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

Yang Tingting, Li Aijun

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

1 Scopus citations

Abstract

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.

Original languageEnglish
Title of host publication2014 13th International Conference on Control Automation Robotics and Vision, ICARCV 2014
PublisherInstitute of Electrical and Electronics Engineers Inc.
Pages147-150
Number of pages4
ISBN (Electronic)9781479951994
DOIs
StatePublished - 2014
Event2014 13th International Conference on Control Automation Robotics and Vision, ICARCV 2014 - Singapore, Singapore
Duration: 10 Dec 201412 Dec 2014

Publication series

Name2014 13th International Conference on Control Automation Robotics and Vision, ICARCV 2014

Conference

Conference2014 13th International Conference on Control Automation Robotics and Vision, ICARCV 2014
Country/TerritorySingapore
CitySingapore
Period10/12/1412/12/14

Keywords

  • flying wing aircraft
  • LI adaptive control
  • reconfiguration control
  • sliding mode
  • state observer

Fingerprint

Dive into the research topics of 'Flying wing aircraft sliding mode LI adaptive reconfiguration flight control law design'. Together they form a unique fingerprint.

Cite this