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探讨了气动舵面和侧向喷流复合控制模式下拦截弹飞行系统的制导与控制.由于高空气动力不足,同传统的只装配气动舵面的拦截弹相比,为改进对于机动目标的拦截精度,将侧向喷流装置引入以增加导弹的机动能力.使用脉冲型混杂切换系统对侧向喷流导弹动力学进行描述;滑模制导律和决定侧向喷流装置开启策略的逻辑切换律被提出用于产生期望制导指令.仿真和比较证实:滑模制导律和逻辑切换律对目标机动敏感,末端脱靶量很小(<0.1 m),拦截弹动能碰撞杀伤目标.
The guidance and control of the interceptor missile flight system under the combined control of the aerodynamic rudder and the lateral jet are discussed.For the lack of high aerodynamics, in order to improve the interception of the maneuvering target, Accuracy, the lateral jet device is introduced to increase the maneuverability of the missile.The pulse jet hybrid system is used to describe the lateral jet missile dynamics, the sliding mode guidance law and the logic switching law that determines the opening strategy of the lateral jet device Was proposed to generate the desired guidance order.The simulation and comparison proved that the sliding mode guidance law and the logic switching law are sensitive to the target maneuver, the terminal miss distance is very small (<0.1 m) and the interception missile can collide with the killing target.