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Truss-type satellite structure with central capsule

A satellite structure and truss technology, applied in the field of satellite structures

Active Publication Date: 2012-08-01
AEROSPACE DONGFANGHONG DEV LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem solved by the present invention is to construct a truss-type micro-satellite structure with a central cabin body, which overcomes the limitation of the satellite space for carrying and launching, and improves the space utilization rate; overcomes the space limitation and heat dissipation problems of the solar array, and solves the Satellite energy constraints; overcame the technical problem of coupling the satellite layout caused by changing test load equipment, improved the versatility of the satellite; realized a satellite configuration scheme with efficient structure, compact and flexible layout

Method used

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  • Truss-type satellite structure with central capsule
  • Truss-type satellite structure with central capsule
  • Truss-type satellite structure with central capsule

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Embodiment Construction

[0021] The technical solutions of the present invention will be further described below in conjunction with specific embodiments.

[0022] Such as figure 1 , figure 2 As shown, the specific embodiment of the present invention is: build a kind of center cabin body truss type satellite structure, comprise center cabin body 1, satellite platform equipment 2, payload equipment 3 and truss unit 5, described satellite platform equipment 2 is arranged on On the central cabin 1, the truss unit 5 is arranged outside the central cabin 1, the truss unit 5 includes a truss 51 and a truss plate 52 connecting the truss 51, and the central cabin 1 passes through the The truss 51 is directly connected to the payload device 3 or connected to the payload device 3 through the truss 51 and the truss plate 52 , and the bulkhead of the central cabin 1 is formed by the plate or shell.

[0023] Such as figure 1 , figure 2 As shown, the specific implementation process of the present invention is...

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Abstract

The invention relates to a truss-type satellite structure with a central capsule, which comprises the central capsule, a satellite platform device, a payload device and a truss element. The satellite platform device is disposed on the central capsule and the truss element is disposed outside the central capsule. The central capsule is connected with the payload device through the truss element. The truss element comprises a truss and a truss plate which is connected with the truss. The wall of the central capsule is made of plates or shells. Due to the fact that interior of the capsule is used for installation of the satellite platform device and outside of the capsule is used for installation of the payload device, structure efficiency and spatial efficiency of the satellite are high, the structure efficiency can reach 19%, and the spatial efficiency can reach 400 kg per m3.

Description

technical field [0001] The invention relates to a satellite structure, in particular to a central cabin body truss type tiny satellite structure. Background technique [0002] Microsatellite experimentation is a highly competitive market. In the current design of microsatellites, most of them are launched by means of carrying, and the separation surface for carrying is mostly selected in the middle of the rocket or the side of the rocket adapter. Due to the limitation of loading space, most of the microsatellites currently carried and launched are below 80kg, and the power is within 40w, which limits the field of application of the loading test of this type of microsatellite, and makes full use of the load margin and fairing space margin to form a normalized load. The advantages will play a key role in striving for the future to carry test satellites with better performance and price. [0003] Contents of the invention [0004] The technical problem solved by the pr...

Claims

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Application Information

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IPC IPC(8): B64G1/10
Inventor 张胜唐心春韩飞
Owner AEROSPACE DONGFANGHONG DEV LTD
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