Folding tail adaptive control method for improving wind resistance of vertical take-off and landing aircraft
By constructing a nonlinear dynamic model of the variable-surface tail and implementing dual hysteresis logic control, the problem of attitude instability of vertical take-off and landing aircraft under crosswind conditions was solved, and aerodynamic performance optimization and stability improvement were achieved throughout the entire flight cycle.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- DALIAN UNIV OF TECH
- Filing Date
- 2026-04-14
- Publication Date
- 2026-07-17
AI Technical Summary
Under medium to high intensity crosswind conditions, existing control methods cannot effectively eliminate the aerodynamic load caused by the excessive physical wind-receiving area of the tail fin, leading to attitude instability and safety issues, especially the risk of mechanical structural impact overload during mode transition.
By fusing multi-source sensor information to obtain flight state parameters, a nonlinear dynamic model of the variable surface tail is constructed. A folding control law based on airspeed threshold and an active aerodynamic alignment strategy are designed. Combined with a shake-resistant deployment control law with dual closed loop and hysteresis logic, the aerodynamic performance and stability of the aircraft are optimized.
By using nonlinear dynamics models and hysteresis control laws, the impact of wind disturbances on the tail fin is reduced, the mechanical impact during mode transitions is decreased, the wind resistance and robustness of the aircraft are improved, and the overall performance of the control system is enhanced.
Smart Images
Figure CN122413675A_ABST