Satellite shell and satellite using the shell

A satellite and shell technology, applied in the field of satellites and aerospace satellites, can solve the problems of frequent changes, etc., and achieve the effects of expanding types, good low-temperature space environment, and precise imaging

Active Publication Date: 2016-07-20
SHANGHAI ENG CENT FOR MICROSATELLITES
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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

Method used

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  • Satellite shell and satellite using the shell

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Embodiment Construction

[0027] The specific implementation of a satellite housing provided by the present invention and a satellite using the housing will be described in detail below with reference to the accompanying drawings.

[0028] see figure 1 , The satellite casing 10 of the present invention includes a first end surface 11 and a bottom end surface 12 opposite to the first end surface 11 .

[0029] The bottom surface 12 is used for connecting with an external device (not marked in the drawings). The external device may be a rocket. When the satellite is launched, the bottom end surface 12 is connected to the rocket, and the bottom end surface 12 is separated from the rocket after entering the satellite orbit. The external device can also be another satellite, and when multiple satellites need to be connected in series, the bottom surface 12 is connected to another satellite.

[0030] The satellite housing 10 also includes a second end surface 13 . Both the second end surface 13 and the fir...

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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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/10B64G1/66
Inventor 诸成陈有梅张文巧王慧元蒋桂忠
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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