Progressive damage analysis of composite bolted joints with liquid shim layers using constant and continuous degradation models

2010 ◽  
Vol 92 (2) ◽  
pp. 189-200 ◽  
Author(s):  
C. Hühne ◽  
A.-K. Zerbst ◽  
G. Kuhlmann ◽  
C. Steenbock ◽  
R. Rolfes
Keyword(s):  
Bolted Joints ◽  
Progressive Damage ◽  
Damage Analysis ◽  
Degradation Models

scholarly journals Thermal Mismatch Effect and High-Temperature Tensile Performance Simulation of Hybrid CMC and Superalloy Bolted Joint by Progressive Damage Analysis

2020 ◽  
Vol 2020 ◽  
pp. 1-14
Author(s):  
Shuyuan Zhao ◽  
Jianglong Dong ◽  
Chao Lv ◽  
Zhengyu Li ◽  
Xinyang Sun ◽  
...  
Keyword(s):  
Thermal Expansion ◽  
High Temperature ◽  
Transportation Systems ◽  
Bolted Joints ◽  
Failure Behavior ◽  
Progressive Damage ◽  
Damage Analysis ◽  
New Findings ◽  
Tensile Performance ◽  
High Temperature Tensile

The hybrid CMC and superalloy bolted joints have exhibited great potential to be used as thermostructural components of reusable space transportation systems, given the respective strengths of these two materials. In the high temperature excursion of the hybrid joints with the aircrafts and space vehicles, the substantial difference in thermal expansion coefficients of CMC and superalloy materials will induce complex superposition of initial assembly stress, thermal stress, and tensile stress around fastening area, which might lead to unknown failure behavior of joint structure. To address this concern, a finite element model embedded with progressive damage analysis was established to simulate the thermostructural behavior and high-temperature tensile performance of single-lap, single-bolt C/SiC composite and superalloy joint, by using the ABAQUS software. It was found that the initial stiffness of the CMC/superalloy hybrid bolted joints decreases with the rise of applied temperature under all bolt-hole clearance levels. However, the load-bearing capacity varies significantly with the initial clearance level and exposed temperature for the studied joint. The thermal expansion mismatch generated between the CMC and superalloy materials led to significant changes in the assembly preload and bolt-hole clearance as the high-temperature load is applied to the joint. The evolution in the thermostructural behavior upon temperature was then correlated with the variations in stiffness and failure load of the joints. The provided new findings are valuable for structural design and practical application of the hybrid CMC/superalloy bolted joints at high temperatures in next-generation aircrafts.

Temperature effects on joint strength and failure modes of hybrid aluminum–composite countersunk bolted joints

2019 ◽  
Vol 233 (11) ◽  
pp. 2204-2218 ◽  
Author(s):  
Calin-Dumitru Coman ◽  
Dan Mihai Constantinescu
Keyword(s):  
Temperature Effects ◽  
Failure Modes ◽  
Testing Machine ◽  
Material Model ◽  
Bolted Joints ◽  
Progressive Damage ◽  
Damage Analysis ◽  
Bearing Failure ◽  
Aluminum Composite ◽  
Damage Initiation

This paper presents the effects of temperature on the damage initiation and growth in the carbon fiber-reinforced polymer composite laminate of a hybrid aluminum–composite countersunk bolted joints designed for the bearing failure mode. Strain gage measurements conducted using an Instron testing machine coupled to a temperature-controlled chamber together with a detailed three-dimensional finite element model incorporating geometric, material and friction-based full contact nonlinearities are used to investigate the temperature effects on the progressive damage analysis of the orthotropic material model. The progressive damage analysis material model integrates the lamina nonlinear shear deformation, Hashin-type failure criteria and strain-based continuum degradation rules, being developed using the UMAT user subroutine in the MSC Patran-Nastran (MSC Software Corporation) commercial software. The results showed that the temperature effects on damage initiation and failure modes are quite accurately predicted by the progressive damage analysis material model, which proved to be computationally efficient and therefore can predict failure propagation and damage mechanisms. A low temperature increases the limit and ultimate forces and produces net-section failure, while a high temperature favors a bearing failure and even shear-out of the composite adherend of the hybrid aluminum–composite countersunk bolted joint.

