Impact response modeling method for composite laminated plate

A composite material layer and modeling method technology, which is applied in the field of impact response modeling of composite material laminates, can solve the problems of damage process monitoring, dynamic response of laminated structures and complex failure process, and achieve the effect of improving accuracy

Inactive Publication Date: 2020-06-30
SHANDONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the anisotropy of composite laminates and the uneven distribution of stress under dynamic loading, the dynamic response and failure process of the laminated structure are very complicated, and it is difficult to accurately monitor the damage process by naked eyes or experiments.

Method used

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  • Impact response modeling method for composite laminated plate
  • Impact response modeling method for composite laminated plate
  • Impact response modeling method for composite laminated plate

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Experimental program
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Effect test

Embodiment 1

[0051]In this embodiment, a method for modeling the impact response of a composite laminate is provided, and the impact response of the composite laminate is analyzed by using the smoothed particle dynamics (Smoothed Particle Hydrodynamics, SPH) method. The modeling method includes the following steps:

[0052] Step 1: Calculate the Hertz contact stiffness k according to formula (1) c :

[0053]

[0054] Among them, R p ,E p and v p Respectively represent the punch radius, elastic modulus and Poisson's ratio, E T Indicates the modulus of elasticity of the outermost plate of the composite material laminate along the thickness direction;

[0055] Step 2: Obtain the indentation depth h of the composite material laminate c , and calculate the contact load F between the composite laminate and the impactor according to formula (2) imp :

[0056]

[0057] Step 3: according to formula (3) and (4), utilize the smooth particle dynamics SPH discretization method of Lagrangi...

Embodiment 2

[0087] This embodiment provides a method for modeling the impact response of a composite material laminate, wherein the composite material laminate is a square carbon fiber reinforced epoxy resin composite material laminate supported on four sides, and the impact object is a rigid ball, and the two collide. The relevant information of the punch and the laminate is shown in Table 2.1:

[0088] Table 2.1 Geometric dimensions and material parameters of punches and laminates

[0089]

[0090]In this embodiment, the laminate is a bounded flat plate. During impact contact, the shock wave encounters the boundary and is bounced back, which can be classified as a boundary-controlled shock problem. The high-order oscillations in the impact load history cannot be obtained with the infinite plate model, so this embodiment uses the finite element solution results for comparison. In the SPH model, 1 / 4 of the neutral plane is discretized into 26×26 particles, and the modeling method of ...

Embodiment 3

[0103] In this embodiment, a method for modeling the impact response of a composite laminate is provided, wherein the composite laminate is a carbon fiber double-horse resin composite laminate simply supported on four sides, and the impact object is a pointed punch. collision. The shapes and material properties of laminates and punches are given in Table 3.1.

[0104] Table 3.1 Geometric dimensions and material parameters of punches and laminates

[0105]

[0106] The finite element method uses 4-node, 48-degree-of-freedom hyperbolic quadrilateral shell elements. In this example, 16×16, 21×21, 26×26 and 41×41 SPH shell particles are respectively used to discrete the 1 / 4 neutral plane, and the geometric nonlinear SPH modeling method is used to analyze and calculate the impact damage and position. Figure 6 It is a schematic diagram of the impact damage outline and location, in which, the internal damage caused by the impact of composite laminates is obtained by ultrasonic ...

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Abstract

The invention relates to the field of materials, and provides a composite laminate impact response modeling method. The method comprises the following steps: calculating Hertz contact stiffness kc; acquiring the indentation depth hc of the composite material laminated plate, and calculating the contact load Fimp between the composite material laminated plate and an impacted object; employing a smooth particle dynamics SPH discretization method in a Lagrange form, and calculating the motion of the composite material laminated plate, and calculating the longitudinal acceleration of the punch. According to the relationship between the contact force and the indentation of the composite material laminated structure, the laminated plate impact response SPH model is established, the displacementchange of the laminated plate and the punch is analyzed, the damage form and the expansion mode of the laminated plate when the laminated plate is impacted are established, and the numerical monitoring of the impact response of the composite material layer is realized.

Description

technical field [0001] The invention relates to the field of material technology, and more specifically relates to a modeling method for impact response of composite material laminates. Background technique [0002] Composite materials have light density and high tensile strength, and are the structural materials with the highest specific strength currently available. In addition, composite materials also have the advantages of excellent energy absorption performance, high fatigue life and low manufacturing cost, and are widely used in aerospace, new energy, high-speed trains, marine engineering, energy-saving and new energy vehicles, and disaster prevention and mitigation, etc. field. The structural parts of composite materials used in the above fields are often subjected to low-speed or high-speed impacts of foreign objects during their work. Therefore, in the safety design of composite structures, damages under the impact of foreign objects must be considered, including ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F119/14
Inventor 李姣林军管延锦王广春赵国群富芳艳刘帅
Owner SHANDONG UNIV
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