Two-stage fatigue life evaluation of an aircraft fuselage panel with a bulging circumferential crack and a broken stringer

Date

2014-05-01

Author

Sayar, B.
Kayran, Altan

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

201
views

0
downloads

The article presents two-stage fatigue life evaluation of a stiffened aluminium aircraft fuselage panel, subject to ground-air-ground pressure cycles, with a bulging circumferential crack and a broken stringer. As a worst-case scenario, it is assumed that double cracks start at the edge of a rivet hole both in the skin and in the stringer simultaneously. In the first stage, fatigue crack growth analysis is performed until the stringer is completely broken with the crack on the fuselage skin propagating. After the stringer is completely broken, the effect of bulging crack on the fatigue life of the panel is investigated utilizing the stress intensity factors determined by the three-dimensional finite element analyses of the fuselage panel with the broken stringer. It is concluded that bulging of the skin due to the internal pressure can have significant effect on the stress intensity factor, resulting in fast crack propagation after the stringer is completely broken.

Subject Keywords

Damage tolerance, Broken stringer, Pressurized aircraft fuselage, Fatigue life, Stress intensity factor, Bulging crack, Fatigue crack growth

URI

https://hdl.handle.net/11511/34444

Journal

FATIGUE & FRACTURE OF ENGINEERING MATERIALS & STRUCTURES

DOI

https://doi.org/10.1111/ffe.12127

Collections

Department of Aerospace Engineering, Article

Suggestions

OpenMETU
Core

Development of a regression model for the fatigue life assessment of open-hole specimens with double through the thickness cracks Heidari Shabestari, Seyed Sohrab; Kayran, Altan; Department of Aerospace Engineering (2019) This thesis mainly deals with the investigation of the fatigue crack growth characteristics of open rivet holes in aluminum 2024-T3 material. In this respect, most commonly observed type of cracks emanating from rivet holes, namely, double through the thickness edge cracks with centered configurations has been considered. Stress intensity factors and the fatigue lifes are calculated analytically and also with the Extended Finite Element Method (XFEM).Analytical calculations have been carried out using the c...
An enhanced analytical model for residual stress prediction in machining Lazoglu, I.; Ulutan, D.; Alaca, B. E.; Engin, S.; Kaftanoglu, B. (2008-01-01) The predictions of residual stresses are most critical on the machined aerospace components for the safety of the aircraft. In this paper, an enhanced analytic elasto-plastic model is presented using the superposition of thermal and mechanical stresses on the workpiece, followed by a relaxation procedure. Theoretical residual stress predictions are verified experimentally with X-ray diffraction measurements on the high strength engineering material of Waspaloy that is used critical parts such as in aircraft...
Analysis of the thermoviscoplastic behavior of [0/90] SCS-6/timetal®21S composites Çöker, Demirkan; Nicholas, Theodore (1996-01-01) Micromechanical modeling is used to determine the stresses and strains due to both mechanical and thermal loads in [0/90] titanium matrix composites (TMCs) subjected to cooldown from the processing temperature and subsequent thermomechanical fatigue (TMF) loading conditions. The [0/90] composite is treated as a material system composed of three constituents: fiber and matrix in the [0] ply, and a [90] ply. The [0/90]s layup is modeled by a uniaxial stress rule of mixtures model for the [0] ply and adding a ...
Development of a computer program for the analysis of fatigue crack growth Dalgıç, Ali Murtaza; Bilir, Ömer Gündüz; Kadıoğlu, Suat; Department of Mechanical Engineering (2002) In this study, a computer program is developed for fatigue crack propagation analysis of metal alloys and random fiber composites. The developed program takes the fatigue crack propagation experiment data in the form of crack length vs. number of cycles from the user. The user also, selects the crack geometry and defines loading conditions of the test specimen. Developed program analyze the experimental data and evaluates crack growth rate and stress intensity range. For the calculated or ready crack growth...
A simplistic flight model for exergy embodiment of composite materials towards nearly-zero exergy aviation Kilkis, Birol; Kilkis, San; Kılkış, Şiir (2019-01-01) In this paper, a new model for the embodied exergy payback period is presented, which considers the exergy savings during acceleration and take-off, climb, trim-level cruise, descent and thrust reversal in landing for each flight versus higher exergy embodiment of composites that are used during manufacturing when compared to metals. The research work has ramifications for determining the optimum balance of lightweight and conventional material usage, thus improving the economic and environmental performanc...

Citation Formats

B. Sayar and A. Kayran, “Two-stage fatigue life evaluation of an aircraft fuselage panel with a bulging circumferential crack and a broken stringer,” FATIGUE & FRACTURE OF ENGINEERING MATERIALS & STRUCTURES, pp. 494–507, 2014, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/34444.