The invention relates to a satellite heterogeneous flywheel configuration and a combined use method, the satellite heterogeneous flywheel configuration comprises a conventional angular momentum flywheel FLx, a conventional angular momentum flywheel FLy, a conventional angular momentum flywheel FLz and a conventional angular momentum flywheel FLs; a high-torque flywheel HFx and a high-torque flywheel HFy; angular momentum directions of the conventional angular momentum flywheel FLx, the conventional angular momentum flywheel FLy and the conventional angular momentum flywheel FLz are respectively parallel to X, Y and Z directions of a satellite coordinate system; the absolute value of the included angle between the angular momentum direction of the conventional angular momentum flywheel FLs and the X axis, the Y axis and the Z axis of a satellite coordinate system is about 57.3 degrees; angular momentum directions of the high-torque flywheel HFx and the high-torque flywheel HFy are respectively parallel to an X axis and a Y axis of a satellite coordinate system. The heterogeneous flywheel is simple in structure, easy to implement and low in cost, and the rapid maneuvering capability of a satellite is remarkably improved; according to the combined use method of the satellite heterogeneous flywheel configuration, the logic of the high-torque flywheel participating in and exiting attitude control is simple and clear, and engineering implementation is easy.
本发明涉及一种卫星异构飞轮构型与组合使用方法,该卫星异构飞轮构型,包括:常规角动量飞轮FLx、常规角动量飞轮FLy、常规角动量飞轮FLz和常规角动量飞轮FLs;大力矩飞轮HFx和大力矩飞轮HFy;常规角动量飞轮FLx、常规角动量飞轮FLy、常规角动量飞轮FLz的角动量方向分别与卫星坐标系X、Y、Z方向平行;常规角动量飞轮FLs的角动量方向与卫星坐标系X、Y、Z三轴的夹角绝对值约为57.3度;大力矩飞轮HFx和大力矩飞轮HFy的角动量方向分别与卫星坐标系X、Y轴平行。本发明的异构飞轮构型简单、易实现、成本低,对于卫星实现快速机动能力得到显著提升;本发明的卫星异构飞轮构型的组合使用方法,大力矩飞轮参与和退出姿态控制的逻辑简洁、清晰易于工程实现。
Satellite heterogeneous flywheel configuration and combined use method
一种卫星异构飞轮构型与组合使用方法
10.05.2024
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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