Large-dip-angle orbiting satellite solar panel orientation method under simple posture control

A solar panel and attitude control technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as satellite failure and reliability reduction, and achieve high load stability, high stability, and hardware mechanism. achieve simple effects

Active Publication Date: 2016-11-09
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

[0004] Compared with the single-axis solar cell array drive mechanism in the one-dimensional pointing control method, the reliability of the two-axis solar cell array drive mechanism is significantly lower, but the solar cell array drive mechanism is one of the key components of the satellite, and its failure will cause the entire satellite failure of

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  • Large-dip-angle orbiting satellite solar panel orientation method under simple posture control

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Embodiment Construction

[0028] Aiming at the deficiencies of the prior art, the present invention proposes a solar panel pointing method for large-inclination orbit satellites under simple attitude control, and designs three solar panel pointing adjustment modes according to the angle θ between the vector direction of the sun's rays and the normal direction of the satellite orbit To meet the pointing requirements of the solar panels of the satellites in the high-inclination orbit, the present invention will be further described below in conjunction with the accompanying drawings.

[0029] like figure 1 Shown is the coordinate system that the inventive method needs to use, comprises (1) earth center equator inertial coordinate system Ox 0 the y 0 z 0 (S 0 ); (2) Spacecraft centroid orbital coordinate system Sx 2 the y 2 z 2 (S 2 ): the origin is on the center of mass of the satellite, the axis z 2 From the center of the earth to the center of mass of the satellite, axis x 2 Pointing to the di...

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Abstract

A large-dip-angle orbiting satellite solar panel orientation method under simple posture control includes the steps that firstly, a satellite centroid orbit coordinate system, a spacecraft body coordinate system and a geocentric equatorial inertia coordinate system are built, the included angle between sunlight and the normal of a satellite orbital plane is obtained, then the included angle is judged, a satellite solar panel is controlled to rotate according to different included angles, the direction of a rotary shaft of the satellite solar panel is adjusted, and large-dip-angle orbiting satellite solar panel orientation control is finished. The method overcomes the defects that in the prior art, in order to meet the requirement that sunlight is perpendicular to a satellite solar panel, the satellite yaw angle of a satellite with a single-degree-of-freedom solar panel driving mechanism is controlled all the time, rotation speed of the solar panel is large, and stability of satellite effective loads is not benefited. Three solar panel orientation adjustment modes are designed according to the angle theta between the vector direction of sunlight and the normal direction of a satellite orbit to meet orientation requirements of a large-dip-angle orbiting satellite solar panel, and the method has the advantages of being high in load stability and easy to operate.

Description

technical field [0001] The invention relates to the technical field of satellite orbit attitude dynamics and control, in particular to a solar panel pointing method for a satellite orbiting with a large inclination angle under simple attitude control. Background technique [0002] In order to make full use of the electric energy generated by the on-board solar cells, satellites generally have one or two sail-like panels covered with solar cells, in order to achieve a higher utilization rate of the on-board solar cells and meet the requirements of the satellite power supply and distribution subsystem. The power supply requirements of the satellite need to control the angle θ between the normal direction of its solar panel and the sun's rays s Not greater than 45°. The existing solar panel pointing methods include a one-dimensional pointing control method and a two-dimensional pointing control method. [0003] Since the included angle of the sun's ecliptic plane is about 23....

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 经姚翔赵义平李峰
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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