Fatigue crack growth under flight spectrum loading with superposed biaxial loading due to fuselage cabin pressure

Sunder, R.; Ilchenko, B. V.

doi:10.1016/j.ijfatigue.2010.11.018

Cited by 27 publications

(10 citation statements)

References 15 publications

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“…Less data are available on multiaxial loading, and most of it concerns combined tension and shear, rather than biaxial tension, partly because of the challenges involved in conducting cyclic biaxial tension tests. Biaxial tension can be applied to cruciform specimens loaded in two orthogonal directions, 1‐3 circular or elliptical plates submitted to biaxial bending 4‐6 and tubular specimens loaded in tension and internal pressure 7,8 . The effect of biaxial tension on fatigue lives was reported to be beneficial 9,10 or detrimental 11,12 or neutral 13 depending on the load biaxiality ratio.…”

Section: Introductionmentioning

confidence: 99%

Corrosion‐fatigue behaviour of Cr–Mo steel under biaxial tension

Gaur

Doquet

Persent

et al. 2020

Fatigue Fract Eng Mat Struct

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Combined cyclic tension and internal pressure tests with various proportions of each loading were run on a 2.5%Cr-1%Mo steel in air and in 3.5% NaCl solution, with and without cathodic protection to investigate the effect of positive stress biaxiality on corrosion-fatigue lives and damage mechanisms. At free potential, a strong reduction in fatigue resistance was observed for uniaxial as well as for equibiaxial cyclic tension and attributed to multiple crack initiation from corrosion pits. Cathodic protection completely cancelled the detrimental effect of the corrosive environment on fatigue lives whatever the load biaxiality was, in spite of an obvious enhancement of intergranular fracture attributed to hydrogen embrittlement.

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Section: Introductionmentioning

confidence: 99%

Corrosion‐fatigue behaviour of Cr–Mo steel under biaxial tension

Gaur

Doquet

Persent

et al. 2020

Fatigue Fract Eng Mat Struct

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“…The authors concluded that structural health management (SHM) system was a cheap and viable solution to detect faults in the structure of the fuselage, acting as a maintenance system. R. Sunder et al [13] identified the general lack of consensus in analytical studies on fatigue crack growth when exposed to biaxial loading caused by cabin pressure in the fuselage. This inability or lack thereof reproducible and digitally controlled system to test this phenomenon persuaded them to construct a standardized experimental setup and investigate for the circumferential crack progression in fuselages of aircrafts.…”

Section: Experimental Analysis Of Aircraft Fuselagementioning

confidence: 99%

“…Experimental load frame setup for the application of biaxial forces on a fuselage cross section [13]. …”

mentioning

confidence: 99%

Recent Developments of an Aircraft Fuselage along Theoretical, Experimental and Numerical Approach - A Review

Potty¹,

Angelo²,

Rao

et al. 2019

ujme

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Expressed in nature's infinite subtleties, the Fuselage draws its inspiration from the streamlined body of a bird or a fish, channelizing the flow of air around, enabling its ease in flight. Spanning most of the aircrafts structure, it plays a crucial role in the ferrying of people and cargo, simultaneously balancing the shears due to the empennage and wing structures all in mid-air. Its structural integrity is often questioned by failures due to load or bad air during maneuvers, causing instability which has led many to intensively explore and develop an ideal fuselage. The behaviour of the fuselage is crucially determined by the structural integrity and aerodynamic performance. This paper is an attempt at collating the recent technological advances pertaining to the fuselage. We've streamlined and categorised the wide-ranging scholarly articles by three fundamentally varying approaches-Theoretical, Experimental and Numerical. The theoretical approach saw the authors test out their hypothesis by utilizing and constructing various mathematical models using scientific principles with no verification by actual experimentation or simulation work. The experimental approach pertains to those papers whose authors devised experiments, whose data was used to draw distinct conclusions. The numerical approach mainly dealt with heavy computational analysis using FEM and CFD analysis. Therefore, this paper serves as a compendium for researchers and developers attempting to familiarise themselves with the current advancements and developments in domain of fuselage technology.

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“…Some early studies have shown that the fatigue crack growth rate in the in‐plane direction is dependent on the biaxial stress state near the crack tip(s). Recently, the crack growth mechanism of aluminum AA5083‐H116 was examined under an in‐plane biaxial tension‐tension fatigue under ambient laboratory and saltwater environments.…”

Section: Introductionmentioning

confidence: 99%

An online‐offline prognosis model for fatigue life prediction under biaxial cyclic loading with overloads

Datta

Chattopadhyay

et al. 2019

Fatigue Fract Eng Mat Struct

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This paper presents a robust online‐offline model for the prediction of crack propagation under complex in‐phase biaxial fatigue loading in the presence of overloads of different magnitudes. The online prognosis model comprises a combination of finite element analysis and data‐driven regression to predict the crack propagation under constant loading, while the offline model is trained using experimental data to inform the post‐overload crack growth retardation behavior to the online model. The developed methodology is validated by conducting biaxial fatigue experiments using aluminum AA7075‐T651 alloy cruciform specimens. A close correlation is observed between the experimental results and model predictions. The results show that the model successfully predicts the crack retardation behavior under the influence of overloads with different magnitudes occurring at different stages of fatigue crack growth. Error analysis is conducted to investigate the sensitivities of the number of training points and crack increments to the prediction accuracy. In addition, the error propagation with respect to the crack length is studied, which provides constructive suggestions for further model improvement.

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Fatigue crack growth under flight spectrum loading with superposed biaxial loading due to fuselage cabin pressure

Cited by 27 publications

References 15 publications

Corrosion‐fatigue behaviour of Cr–Mo steel under biaxial tension

Corrosion‐fatigue behaviour of Cr–Mo steel under biaxial tension

Recent Developments of an Aircraft Fuselage along Theoretical, Experimental and Numerical Approach - A Review

An online‐offline prognosis model for fatigue life prediction under biaxial cyclic loading with overloads

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