Aerodynamics-Aware Design and Analysis of Controllers for Tailsitter Vehicles

Tailsitter transitioning unmanned aerial systems (t-UAS) are vehicles that, through rigid body rotation, are capable of operating in both vertical takeoff and landing (VTOL) and fixed-wing flight regimes. The typical approach for control design for tailsitter t-UAS considers the aerodynamics of the...

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Bibliographic Details
Published in:IEEE/ASME transactions on mechatronics 2024-08, Vol.29 (4), p.3100-3108
Main Authors: McIntosh, Kristoff, Smith, Jayden Marvin, Mishra, Sandipan
Format: Article
Language:English
Subjects:
Aerodynamic forces
Aerodynamic stability
Aerodynamics
Aerospace control
Attitude control
Attitude stability
Control systems design
Controllers
Design analysis
drones
Feedback linearization
Feedforward control
Flight
Mathematical models
Mission planning
nonlinear control
Performance degradation
Rigid structures
Rotating bodies
Rotors
Thermal stability
Trajectory
Transition flight
Uncertainty analysis
Unmanned aerial vehicles
Vehicle dynamics
Vertical flight
Vertical takeoff
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Summary:Tailsitter transitioning unmanned aerial systems (t-UAS) are vehicles that, through rigid body rotation, are capable of operating in both vertical takeoff and landing (VTOL) and fixed-wing flight regimes. The typical approach for control design for tailsitter t-UAS considers the aerodynamics of the wings as a disturbance to either be avoided or compensated for, specifically during the pure VTOL and transition flight regimes. This can result in overly conservative controllers or otherwise degraded tracking performance. To address this, we present a unified design and analysis approach for a controller that explicitly accounts for the effect of wing aerodynamics for tailsitter t-UAS operating in the transition flight regime. The overall control architecture uses feedback linearization with nested control loops, with position controlled in the outer-loop and attitude controlled in the inner loop. The outer loop uses feedforward knowledge of the aerodynamic forces from the mission planning stage, whereas the inner loop is designed assuming that moments generated by the aerodynamic forces are negligible. We derive analytical conditions that guarantee stability of the outer and inner loop controllers in the presence of bounded uncertainty in the aerodynamic forces and moments. We then provide performance bounds for both the outer and inner loop in the presence of these unmodeled or uncertain aerodynamic forces and moments. Finally, we use a high fidelity simulation of a quadrotor biplane tailsitter to illustrate the stability result and quantify controller performance statistically.
ISSN:1083-4435
1941-014X
DOI:10.1109/TMECH.2024.3402621