基于控制力矩陀螺仪的敏捷卫星姿态控制系统验证

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011 Pub Date : 2011-06-09 DOI:10.1109/RAST.2011.5966897

Emre Yavuzoğlu, E. Topal, A. Kutlu, Halime Urek, M. E. Gulluoglu, O. Tarakcioglu, Emre Yurtoglu, Değer Akin, K. Çelik, C. Ozyurt, K. Aydin, K. Yilmaz

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引用次数: 7

摘要

相对于航天器姿态控制中常用的反作用轮和动量轮，大扭矩放大和动量存储能力是控制力矩陀螺仪的两个基本特性。为了验证基于CMG的姿态控制系统(ACS)的要求，进行了软件和硬件在环(HIL)测试。为了获得更真实的结果，考虑到所使用的空气轴承台的限制，在三轴空气轴承试验台上进行了基于CMG的ACS HIL试验。最后给出了仿真和试验结果。

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Verification of control moment gyroscopes based attitude control systems for agile satellite missions

Large torque amplification and momentum storage capacity are the two basic properties that make control moment gyroscopes (CMGs) superior when compared to the reaction and momentum wheels commonly used in spacecraft attitude control. Software and Hardware in the Loop (HIL) tests are carried out for the verification of the requirements of CMG based attitude control systems (ACS). In order to have even a more realistic results, CMG based ACS HIL tests are performed on three axis air bearing test bed by taking into account the restrictions of the air bearing table used. The results of these simulations and tests are presented.

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Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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