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Aramid skin-paper honeycomb sandwich cylinder shell structure, preparation method thereof and application thereof

A technology of paper honeycomb and interlayer cylinder, which is applied in the direction of chemical instruments and methods, paper/cardboard layered products, lamination, etc., and can solve the problems that cannot be adopted

Active Publication Date: 2019-10-01
BEIJING SATELLITE MFG FACTORY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the support structure in the spacecraft antenna subsystem not only has predetermined requirements for the bearing capacity of static loads, but also has specific requirements for the product's structural weight, wave-transmitting performance, electrical performance, and its ability to withstand dynamic loads and local impact loads. More stringent requirements, so the traditional brittle carbon fiber reinforced resin matrix composite skin (hereinafter referred to as carbon skin) and aluminum honeycomb sandwich core cannot be used

Method used

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  • Aramid skin-paper honeycomb sandwich cylinder shell structure, preparation method thereof and application thereof
  • Aramid skin-paper honeycomb sandwich cylinder shell structure, preparation method thereof and application thereof
  • Aramid skin-paper honeycomb sandwich cylinder shell structure, preparation method thereof and application thereof

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Embodiment

[0061] A kind of aramid fiber skin - paper honeycomb sandwich shell structure such as figure 1 As shown, the structure includes an upper flange 1, a cylinder body 2 and a lower flange 3; the upper flange 1 includes an aramid outer skin A4, a paper honeycomb sandwich core A5, an aramid inner skin A6 and a connecting joint A7; the cylinder body 2 includes aramid inner skin B8, paper honeycomb sandwich B9, aramid outer skin B10, connecting joint B11 and lightening hole 12; lower flange 3 includes aramid outer skin C13, paper honeycomb sandwich C14, aramid inner Skin C15 and connecting joint C16;

[0062] Between the aramid outer skin A4 and the aramid inner skin A6 of the upper flange 1 is a paper honeycomb sandwich A5, and the connecting joint A7 includes two parts: a flange A17 and a connecting column A18, and the flange A17 is located on the aramid On the inner skin A6, the connecting column A18 is embedded in the paper honeycomb sandwich core A5;

[0063] Between the aramid...

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Abstract

The invention relates to an aramid skin-paper honeycomb sandwich cylinder shell structure, a preparation method thereof and application thereof and particularly relates to a Kevlar49 aramid fiber woven fabric reinforced epoxy resin based composite material skin-Nomex perforated paper honeycomb sandwich cylinder shell structure applied to a spacecraft antenna sub-system support structure and a preparation method thereof, belonging to field of spacecraft composite material structures and the forming technology.

Description

technical field [0001] The invention relates to an aramid skin-paper honeycomb sandwich shell structure and its preparation method and application, in particular to a Kevlar49 aramid fiber woven cloth reinforced epoxy resin base compound applied to the support structure of the spacecraft antenna subsystem The material skin-Nomex porous aramid paper honeycomb sandwich shell structure and its preparation method belong to the field of spacecraft composite material structure and its forming technology. Background technique [0002] The honeycomb sandwich shell structure has outstanding advantages such as light weight, high specific strength, high specific stiffness, and high bending stiffness, and under the same load conditions, it has smaller deformation and stress than solid structures, so it has been widely used in spacecraft The main load-bearing structure and secondary load-bearing structure, such as the satellite central load-bearing cylinder in the spacecraft structure su...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H01Q1/00B32B27/34B32B27/02B32B27/10B32B29/00B32B5/02B32B5/26B32B3/12B32B7/08B32B33/00B32B37/10B32B37/06B32B38/08B32B38/16
CPCB32B3/12B32B5/02B32B5/26B32B7/08B32B29/02B32B33/00B32B37/06B32B37/1009B32B38/08B32B38/164B32B2260/021B32B2260/046B32B2262/0269H01Q1/00
Inventor 李莺歌沈淑康关鑫黎昱宫顼陈维强
Owner BEIJING SATELLITE MFG FACTORY
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