Constellation satellite solar cell array sun tracking method

Abstract

The invention discloses a constellation satellite solar cell array sun tracking method. A one-dimensional yaw maneuvering strategy is adopted for sun orientation; the maneuvering of the solar cell array is controlled according to the size of the solar angle of the orbit; when the orbit solar angle is smaller than a first preset value, the normal initial state of the solar cell array is adjusted, the normal direction of the solar cell array is made to be consistent with the flight direction of a constellation satellite, and the solar cell array is controlled within a preset time period T beforeand after the sun passes through the top, so that one-dimensional yawing maneuver is achieved by 180 degrees; when the orbit solar angle is greater than a second preset value, the normal direction ofthe solar cell array is controlled to be fixed on the normal direction of the orbit plane to face the direction of the sun; and when the orbit solar angle is greater than or equal to the first presetvalue and less than or equal to the second preset value, the normal direction of the solar cell array is controlled to enable the solar cell array to track the projection of the sun vector in the horizontal plane.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a solar cell array tracking method for constellation satellites. Background technique [0002] The solar cell array of the satellite is a device used to receive sunlight and convert solar energy into the electrical energy required by the satellite. It is composed of a large number of solar cells. The solar cells can be directly attached to a certain surface of the star, or can be attached to one or more flat plates that can be unfolded to form a solar panel (or called a solar wing). [0003] As the most important way for satellites to obtain solar energy, keeping sunlight vertically irradiating the surface of the solar cell array is undoubtedly the most efficient geometric angle for converting light into electricity. However, the relative angle relationship between the satellite and the sun is mainly determined by the orbital inclination of the satellite, the local time of th...

AI Technical Summary

Problems solved by technology

Among them, using SADA and turntables to drive the solar cell array to perform two-dimensional maneuvers will have a large inertial impact on the entire star, which in turn will affect the attitude control of the satellite; , for large satellites with large mass and large inertia, it will bring design pressure to the attitude control system, and will affect the existing pointing requirements of loads such as inter-satellite communication

[0004] Relatively speaking, although it is difficult for the one-dimensional maneuvering of the solar cell array to achieve the effect of obtaining 100% of the solar energy by the two-dimensional maneuvering, considering the compromise of reliability, complexity and energy acquisition efficiency, the one-dimensional solar cell array Maneuvering is a cost-effective option for engineering implementation

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