A cryogenic optical satellite configuration suitable for large elliptical frozen orbits under complex illumination conditions

Abstract

The invention discloses a low-temperature optical satellite configuration suitable for a great elliptic frozen orbit complex light condition. The low-temperature optical satellite configuration comprises a platform and an auxiliary cabin, wherein the platform is in charge of bearing most of stand-alone equipment in the satellite, and divided into an upper cabin section and a lower cabin section; the auxiliary cabin is mounted on a top plate of the platform and in a cubic shape to carry antennas required by satellite data transmission, measurement and control, satellite-to-satellite communication and other antennas required over the ground; a cross section of the platform is in a rectangular sealed hexahedron; the upper cabin section is formed by a top plate, six side plates, four upper separation frames and layer plates; and the lower cabin section is formed by a base plate, six side plates, fourth lower separation frames and layer plates. By the use of the low-temperature, a stable and great-area nightside surface can be guaranteed upon the complex light conditions of the great elliptic frozen orbit, and imaging temperature environment demands for a low-temperature optical cameracan be guaranteed; a great over-the ground area can be provided, so ground load layout space utilization rate can be ensured; great specific stiffness and specific strength can be provided; and when astorage case is flatly placed, the whole satellite centroid deviation range can be well controlled.

Description

technical field [0001] The invention relates to an aerospace vehicle in the field of aerospace technology, in particular to a configuration of a cryogenic optical satellite suitable for a large elliptical frozen orbit under complex illumination conditions. Background technique [0002] Satellites operating in large elliptical frozen orbits face extremely complex lighting conditions, which can cause satellites operating in this orbit to have a thermal environment in which all sides are irradiated by sunlight in turn, and the satellites are illuminated in a chaotic and unobvious pattern throughout their lifespan. It is extremely difficult to implement, and it cannot meet the working conditions that the low-temperature heat dissipation surface of the low-temperature optical load cannot be exposed to sunlight. Although satellite attitude control can be designed so that a certain reference axis direction of the satellite is always in a state that is not illuminated by the sun aft...

AI Technical Summary

Problems solved by technology

[0002] Satellites operating in large elliptical frozen orbits face extremely complex lighting conditions, which can cause satellites operating in this orbit to have a thermal environment in which all sides are irradiated by sunlight in turn, and the satellites are illuminated in a chaotic and unobvious pattern throughout their lifespan. It is extremely difficult to implement, and it cannot meet the working conditions that the low-temperature heat dissipation surface of the low-temperature optical load cannot be exposed to sunlight

Although satellite attitude control can be designed so that a certain reference axis direction of the satellite is always in a state that is not illuminated by the sun after combining the image rotation avoidance of the earth observation, but considering the low temperature optical load, the low temperature heat dissipation surface cannot be exposed to direct sunlight and Platform reflection, ensuring that the platform has a sufficiently large heat dissipation surface and cannot be continuously exposed to sunlight, that the center of mass of the satellite cannot be shifted too much, and that the rigidity and strength of the satellite are guaranteed, the platform cannot adopt the configuration of a public platform for geostationary orbit remote sensing satellites

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