一种多约束条件下的三维变结构制导律

A New Variable Structure Guidance Law of Three Dimensional with Multiple Constraints

针对现代空地导弹多约束、高精度制导的基本需求,从末段精确制导问题的三维数学模型出发,利用虚位移概念构建弹目相对运动关系,结合滑模变结构理论的基本特点,推导出一种满足制导精度、落角和入射角多约束条件的三维变结构制导律。并利用滑模理论构建非线性观测器,对未知量进行估计和预测。最后通过典型弹道的仿真,验证了本文提出的制导律的良好性能和较强的通用性。结果显示该制导律具有较强的鲁棒性和自适应能力,能较灵活地解决各约束量间的平衡关系。

In order to solve the matter of the precision guidance with multiple constraints in the modern air-to-surface missile, the three dimensional model of terminal precision guidance is set up. Then the relative motion model of missile and target is established using virtual displacement. Based on the sliding-mode variable structure control theory, a new 3D variable structure guidance law is deduced, which is satisfied with the multi-constraint conditions of precision, impact angular and incidence angular. In order to estimate and predict the unmeasured parameters, a nonlinear observer is designed. In the end, the simulation results of the characteristic trajectory is validated the effectiveness and applicability of the guidance law. Through the simulation and analysis, the robustness and adaptability of the guidance law is proved, and the flexible balance among the multiple constraints＇ parameter is showed.