Advances in aircraft and spacecraft science

  • 제6권5호
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  • Pages.371-389
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  • 2019
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  • 2287-528X(pISSN)
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  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
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Robust H∞control applied on a fixed wing unmanned aerial vehicle

  • Uyulan, Caglar (Department of Mechatronics Engineering, Bulent Ecevit University) ;
  • Yavuz, Mustafa Tolga (Department of Aeronautics and Astronautics, Istanbul Technical University)
  • 투고 : 2018.08.03
  • 심사 : 2019.04.05
  • 발행 : 2019.09.25
⟨ 이전 논문 다음 논문 ⟩

초록

The implementation of a robust $H_{\infty}$ Control, which is numerically efficient for uncertain nonlinear dynamics, on longitudinal and lateral autopilots is realised for a quarter scale Piper J3-Cub model accepted as an unmanned aerial vehicle (UAV) under the condition of sensor noise and disturbance effects. The stability and control coefficients of the UAV are evaluated through XFLR5 software, which utilises a vortex lattice method at a predefined flight condition. After that, the longitudinal trim point is computed, and the linearization process is performed at this trim point. The "${\mu}$-Synthesis"-based robust $H_{\infty}$ control algorithm for roll, pitch and yaw displacement autopilots are developed for both longitudinal and lateral linearised nonlinear dynamics. Controller performances, closed-loop frequency responses, nominal and perturbed system responses are obtained under the conditions of disturbance and sensor noise. The simulation results indicate that the proposed control scheme achieves robust performance and guarantees stability under exogenous disturbance and measurement noise effects and model uncertainty.

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참고문헌

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