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Concrete exhibits specific behaviors under different compressive loads. Understanding this is crucial for understanding its structural integrity. When concrete undergoes uniaxial compression, it tends to develop cracks that run parallel to the direction of the force. These parallel cracks stem from localized tensile stresses that occur perpendicular to the compression direction. Additionally, angled cracks may appear due to the formation of shear planes.
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A material's elastic behavior is characterized by the disappearance of stress once the load is removed, allowing the material to return to its original state. However, when stress surpasses the yield point, yielding commences, marking the onset of plastic deformation or permanent set. This change from elastic to plastic behavior is influenced by the peak stress value and the duration before the load is removed. An intriguing observation occurs when a specimen is loaded, unloaded, and...
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Normal strain under axial loading is an important concept in the field of mechanics of materials. Axial loading implies the application of a force along the axis of a material, like a column or bar. This force can either compress or stretch the material. In the context of axial loading, normal strain is the deformation experienced by the material in the direction of the loading force. It's calculated as the change in length divided by the original length of the material. This unitless ratio...
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Updated: May 20, 2025

Cutting Procedures, Tensile Testing, and Ageing of Flexible Unidirectional Composite Laminates
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A Study on the Failure Behavior and Force Transmission of Composite Skin-Stringer Structures Under a Compressive

Guoyang Zhao1, Jian Shi2, Wei Xu1

  • 1School of Aviation Maintenance Engineering, Chengdu Aeronautic Polytechnic, Chengdu 610100, China.

Materials (Basel, Switzerland)
|March 27, 2025
PubMed
Summary

A new model accurately predicts failure in carbon fiber composite aircraft structures. This research enhances understanding of load-bearing capacities and failure mechanisms in skin-stringer components.

Keywords:
Hashin initiation criteriaTserpes degradation lawcomposite skin-stringer structuresfailure analysisload transfer

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Area of Science:

  • Materials Science
  • Mechanical Engineering
  • Aerospace Engineering

Background:

  • Carbon fiber-reinforced composites are crucial for aircraft structures, enhancing performance and safety.
  • Understanding the load-bearing capacity and failure mechanisms of composite skin-stringer structures is vital for structural integrity.

Purpose of the Study:

  • To develop and validate a novel computational model for analyzing the complex failure and load transmission behavior of T800/3900S-2B fiber-reinforced composite skin-stringer structures under compressive loading.

Main Methods:

  • Experimental compression strength tests were performed on a composite stringer/skin structure.
  • A three-dimensional Finite Element Method (FEM) model was developed using Abaqus/Standard 2022.
  • The FEM incorporated modified 3D Hashin initiation criteria and the Tserpes degradation law via a UMAT subroutine to simulate in-plane ply and interlaminar damage.

Main Results:

  • The developed FEM model showed high similarity with experimental data for load-displacement curves.
  • Simulated failure modes, including matrix compressive cracking, fiber compressive failure, and fiber-matrix shear-out failure, closely matched experimental observations.
  • The model effectively captured complex failure and load transfer phenomena in the composite skin-stringer structures.

Conclusions:

  • The study presents an efficient and accurate FEM model for simulating composite skin-stringer structures.
  • This model significantly advances the understanding and prediction of failure and load transfer in these critical aircraft components.
  • The validated model can aid in the design and safety assessment of composite aerospace structures.