The invention discloses an attitude maneuver method for adaptive angular momentum amplitude limiting adjustment. The attitude maneuver method comprises the following steps: acquiring attitude quaternion deviation and angular velocity deviation of a satellite body; according to the attitude quaternion deviation of the satellite body, a three-axis attitude maneuver angular velocity amplitude limiting value is obtained; obtaining a three-axis quaternion deviation amplitude limit value of the satellite body according to the three-axis attitude maneuvering angular velocity amplitude limit value of the satellite body; calculating attitude quaternion deviation of the satellite body after vector amplitude limiting according to the three-axis quaternion deviation amplitude limiting value of the satellite body; and according to the three-axis quaternion deviation and the angular velocity deviation of the satellite body after vector amplitude limiting, a three-axis instruction control moment is obtained. On the premise that the angular momentum of an executing mechanism in the maneuvering process does not exceed the output capacity, the angular momentum can be utilized and executed to the maximum degree, and meanwhile three-axis simultaneous maneuvering in place is achieved.
本发明公开了一种自适应角动量限幅调整的姿态机动方法,包括:获取卫星本体的姿态四元数偏差和角速度偏差;根据卫星本体的姿态四元数偏差得到三轴姿态机动角速度限幅值;根据卫星本体三轴姿态机动角速度限幅值得到卫星本体三轴四元数偏差限幅值;根据卫星本体三轴四元数偏差限幅值计算矢量限幅后的卫星本体的姿态四元数偏差;根据矢量限幅后的卫星本体三轴四元数偏差和角速度偏差得到三轴指令控制力矩。本发明能够保证机动过程执行机构角动量不超过输出能力的前提下最大程度利用执行够角动量,同时实现三轴同时机动到位。
Attitude maneuvering method for adaptive angular momentum amplitude limiting adjustment
一种自适应角动量限幅调整的姿态机动方法
2024-05-17
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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