A multi-plate pinch release system

A technology of releasing system and pressing piece, which is applied to the docking device of space navigation vehicle, etc., can solve the problem of not being able to meet the demands of pressing and releasing tasks, and achieve the effect of high strength and high reliability

Active Publication Date: 2019-02-01
SHANGHAI AEROSPACE SYST ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] In order to solve the problem that the traditional compression and release system cannot meet the requirements of the compression and release task when the number of compression plates is large, the present invention provides a method for realizing the compression of the launch section and the release after entering orbit for a large number of plate and frame structures. multi-plate clamp release system

Method used

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  • A multi-plate pinch release system

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Embodiment Construction

[0030] The invention will be described in more detail hereinafter with reference to the accompanying drawings showing embodiments of the invention. However, this invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In these drawings, the size and relative sizes of layers and regions may be exaggerated for clarity.

[0031] refer to figure 1 , the present invention provides a multi-plate compression and release system, which is used to realize the compression and release between a plurality of sequentially arranged plate and frame structures on a spacecraft; the multi-plate compression and release system includes a compression structure and multiple sets of compression Compression components, at least one set of compression components ...

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Abstract

The invention discloses a multi-plate compressing and releasing system which is used for compressing and releasing a plurality of plate frame structures arranged on a spacecraft in sequence. The multi-plate compressing and releasing system comprises compressing assemblies and a compressing structure, wherein at least one compressing assembly is arranged between every two adjacent plate frame structures; the compressing structure comprises a fixed structure and a movable structure, and the multiple plate frame structures are pressed between the fixed structure and the movable structure; at least one compressing assembly is arranged between the plate frame structures and the fixed structure as well as between the plate frame structures and the movable structure; the end face, backing on the plate frame structures, of the movable structure is provided with at least one first compressing piece; and the first compressing pieces, the compressing assemblies between the movable structure and the plate frame structures, the compressing assemblies between the adjacent plate frame structures and the compressing assemblies between the plate frame structures and the fixed structure are located on the same axis. By the adoption of the multi-plate compressing and releasing system, compressing of the plate frame structures which are large in number and overall thickness is achieved, and the multi-plate compressing and releasing system is suitable for various spacecraft tasks.

Description

technical field [0001] The invention relates to the technical field of design of a compression release system for a plate frame structure on a spacecraft, in particular to a multi-plate compression release system for realizing compression of a launch section and release after orbiting for a large number of plate frame structures. Background technique [0002] With the diversification of functions and the increasing functional requirements of military and civilian spacecraft, the space scale parameters such as the length and area of ​​the plate-frame structure mounted on the spacecraft need to be improved accordingly. However, limited to the envelope of the fairing of the launch vehicle, the high-length and large-area plate-frame structure cannot be launched into orbit in a working state. It is necessary to divide the plate-frame structure into multiple sub-modules and implement it through an additional deployment mechanism. Launch in the folded state, unfold and lock into th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/64
CPCB64G1/64
Inventor 周鑫李明刘殿富陈飞飞顾珏华袁伟杜涵杨悦宋佳
Owner SHANGHAI AEROSPACE SYST ENG INST
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