关键词: 飞行器控制、导航技术 , 制导与控制 , 对地攻击导弹 , 末制导 , 基准弹道 , 命中点姿态约束

Abstract: 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. I by numerical simula?tion. TKe 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 mis?sile and guided bomb unit.

Key words: control and navigation technology of aerocraft , guidance and control , air-to-ground mis-sile , terminal guidance , reference trajectory , impact angle constraint