Satellite casing and satellite using same

Abstract

The invention provides a satellite casing and a satellite using the same. The satellite comprises the satellite casing and an optical load, wherein the satellite casing comprises a casing main body; the casing main body comprises a first end surface, a bottom end surface opposite to the first end surface, and a second end surface; the bottom end surface is used for being connected with an external component, the second end surface and the first end surface are both positioned on the same side of the bottom end surface, and a distance from the second end surface to the bottom end surface is smaller than that from the first end surface to the bottom end surface; and the optical load is arranged on the second end surface. The satellite casing and the satellite, disclosed by the invention, have the advantages that the vibratory response of the satellite can be reduced when a powered phase is launched, and the large visual field requirement of the optical load can also be satisfied.

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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