Attitude control of Low Earth Orbit satellites by reaction wheels and magnetic torquers

Avanzini G.; de Angelis E. L.; Giulietti F.; Serrano N.

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Attitude control of Low Earth Orbit satellites by reaction wheels and magnetic torquers

机译：反应轮和磁性扭转器的低地轨道卫星的姿态控制

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The purpose of this paper is the design and the performance analysis of a control technique that allows simultaneous attitude control and angular momentum management for a Low Earth Orbit satellite equipped with a set of three magnetic actuators and three reaction wheels. A Proof of global asymptotic stability is derived for a control law driving a rigid spacecraft towards a prescribed, yet generic attitude fixed in the orbit frame. An analytical technique allowing for control gain selection is also proposed, which provides optimal convergence performance for the proposed controller, as demonstrated by means of Monte Carlo simulations. Robustness to external disturbances is finally evaluated within a realistic implementation scenario.

机译：本文的目的是对控制技术的设计和性能分析，其允许具有配备有一组三个磁致电致动器和三个反应轮的低地轨道卫星的同时姿态控制和角动能管理。导出全局渐近稳定性的证据，用于控制法朝着在轨道框架中固定的规定的但通用姿态朝向规定的且普遍的姿态。还提出了一种分析技术，允许控制增益选择，为所提出的控制器提供最佳收敛性能，如蒙特卡罗模拟所示。最终在现实的实施方案中最终评估对外部干扰的稳健性。

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来源
《Acta astronautica》 |2019年第7期|625-634|共10页
作者
Avanzini G.; de Angelis E. L.; Giulietti F.; Serrano N.;
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作者单位

Univ Salento Dept Engn Innovat DII Complesso Ecotekne Corpo O Via Per Monteroni I-73100 Lecce Italy;

Univ Bologna DIN Via Fontanelle 40 I-47121 Forli Italy;

Univ Bologna DIN Via Fontanelle 40 I-47121 Forli Italy;

Deimos Imaging Calle Francia 9 Puertollano 13500 Spain;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
中图分类
关键词
Spacecraft attitude control; Magnetic control; Reaction wheels; Angular momentum management;

机译：航天器姿态控制;磁控制;反应轮;角动量管理;

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专利

1. Attitude control of Low Earth Orbit satellites by reaction wheels and magnetic torquers [J] . Avanzini G., de Angelis E. L., Giulietti F., Acta astronautica . 2019,第JULa期

机译：通过反作用轮和电磁转矩控制低地球轨道卫星的姿态
2. Design and analysis of attitude control algorithm for low earth orbiting satellite with magnetic torquer concepts using nonlinear unscented Kalman filter [J] . M. Raja, Dr. Ugur Guven, Dr. Om Prakash International Journal of Engineering & Technology . 2020,第1期

机译：使用非线性无限卡尔曼滤波器用磁性彩色扭矩概念的低地轨道轨道姿态控制算法的设计与分析
3. Three-axis attitude control by two-step rotations using only magnetic torquers in a low Earth orbit near the magnetic equator [J] . Inamori Takaya, Otsuki Kensuke, Sugawara Yoshiki, Acta astronautica . 2016,第novaadeca期

机译：仅在磁赤道附近的低地球轨道上使用电磁转矩器通过两步旋转进行三轴姿态控制
4. Attitude control of low-orbit micro-satellite with active magnetic torque and aerodynamic torque [C] . Peng Wang, Wei Zheng, Hongbo Zhang, The 3rd International Symposium on Systems and Control in Aeronautics and Astronautics . 2010

机译：具有主动磁转矩和气动转矩的低轨道微卫星姿态控制
5. Hybrid magnetic attitude controller for low earth orbit satellites using the time-varying Linear Quadratic Regulator. [D] . Seth, Nitin. 2009

机译：使用时变线性二次调节器的用于低地球轨道卫星的混合磁姿态控制器。
6. BeiDou Augmented Navigation from Low Earth Orbit Satellites [O] . Mudan Su, Xing Su, Qile Zhao, 2019

机译：北斗增强低地球轨道卫星导航
7. Development of an active magnetic attitude determination and control system for picosatellites on highly inclined circular low earth orbits [O] . Giesselmann J 2006

机译：高倾斜圆形低地球轨道上的微卫星主动磁姿态确定与控制系统的研制
8. Attitude Determination of an Orbiting Satellite. Part I. Gravitational Torque. Part II. Dynamical Equations for the Attitude Matrix. Part III. Magnetic Torque [R] . Goodman, G. S., Margulies, G. 1962

机译：轨道卫星的姿态确定。第一部分引力扭矩。第二部分。姿态矩阵的动力学方程。第三部分。磁力矩

Attitude control of Low Earth Orbit satellites by reaction wheels and magnetic torquers

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