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Satellite platform structure

A satellite platform and side cabin technology, applied in the field of satellites, can solve the problems of long duration and achieve the effects of simple structure, shortened manufacturing and assembly time, and saved launch space

Active Publication Date: 2022-05-13
ZHEJIANG GEESPACE TECH CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

On this basis, the final assembly of satellite instruments and equipment and the tests at all levels can be interspersed in sequence from the inside to the outside, from the module to the whole satellite, and it takes a long time.

Method used

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Embodiment 1

[0052] See attached Figure 1 to Figure 10 , the present embodiment provides a satellite platform structure, including a closed trapezoidal box 1 and at least four connecting components 2;

[0053] The trapezoidal box 1 comprises a first side deck 11, a second side deck 12, a third side deck 13, a fourth side deck 14, a first bottom deck 15 and a second bottom deck 16; The deck 11 and the second side deck 12 are arranged oppositely, and the third side deck 13 and the fourth side deck 14 are arranged oppositely; and the third side deck 13 and the fourth side deck 14 are only provided with Electric solar panel components;

[0054] Some or all of the first side deck 11, the second side deck 12, the third side deck 13, the fourth side deck 14, the first bottom deck 15 and the second bottom deck 16 are pre-embedded with connections Assembly 2, adjacent decks of the first side deck 11 , the second side deck 12 , the third side deck 13 , the fourth side deck 14 , the first bottom d...

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Abstract

The invention relates to the technical field of satellites, in particular to a satellite platform structure which comprises a trapezoid box capable of being closed and at least four connecting assemblies. The trapezoidal box body comprises a first side cabin plate, a second side cabin plate, a third side cabin plate, a fourth side cabin plate, a first bottom cabin plate and a second bottom cabin plate; connecting assemblies are pre-buried in parts or all of the first side cabin plate, the second side cabin plate, the third side cabin plate, the fourth side cabin plate, the first bottom cabin plate and the second bottom cabin plate, and adjacent cabin plates in the first side cabin plate, the second side cabin plate, the third side cabin plate, the fourth side cabin plate, the first bottom cabin plate and the second bottom cabin plate are detachably connected; the satellite platform structure is simple in structure, so that the manufacturing and assembling time is greatly shortened; the space in the carrying fairing is fully utilized, and the launching space is saved; and meanwhile, only the solar panel assemblies are arranged on the third side cabin plate and the fourth side cabin plate, so that cabin opening or cabin sealing operation of the satellite platform structure is greatly simplified, the test time is further shortened, and the production efficiency is improved.

Description

technical field [0001] The invention relates to the field of satellite technology, in particular to a satellite platform structure. Background technique [0002] In recent years, my country's remote sensing satellite technology has made great progress, and has been successfully applied in the fields of land and resources, surveying and mapping, ocean observation, and environmental disaster reduction. As remote sensing satellite technology enters the stage of engineering application, in order to reduce costs and improve development efficiency, generalized and shelf-oriented satellite platform technology has become a research hotspot. [0003] And under the trend of rapid development of communication technology and central processing unit, satellite products are also changing from the original high-orbit and large satellites to small satellite constellations. The famous ones are the Iridium constellation, OneWeb constellation and Starlink constellation. The number of satellite...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/10B64G1/22B64G1/44
CPCB64G1/10B64G1/22B64G1/44Y02E10/50
Inventor 张华郝星凯刘勇
Owner ZHEJIANG GEESPACE TECH CO LTD
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