机动目标拦截含攻击角约束的新型滑模制导律

A Novel Sliding Mode Guidance Law with Impact Angle Constraint for Maneuvering Target Interception

针对导弹带有攻击角约束的机动目标拦截问题,结合积分滑模和全局滑模控制方法的优点,设计了一种全新的导弹滑模制导律(SMGL)。在纵向平面内建立考虑攻击角约束的弹目相对运动方程。采用一种新的非线性饱和函数来构造积分滑模面中的积分项,提出了一种新型的非线性全局积分滑模控制方法,解决了传统积分滑模控制中系统暂态性能恶化的问题,降低了系统的稳态误差,保证导弹在有限时间内以更理想的攻击角命中目标,同时使导弹在整个拦截过程中具有很强的鲁棒性。采用动态面控制方法设计了考虑攻击角约束和自动驾驶仪动态特性的导弹全局非线性积分SMGL,基于Lyapunov稳定性准则证明了闭环系统所有状态最终一致有界。与传统线性积分SMGL和偏置比例导引律进行仿真对比,仿真结果验证了全局非线性积分SMGL的有效性和优越性。

A novel missile sliding mode guidance law （SMGL） in which a missile intercepts maneuvering target is proposed, which is based on a combination of the advantages of integral sliding mode control and global sliding mode control. The relative motion equations of missile and target, in which the impact an- gle constraints are considered, are established within the perpendicular plane. A new nonlinear saturation function is adopted to construct an integral term in global integral sliding mode surface, and then an im- proved nonlinear global integral sliding mode control technique is presented, which solves the problem a- bout system transient performance deterioration and decreases the steady state errors. It is obvious that the designed guidance law enables the missile to hit target at a desirable impact angle in finite time, and the missile to be of strong robustness during the whole interception. The missile global nonlinear integral SMGL in which the autopilot dynamics and impact angle constraints are considered is investigated by adopting dynamic surface control. It is demonstrated that all states in the closed loop system are ultimately bounded on the account of Lyapunov stability theorem. The simulation results verify the effectiveness and superiority of global nonlinear integral SMGL.