Trajectory control and dynamic modeling of a tailless flapping-wing robot

Trajectory control and dynamic modeling of a tailless flapping-wing robot

Kelbling, Jelle (TU Delft Mechanical, Maritime and Materials Engineering; TU Delft Delft Center for Systems and Control; TU Delft Biomechanical Engineering)

Steur, E. (mentor)
Seth, A. (mentor)
van den Boom, A.J.J. (graduation committee)
Moore, J.K. (graduation committee)

Delft University of Technology

2020-09-24

The DelFly Nimble is a type of tailless flapping-wing micro air vehicles (FWMAVs) that has received an increasing amount of attention. FWMAVs show efficient and agile flight possibilities at small scale. The aerodynamics and dynamics of these flapping vehicles are challenging and not fully understood. In this work, a strategy to implement a 3D dynamic model and a trajectory control algorithm is proposed for the DelFly Nimble by the use of a quasi-steady state framework. The design of a suitable tracking control algorithm is the essence of this task. A globally defined smooth nonlinear geometric framework of the flapping-wing vehicle’s rigid body dynamics is introduced as a basis for the analysis. This grants an unambiguous coordinate-free dynamic model in which problem of singularities are avoided. The Nimble has four inputs used to control the six translational and rotational degrees of freedom. A nonlinear tracking controller is chosen on the special Euclidean group 푆퐸(3) for the underactuated aerial vehicle, where position and yaw trajectory tracking are achieved. The full system is classified into the coupled attitude and position subsystems. Using the Lyapunov Stability theorem, the nonlinear controller is shown to achieve almost global asymptotic tracking of the attitude error dynamics of the Nimble and almost global asymptotic tracking of the position error dynamics of the center of mass of the Nimble, enabling sufficient tracking of aggressive maneuvers. Finally, the dynamic model and the controller are examined with numeric simulations. From the results can be concluded that the nonlinear control design allows for aggressive aerobatic maneuvers while maintaining stability of the closed-loop system, provided that the control inputs and damping forces remain moderate.

Autonomous vehicles
Nonlinear control systems
Lie algebra
Flapping flight
Flapping wings
Micro air vehicles
Robotics
Trajectory tracking
Geometric Control

http://resolver.tudelft.nl/uuid:b164a5d7-92c6-47d0-8fa0-5f3667b6d012

Student theses

master thesis

© 2020 Jelle Kelbling