4114 CMGを用いた人工衛星の最短時間姿勢変更(S75-2 宇宙システムの誘導・制御(2),S75 宇宙システムの誘導・制御)

概要

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The next-generation satellites will require rapid rotational agility as well as precision steady -state pointing accuracy for high-resolution images. For a torque generator to control direction posture of a n artificial satellite, reaction wheels and thrusters are used mainly now. A reaction wheel changes the number of the turns of a flywheel and, by reaction of torque of the picking up speed and slowing down, turns a satellite. However they has limitation for torque. As the actuator which can create big torque than a reaction wheel, a control moment gyro (CMG) is promising. So, the other try to design to minimum-time reorientation maneuver of satellites using CMG. In this thesis, the input value is angular velocities of gimbal and output is satellite's angular velocities. Bang-bang control is one of the candidates in minimum-time attitude control. But, the numerical results shows that input is not bang-bang control using CMGs.
社団法人日本機械学会の論文
2007-09-07