A multi-plate pinch release system

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...

AI Technical Summary

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

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