The author introduces a test platform system that has been developed for variable-speed control moment gyroscopes(VCMGs). VCMGs are important actuators for spacecraft attitude control. The test platform consists of two VCMGs driven by servo motors and sensor modules. The control program has been coded by the NI LabVIEW. Accelerometers and gyros have been used to measure the attitude angle and angular speed of the platform. The 2nd order low pass filters have effectively filtered out noises from measurements. Wheel speeds and gimbal angles have been controlled satisfactory by PI control. Through some tests, moment generation has been verified. The moment has been generated as commanded. However, friction effect by a ball bearing, that supports the platform’s rotation, has been not negligible. As further studies, friction reduction will be studied. In conclusion, this test platform will be used for engineering education and research.

Abstract
 1. 서론
 2. 동작 원리
  2.1 모멘트 발생원리
  2.2 동역학 방정식
 3. 테스트 플랫폼 구성
  3.1 플랫폼과 휠
  3.2 신호측정
  3.3 모터제어
  3.4 동작 테스트 및 결과 검토
 4. 결론
 부록
 References

• 진재현(순천대학교 우주항공공학전공) | Jaehyun Jin