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A Method for Analyzing the Residual Compressive Strength of Composite Materials After Impact Damage

A composite material, impact damage technology, used in instrumentation, computing, electrical digital data processing, etc.

Active Publication Date: 2019-11-15
HARBIN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Before this analysis method is successfully studied, there is no suitable analysis method that can comprehensively consider the influence of factors such as the change of layup and thickness of the composite structure and the combination of loads on the residual strength of compression after low-velocity impact

Method used

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  • A Method for Analyzing the Residual Compressive Strength of Composite Materials After Impact Damage
  • A Method for Analyzing the Residual Compressive Strength of Composite Materials After Impact Damage
  • A Method for Analyzing the Residual Compressive Strength of Composite Materials After Impact Damage

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Embodiment Construction

[0035] Residual strength analysis of aircraft rudder composite laminates after impact damage.

[0036] 1 Aircraft Rudder Composite Laminate Information

[0037] Typical layup: (±45) / 0 2 / (0,90) / 0 / (±45) / 0 / (0,90) / 0 2 / (±45)

[0038] Thickness: 2.427mm

[0039] 2 Determine the impact energy and punch diameter

[0040] The impact object is a steel ball with a diameter of 12.7 mm, the mass of the impact object is 5.5 kg, and the impact energy is 4.45 J / mm.

[0041] 3 Establish impact damage calculation model

[0042] Such as figure 1 As shown, the size of the laminated plate is 150mm*100mm, and 4-node shell elements are used for simulation, and the impact object is simulated by rigid body elements. In order to improve the simulation accuracy, the mesh is refined in the impact center area. The laminate boundary is simply supported on four sides, with adaptive master-slave contact between the impact ball and the laminate. In order to comprehensively characterize the failure m...

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Abstract

The invention belongs to the field of damage tolerance design of composite material structures, and in particular relates to an analysis method for residual compressive strength of composite materials after impact damage, and is an analysis method for determining residual compressive strength of composite materials after impact damage. The present invention comprises 3 steps, the first step selects the Hanshin failure criterion as the damage failure criterion of the laminated plate low-velocity impact according to the failure characteristics of the composite material; the second step adopts the large-scale dynamic finite element program DYTRAN, introduces the Hanshin failure criterion, and calculates the laminated plate low-velocity impact The damage area under impact; in the third step, according to the damage area determined in the second step, the stiffness of the damaged area after low-velocity impact is attenuated, and the residual compressive strength of the laminate after low-velocity impact is calculated using the global-local model analysis method. The invention proposes a brand-new analysis method, which can effectively predict the residual strength of typical components of composite materials after impact damage, and provides a basis for the design, analysis and verification of aircraft composite material structures.

Description

technical field [0001] The invention belongs to the field of damage tolerance design of composite material structures, and is an analysis method for determining the residual compressive strength of composite materials after impact damage. Background technique [0002] Composite materials are very sensitive to low-velocity impact damage of many types of foreign objects, and low-velocity impact will greatly weaken the pressure-bearing capacity of composite laminate structures. At present, for the damage tolerance analysis of composite materials with barely visible impact damage, the method of setting the allowable strain is generally adopted in China, and the residual compressive strength of the laminate after impact is calculated according to the set allowable strain. Before this analysis method is successfully studied, there is no suitable analysis method that can fully consider the influence of factors such as the change of layup and thickness of the composite structure and...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 韩刘温永海云庆文齐德胜张震徐忠岩朱洪艳李世峰南力强张野印明勋
Owner HARBIN
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