Effect of Bolt Tightness on the Behavior of Composite Joints

2006 ◽  
Vol 129 (1) ◽  
pp. 43-51 ◽  
Author(s):  
Sayed A. Nassar ◽  
Vinayshankar L. Virupaksha ◽  
Saravanan Ganeshmurthy
Keyword(s):  
Finite Element ◽  
Element Model ◽  
Optical Microscope ◽  
Analytical Investigation ◽  
Bolted Joints ◽  
Progressive Damage ◽  
Damage Analysis ◽  
Bolted Joint ◽  
Composite Joint ◽  
Lap Shear

This study provides an experimental and analytical investigation of the behavior of a double bolted single lap shear composite joint. Various scenarios of bolt tightness are considered for composite-to-composite and composite-to-aluminum bolted joints. Progressive damage analysis is provided for the composite coupons in two regions; namely, the surface under bolt heads and near the contact with the shank of the bolt; the damage analysis is performed using an optical microscope. Four tightening configurations are used in the testing of each double bolted joint. These configurations permit each of the two bolts to be either tight or loose. The analytical part of the study utilizes a 3-D finite element model that simulates the bolt tightness and the multilayered composite coupons. The experimental and finite element results are correlated.

Progressive Fatigue Damage Simulation in Laminated Composites Based on Explicit Finite Element Formulation

2019 ◽  
Vol 64 (2) ◽  
pp. 1-12
Author(s):  
Yuri Nikishkov ◽  
Guillaume Seon ◽  
Andrew Makeev
Keyword(s):  
Finite Element ◽  
Laminated Composites ◽  
Test Methods ◽  
Remaining Useful Life ◽  
Image Correlation ◽  
Progressive Damage ◽  
Damage Analysis ◽  
Explicit Finite Element ◽  
Analysis Methods ◽  
Open Hole

Advanced polymeric composites are playing a major role in designing high-performance and lightweight vertical lift structures. However, uncertain residual strength and remaining useful life of the composite rotor and airframe structures due to complexity of failure mechanisms and susceptibility to manufacturing irregularities, which may be precursors to structural damage, impose risks that cannot be mitigated exclusively by time-consuming and costly experimental iterations. Validated analysis techniques accelerating design, certification, and qualification of composite structures are needed. Our team has been taking essential steps toward improving confidence in material qualification for laminated composites. The first step started with our reduced lamina test methods, short-beam shear, and small-plate twist based on digital image correlation measuring as a subset the standard material properties and, in addition, key properties that cannot be currently measured using any standard test methods. The lamina properties provide essential material input data for laminate analysis. The laminate analysis was the second step increasing confidence in material qualification. A known weakness of the existing progressive damage analysis methods is the lack of effective techniques to predict ultimate failure. The newly developed methodology relies on explicit finite element modeling and eliminates convergence issues in the ply-level progressive damage analysis methods due to severe nonlinear discontinuities after propagation of damage beyond detectable size. This work shows results of applying this methodology to nanosilica-toughened IM7/PMT-F3GHT open-hole tension strength/fatigue, open-hole compression strength/fatigue, and bearing strength multidirectional laminate configurations. The ability to predict progression of damage from initiation to ultimate strength and fatigue for advanced material systems including IM7/PMT-F3GHT carbon/epoxy reinforced by nanosilica has been demonstrated for the first time.

Progressive damage analysis of composite structures using higher-order layer-wise elements

2020 ◽  
Vol 190 ◽  
pp. 107921 ◽  
Author(s):  
M.H. Nagaraj ◽  
J. Reiner ◽  
R. Vaziri ◽  
E. Carrera ◽  
M. Petrolo
Keyword(s):  
Composite Structures ◽  
Higher Order ◽  
Progressive Damage ◽  
Damage Analysis
Sign in / Sign up

Export Citation Format

Share Document