考虑自动驾驶仪延迟的多约束末制导律

Guidance Law with Drop Angle and Field-of-View Angle Constraints Considering Autopilot Lag

设计了一种带有落角和视场角约束的末制导律。建立了带有导弹自动驾驶仪二阶动态特性的末制导模型;构造了一种新型的滑模面并结合动态面控制给出了制导律的设计方法;利用Lyapunov稳定性理论,证明了制导系统的弹目视线角和弹目视线角速率是收敛的,结合构造的障碍Lyapunov函数和滑模面的特性证明了视场角始终满足约束条件;仿真验证了制导律的有效性。

A terminal guidance law with drop angle and field-of-view constraints was proposed. The guidance model considering the second-order dynamic characteristics of the missile autopilot was established. A new sliding surface was constructed and the guidance command was given in combination with the dynamic surface control. By using the Lyapunov stability theory, it is proved that the line of sight angle and the line of sight angular rate of the guidance system are convergent. Combined with the characteristics of the barrier Lyapunov function and the sliding surface, it is proved that field-of-view angle satisfies the constraint condition. Simulation verifies the effectiveness of the guidance law.