考虑自动驾驶仪二阶动态与输入受限的制导律设计  

Guidance law with second-order dynamics of autopilot and acceleration saturation

作　　者：王立晶[1] 金伟志[2] 孙经广 WANG Lijing1,JIN Weizhi2,SUN Jingguang3(1. School of Mechanical and Electrical Engineering, Heilongjiang University, Harbin 150080, China; 2. Harbin Power Bureau, Harbin 150046, China; 3. School of Astronautics, Harbin Institute of Technology, Harbin 150001, China)

机构地区：[1]黑龙江大学机电工程学院,哈尔滨150080 [2]哈尔滨电业局,哈尔滨150046 [3]哈尔滨工业大学航天学院,哈尔滨150001

出　　处：《中国惯性技术学报》2018年第4期511-517,共7页Journal of Chinese Inertial Technology

基　　金：国家自然科学基金重点项目(61333003);航空科学基金(20140177002);哈尔滨市科技局项目(2017RAQXJ133)

摘　　要：在输入受限情形下,为了提高导弹拦截机动目标的拦截概率和毁伤效果,首先,建立了同时考虑攻击角约束、输入受限和导弹自动驾驶仪二阶动态特性的制导系统模型。其次,基于动态面技术、低通滤波器和自适应技术,设计了满足攻击角约束、输入受限和自动驾驶动态特性的自适应动态面制导律,通过引入辅助系统和新型自适应算法,不仅满足执行器物理受限的要求,同时也保证了自适应参数在系统动态过程中的有界性。最后,利用李雅普诺夫理论对整个闭环系统的稳定性给出了严格的理论证明,仿真获得的脱靶量和拦截时间分别为0.831 m和16.375 s,仿真结果表明所提出制导策略的有效性。For the interception of the maneuvering targets in case of considering input constraint, a threedimensional guidance system model with impact angle constraint, input constraint and second-order dynamics of missile autopilot is established to improve the intercept probability and damage effect of the missile. Then, an adaptive dynamic surface guidance strategy with impact angle constraints, autopilot lag and input constraints is designed based on the dynamic surface method and low-pass filter, which can satisfy the physically constrained of the actuator by introducing the auxiliary system and guarantee the boundedness of the adaptive parameters with a new adaptive algorithm in the process of system dynamics. Finally, the closed-loop stability under the proposed guidance scheme is analyzed by applying the Lyapunov-based approach, and the results show that the miss distances and interception times are 0.831 m and 16.375 s, respectively. The numerical simulations are demonstrated, which further confirm the effectiveness of the proposed guidance law.

关 键 词：制导律 输入受限 自动驾驶仪二阶动态特性 动态面控制 

分 类 号：V448.234[航空宇航科学与技术—飞行器设计]