Strength Prediction Method of Composite Laminates with Hole Delamination Damage

A composite material layer and composite material technology, applied in the field of composite material detection, can solve problems such as deviation of simulation results

Active Publication Date: 2022-06-28
TIANJIN UNIV
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0004] At present, there are many research methods for the strength and damage prediction of composite laminates, but most of them assume that the laminates are defect-free, which leads to deviations between simulation results and reality.

Method used

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  • Strength Prediction Method of Composite Laminates with Hole Delamination Damage
  • Strength Prediction Method of Composite Laminates with Hole Delamination Damage
  • Strength Prediction Method of Composite Laminates with Hole Delamination Damage

Examples

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Embodiment

[0073]Step 1, according to the composite material constitutive model in the specific embodiment, this example utilizes the VUMAT user-defined subprogram interface in the ABAQUS software to define the constitutive model of the intra-layer element of the composite material and the constitutive model of the interlayer cohesive force element, And establish the corresponding two material properties in the software, and fill in in order according to the actual material mechanical properties parameters. In this example, the laminate is T700 carbon fiber reinforced epoxy resin composite material, and its specific mechanical property parameters are shown in Table 2.

[0074] Step 2: Establish a geometric model of the laminate according to the example of simulation analysis. This example model adopts a perforated laminate with a size of 300mm × 36mm × 3mm, the hole diameter is 6mm, and the thickness of the single layer is 0.125mm.

[0075] Table 2 Mechanical properties parameters of com...

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Abstract

The invention discloses a method for predicting the strength of a composite material laminated plate containing hole-making delamination damage. The main steps are: establishing the constitutive model of the inner unit and the interlayer unit of the composite material; using the VUMAT interface of ABAQUS to complete the inner unit and the interlayer unit of the composite material Write the constitutive model of the interlayer unit; establish the finite element model of the complete composite laminate and the composite laminate with delamination defects; establish boundary conditions for the laminate model, apply loads, and calculate the two models in ABAQUS The load-displacement curve and the overall damage value cloud map of the load application position. The invention can effectively predict the influence of different delamination defects on the strength of composite material laminates, has certain guiding significance for further establishing a reasonable hole-making quality evaluation index, and establishes a mapping relationship between hole-making technology and service performance.

Description

technical field [0001] The invention relates to a technology in the field of composite material detection, in particular to a method for strength prediction and damage analysis of a fiber-reinforced composite material laminate structure based on finite element simulation analysis. Background technique [0002] Compared with metal materials, composite materials have higher specific strength and specific modulus, and have significant advantages in corrosion resistance and fatigue resistance, so they have been widely used in the aerospace field. For aerospace structures, weight is an important factor affecting the fuel consumption rate of flying objects, and the extensive use of carbon fiber reinforced composite materials can optimize the weight of the aircraft structure without affecting the structural strength. As an important research method of composite materials, finite element simulation plays a very important role in the design and analysis of laminate components. The si...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F113/26G06F119/14
CPCG06F30/23G06F2113/26G06F2119/14
Inventor 秦旭达陈世广李皓李士鹏赵庆
Owner TIANJIN UNIV
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