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Fiber layering and layer losing method for reinforcing composite material structure

A composite material and structural reinforcement technology, applied in the field of composite materials, can solve the problems of affecting the fatigue performance of the structure, weakening the strength and stiffness of the structure, and not giving a layer loss method, etc.

Pending Publication Date: 2021-08-27
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The researchers studied the influence of ply thickness and different ply angles on the mechanical properties of the composite material structure, but did not give a layer loss method. An inappropriate layer loss method will weaken the strength and stiffness of the structure. It is very likely that Cause the effect of stress concentration and affect the fatigue performance of the structure

Method used

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  • Fiber layering and layer losing method for reinforcing composite material structure
  • Fiber layering and layer losing method for reinforcing composite material structure
  • Fiber layering and layer losing method for reinforcing composite material structure

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Embodiment Construction

[0028] The technical solution of the present invention will be described in detail below, but the scope of the invention is not limited to the embodiment.

[0029] like figure 1 The flow chart of the present invention is shown, including the following steps:

[0030] Structure initial flooring is [45 / -45 / 0 / 90 / -45 / 90 / 45 / 90 / 0 / 90] s , Determine the fiber layers after composite structural reinforcement as follows

[0031]

[0032] like figure 1 As shown, the composite structural reinforced fiber laying and the lost layer method are divided into a U / 2M segment, and two layers per segment are blocked each other, and the two layers of opposite layers are configured.

[0033] like figure 2 As shown, in particular, the composite structural reinforced fiber layup and the loss layer method are mutated in an illustrated manner, i.e., the lost layer should be intervals.

[0034] like figure 2 As shown in, specifically, the composite structural reinforced fiber laying and loss layer...

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Abstract

The invention discloses a fiber layering and layer losing method for reinforcing a composite material structure, which relates to the field of typical structure layering design of aero-engine outer culvert casings. A certain number of layers are added at the position with weak mechanical property, so that the purpose of improving the mechanical property of the opening position and the mechanical connection position is achieved. According to the method, the influence of the angle of the lost layer, the position of the lost layer and the transition section of the lost layer is considered, and the integrity, continuity and symmetry of the structure are guaranteed. The mechanical property of the target part can be effectively improved, and the method has the advantages of being simple in design and high in applicability.

Description

Technical field [0001] The present invention belongs to the field of composite, and more particularly to a fiber paving and a sliding layer for composite structural reinforcement. Background technique [0002] The damage mechanism of the laminar structure of the cartridge composite is very complex, and the complexity is expressed in many ways, such as opening, mechanical connection, variable thickness, and initial layering, etc., the mechanical properties of the structure cannot be ignored. Aviation engine globes constitute a sensor, pipeline, and external accessories, brackets, and pipelines such as a hollow engine. Therefore, a number of openings and mounts are arranged on their housing. These holes cut a continuous long fiber, resulting in more complex pore stress distribution, and the composite material itself is a brittle material, and the stress concentration of the hole is more severe than other locations. In order to enhance the carrying performance of the structural open...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20
CPCG06F30/20
Inventor 胡恩如
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS