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Satellite docking structure, docking satellites and docking method

A technology for connecting flanges and satellites, which is applied in the field of satellites and can solve problems such as limitations

Active Publication Date: 2018-06-01
星际漫步(北京)航天科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the problems of functional density, complexity, development cycle, and development funds, research on traditional large satellites is greatly restricted

Method used

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  • Satellite docking structure, docking satellites and docking method
  • Satellite docking structure, docking satellites and docking method
  • Satellite docking structure, docking satellites and docking method

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Embodiment Construction

[0036] In order to make the purpose, technical solution and advantages of the present invention clearer, the satellite docking structure, docking satellite and docking method of the present invention will be further described in detail through the following embodiments and in conjunction with the accompanying drawings. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0037] It should be noted that when an element is referred to as being “fixed” to another element, it can be directly on the other element or there can also be an intervening element. When an element is referred to as being "connected to" another element, it can be directly connected to the other element or intervening elements may also be present. In contrast, when an element is referred to as being "directly on" another element, there are no intervening elements present. The terms "vertical," "horizontal," ...

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Abstract

The invention discloses a satellite docking structure. The satellite docking structure comprises an active docking flange assembly and a passive docking flange assembly, wherein the active docking flange assembly is connected with an active satellite, and the passive docking flange assembly is connected with a passive satellite. The active docking flange assembly comprises an active docking flangebody, electromagnets, locking motors and mechanical locking shafts, and a first through hole is formed in the active docking flange body. The passive docking flange assembly comprises a passive docking flange body, permanent magnets and locking sliding channels, the permanent magnets correspond to the electromagnets in position, and the locking sliding channels correspond to the mechanical locking shafts in position. The locking sliding channels are provided with limiting portions, and the locking motors are used for driving the mechanical locking shafts to enter or fall off from the limitingportions of the locking sliding channels, so that the active docking flange assembly is connected with or separated form the passive docking flange assembly. A second through hole is formed in the passive docking flange body and corresponds to the first through hole in position. The satellite docking structure is used for electrically connecting the active satellite and the passive satellite.

Description

technical field [0001] The invention relates to the field of satellites, in particular to a satellite docking structure, a docking satellite and a docking method. Background technique [0002] The docking of satellites is the key factor to realize the information transmission between satellites. Due to the problems of functional density, complexity, development cycle, and development funds, the research on traditional large satellites is greatly restricted. With the development of science and technology, the miniaturization technology of satellites is becoming more and more mature, but the short board of miniaturization is that the function of each satellite is limited by its own volume, carry load and power supply system, and cannot be realized as large satellites can. However, its functional density, complexity, development cycle, and development funds all have great advantages. Therefore, if micro-satellites can be docked, the advantages of micro-satellites can be used t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
CPCB64G1/646Y02D30/70
Inventor 吴前进
Owner 星际漫步(北京)航天科技有限公司
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