考虑探测效能的有限时间协同制导方法

A Finite-time Cooperative Guidance Method Considering Cooperative Detection Efficiency

针对多飞行器协同拦截机动目标问题,基于有限时间控制理论设计了一种考虑探测几何构形的协同制导方法。假设飞行器具有1阶动力学特性,根据质点相对运动方程和协同探测原理建立了考虑探测几何构形的协同拦截模型。基于微分不等式理论给出系统状态有限时间有界和输入输出有限时间稳定的充分条件,并在此基础上设计了有限时间协同制导方法。该方法用度量矩阵刻画系统状态和输出动态品质,能够同时保证制导系统状态和输出在有限时间内有界和稳定。仿真结果表明:在目标进行不同程度机动情况下,所提制导方法均能够保证视线分离角收敛到预置角度、视线角速率收敛到0rad/s且加速度不超过最大物理限制;与比例导引与最优制导方法相比,有限时间协同制导方法在探测和制导环节均具有较大优势。

For the multiple missiles intercepting a maneuvering target cooperatively,a cooperative guidance method considering a cooperative detection geometry configuration is designed based on the finite-time control theory.For the first-order dynamics of the missiles,a cooperative interception model with detection geometry configuration is established according to the relative motion equations of particles and the principle of cooperative detection.The sufficient conditions for the finite time boundedness of system state and the finite time stability of system input and output are given based on the differential inequality theory.And on this basis,a finite time cooperative guidance method is designed.The proposed method uses the measurement matrix to characterize the dynamic quality of system state and output,and can ensure that the state and output of guidance system are bounded and stable within a finite time interval.The simulated results show that the proposed guidance method can ensure that the LOS separation angle converges to the preset angle,the LOS angular rate converges to zero,and the acceleration does not exceed the maximum physical limit when a target is maneuvering.Compared with proportional navigation and optimal guidance law,the proposed method has the advantages in cooperative detection and guidance.