考虑输入受限和自动驾驶仪延迟的自适应滑模制导律  

Adaptive sliding mode guidance law with input constraints and autopilot lag

作　　者：宋俊红[1] 宋申民[1] 

机构地区：[1]哈尔滨工业大学控制理论与制导技术研究中心,哈尔滨150001

出　　处：《中国惯性技术学报》2015年第3期339-344,共6页Journal of Chinese Inertial Technology

基　　金：航空科学基金(20140177002);上海航天科技创新基金(SAST201402);国家自然科学基金创新群体项目(61021002)

摘　　要：在输入受限的情况下,为了满足导弹拦截机动目标时高精度制导的需求,首先建立了满足输入受限和考虑导弹自动驾驶仪一阶动态特性的制导模型,其把目标加速度视为未知有界的外界干扰,通过设计自适应控制估计干扰的上界来避免对干扰上界的先验要求,同时结合滑模控制,设计了一种考虑输入受限和自动驾驶仪延迟的自适应滑模制导律,并且基于Lyapunov稳定性理论证明了制导系统状态渐进收敛到零。最后,在所设计的制导律下,对目标余弦机动和阶跃机动两种情况进行了仿真,得到的脱靶量分别为0.040 m和0.036 m,拦截时间分别为6.460 s和7.833 s。仿真结果表明所设计的制导律不仅保证导弹有效击中目标,并且具有较高的制导精度。In order to realize high-precision guidance when a missile intercepts a maneuvering target under the input constraints, a guidance model under input constraints is proposed based on the first-order dynamics of missile autopilot. Regarding the target acceleration as unknown bounded external disturbance, the adaptive control is designed to estimate the upper bound of the disturbance in such a way that it is not required to be known in advance. An adaptive control is designed to estimate the upper bound of the disturbance to avoid knowing it in advance. Combined with the sliding mode control, a new adaptive sliding mode guidance law with autopilot lag and input constraints is designed. Based on the Lyapunov stability theory, it is proved that the states of guidance system asymptotically converge to zero. Then, simulations on intercepting targets with consine maneuvering and with step maneuvering are made, respectively, by the proposed guidance law, and the results show that the miss distances are 0.040 m and 0.036 m, respectively, and the interception times are 6.460 s and 7.833 s, respectively.

关 键 词：制导律 自动驾驶仪延迟 输入受限 自适应控制 滑模控制 

分 类 号：V448.133[航空宇航科学与技术—飞行器设计]