Overall optimization design method based on inclined orbit satellite illumination conditions

Abstract

The invention provides an overall optimization design method based on inclined orbit satellite illumination conditions, which comprises the following steps: a calculation step: obtaining a solar vector by on-board orbit parameter recursion or sun sensor measurement, calculating to obtain a solar altitude angle, and representing the energy supply change and heat dissipation surface change of the whole satellite by taking the solar altitude angle as a parameter; determining a flight scheme, wherein a satellite U-turn flight scheme considering whole satellite energy and fixed heat dissipation surface design is adopted; determining satellite flight polarity: determining the satellite flight polarity according to the sun vector change direction; an applicability determination step: adaptabilityof a shadow area judgment method and a shadow area turning-around flight scheme; and a basis selection step: selecting a basis for the turn-around flight time. Starting from the perspective of overall optimization design of the whole satellite, thermal control design of the whole satellite is facilitated; enough illumination time is ensured, so that the energy of the whole satellite is balanced;and the constraint of sensor and load layout design is also solved by the fixed illumination surface.

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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