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Method for analyzing residual compression strength of composite materials after impact damage

A composite material, compressive strength technology, applied in special data processing applications, instruments, electrical digital data processing, etc.

Active Publication Date: 2016-12-07
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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  • Method for analyzing residual compression strength of composite materials after impact damage
  • Method for analyzing residual compression strength of composite materials after impact damage
  • Method for analyzing residual compression 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] like 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 mode...

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Abstract

The invention belongs to the field of structural damage tolerance design of composite materials, and specifically relates to a method for analyzing residual compression strength of composite materials after impact damage; and the method is used for determining the residual compression strength of composite materials after impact damage. The method comprises three steps of 1, selecting a Hanshin failure criterion as a damage failure criterion for low-speed impact of a laminated plate according to failure characteristics of a composite material; 2, importing the Hanshin failure criterion by adopting a large-scale dynamic finite element program DYTRAN, so as to calculate a damage area under the low-speed impact of the laminated plate; and 3, carrying out rigidity attenuation on a damage area after the low-speed impact according to the damage area determined in the second step, and calculating the residual compression strength of the laminated plate after the low-speed impact by adopting a global-local model analysis method. The invention discloses a brand new analysis method, so that the residual strength of typical components of composite materials after impact damage can be effectively predicted, and basis is provided for the structural design, analysis and verification of the composite materials of airplanes.

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 Applications(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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