The attitude control law is designed for the orbital maneuver with considering the output character of the attitude control thrusters.
根据姿态控制推力器的输出特性，设计了轨道控制期间卫星姿态控制方案。
When the satellite takes orbital maneuver, the control force may stimulate the vibration of the flexible appendages and, therefore, affects the attitude of the satellite.
卫星轨道控制期间，轨道控制推力会激振挠性太阳帆板，从而也影响卫星的姿态。
When the satellite takes orbital maneuver, the control force may stimulate the vibration of the flexible appendages and, therefore, affects the attitude of the satellite.
卫星轨道控制期间，轨道控制推力会激振挠性太阳帆板，从而也影响卫星的姿态。
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