Journal of Space Technology and Applications (우주기술과 응용)

The Korean Space Science Society (한국우주과학회)
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Control Moment Gyroscope Torque Measurements Using a Kistler Table for Microsatellite Applications

  • Goo-Hwan Shin (Korea Advanced Institute of Science and Technology) ;
  • Hyosang Yoon (Korea Advanced Institute of Science and Technology) ;
  • Hyeongcheol Kim (Korea Advanced Institute of Science and Technology) ;
  • Dong-Soo Choi (Justek Incorporated) ;
  • Jae-Suk Lee (Justek Incorporated) ;
  • Yeong-Ho Shin (Justek Incorporated) ;
  • EunJi Lee (Hanwha Systems) ;
  • Sang-sub Park (Hanwha Systems) ;
  • Seokju Kang (Hanwha Systems)
  • Received : 2024.01.19
  • Accepted : 2024.02.13
  • Published : 2024.02.28
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Abstract

Attitude control of a satellite is very important to ensure proper for mission performance. Satellites launched in the past had simple missions. However, recently, with the advancement of technology, the tasks to be performed have become more complex. One example relies on a new technology that allows satellites quickly alter their attitude while orbiting in space. Currently, one of the most widely used technologies for satellite attitude control is the reaction wheel. However, the amount of torque generated by reaction wheels is too low to facilitate quick maneuvers by the satellite. One way to overcome this is to implement posture control logic using a control moment gyroscope (CMG). Various types of CMGs have been applied to space systems, and CMGs are currently mounted on large-scale satellites. However, although technological advancements have continued, the market for CMGs applicable to, small satellites remains in its early stages. An ultra-small CMG was developed for use with small satellites weighing less than 200 kg. The ultra-small CMG measured its target performance outcomes using a precision torque-measuring device. The target performance of the CMG, at 800 mNm, was set through an analysis. The final torque of the CMG produced through the design after the analysis was 821mNm, meaning that a target tolerance level of 10% was achieved.

Keywords

Acknowledgement

This work was supported by the program of the CMG-based Small Satellite Agile Attitude Control Technology funded by the Hanwha Systems of Korea.

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