Volume 34 Issue 10
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WANG Zian, XU Jinfa. Longitudinal flight characteristics analysis and control design for hybrid VTOL UAV in accelerative transition[J]. Journal of Aerospace Power, 2019, 34(10): 2177-2190. doi: 10.13224/j.cnki.jasp.2019.10.011
Citation: WANG Zian, XU Jinfa. Longitudinal flight characteristics analysis and control design for hybrid VTOL UAV in accelerative transition[J]. Journal of Aerospace Power, 2019, 34(10): 2177-2190. doi: 10.13224/j.cnki.jasp.2019.10.011
shu

Longitudinal flight characteristics analysis and control design for hybrid VTOL UAV in accelerative transition

doi: 10.13224/j.cnki.jasp.2019.10.011
  • 1.

    College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

  • 2.

    National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

  • Received Date: 2019-02-17
  • Publish Date: 2019-10-28
    Abstract
  • A comprehensive aerodynamic/flight-control problem was studied on a high-cost hybrid vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) in the accelerative stage from hovering to cruising. A computational model of the rotor under oblique inflow was established based on the blade-element momentum theory (BEMT), and its accuracy was verified by comparison with the CFD calculation model. It was analyzed that the rotor system caused the aerodynamic focus of the aircraft to move forward, resulting in static instability effect, and its center should be placed after the center of gravity of the aircraft. By analyzing acceleration features and the control input margin under different acceleration strategies, the fixed -5 degree pitch angle and fixed throttle acceleration strategy were determined. Considering the control input redundancy and the different response of the actuator, the allocation criterion of frequency domain was adopted to realize static allocation. Considering the modeling error, the L1 adaptive attitude control framework was designed to achieve dynamic control stabilization, and the deflection simulation was used to verify its robustness. Flight test verified the effectiveness of the modeling method, acceleration strategy, and control law framework.

     

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