使用单轴磁力矩器的小卫星非线性模型预测消旋
Nonlinear Model Predictive Detumbling of Small Satellites with a Single-axis Magnetorquer
AI总结：
针对仅配备单轴磁力矩器的严重欠驱动小卫星消旋难题，本文分析其姿态控制可行性并探讨非线性模型预测等可用控制方法。
摘要：
航天器使用各种执行机构来实现姿态稳定，包括推力器、动量轮和控制力矩陀螺。然而，小卫星在尺寸、重量和成本方面受到严格限制，这使得许多执行机构选择难以承受。因此，磁力矩器通常被应用于航天器以衰减角速率。此前已有研究探讨了由于磁控制力矩依赖磁场以及所需的高磁通密度而导致的欠驱动问题。一般而言，对因星上故障而变得欠驱动的卫星进行控制，一直是文献中反复出现的主题。由于小卫星发射数量增加，对执行机构少于自由度的航天器控制方法的需求日益增长。磁力矩器已被广泛研究，用于配备动量轮的航天器的动量管理，以及自旋卫星、动量偏置卫星和双自旋卫星的章动阻尼。尽管如此，此前尚未研究过仅携带单轴磁力矩器的严重欠驱动小型航天器。本技术说明考虑仅使用单轴磁力矩器对小型航天器进行消旋。即使使用三轴磁力矩器，航天器也是欠驱动的；而在仅有单轴磁力矩器的情况下，该问题的难度要大得多。本说明考察了使用单轴磁力矩器进行航天器姿态控制的可行性以及可采用的可能控制方法。
英文摘要：
Various actuators are used in spacecraft to achieve attitude stabilization, including thrusters, momentum wheels, and control moment gyros. Small satellites, however, have stringent size, weight, and cost constraints, which makes many actuator choices prohibitive. Consequently, magnetic torquers have commonly been applied to spacecraft to attenuate angular rates. Approaches for dealing with under-actuation due to magnetic control torque's dependency on the magnetic field and required high magnetic flux densities have been previously considered. Generally speaking, control of a satellite that becomes under-actuated as a result of on-board failures has been a recurrent theme in the literature. Methods for controlling spacecraft with fewer actuators than degrees of freedom are increasingly in demand due to the increased number of small satellite launches. Magnetic torquers have been extensively investigated for momentum management of spacecraft with momentum wheels and for nutation damping of spin satellites, momentum-biased, and dual-spin satellites. Nonetheless, severely under-actuated small spacecraft that carry only a single-axis magnetic torquer have not been previously treated. This note considers the detumbling of a small spacecraft using only a single-axis magnetic torquer. Even with a three-axis magnetic torquer, the spacecraft is under-actuated, while, in the case of only a single axis magnetic torquer, the problem is considerably more demanding. Our note examines the feasibility of spacecraft attitude control with a single-axis magnetic torquer and possible control methods that can be used.
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