Satellite shell and satellite using the shell

Abstract

The invention provides a satellite shell and a satellite using the shell, the satellite includes a satellite shell and an optical load, the satellite shell includes a shell main body, the shell main body includes a first end surface and the The bottom end surface opposite to the first end surface, the bottom end surface is used to connect with the external member, and also includes a second end surface, the second end surface and the first end surface are located on the same side of the bottom end surface, and the The distance from the second end surface to the bottom end surface is smaller than the distance from the first end surface to the bottom end surface; the optical load is arranged on the second end surface. The invention has the advantages that it can not only reduce the vibration response of the satellite when launching the active segment, but also meet the requirement of large field of view of the optical load.

Description

technical field [0001] The invention relates to the technical field of aerospace satellites, in particular to a satellite casing and a satellite using the casing. Background technique [0002] The configuration and layout of the satellite is to organically connect the stand-alone machines, instruments and parts of each subsystem, to provide a good working foundation for each subsystem, to form a complete satellite, and to withstand rocket launch and satellite-rocket separation. Examination of the resulting mechanical environment. [0003] The shape of the satellite shell is mainly determined by the stabilization method adopted by the satellite. Spin-stabilized satellites are generally cylindrical, such as "Dongfanghong-2" and "Dongfanghong-2A" satellites, and their main bodies are cylinders. Three-axis stabilized satellites are generally cuboid. For example, satellites such as "Dongfanghong-3", "Fengyun-1", "Ziyuan-1" and "Ziyuan-2" are all cuboid in shape. Gravity-gradie...

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Problems solved by technology

[0005] The optical load of the two-dimensional turntable, which requires a higher field of view, must be exposed to space like other satellite structures, and it must withstand the sunlight under high vacuum conditions and the cold space environment after entering the shadow area. The maximum ambient temperature can reach 500K, and the minimum temperature can reach 3K. And the changes are very frequent (the general period of the sun-synchronous orbit is only about 100min), which will be intolerable for the optical load of the two-dimensional turntable that requires high imaging quality

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