Attitude–Orbit Integrated Modeling and Control for Flexible Spacecraft Based on Twistors and Fully Actuated System Approach
针对柔性航天器姿态、轨道与振动复杂耦合的控制难题，提出基于旋量的姿态轨道一体化模型和全驱动系统控制策略，可设计任意线性闭环系统，仿真验证了模型正确性和控制有效性。
The complex coupling relationship among attitude, orbit, and vibration challenges the control of flexible spacecraft. This article investigates the integrated attitude–orbit dynamical modeling and control of flexible spacecraft, which accurately describes the above complex coupling relationship to improve control performance. First, a twistor-based attitude–orbit integrated model of flexible spacecraft is established, avoiding the unitary constraint of the dual-quaternion-based model. Then, the attitude–orbit integrated control strategy based on the fully actuated system (FAS) approach is proposed for flexible spacecraft, which yields an arbitrary designable linear closed-loop system. Finally, the correctness of the dynamical model and the effectiveness and superiority of the proposed control strategy are demonstrated by two sets of simulations.