A guidance problem for impact angle control applicable to a missile equipped with a passive seeker is investigated. The proposed guidance law based on the sliding mode control consists of the proportional navigation guidance term with a varying navigation constant and the additional biased term which is a function of the novel sliding surface. The guidance law directly uses the impact angle error but does not require any range information to be estimated by the additional filter loop of the passive seeker. The asymmetric limit of the passive seeker’s field-of-view is also taken into account, which is not violated by introducing a continuous switching function. The finite time convergence properties are analyzed, and nonlinear simulations are performed to investigate the effectiveness of the proposed guidance law.

中文翻译：

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被动寻的导弹直接撞击角控制制导

研究了一种适用于装有被动导引头的导弹的撞击角控制制导问题。所提出的基于滑模控制的制导律由具有变化导航常数的比例导航制导项和作为新型滑动面函数的附加偏置项组成。制导法则直接使用撞击角误差，但不需要任何距离信息由无源导引头的附加滤波器环路估计。还考虑了被动导引头视场的不对称限制，引入连续切换功能不会违反这一限制。分析了有限时间收敛特性，并进行了非线性仿真以研究所提出的制导律的有效性。