Light-type structure composite material

A composite material and lightweight technology, applied in the direction of synthetic resin layered products, layered products, chemical instruments and methods, etc., can solve the problems that cannot meet the requirements of structural weight reduction, and achieve the effect of moderate mechanical properties

Inactive Publication Date: 2016-08-03
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional composite material laminated structure can no longer meet the structural weight reduction requirements of long-endurance solar unmanned aircraft, and puts forward unique requirements for new ultra-light composite materials

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] Ultra-thin carbon fiber prepreg (fiber surface density: 35g / m2) was prepared by using Toray T300 (6K) carbon fiber and epoxy resin in Japan. 2 , Resin surface density: 28g / m 2 ) and carbon fiber prepreg tow, the preparation method is one of the following methods: melting method, wet method. Using the prepared carbon fiber prepreg tow, a 2D 2-direction hollow carbon fiber hollow skeleton is prepared by weaving. According to the conventional requirements of autoclave composite material molding, the above-mentioned ultra-thin unidirectional carbon fiber prepreg and 2-dimensional 2-way hollow carbon fiber skeleton are combined according to "hollow skeleton-ultra-thin prepreg" and "ultra-thin prepreg- Hollow skeleton-ultra-thin prepreg" and "hollow skeleton-ultra-thin prepreg-hollow skeleton" and other lay-up designs are laid in composite material molding molds, and then prepared according to the curing molding procedure of epoxy resin to produce lightweight Composite lami...

Embodiment 2

[0028] Ultra-thin unidirectional carbon fiber prepreg (fiber surface density: 50g / m2) was prepared by using T800 (6K) carbon fiber and epoxy resin from Toray Corporation of Japan. 2 , Resin surface density: 30g / m 2 ) and carbon fiber prepreg tow, the preparation method is one of the following methods: melting method, wet method. Using the prepared carbon fiber prepreg tow, a 2D 2-direction hollow carbon fiber hollow skeleton is prepared by weaving. According to the conventional requirements of autoclave composite material molding, the above-mentioned ultra-thin unidirectional carbon fiber prepreg and 2-dimensional 2-way hollow carbon fiber skeleton are combined according to "hollow skeleton-ultra-thin prepreg" and "ultra-thin prepreg- Hollow skeleton-ultra-thin prepreg" and "hollow skeleton-ultra-thin prepreg-hollow skeleton" and other lay-up designs are laid in composite material molding molds, and then prepared according to the curing molding procedure of epoxy resin to pro...

Embodiment 3

[0030] Ultra-thin plain weave carbon fiber prepreg was prepared by using T300 (1K) carbon fiber plain weave fabric and epoxy resin from Toray Corporation of Japan (fiber surface density: 60g / m2) 2 , Resin surface density: 35g / m 2 ), adopt Japan Toray Company T300 (3K) carbon fiber to prepare carbon fiber prepreg tow, the preparation method of the above ultra-thin plain carbon fiber prepreg and carbon fiber prepreg tow is one of the following methods: melting method, wet method . Using the prepared carbon fiber prepreg tow, a 2D 2-direction hollow carbon fiber hollow skeleton is prepared by weaving. According to the conventional requirements of autoclave composite material molding, the above-mentioned ultra-thin plain carbon fiber prepreg and 2D 2-direction hollow carbon fiber hollow skeleton are combined according to "hollow skeleton-ultra-thin prepreg" and "ultra-thin prepreg-hollowout Skeleton-ultra-thin prepreg", "hollow-out skeleton-ultra-thin prepreg-hollow-out skeleton...

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Abstract

The invention provides a lightweight structural composite material, which relates to a layered composite lightweight composite material with relatively low uniform surface density and periodic or non-periodic modulation. The composite material includes: at least one layer of layers with uniform surface density and at least one layer of hollow fiber skeleton, and periodic or non-periodic lamination is adopted between the layer of uniform surface density and the hollow fiber skeleton. The main materials selected in the present invention all have relatively low surface density. Compared with common composite materials, the laminated composite materials in the present invention have ultra-light weight, and their mechanical structure design is relatively simple. This new type of composite material can be used in long-endurance solar unmanned aircraft, space vehicles and other occasions that do not bear too much mechanical load, but require lightweight applications.

Description

technical field [0001] The invention belongs to a structural design and manufacturing technology of light composite materials, and relates to a lightweight structural composite material with layered composite, periodic or non-periodic modulation. Background technique [0002] With the development of the aviation industry, the application of composite materials in aircraft has developed from the secondary load-bearing structure to the main load-bearing structure, and the application parts are becoming more and more important, and the requirements for composite material structural parts are also getting higher and higher. With the development of multi-functional and lightweight new aircraft, structural weight reduction has become an eternal theme in the design of aircraft composite structures. [0003] As a new type of aerial reconnaissance and combat weapon, the high-altitude long-endurance solar-powered UAV has the characteristics of large radius of action, long range, long ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/06B32B27/06
Inventor 高军鹏邓华包建文益小苏
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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