Nonlinear Autopilot Design for Endoatmospheric Interceptors with Dual Control Systems

摘要：

The nonlinear system model of an endoatmospheric missile whose attitude is controlled by tail fins and reaction jets is presented. By choosing the divert accelerations and rotational rates as output variables, internal dynamics of the nonlinear system are derived and are proved to be bounded under a bounded input. The blending principle of the reaction jets and tail fins is addressed to ensure the normal acceleration is mainly maintained by angle of attack or sideslip angle. An autopilot is designed by using the feedback linearization technique. Results of numerical simulation of an autopilot design example show the effectiveness of the proposed blending principle and the autopilot design.

作者: Shao Chuntao Zhou Di

作者单位: Mailbox 327,School of Astronautics,Harbin Institute of Technology,150001 Harbin,P.R.China

会议类型: 国际会议

会议名称: The 2nd International Symposium on Systems and Control in Aeronautics and Astronautics(第二届航空航天系统与控制国际会议 ISSCAA 2008)

会议地点: 深圳

会议语种:英文

页码: 838-843

在线出版日期: 2008-12-10（万方平台首次上网日期，不代表论文的发表时间）