Overall Optimal Design Method Based on Illumination Conditions of Inclined Orbit Satellites

Abstract

The present invention provides an overall optimization design method based on the illumination conditions of inclined orbit satellites, comprising: a calculation step: the sun vector is obtained by recursion of orbital parameters on the satellite or measured by a sun sensor, and the sun altitude angle is obtained by calculation, and the sun altitude angle is used as a parameter Characterize the change of the energy supply of the whole star and the change of the heat dissipation surface; determine the flight plan step: take into account the satellite U-turn flight plan designed by the whole star energy and fixed heat dissipation surface; determine the satellite flight polarity step: determine the satellite flight polarity according to the direction of the sun vector change; determine Applicability step: the judgment method of the shadow area and the adaptability of the U-turn flight plan in the shadow area; the basis selection step: the basis for the U-turn flight time selection. From the point of view of the overall optimization design of the whole star, the invention is beneficial to the thermal control design of the whole star; it ensures enough illumination time to balance the energy of the whole star; the fixed light surface also solves the constraints of sensor and load layout design.

Description

technical field [0001] The invention relates to the field of satellite overall optimization design methods, in particular to an overall optimization design method based on illumination conditions of inclined orbit satellites. Background technique [0002] With the continuous development of aerospace technology, higher requirements are put forward for the satellite detection area, and the low-latitude areas in the north and south have gradually become hot spots for detection. more and more. [0003] The notable feature of satellites in inclined orbits is that the angle between the sun vector and the orbit plane is constantly changing, the lighting conditions of the whole star are complex, and the star has no fixed heat dissipation surface, which makes it difficult to design the thermal control of the whole star. Due to the change of the lighting conditions of the whole star, the traditional The fixed-wing single-axis one-dimensional drive solar panel has a short illumination...

AI Technical Summary

Problems solved by technology

[0003] The notable feature of satellites in inclined orbits is that the angle between the sun vector and the orbit plane is constantly changing, the lighting conditions of the whole star are complex, and the star has no fixed heat dissipation surface, which makes it difficult to design the thermal control of the whole star. Due to the change of the lighting conditions of the whole star, the traditional The fixed-wing single-axis one-dimensional drive solar panel has a short illumination time, which cannot meet the energy supply demand, and the energy of the whole star cannot be balanced. The driving mechanism of the non-fixed-wing two-dimensional drive solar panel is complex and has low reliability. Development stage

In addition, the layout of the whole star is also restricted, the attitude sensor is often invalid due to the influence of sunlight, and the remote sensing load cannot be imaged

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