Carbon/carbon composite honeycomb and preparation method thereof

A carbon composite material and honeycomb technology, which is applied in ceramic products, other household appliances, household appliances, etc., can solve the problems of poor thermal stability and unfavorable lightweight requirements in the aerospace field, and achieve short densification cycle and densification process adaptability Excellent, realize the effect of engineering application

Active Publication Date: 2018-11-20
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Abstract
  • Description
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Problems solved by technology

[0003] In the prior art, carbon / carbon composite blocks, carbon / silicon carbide composite blocks or carbon fiber reinforced resin-based honeycombs are usually used in the domestic aerospace field as the supporting structure of precision instruments to maintain good stability; due to carbon / carbon composite block or carbon / silicon carbide composite block are all solid structures, which is not conducive to the lightweight requirements of the aerospace field; the carbon fiber reinforced resin-based honeycomb thermal expansion system is about 10 -4 magnitude, poor thermal stability

Method used

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  • Carbon/carbon composite honeycomb and preparation method thereof
  • Carbon/carbon composite honeycomb and preparation method thereof
  • Carbon/carbon composite honeycomb and preparation method thereof

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[0039] The embodiment of the present invention also provides a method for preparing a carbon / carbon composite material honeycomb, comprising the following steps:

[0040] Step 1, preparing a carbon fiber reinforced body of a honeycomb structure, in which the L direction has continuous carbon fibers, and the W direction also has continuous carbon fibers;

[0041] Specifically, in the embodiment of the present invention, the L-direction and W-direction of the carbon fiber reinforced body honeycomb structure can be realized to have continuous fibers by splicing and sewing carbon cloth, specifically, as figure 2 As shown, the carbon cloth m is first cut into a predetermined shape according to the honeycomb design size and marked at the position to be stitched, and then the two pieces of carbon cloth m are bonded together, and the butt joint surface is stitched by the stitching line n. Insert the mandrel at the seam, and release the mold after solidifying the dimension shape, you ...

Embodiment 1

[0053] This embodiment provides a carbon / carbon composite material honeycomb for satellites with an outline size of 200mm×200mm×80mm, a honeycomb cell side length of 5mm, and a honeycomb wall thickness of 0.8mm. The preparation method includes:

[0054] 1) Use general-purpose T300-3K polyacrylonitrile-based carbon fiber to weave to an area density of 240g / cm 3 Plain carbon cloth, warp and weft density 6 threads / cm×6 threads / cm. Then cut the carbon cloth into carbon cloth blocks of a certain specification according to the expanded size of the honeycomb wall; during the cutting process, the warp yarn direction is 0°, rotate counterclockwise to form +45° carbon cloth, and rotate clockwise to form -45° carbon cloth.

[0055] 2) Lay the carbon cloth blocks in step 1) according to the designed layering sequence, and arrange the adjacent carbon cloths in the order of +45 / -45 layering; stitch the carbon cloths in pairs, and stitch the spacing in the thickness direction of the honeyco...

Embodiment 2

[0061] This embodiment provides a carbon / carbon composite material honeycomb with an outline size of 400mm×400mm×80mm, a honeycomb cell side length of 5mm, and a honeycomb wall thickness of 0.8mm. The preparation method includes:

[0062] 1) Use general-purpose T300-3K polyacrylonitrile-based carbon fiber to weave to an area density of 240g / cm 3 Plain carbon cloth, warp and weft density 6 threads / cm×6 threads / cm. Then cut the carbon cloth into carbon cloth blocks of a certain specification according to the expanded size of the honeycomb wall; during the cutting process, the warp yarn direction is 0°, rotate counterclockwise to form +45° carbon cloth, and rotate clockwise to form -45° carbon cloth.

[0063] 2) Lay the carbon cloth blocks in step 1) according to the designed layering sequence, and arrange the adjacent carbon cloths in the order of +45 / -45 layering; stitch the carbon cloths in pairs, and stitch the spacing in the thickness direction of the honeycomb 4mm, the st...

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Abstract

The invention discloses a carbon / carbon composite honeycomb and a preparation method thereof, and belongs to the technical field of carbon / carbon composites. The carbon / carbon composite honeycomb comprises a carbon fiber reinforcement body and a carbon substrate covering the surface of the carbon fiber reinforcement body; the carbon fiber reinforcement body adopts the honeycomb structure; and thehoneycomb structure has continuous carbon fibers in the L direction and also has continuous carbon fibers in the W direction. The carbon / carbon composite honeycomb has the excellent heat stability andmechanical properties, can meet the requirement for lightweight in the aerospace field and has main performance parameters such as the flat compression strength being higher than or equal to 8 MPa, the flat compression modulus being higher than or equal to 900 MPa, the L-direction shearing strength being higher than or equal to 6.7 MPa, the L-direction shearing modulus being higher than or equalto 1,500 MPa, the W-direction shearing strength being higher than or equal to 4.5 MPa, the W-direction shearing modulus being higher than or equal to 730 MPa and the thermal expansion coefficient ranging from 0 to 0.2*10<-6> / K.

Description

technical field [0001] This patent relates to a low-density, high-stability, high-strength integral carbon / carbon composite material honeycomb for a high-precision observation platform, which belongs to the technical field of carbon / carbon composite materials. Background technique [0002] Traditional composite materials for spacecraft structures generally only require high specific strength, high specific modulus, etc., and do not have high requirements for dimensional stability. However, in the field of research and development of composite material structures for high-precision spacecraft such as satellites, composite materials with high stability, light weight, and high strength are an important development direction. Advanced countries have begun to study zero-expansion, high-stability composite material structures for spacecraft, which are mainly used for supporting structures of optical instruments such as space telescopes, supporting bases for gravity gradiometers, a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/83C04B35/622C04B38/00C04B35/84
CPCC04B35/622C04B35/83C04B38/0009C04B2235/96C04B38/0067
Inventor 张中伟刘宇峰许正辉李同起俸翔
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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