火力与指挥控制2017，Vol.42Issue(8)：52-55,60,5.DOI:10.3969/j.issn.1002-0640.2017.08.012
导弹自动驾驶仪控制算法鲁棒性研究
Research on Robustness of Missile Autopilot Control Alogorithm
摘要
Abstract
Taking a certain type of axis symmetrical missile as the research object ,a simplified mathematical model is obtained in the case of decoupling and linearization. The state feedback H∞control missile autopilot is designed by solving linear matrix inequality (LMI), and the variable universe fuzzy PID control autopilot is designed by using fuzzy and variable universe theory . Considering the disturbance and the perturbation of aerodynamic parameters during flight, a comparative study is carried out on the control performance of the both autopilots. The simulation results show that both of them can achieve tracking of the missile guidance command effectively, especially the state feedback H∞ control missile autopilot has obvious advantages in rapidity and accuracy of the command tracking and anti-interference.关键词
线性矩阵不等式/变论域/模糊控制/自动驾驶仪/鲁棒性Key words
linear matrix inequality/variable universe/fuzzy control/autopilot/robustness分类
军事科技引用本文复制引用
屈秀敏,刘珊中,刘永斌..导弹自动驾驶仪控制算法鲁棒性研究[J].火力与指挥控制,2017,42(8):52-55,60,5.基金项目
国家自然科学基金(61203047) （61203047）
河南省教育厅自然科学基金资助项目(12A120004) （12A120004）
