The invention relates to a switching control method for optical remote sensing satellite attitude rapid maneuver. The switching control method comprises the following steps: step 1, establishing a satellite reference coordinate system and an attitude kinetic equation; step 2, path planning of an attitude maneuvering section; step 3, path planning of an attitude convergence section; step 4, establishing an error kinetic equation for controller design; 5, attitude switching control is carried out; and step 6, rate compensation control. According to the switching control method for optical remote sensing satellite attitude rapid maneuver, the satellite attitude maneuver control efficiency can be further improved, the attitude adjustment time is effectively shortened, the number of imaging targets of a remote sensing satellite in finite time is increased, and the imaging area is expanded; high-efficiency and high-quality multi-target image acquisition is realized; parameters are easy to debug, attitude control efficiency is high, and the method is suitable for attitude control system design of small and medium-sized low-cost optical remote sensing satellites in engineering practice.
本发明涉及一种用于光学遥感卫星姿态快速机动的切换控制方法,包括以下步骤:步骤1,建立卫星参考坐标系和姿态动力学方程;步骤2,姿态机动段的路径规划;步骤3,姿态收敛段的路径规划;步骤4,建立用于控制器设计的误差动力学方程;步骤5,姿态切换控制;步骤6,速率补偿控制。本发明的用于光学遥感卫星姿态快速机动的切换控制方法,能够进一步提升卫星姿态机动控制的效率,有效缩短姿态调节的时间,提升遥感卫星在有限时间内的成像目标数量,扩大成像区域;实现高效率、高质量的多目标图像获取;参数易于调试,姿态控制效率高,适用于工程实际中小型低成本光学遥感卫星的姿态控制系统设计。
Switching control method for rapid maneuvering of attitude of optical remote sensing satellite
一种用于光学遥感卫星姿态快速机动的切换控制方法
2024-12-10
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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