High Angle of Attack Missile Autopilot Design by Pole Placement Approach

摘要：

This paper presents the missile autopilot design for 180° heading reversal maneuver. For this purpose, angle of attack controller using pole placement approach is designed. The three autopilot gains can be computed from aerodynamic coefficients and three design parameters to satisfy some designer-chosen criteria. Design parameters are closed-loop frequency, damping ratio, and time constant, representing the characteristics of control system. To deal with nonlinear control problems in high angle of attack missile, gain scheduled technique is employed. The simulation results validate performances and capabilities of the control system.

作者: Sun-Mee Ryu Dae-Yeon Won Chang-Hun Lee Min-Jea Tahk

作者单位: Department of Aerospace Engineering,KAIST

会议类型: 国际会议

会议名称: The 3rd International Symposium on Systems and Control in Aeronautics and Astronautics(第三届航空航天系统与控制国际会议 ISSCAA 2010)

会议地点: 哈尔滨

会议语种:英文

页码: 523-527

在线出版日期: 2010-01-08（万方平台首次上网日期，不代表论文的发表时间）