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Dynamics and control of spacecraft with a large misaligned rotational component

机译：旋转分量大的航天器的动力学和控制

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摘要

A new type of earth observation mission using a spacecraft with rotational payload is introduced in this paper. The kinematic and dynamic equations for the nadir-aligned attitude tracking problem are derived in the presence of a misaligned rotational payload. A quaternion-based feedback control law is proposed and its stability is analyzed using the Lyapunov direct method. Comparisons are made between the simulation results of the proposed control law and that of a conventional PD feedback control law. The analytical solution of the spacecraft's residue angular momentum is obtained. Monte Carlo analyses are employed to demonstrate the angular rate accuracy of the system and to study the effects caused by the knowledge error of parallel misalignment. Simulation results show that the angular rate accuracy improves greatly by the proposed control law. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：介绍了一种新型的利用旋转有效载荷的航天器进行的地球观测任务。在存在未对准的旋转有效载荷的情况下，得出了天底对准的姿态跟踪问题的运动方程和动力学方程。提出了基于四元数的反馈控制律，并使用Lyapunov直接法分析了其稳定性。比较了所提出的控制律和传统的PD反馈控制律的仿真结果。得到了航天器残余角动量的解析解。蒙特卡洛分析用于证明系统的角速率精度，并研究由平行未对准的知识误差引起的影响。仿真结果表明，该控制律大大提高了角速率精度。 （C）2019 Elsevier Masson SAS。版权所有。

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