06.1 - Flight Dynamics and Control (Control & Modelling)
PRELIMINARY VIRTUAL FLIGHT VALIDATION OF A QUAD TILT ROTOR UAV IN WIND TUNNEL
D.-N. Liu¹, W.-K. Wang¹, B.-D. Zhao¹, X.-Z. Hu¹, B.-W. Nie¹; ¹China Aerodynamics Research and Development Center, China
Flight dynamics and control law of a quad tilt rotor UAV are formulated for helicopter, transition and fixed-wing modes using Linear Parameter Varying method. The wind tunnel virtual flight test in which the flight control system is integrated validates the control law performance satisfying the requirements of attitude stabilization control in different flight modes during transition.