Flying wing aircraft sliding mode LI adaptive reconfiguration flight control law design

Yang Tingting, Li Aijun

科研成果: 书/报告/会议事项章节会议稿件同行评审

1 引用 (Scopus)

摘要

Flying wing aircraft reconfiguration flight control law design method based on the LI adaptive control and sliding mode observer is proposed in this paper. In the condition of no failure information, the LI adaptation law and control law are used to reconfiguration actuator failures. For high gain question, low-pass filter is used to restrain the high frequency oscillation and eliminate the high frequency control signal. For LI adaptive reconfiguration control system, the asymptotical control stability is proved. In order to decrease the control error caused by reconfiguration error and airplane model uncertainty, the sliding mode observer is designed and used to generate the compensating signal. The simulation results show that the flying wing aircraft has good control performance in the condition of actuator surface failure.

源语言英语
主期刊名2014 13th International Conference on Control Automation Robotics and Vision, ICARCV 2014
出版商Institute of Electrical and Electronics Engineers Inc.
147-150
页数4
ISBN(电子版)9781479951994
DOI
出版状态已出版 - 2014
活动2014 13th International Conference on Control Automation Robotics and Vision, ICARCV 2014 - Singapore, 新加坡
期限: 10 12月 201412 12月 2014

出版系列

姓名2014 13th International Conference on Control Automation Robotics and Vision, ICARCV 2014

会议

会议2014 13th International Conference on Control Automation Robotics and Vision, ICARCV 2014
国家/地区新加坡
Singapore
时期10/12/1412/12/14

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