精确对地攻击姿态约束最优末制导设计

Optimum Terminal Guidance for Air-to-Ground Missile with Impact Angle Constraint

针对远程精确对地攻击姿态约束末制导问题,提出按照命中点姿态角需求设计基准弹道,并建立了围绕基准弹道的线性时变弹目运动方程。以弹道跟踪误差和控制能量最小为优化指标,取弹道跟踪误差加权阵与剩余飞行时间的平方成反比,求得了一种新的精确对地攻击姿态约束末制导律。制导指令由基准弹道补偿项和弹道跟踪误差项两部分组成。与文献[1]制导律的仿真对照表明,本文给出的制导律具有较小的需用过载,命中点姿态角控制精度高、脱靶量小、适用性好。研究结果对远程对地攻击导弹或制导炸弹末制导系统设计具有参考价值。

The optimum terminal guidance for long range air-to-ground missile in vertical plane with impact angle constraint was investigated. The missile reference trajectory was designed according to the impact angle requirement. Around the reference trajectory, a linear-time-variable missile-target model was established. The performance index of minimizing the tracking error and control energy was used in the design of optimum terminal guidance law, while the weighting matrices were chosen as the functions of time-to-go. The guidance law is combined by two parts such as the reference trajectory compensation term and the tracking error. The properties of miss distance, control energy requirement and impact angle error were compared with those of the guidance law in Ref. 1 by numerical simulation. The simulated results show that the proposed method is better than that in Ref. 1. The proposed method has reference value for the optimum terminal guidance design of long range air-to-ground missile and guided bomb unit.