Loading plate unfolding component of spacecraft

Abstract

The invention relates to a loading plate unfolding component of a spacecraft. The loading plate unfolding component of the spacecraft comprises a loading single wing; the loading single wing comprisesat least four loading plate groups hinged to each other; the loading plate groups comprise two hinged loading plates and supporting rods I, wherein the supporting rods I are hinged to the left and right ends of the loading plate groups; at least one active interplate hinge is arranged between the adjacent loading plates of the loading single wing; one ends of the supporting rods I are hinged to the end parts of the loading plates; the other ends of the supporting rods I are hinged to the other supporting rod of the same loading plate groups; middle supporting rod groups are arranged between the adjacent loading plate groups of the loading single wing; and moreover, the middle supporting rod group in the midst is a first middle supporting rod group; the other middle supporting rod groups are second middle supporting rod groups; the first middle supporting rod group comprise two symmetrically arranged connecting rod groups; each connecting rod group comprises a supporting rod IV and a supporting rod V; and the second middle supporting rod groups comprise two supporting rods II. The loading plate unfolding component of the spacecraft is used for unfolding the multiple loading platesand possesses high storage ratio.

Description

technical field [0001] The invention relates to a load plate expansion assembly of a spacecraft, in particular to a high storage ratio expansion mechanism for load single wing plates with an even number of not less than four. Background technique [0002] With the diversification of military and civil spacecraft functions and the increasing functional requirements, the space scale parameters such as the payload length and area of ​​the spacecraft configuration have been greatly improved. Limited by the fairing envelope of the vehicle, a large The standard load cannot be launched in a working state, and it is necessary to divide the load into load plates, and use the deployment mechanism to implement configuration conversion after entering orbit. A large number of single-wing single-plate and single-wing double-plate deployment mechanisms are used in current spacecraft, but for single-wing multi-plate, that is, single-wing four-plate or more deployment mechanisms, it is impos...

AI Technical Summary

Problems solved by technology

A large number of single-wing single-plate and single-wing double-plate deployment mechanisms are used in current spacecraft, but for single-wing multi-plate, that is, single-wing four-plate or more deployment mechanisms, it is impossible to expand the single-wing single-plate or single-wing double-plate expansion mechanism. Realize the design

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