Study on the Missile Autopilots Design Based on Robust Control Theory

摘要：

The high-performance autopilot design is studied based on robust control theory. The model of a certain characteristics point in a given airspace is regarded as a nominal model, which is made some assumptions and simplifications. The state feedback compensation is adopted to reduce the model uncertainty. Robust H∞ control/mixed sensitivity is applied to design a missile autopilot pitching stable loop. The whole process of design and simulation are made in use of MATLAB/Robust Control Toolbox. Simulation results show that the designed autopilot could control missile flight along certain trajectories in a given airspace, and also have robust stability.

关键词： autopilot mathematical model robust control uncertainty weight function

作者: Wu Xiaoyan Fan Zongchen Zhou Yanyan He Guangjun

作者单位: The Missile Institute, Air Force Engineering University, Sanyuan 713800, Shaanxi Chian

会议类型: 国际会议

会议名称: 第七届国际测试技术研讨会

会议地点: 北京

会议语种:英文

在线出版日期: 2007-08-05（万方平台首次上网日期，不代表论文的发表时间）