基于相对速度偏角的舰空导弹三维制导律设计

Design of Three-Dimensional Guidance Law Based on Relative Velocity Deflection Angle for Ship-Air Missile

针对舰空导弹拦截掠海飞行目标问题,考虑到目标具有强机动性和导引头对低空海面目标的视线角速度量测噪声,以及末制导在三维空间中进行,在建立空间导弹拦截目标相对运动模型基础上,选择空间导弹和目标的相对速度偏角作为零化目标,设计了一种具有强鲁棒性的基于零化相对速度偏角的空间变结构末制导律,给出了导引指令信息解算模型,仿真结果不仅验证了解算模型的正确性,还表明了在对抗目标大机动和低空目标视线角速度量测噪声等方面,所设计导引律比传统的空间末制导律具有更强的鲁棒性.

Aiming at the ship-air missile intercepting the low target, the three-dimensional relative motion between missile and target was established. The high maneuverability of the target and the measurement noise of seeker measuring line of sight（LOS） angular rate were considered,and it was also considered that terminal guidance should be carried out in three-dimensional space. The relative motion model of missile intercepting target was constructed, and the relative-velocity deflection-angle was chosen as the purpose to be zeroed. A variable-structure three-dimensional terminal guidance with strong robustness was designed based on the theory of variable structure, and the model of the guidance instruction solution was presented. The simulation result not only verifies the accuracy of solution model, and it also shows that the robustness of the designed three-dimensional variable-structure terminal guidance law is much better than that of the traditional three-dimensional terminal guidance law.