A low-impact self-locking hinge for space-deployable structures

Abstract

The invention provides a low impact self-locking hinge applied to space spreadable structures, comprising a male hinge, a female hinge, a main shaft, a secondary shaft, three-axis, a rotating connecting rod, and cable pulley components, the male hinge and the rotating connecting rod are connected by the main shaft, with a common rotating shaft; the female hinge and the rotating connecting rod areconnected by the secondary shaft, with a common rotating shaft; the cable pulley components are connected with the male hinge and the female hinge respectively, the cable pulley components provide theinitial expansion moment and the recovery moment in the expansion process, and realize the self-locking after the expansion is in place, the underexpansion state and overexpansion state are adopted for multiple loop switching during the expansion process, According to the low impact self-locking provided by the invention, the power and locking functions are integrated as a whole , and the complexity of the hinge is greatly reduced.

Description

technical field [0001] The invention relates to a spacecraft structure and mechanism, in particular to a novel low-impact self-locking hinge applied to a space deployable structure. Background technique [0002] With the development of aerospace technology, space deployable structures have gradually been widely used in the field of aerospace due to their reusability, convenient transportation and storage. Payloads (such as vector magnetometers, etc.) also put forward higher and higher requirements for the residual magnetism of deployable structures. The traditional hinge devices based on metal springs used on existing spacecraft usually adopt a design that is deployed once and locked. The mechanical locking method brings great impact, and the electrical locking method brings great residual magnetic interference, which makes it difficult to meet the requirements of low residual magnetic field and no impact. Contents of the invention [0003] In view of the defects in the p...

AI Technical Summary

Problems solved by technology

Payloads (such as vector magnetometers, etc.) also put forward higher and higher requirements for the residual magnetism of deployable structures. The traditional hinge devices based on metal springs used on existing spacecraft usually adopt a design that is deployed once and locked. The mechanical locking method brings a large impact, and the electric locking method brings a large residual magnetic interference, which is difficult to meet the requirements of low residual magnetic field and no impact.

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