Abstract
A finite element (FE) modeling method with cohesive interface and sublaminates was proposed to study interlaminar stress distribution and strength of thick-section composite materials lug. And numerical calculation was carried out on the thick composite laminates three-point bending problem; effectiveness of modeling method for thick-section composite materials stress calculation was verified, Based on this, a three dimensional (3D) FE model of thick-section composite materials lug is designed; then the 3D stress distribution along the hole edge and failure mode of the lug subjected to axial load are discussed. The results and their analysis show preliminarily that: (1) the failure stress and damage position are mainly concentrated in the no contact region of the hole-axis; stiffer metal sleeves reduce the interlaminar stress concentrations of hole edge, however, this and higher radial tensile stresses in the region lead to reduced carrying capacity of the sleeves adhesive; (2) the adhesive of sleeves fails before the thick-section composites lug; this destroyed the integrity of the protective structure and will adversely affect the strength of the thick-section composites lug.
| Original language | English |
|---|---|
| Pages (from-to) | 9-13 |
| Number of pages | 5 |
| Journal | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| Volume | 33 |
| Issue number | 1 |
| State | Published - 1 Feb 2015 |
Keywords
- Bushing sleeve
- Calculations
- Composite materials
- Constitutive equations
- Design
- Efficiency
- Failure modes
- Finite element method
- Interlaminar stress
- Joints (structural components)
- Laminates
- Mathematical models
- Mesh generation
- Schematic diagrams
- Stiffness
- Stress concentration
- Three dimensional