Comparative Study of Prediction Methods for Fatigue Life Evaluation of an Integral Skin-Stringer Panel under Variable Amplitude Loading

Šedek, Jakub; Růžek, Roman; Raška, Jan; Běhal, Jiří

doi:10.1016/j.proeng.2015.08.050

Cited by 9 publications

(4 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Some research achievements have been made in integral panel forming technology. Edek et al [1] studied the failure mode of the longitudinal beam wing plate of an aircraft under flight load, and analyzed the crack growth mechanism. Iuspa [2] designed a thin-walled structural wall panel with a free topology structure by using fast generation and parameterization methods and integrating the whole potential field irradiated by soft targets.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation study on progressive bending of magnesium alloy grid panel

Huang

Wang

Liang

et al. 2023

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

Research and development of magnesium alloy integral panel forming technology to replace existing titanium alloy and aluminum alloy panel materials are of great significance for saving aluminum and titanium resources. The material flow law during progressive bending technology of panel (PBTP) was analyzed by numerical simulation study. The deformation forming parameters of PBTP for Mg alloy grid panel and panel size control parameters are defined. The process parameters include deformation temperature, bending deformation coefficient, and reduction speed. The size and accuracy control parameters include the width of the bending die, pressing height, and feed rate. The panel radius was related to the width of the bending die and the height of the reduction. With increase of forming temperature, maximum damage coefficient, maximum equivalent stress and maximum equivalent strain reduce. With increase in bending deformation coefficient, maximum damage coefficient, maximum equivalent stress and maximum equivalent strain increase. Based on simulation and experimental results, reasonable forming parameters for PBTP of AZ31 Mg alloy grid panel was obtained. Magnesium alloy panel components were successfully processed by progressive bending technology. The influence of die width and pressing height on panel radius was analyzed. The numerical simulation results were consistent with experimental results. The maximum relative error was 3.5%.

show abstract

Section: Introductionmentioning

confidence: 99%

Numerical simulation study on progressive bending of magnesium alloy grid panel

Huang

Wang

Liang

et al. 2023

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

show abstract

“…Certification of any airframe structure can be performed by numerical or experimental methodology in accordance with airworthiness requirements. Although advanced numerical methods are very sophisticated, experimental verification of any primary structure through static and fatigue testing is still necessary [1]. Current airworthiness requirements specify to prove the durability of composite structure based on damage tolerance philosophy [2,3].…”

Section: Introductionmentioning

confidence: 99%

Non-destructive Inspection of Composite Aileron during Fatigue Test

et al. 2021

View full text Add to dashboard Cite

The operational safety and reliability of an airplane must be an integral part of its design. The use of suitable materials that pass material certification tests is very important for a new aircraft design. The next part is testing specific samples, sub-components, and components such as the aileron. The paper deals with a non-destructive evaluation of composite primary structural part fatigue tests in accordance with damage tolerance philosophy considering impact damage presence. NDT methods such as visual, eddy current, and ultrasonic testing included phased array technique, are used for the inspections. A schedule of inspections was created, and structural durability was verified.

show abstract

“…Yan Xiaozhong used the finite element software ABAQUS to set up a parameterized model of cracks in the integral panel of a typical aircraft, and analyzed the changes of stress intensity factors of cracks in the boss and rib during the crack growth process and the crack arrest performance [7]. Taking the commuter aircraft as an example, J. Sedek analyzed the crack growth under the action of section by section load, and predicted the crack growth using the linear damage accumulation principle and FASTRAN delay model [8]. M. Fossati demonstrated the application of numerical methods to evaluate the behavior of the longitudinal cracked plate on the whole machined surface, introduced the different finite element methods for a single cracked plate, and proposed an "analytical cycle method for predicting crack growth and residual strength in integral structures" [9].…”

Section: Introductionmentioning

confidence: 99%

Integral Aircraft Wing Panels with Penetration Cracks: The Influence of Structural Parameters on the Stress Intensity Factor

Gong

et al. 2020

Applied Sciences

View full text Add to dashboard Cite

The finite element model of integral wing panels with central penetration cracks under bending load was established, and the crack propagation process of the aircraft panel was simulated. The stress intensity factor (SIF) of the crack tip during crack propagation under varying conditions of crack length and panel structural parameters was determined. The effects of the panel structure parameters and crack size on the crack tip SIF were obtained. The regression analysis of the finite simulation element results has been performed and a regression model of SIF at the crack tip of the integral panel has been established, the determination coefficient of the regression model is 0.955.

show abstract

Comparative Study of Prediction Methods for Fatigue Life Evaluation of an Integral Skin-Stringer Panel under Variable Amplitude Loading

Cited by 9 publications

References 11 publications

Numerical simulation study on progressive bending of magnesium alloy grid panel

Numerical simulation study on progressive bending of magnesium alloy grid panel

Non-destructive Inspection of Composite Aileron during Fatigue Test

Integral Aircraft Wing Panels with Penetration Cracks: The Influence of Structural Parameters on the Stress Intensity Factor

Contact Info

Product

Resources

About