基于三维(3D)空间坐标系下目标-导弹相对运动方程,考虑导弹自动驾驶仪的二阶动态特性,应用动态面控制方法设计了一种新的三维空间导引律。在设计过程中,通过引入一阶低通滤波器,使得导引律的最终表达式中不含有视线角速率的高阶导数,更易于实际应用。该导引律有效地克服了导弹控制系统的动态延迟对制导精度的影响。将该导引律与未考虑导弹自动驾驶仪动态特性的自适应滑模导引(ASMG)律和考虑导弹自动驾驶仪一阶动态特性的三维非线性导引律相比较,对目标非机动、阶跃机动和正弦机动3种情况进行仿真。仿真结果表明,在目标机动加速度快速变化,而且导弹自动驾驶仪存在较大滞后的情况下,该导引律具有更高的制导精度。
A new three-dimensional (3D) guidance law is designed using the dynamic surface control method in this paper which is based on the target-missile dynamics in 3D coordinates and the second-order dynamics of the missile autopilot. Certain first-order low-pass filters are introduced into the designing process to avoid the occurrence of high-order derivatives of the line of sight angular rate in the expression of the guidance law, which makes it easy to implement in practical applications. The proposed guidance law is effective in compensating for the adverse influence of autopilot lag on guidance accuracy. In simulations of intercepting non maneuvering targets, targets with step acceleration, and targets with sinusoidal acceleration respectively, the guidance law is compared with the adaptive sliding mode guidance (ASMG) law, which is designed without accounting for the dynamics of the missile autopilot, and the 3D nonlinear guidance law, which is designed accounting for the first-order dynamics of missile autopilot. Simulation results show that the guidance law still ensures an accurate guidance result, even if the target escapes in a great and fast maneuver and the autopilot has a relatively large lag.
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