The invention provides an attitude and orbit control method suitable for a sun-earth Lagrange point L2 aircraft, and the method comprises the following steps: S1, after satellite-rocket separation, rapidly eliminating the angular velocity and attitude deviation caused by satellite-rocket separation, and achieving the sun orientation of a solar cell array; s2, the satellite is controlled to be transferred from the GTO to the L2 orbit; s3, after the scientific cabin and the propulsion cabin of the satellite are separated, the separation angular velocity and attitude deviation are eliminated, and sun orientation of the satellite solar cell array is achieved again; s4, in the satellite task stage, attitude measurement and attitude control are carried out according to load requirements; and S5, performing orbit maintenance control according to the satellite orbit drifting condition during the orbit operation period of the satellite. According to the method, accurate control of the L2 aircraft in different operation states can be realized.
本发明提供了一种适应日地拉格朗日点L2飞行器的姿轨控方法,包括如下步骤:S1、星箭分离后,快速消除所述星箭分离引起的角速度和姿态偏差,实现太阳电池阵对日定向;S2、控制实现卫星从GTO转移到L2轨道;S3、所述卫星的科学舱和推进舱分离后,消除分离角速度和姿态偏差,再次实现卫星太阳电池阵对日定向;S4、在所述卫星任务阶段,根据载荷需求进行姿态测量和姿态控制;S5、在所述卫星的轨运行期间,根据所述卫星轨道漂移情况进行轨道维持控制。该方法能够实现对L2飞行器不同运行状态下的精准控制。
Attitude and orbit control method and system suitable for sun-earth Lagrange point L2 aircraft
一种适应日地拉格朗日点L2飞行器的姿轨控方法和系统
2023-09-05
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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