Controle de atitude por realimentação de quatérnios aplicado a um cubesat-3u

Abstract

The attitude control of a spacecraft has been subject of great relevance in recent years, presenting increasingly restrictive mission requirements, for example: precision points control; rapid multi target acquisition; and tracking capabilities, which are indispensable requirements. This work aims to develop a quaternion feedback controller for spacecraft eigenaxis rotational rest-to-rest maneuver. The Euler’s eigenaxis rotation that provides the shortest angular path between two orientations. The control law basically consists of the feedback of error quaternions and body rates. The obtained results show that large-angle, rest-torest maneuver about the Euler’s eigenaxis can be simply achieved by a proper selection of feedback gain matrices of the quaternion feedback controller. For the implementation of the controller, a set of reaction wheels in pyramid configuration was considered as an actuator. In addition, white Gaussian noise was injected as an external disturbance, associated with the reaction wheels.