Volume 49 Issue 9
Oct.  2023
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WANG L N,LIU Z B,YUAN J B,et al. Adaptive fault diagnosis and estimation for quadrotor UAV[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(9):2395-2405 (in Chinese) doi: 10.13700/j.bh.1001-5965.2021.0656
Citation: WANG L N,LIU Z B,YUAN J B,et al. Adaptive fault diagnosis and estimation for quadrotor UAV[J]. Journal of Beijing University of Aeronautics and Astronautics,2023,49(9):2395-2405 (in Chinese) doi: 10.13700/j.bh.1001-5965.2021.0656

Adaptive fault diagnosis and estimation for quadrotor UAV

doi: 10.13700/j.bh.1001-5965.2021.0656
Funds:  National Natural Science Foundation of China (61672430); China Scholarship Fund International Cooperation Training Program for Innovative Talents (201906290246);Aeronautical Science Foundation of China (ASFC-2018ZC53026); Key R & D Program of Shaanxi Province (2019ZDLGY14-02-010); Shenzhen Fundamental Research Program (JCYJ20190806152203506); Shenzhen Basic Research Funding Project (GXWD202012311 65807008, 20200830220334001); Beijing Institute of Space Systems Engineering (JSZL2020203B004)
More Information
  • Corresponding author: E-mail:lena@mail.nwpu.edu.cn
  • Received Date: 02 Nov 2021
  • Accepted Date: 13 Feb 2022
  • Publish Date: 18 Mar 2022
  • A fault detection and estimation(FDA) method based on adaptive technology and observer is designed for common actuator faults of quadrotor unmanned aerial vehicle. In the stage of fault detection, the nonlinear diagnostic observer is designed, and the threshold value is derived by analytic function to ensure the robustness of the proposed detection method. Moreover, the designed observer and residual evaluation function are proved. In the stage of fault estimation, an adaptive law based on switching ρ-correction is proposed to accurately estimate the detected faults. This scheme can not only simultaneously estimate the system state and residual signal, but also estimate the characteristics and magnitude of unknown faults. The design parameters are calculated by linear matrix inequality method. The simulation results are verified in two fault scenarios, and the validity of the proposed method is discussed in four cases. The experimental results show the effectiveness of the proposed method by using the hardware-in-loop simulation of quadrotor unmanned aerial vehicle.

     

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