In this paper, the rigid spacecraft attitude tracking control problem is investigated. Firstly, the spacecraft attitude dynamics model is converted into a fully-actuated (FA) system model. Then, a direct parametric approach for spacecraft attitude tracking control is proposed in the sense of FA system. At the same time, the validity of the proposed control algorithm is verified by numerical simulation example, and physical experiments are designed to illustrate the practicability of the algorithm.
Fully-Actuated System Approach in Attitude Tracking Control for Spacecraft
19.11.2022
459666 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch