제어로봇시스템학회:학술대회논문집
- 제어로봇시스템학회 2004년도 ICCAS
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- Pages.1747-1753
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- 2004
Spacecraft Attitude Control with a Two-axis Variable Speed Control Momentum Gyro
- Bang, Hyo-Choong (Department of Aerospace Engineering, KAIST) ;
- Park, Young-Woong (Korea Aerospace Research Institute) ;
- Lee, Jung-Shin (Department of Aerospace Engineering, KAIST)
- 발행 : 2004.08.25
초록
CMG(Control Momentum Gyro) is a control device being used for spacecraft attitude control constructing relatively large amount of torque compared to conventional body-fixed reaction wheels. The CMG produces gyroscopic control torque by continuously varying the angular momentum vector direction with respect to the spacecraft body. The VSCMG(Variable Speed Control Momentum Gyro) has favorable advantages with variable speed to lead to better control authority as well as singularity avoidance capability. Attitude dynamics with a VSCMG mounted on a two-axis gimbal system are derived in this study. The dynamic equation may be considered as an extension of the single-axis counterpart. Also, a feedback control law design is addressed in conjunction with the dynamic equations of motion.