Robust Autopilot Design for Missile With Alterable Sweep Wings

摘要：

For the case of attitude control technology problem of missile with alterable sweep wings, a new kind of autopilot control law with robustness is proposed by adopting Hoo control theory. The morphing wings are bird-like wings that have the ability of adapting to obtain better flight performance in the different flight regimes. For the missile with alterable sweep wings, the nonlinear dynamic model was built according to the case of changing wings, based on the multi-rigid body dynamics model method. Consequently, using the method of linearizing dynamic model, the linear mathematic model of autopilot is established by choosing the error between missiles normal acceleration and commanded normal acceleration as the control state variable. A robust autopilot control law is obtained by utilizing robust Hoo control method. Finally an illustrative example is given to show that proposed autopilot control law is robust and suitable to the missile with alterable sweep wings in the case of the different aerodynamic parameters, and at the same time the body of missile is stable.

关键词： nonlinear control system robustness autopolit stability

作者: Guo Jian-guo Zhou Jun Zhang Tian-yi

作者单位: Institute of Precision Guidance and Control Northwestern Polytechnical University Xi an Shanxi Province, China

会议类型: 国际会议

会议名称: 2010 Second Asia-Pacific Conference on Information Processing(2010年第二届亚太地区信息处理国际会议 APCIP 2010)

会议地点: 南昌

会议语种:英文

页码: 162-165

在线出版日期: 2010-09-17（万方平台首次上网日期，不代表论文的发表时间）