Satellite and rocket docking device

A docking device, star rocket technology, which is applied in the docking device of aerospace vehicles, transportation and packaging, aerospace equipment, etc., to achieve the effect of reducing quality, reducing difficulty, and improving strength

Active Publication Date: 2016-03-30
CHINA ACADEMY OF SPACE TECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The structure of the plate-frame satellite is simple, flexible, and highly expandable. It adapts to the characteristics of the electric propulsion satellite platform, effectively improves the satellite space utilization efficiency, and increases the payload carrying capacity. However, there is a technical difficulty in this configuration scheme, which is how to Realize the uniform transition of the whole star's mechanical load from the box-type plate frame platform to the circular carrier docking ring

Method used

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  • Satellite and rocket docking device

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Embodiment Construction

[0029] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0030] Such as figure 1 Shown is the composition diagram of the star-arrow docking device. It can be seen from the figure that it includes the main cylinder 1, the back floor connection frame 2 and the star-arrow docking frame 3; the main cylinder 1 is fixedly installed on the upper part of the star-arrow docking frame 3, and the star-arrow docking The bottom opening of the frame 3 is circular; the back floor connection frame 2 is fixedly installed on the middle and lower part of the outer wall of the main cylinder 1; the top opening of the main cylinder 1 is square; the star-arrow docking frame 3 realizes the connection with the satellite support of the external launch vehicle ; The main cylinder 1 realizes the connection with the external load-bearing partition.

[0031] Each side of the inner wall of the main cylinder body 1 is provided with...

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PUM

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Abstract

The invention provides a satellite and rocket docking device, and relates to the technical field of spaceflight overall configuration. The satellite and rocket docking device comprises a main cylinder, a backland plate connecting frame and a satellite and rocket docking frame, wherein the a circular opening is formed in the bottom of the satellite and rocket docking frame; a square opening is formed in the top of the main cylinder. The satellite and rocket docking frame disclosed by the invention is suitable for a total carbon fiber composite circumference transition satellite and rocket connecting device of a grillage type configuration GEO satellite platform, uniform transition of a whole satellite mechanical load from a box-shaped grillage to a circular delivery butting ring is realized, and as a corn component of the device, the grillage type satellite configuration forms a favorable force transmitting path. The rigidity, the intensity and the stability of the whole satellite device all meet design requirements, and a solid basis is established for the configuration design of the whole satellite.

Description

technical field [0001] The invention relates to the technical field of overall spaceflight configuration, in particular to a satellite-rocket docking device. Background technique [0002] With the rapid development and maturity of electric propulsion technology, electric propulsion technology has been gradually applied on GEO satellites, from north-south position maintenance and partial orbit change, to the use of electric propulsion to realize all orbit change and on-orbit position maintenance tasks. The application of electric propulsion technology can greatly reduce the amount of propellant carried and reduce the weight of satellite launches, so as to realize the launch of two satellites with one arrow and effectively save launch costs. [0003] Due to the application of electric propulsion technology, especially the use of all-electric propulsion to complete the orbit change task, the propellant carrying capacity of GEO satellites has been significantly reduced, and the ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
CPCB64G1/641
Inventor 胡照刘刚王敏袁俊刚李大伟
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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