基于θ-D方法带落角约束的三维末制导律设计

θ-D approach-based 3-dimensional terminal guidance law with impact angle constraint

基于θ-D次优控制方法设计了一种满足落角约束的三维末制导律。对于采用倾斜转弯(BTT)控制方式的高超声速滑翔飞行器,其俯仰、偏航通道存在强耦合关系,基于双通道解耦的制导律设计方法不再适用。针对这一问题,首先建立了飞行器和目标的三维相对运动方程,通过重新定义状态变量,基于θ-D方法设计了一种带落角约束的三维末制导律。所设计的制导律不需要进行通道解耦,制导精度高,计算量小。仿真结果表明了该制导律的可行性和良好性能。

A θ-D approach-based 3-dimensional （3D） terminal guidance law with impact angle constraint is proposed for the hypersonic glide vehicle （HGV）. Considering the motion characteristics of the HGV and requirement of impact angle, the kinematical equations of the guidance problem are formulated in 3 D space. By redefining the state variables and adopting the θ-D suboptimal approach, a closed-form guid- ance law with impact angle constraint is obtained without channel decoupling. Furthermore, the guidance law doesn＇t require excessive online computations. The simulation results demonstrate that the effective- ness and efficiency of the proposed guidance law.