基于ESO的拦截机动目标带攻击角度约束制导律

为满足攻击角度约束的要求,设计了一种考虑导弹自动驾驶仪二阶动态特性的制导律。建立了考虑驾驶仪二阶动态特性的带攻击角度约束项的制导系统模型,采用二阶滑模超螺旋算法对扩张状态观测器进行改进,提出了一种超螺旋扩张状态观测器,对未知目标加速度进行估计,选取一种带攻击角度约束的非奇异快速终端滑模面,结合动态面控制,提出了一种新型制导律。该制导律能使系统状态全局有限时间收敛,补偿驾驶仪动态特性。对比仿真结果表明,所提观测器估计精度高,所提制导律能够实现视线角速率和攻击角度有限时间收敛,且具有更好的制导性能。

ESO-based Guidance Law With Impact Angle Constraintfor Maneuvering Targets

In order to meet the requirements of impact angle constraint,a guidance law considering the second-order dynamics of missile autopilot was designed. A guidance system model with impact angle constraint considering the second-order autopilot dynamics was established. The super-twisting algorithm was used to improve the extended state observer. A super-twisting extended state observer was proposed to estimate the target acceleration. A nonsingular fast terminal-sliding-surface with impact angle constraint was selected. Combined with dynamic surface control,a new guidance law was proposed. The guidance law can achieve global finite-time convergence of the system states and compensate the autopilot dynamics. The comparison of simulation results shows that the proposed observer has high estimation accuracy. The proposed guidance law can achieve finite-time convergence of line-of-sight angular rate and impact angle,and it has better guidance performance.