基于有限时间控制理论提出了一种带有拦截角约束的协同制导方法。基于飞行器相对运动学方程和一阶动力学特性,建立了带有拦截角约束的协同反拦截模型;用度量矩阵刻画系统有限时间输入输出动态品质,基于微分线性矩阵不等式给出了有限时间状态反馈控制器设计方法。数学仿真表明,该方法能够确保防御器在有限时间内以预置的拦截角有效拦截对方拦截器;在突防器进行引诱配合的情况下,协同突防方案能够大幅节省防御器需用加速度,验证了协同制导方法的有效性;同时,所提制导方法在不同拦截角度和初始发射条件下都能达到较好的控制效果,表现出较强的鲁棒性。

In order to accomplish the effective evasion for the high-value aircraft,a cooperative penetration scenario with a defender is carried by the evading aircraft. In the case that the evading aircraft acts as a lure role,a cooperative guidance method with the intercept angle constraint is proposed based on the finite time control theory. Based on the relative kinematics equation of aircrafts and the first-order dynamics,the cooperative anti-interception model with intercept angle constraint is established. The dynamic quality of the system finite time input and output is described by the measurement matrix. Based on the differential linear matrix inequality,a state feedback controller design method of finite time stability is put forward. The mathematical simulation shows that this method can ensure that the defender effectively intercepts the pursuer with the preset intercept angle in the finite time interval. When the evading aircraft cooperates with the defender for luring the pursuer,the cooperative scenario can significantly save the required acceleration for the defender,which verifies the effectiveness of cooperation. At the same time,the proposed guidance method can achieve better control effect under different intercept angles and initial launch conditions,and the strong robustness is also verified.