带热流密度限制的推力可控导弹三维制导律

传统三维制导律设计通常将三维空间分成垂直面和水平面分别考虑，容易导致耦合信息的缺失，同时没有考虑导弹红外导引头对导弹头部热流密度的限制和终端速度约束。针对以上问题，基于具有推力可控能力的导弹，在视线旋转坐标系的视线瞬时旋转平面内进行制导律设计。该制导律包含根据运动伪装理论设计的一种新的满足运动伪装条件的视线法方向加速度指令，以及通过变系数加权法综合考虑导引头热流密度限制及终端速度约束的视线方向加速度指令。数值仿真结果表明了存在导引头初始对准误差时，该制导律在满足红外导引头对导弹头部的热流密度限制、终端速度约束以及轴向过载限制下对高速机动目标制导性能良好，视线角速率可控制在3（）/s以下，具有一定的工程应用价值。

Three-dimensional guidance law for missile of adjustable thrust with heat flux limit

The traditional three-dimensional guidance law generally divides three-dimensional space into vertical plane and horizontal plane respectively, which may lead to the lack of coupling information. It also doesn't take heat flux of infrared seeker and constraint of terminal velocity into account. To solve this problem, a guidance law based on the missile of adjustable thrust was proposed in the instantaneous rotary line-of-sight plane of rotary line-of-sight frame. The acceleration instruction in the direction of perpendicular to line-of-sight was designed to satisfy the criterion of motion camouflage strategy. Meanwhile, an overload instruction in the direction of line-of-sight was built with variable weighted change rate of heat flux limit and ideal overload which can satisfy the constraint of terminal velocity. Simulation results demonstrate that the designed guidance law has a good performance with the heat flux limit of infrared seeker, constraint of terminal velocity and available axial overload limit when attacking the high maneuvering target and initial misalignments of infrared seeker exists. The rate of line-of-sight is under 3 ()/s, so it has certain engineering application value.