Trajectory Tracking for Quadrotors with Attitude Control on $\mathcal{S}^2 \times \mathcal{S}^1$
| Autor: | Duarte Antunes, Angela P. Schoellig, Dave Kooijman |
|---|---|
| Rok vydání: | 2019 |
| Předmět: |
Angle of rotation
FOS: Computer and information sciences 0209 industrial biotechnology 020208 electrical & electronic engineering Mathematical analysis Thrust 02 engineering and technology Rotation matrix Systems and Control (eess.SY) Coupling (probability) Electrical Engineering and Systems Science - Systems and Control Euler angles Attitude control Computer Science - Robotics symbols.namesake 020901 industrial engineering & automation Position (vector) 0202 electrical engineering electronic engineering information engineering symbols FOS: Electrical engineering electronic engineering information engineering Quaternion Robotics (cs.RO) Mathematics |
| Zdroj: | ECC |
| DOI: | 10.48550/arxiv.1906.06926 |
| Popis: | The control of a quadrotor is typically split into two subsequent problems: finding desired accelerations to control its position, and controlling its attitude and the total thrust to track these accelerations and to track a yaw angle reference. While the thrust vector, generating accelerations, and the angle of rotation about the thrust vector, determining the yaw angle, can be controlled independently, most attitude control strategies in the literature, relying on representations in terms of quaternions, rotation matrices or Euler angles, result in an unnecessary coupling between the control of the thrust vector and of the angle about this vector. This leads, for instance, to undesired position tracking errors due to yaw tracking errors. In this paper we propose to tackle the attitude control problem using an attitude representation in the Cartesian product of the 2-sphere and the 1-sphere, denoted by $\mathcal{S}^{2}\times \mathcal{S}^{1}$ . We propose a non-linear tracking control law on $\mathcal{S}^{2}\times \mathcal{S}^{1}$ that decouples the control of the thrust vector and of the angle of rotation about the thrust vector, and guarantees almost global asymptotic stability. Simulation results highlight the advantages of the proposed approach over previous approaches. |
| Databáze: | OpenAIRE |
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