Hybrid interlayer crack propagation analysis method for composite laminated plate

A composite material layer and crack propagation technology, which is applied in the field of hybrid interlayer crack growth analysis of composite material laminates, can solve the problem of large error between the predicted value of the critical energy release rate and the experimental value

Pending Publication Date: 2020-04-24
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

When the interlaminar crack length exceeds the half-length of the specimen, the load in the middle of the specimen has a closing effect on the crack component of the DC

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  • Hybrid interlayer crack propagation analysis method for composite laminated plate
  • Hybrid interlayer crack propagation analysis method for composite laminated plate
  • Hybrid interlayer crack propagation analysis method for composite laminated plate

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Embodiment Construction

[0128] In order to make the object, technical scheme and effect of the present invention clearer and clearer, the following examples are given to further describe the present invention in detail. It should be pointed out that the specific implementation described here is only used to explain the present invention, not to limit the present invention.

[0129] Analysis of pure mode I crack growth of DCB specimens:

[0130] The mechanical properties of the composite material system used in the sample and the geometric dimensions of the sample are shown in Table 1 and Table 2.

[0131] Step 1, DCB test is carried out according to the ASTM D5528 standard. The schematic diagram of the specimen loading process is shown in Figure 6, and the load-displacement curve during the crack growth process is recorded.

[0132] Table 1 Mechanical properties of HTA6376 / C composite single-layer board

[0133]

[0134] Table 2 Geometric dimensions of test piece

[0135]

[0136] In step 2,...

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Abstract

The invention discloses a hybrid interlayer crack propagation analysis method for a composite laminated plate, and relates to the field of composite material laminated plate interlayer failure, the analysis method comprises the following steps: 1, establishing a laminated plate model containing general layered cracks; 2, a single DCB test piece crack propagation analysis model is established; 3, establishing a single ENF test piece crack propagation analysis model; and 4, establishing a crack propagation analysis model of the mixed crack MMB test piece; the method disclosed by the invention issuitable for analyzing the crack propagation process of the composite material laminated plate test piece in a single and mixed layered fracture mode; rigid body rotation around a simply supported constraint point at the right end of a test piece and a softening behavior of a crack tip are simultaneously considered in a mixed fracture mode, and the method can accurately and reliably predict a general mixed layered crack propagation behavior, is suitable for engineering practice, and provides a reliable cross inspection tool for numerical simulation at the same time.

Description

technical field [0001] The invention relates to the field of interlayer failure of composite material laminates, in particular to a hybrid interlayer crack propagation analysis method for composite material laminates. Background technique [0002] Composite material structures in practical engineering applications are mostly typical thin-walled structures. Under external loads, such as bending, impact, in-plane compressive loads or residual stress in the manufacturing process, composite material structures are prone to delamination damage. Delamination damage is mainly caused by interlayer normal stress and shear stress of composite materials, and usually occurs in areas with large stress gradients such as interlayers at different ply angles, ribs, and joint positions. To maximize the design capability of composite structures, it is important to develop effective and reliable delamination damage prediction methods. Although experimental studies are of great value and necess...

Claims

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Application Information

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IPC IPC(8): G06F30/20G06F30/23
Inventor 邓健尹乔之彭昂
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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