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Composite material interlaced structure, and stacking method thereof

A technology of interwoven structure and composite material, applied in the field of composite material manufacturing, can solve the problems of weak interlayer mechanical properties of laminates, weak interlayer performance of laminates, poor impact resistance, etc., so as to improve the annular impact resistance and improve the overall Deformation ability, effect of improving impact damage resistance

Pending Publication Date: 2018-04-10
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional laminate is a typical two-dimensional structure, which is mainly carried by in-plane fibers. Since the strength of the fiber is much higher than that of the resin matrix, the interlayer performance of the laminate is weak, which easily leads to delamination failure and poor impact resistance.
[0003] The traditional laminate structure is to use prepreg tape to cover the entire laminate, and the mechanical properties between the laminates are weak

Method used

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  • Composite material interlaced structure, and stacking method thereof
  • Composite material interlaced structure, and stacking method thereof
  • Composite material interlaced structure, and stacking method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0097] Example 1: Quasi-isotropic interweave ply laminate (m=4, k=2, p=0)

[0098] Such as figure 1 As shown, the specific steps are as follows:

[0099] 1) Select flat mold and carbon fiber epoxy resin prepreg tape;

[0100] 2) Complete the laying of one prepreg tape in one belt at intervals of 45°, so as to cover the entire plane;

[0101] 3) Complete the laying of one prepreg tape at intervals of 90°, so as to cover the entire plane;

[0102] 4) Complete the laying of one prepreg tape at intervals of one belt at -45°, so as to cover the entire plane;

[0103] 5) Complete the laying of one prepreg tape at intervals of 0°, so as to cover the entire plane;

[0104] 6) Use the prepreg tape to cover the 45° prepreg tape for the interval bandwidth in step 2), so as to cover the entire plane;

[0105] 7) Use prepreg tape to cover the interval bandwidth of step 3) with 90° prepreg tape, so as to cover the entire plane;

[0106] 8) Use prepreg tape to cover the width of the in...

Embodiment 2

[0115] Embodiment 2: 2.5-dimensional laminated ring structure interwoven between asymmetric layers (m=3, k=2, p=1)

[0116] 1) Select the ring mold and carbon fiber epoxy resin prepreg tape;

[0117] 2) Complete laying of 1 prepreg tape with 1 width interval at 60° intervals, so as to cover the entire cylinder, recorded as 60 A ,Such as figure 2 shown;

[0118] 3) Lay one prepreg tape at intervals of one belt at -60°, so that the entire cylinder is covered, and it is recorded as -60 A ,Such as image 3 shown;

[0119] 4) Complete the laying of 1 prepreg tape at 0° intervals and 1 belt, so that the entire cylinder is covered, and it is recorded as 0 A ,Such as Figure 4 shown;

[0120] 5) Use prepreg tape to cover the width of the interval in step 2) with 60° prepreg tape, so that the entire cylinder is covered, and it is recorded as 60° B ,Such as Figure 5 shown;

[0121] 6) Use prepreg tape to cover the width of the interval in step 3) to -60° prepreg tape, so tha...

Embodiment 3

[0131] Embodiment 3: Interwoven 2.5-dimensional structure laminated board between symmetrical layers (m=3, k=2, p=1)

[0132] 1) Select flat mold and carbon fiber epoxy resin prepreg tape;

[0133] 2) With reference to the laying method of Example 2, complete an asymmetric interwoven laminate of a certain thickness, and the laying sequence is:

[0134] [±60 A / 0 A ][±60 B / 60 A / 0 B / -60 A / 0 A ] n-1 [±60 B ];

[0135] 3) Complete laying of 1 prepreg tape at intervals of 90°, so as to cover the entire plane, recorded as 90 A ;

[0136] 4) complete 0 B layer laying;

[0137] 5) Use prepreg tape to cover the width of the interval in step 4) with 90° prepreg tape, so that the entire plane is covered, and it is recorded as 90° B ;

[0138] 6) Follow step 2) to complete the laying of the symmetrical part of the interwoven ply board according to the mirrored ply sequence. The total ply sequence is:

[0139]

[0140] In this example n=4, the thickness of the part i...

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Abstract

The invention relates to a composite material interlaced structure, and a stacking method thereof, and belongs to the technical field of composite material manufacturing. A composite material interlaced structure stacked structure is composed of more than three laminated structure units via grid interweaving at different stacking directions; a conventional two dimensional stacked structure can bedeveloped to be a 2.5 dimensional stacked structure through adjusting of stacked layer interweaving sequence, the interlayer performance and impact strength are increased greatly; the angle of the laminated structure unit interweaving can be designed based on loading capacity, designability is achieved. The composite material interlaced structure can be applied in composite material impact resistant structures; compared with conventional weaved structures, the advantages are that: moulding quality is high, manufacturing efficiency is high, and manufacturing cost is reduced greatly.

Description

technical field [0001] The invention relates to a composite material interweaving structure and a laying method thereof, belonging to the technical field of composite material manufacturing. Background technique [0002] Advanced fiber-reinforced resin-based composites represented by carbon fiber-reinforced resin-based composites are widely used in aerospace, automotive, shipbuilding, civil engineering and other engineering fields due to their high specific strength, specific stiffness, and excellent corrosion resistance. Traditional fiber-reinforced resin-based composite laminates are laid with prepreg unidirectional tapes according to a certain layup sequence and angle, and are cured by heating and pressure. The traditional laminate is a typical two-dimensional structure, which is mainly carried by in-plane fibers. Since the strength of the fiber is much higher than that of the resin matrix, the interlayer performance of the laminate is weak, which easily leads to delamina...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B3/14B32B5/02B32B27/18
CPCB32B3/14B32B5/02B32B27/18B32B2262/101B32B2262/106
Inventor 刘永佼张建宝孙文文黄晓川王俊锋
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH