| People | Locations | Statistics |
|---|---|---|
| Naji, M. |
| |
| Motta, Antonella |
| |
| Aletan, Dirar |
| |
| Mohamed, Tarek |
| |
| Ertürk, Emre |
| |
| Taccardi, Nicola |
| |
| Kononenko, Denys |
| |
| Petrov, R. H. | Madrid |
|
| Alshaaer, Mazen | Brussels |
|
| Bih, L. |
| |
| Casati, R. |
| |
| Muller, Hermance |
| |
| Kočí, Jan | Prague |
|
| Šuljagić, Marija |
| |
| Kalteremidou, Kalliopi-Artemi | Brussels |
|
| Azam, Siraj |
| |
| Ospanova, Alyiya |
| |
| Blanpain, Bart |
| |
| Ali, M. A. |
| |
| Popa, V. |
| |
| Rančić, M. |
| |
| Ollier, Nadège |
| |
| Azevedo, Nuno Monteiro |
| |
| Landes, Michael |
| |
| Rignanese, Gian-Marco |
|
Ataş, Akın
in Cooperation with on an Cooperation-Score of 37%
Topics
Publications (21/21 displayed)
- 2022Strain rate effect on the tensile properties of plain weave aramid, carbon, and glass fabric reinforced monolithic and hybrid compositescitations
- 2021Effect of quasi-static and intermediate strain rates on the tensile properties of hybrid polymer compositescitations
- 2018Bolted joints in quasi-unidirectional glass-fibre NCF composite laminatescitations
- 2018Compression after low velocity impact tests of marine sandwich composites: Effect of intermediate wooden layerscitations
- 2018Experimental investigation of pinned joints in NCF Glass-Fibre reinforced composite platescitations
- 2016Bolted joints in three axially braided carbon fibre/epoxy textile composites with moulded-in and drilled fastener holescitations
- 2016Damage and failure analysis of bolted joints in composite laminatescitations
- 2015Open hole compressive strength and damage mechanismscitations
- 2014Application of cohesive zone elements in damage analysis of compositescitations
- 2014Strength prediction of bolted joints in CFRP composite laminates using cohesive zone elementscitations
- 2013Subcritical damage mechanisms of bolted joints in CFRP composite laminatescitations
- 2013Failure analysis of bolted joints in cross-ply composite laminates using cohesive zone elements
- 2012Modelling delamination onset and growth in pin loaded composite laminatescitations
- 2012Effect of clamping force on the delamination onset and growth in bolted composite laminatescitations
- 2012Effect of geometric parameters on the stress distribution in Al 2024-T3 single-lap bolted jointscitations
- 2012Progressive failure analysis of bolted joints in composite laminatescitations
- 2012Strength prediction of bolted joints in cross-ply laminates based on subcritical damage modelling
- 2011A qualitative comparison of stresses at aircraft bolted joint holes under initial clamping forcecitations
- 2009Failure analysis of laminated composite plates with two parallel pin-loaded holescitations
- 2009The effect of curing conditions and fiber end shapes on the mechanical properties of compositescitations
- 2008İki eksenli gerilme altındaki kompozit plakalarda dairesel delik çevresindeki gerilme dağılımları
Places of action
| Organizations | Location | People |
|---|
article
A qualitative comparison of stresses at aircraft bolted joint holes under initial clamping force
Abstract
The stress state around the middle (skin) plate hole of double-lap single bolted joints are investigated under an initial clamping force. Two different materials are considered for the middle plate: a quasiisotropic carbon fiber reinforced plastic (CFRP) composite laminate and an aluminum alloy 7075-T6 plate. The outer (splice) plates are aluminum alloy 7075-T6 for both cases. The noncommercial FE code ANSYS vl2.0 is used for the analyses [1]. Linear solid brick elements are used to model the aluminum plates and the composite laminate. One element per layer approach is employed in through-the-thickness direction to model the laminated composite plate. The bolt and the washer are modeled as a single linear elastic deformable solid body. Surface-to-surface contact elements are used to define the contact behavior between the joint members including the effect of friction. Comparison of the stress results show that the clamping force has a significantly different effect for composite and aluminum plates. Initial clamping force introduces beneficial compressive stresses for aluminum plate whereas both tensile and compressive stresses occur for the composite laminate. The stress analysis results are used to explain the phenomena behind the different clamping force responses. © 2011 Published by Elsevier Ltd.