A Sun Tracking Method for Constellation Satellite Solar Array

Abstract

The invention discloses a solar cell array tracking method for constellation satellites, which adopts a one-dimensional yaw maneuver strategy to orientate the sun, and controls the maneuvering of the solar cell array according to the size of the orbital sun angle: when the orbital sun angle is less than a first preset value , adjust the initial normal state of the solar cell array so that the normal direction of the solar cell array is consistent with the flight direction of the constellation satellite, and control the solar cell array, making it one-dimensional yaw maneuver 180°; when the sun angle of the orbit is greater than the second preset value, control the normal direction of the solar cell array to be fixed at the normal direction of the orbit plane facing the sun; and when the orbit When the sun angle is greater than or equal to the first preset value and less than or equal to the second preset value, the normal direction of the solar cell array is controlled so that it tracks the sun vector and projects 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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