A Continuous Fiber Laminate with Variable Stiffness Composite

A composite material and continuous fiber technology, applied in the field of composite materials, can solve problems such as the unevenness of composite material layers, achieve broad application prospects and value, reduce manufacturing costs, and improve the effect of axial compression stability.

Active Publication Date: 2020-12-29
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Purpose of the invention: To propose a continuous fiber variable stiffness composite material layup to solve the problem that the discontinuous fiber intersects in the plane, resulting in the unevenness of the composite material layup

Method used

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  • A Continuous Fiber Laminate with Variable Stiffness Composite
  • A Continuous Fiber Laminate with Variable Stiffness Composite
  • A Continuous Fiber Laminate with Variable Stiffness Composite

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Embodiment Construction

[0022] A continuous fiber variable stiffness composite material layup, which is sequentially woven by a plurality of continuous variable angle fiber bundles, and a single fiber bundle forms a Z-shaped structure after two inflections.

[0023] The angle of the first straight segment (1) and the third straight segment (3) is the same, and the angle of the second straight segment (2) is different from the angle of the first straight segment (1) and the third straight segment (3), so that the same There are two elastic moduli in the layup to realize the change of the in-plane stiffness of the composite laminate structure; the angle between the first straight line segment and the second straight line segment of the fiber bundle and the angle between the second straight line segment and the third straight line segment The included angles are set as: 20-150 degrees.

[0024] On the basis of the above structure, the method of setting the fiber inflection radius R is as follows:

[00...

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Abstract

The invention belongs to the technical field of composite materials, and in particular relates to a continuous fiber variable stiffness composite material layup. It is woven by a plurality of continuous fiber bundles with variable angles. A single fiber bundle forms a Z-shaped structure after two inflections. The angles of the first straight line segment (1) and the third straight line segment (3) are the same. The angles of the two straight line segments (2) are different from the angles of the first straight line segment (1) and the third straight line segment (3), so that there are two elastic moduli in the same layer, and the in-plane rigidity of the composite laminate structure is realized. Change; the value of the included angle between adjacent straight line segments is: 20‑150 degrees. The invention solves the problem that the existing segmented fiber is discontinuous in the plane, and there is lamination at the intersection of two sections of fibers, which leads to the unevenness of the composite material laminate, and can simply and conveniently realize the in-plane The change of stiffness can effectively improve the axial compression stability of the laminate structure, and the processing and production are simple.

Description

technical field [0001] The invention belongs to the technical field of composite materials, and in particular relates to a continuous fiber variable stiffness composite material layup. Background technique [0002] At present, the composite material laminates widely used at home and abroad are unidirectional tapes or fabrics made of straight fibers, and the composite laminate structures designed and produced by straight fiber laminates are all in-plane structures with equal stiffness. [0003] Patent ZL201120515591.8 (fiber fabric with high buckling resistance) proposes a fiber with variable stiffness in the form of a sine curve or a cosine curve. This fiber is a fiber with a continuously variable angle, but it is necessary to ensure that the fiber remains sinusoidal in making this fiber. Or cosine curve, the processing is very difficult. At the same time, after optimization analysis, it is found that in the actual structural design, it is often not necessary for the fiber t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29B11/14
CPCB29B11/14B29C49/071B29C2949/0715
Inventor 赵占文苏雁飞
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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