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Fatigue of Aircraft Structures
Scopus
ISSN 2300-7591 · Sciendo · 134 artikel di indeks
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Artikel Jurnal
Building a Cad-Native Digital Twin for Ndt and Plm: Workflow, Tools, and Case Study
Digital twins (DTs) can connect inspection data with product models to support safer, more efficient lifecycle decisions. This paper proposes a CAD-native workflow for implementing a digital twin that visualizes and manages non-destructive testing (NDT) results directly on a 3D model. The method…
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Artikel Jurnal
Development of a Robust Multiaxial Fatigue Model for A/C Metallic Assemblies in an Industrial Context
In a context of growing importance of mass reduction and reliability of structures towards greener aircrafts, fatigue of metallic materials is a key issue in the structural optimization. The process used by aeronautic industrials to compute the fatigue life is often based on a large empirical…
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Artikel Jurnal
Random Vibration Fatigue Life Analysis of Aeroengine Bolts Using the Frequency-Domain Method
Bolt connections are widely used in aircraft engines due to their advantages of high stiffness, low weight, and ease of assembly and disassembly. However, they are subjected to complex stress states in service, including high preloads, combustion-induced forces, and random vibrations, which may…
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Artikel Jurnal
Weibull or Lognormal Distribution to Characterize Fatigue Life Scatter – Which is More Suitable? – Continued
This paper describes a study to determine whether fatigue test life scatter is best characterised by a Weibull or lognormal statistical distribution for a high strength steel used for landing gear structures. It is a response to “Face 2” of the ICAF 2017 Plantema Memorial Lecture and 2019 follow-up…
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Artikel Jurnal
Fatigue Life Estimation of the Critical Wing Structure in a New-Generation Stol Aircraft
The lower wing section of an aircraft is considered particularly vulnerable to fatigue failure due to the presence of inspection holes, which create stress concentrations and increase local stress in the surrounding material. This study estimates the fatigue life of the lower wing structure…
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Artikel Jurnal
Optimizing Inspection Intervals Through Risk Evaluation in Aircraft Structures
As aircraft fleets age, maintaining operational readiness at an affordable cost becomes increasingly challenging. This is largely due to the rise in Preventive Maintenance Task Requirements (PMTRs) outlined in the Aircraft Maintenance Program (AMP). While aging aircraft may require more frequent…
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Artikel Jurnal
Effect of Thermal and External Load on Mechanical Behaviour on CFRP/Aluminium Hybrid Joints
JAXA has been conducted the research to evaluate the fatigue life up to form a certain size of fatigue crack in a CFRP/Aluminum hybrid joint. Thermal stress occurs in the hybrid joints during operation due to the difference of coefficient of thermal expansion between Aluminum and CFRP. In ICAF2023…
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Artikel Jurnal
Bayesian-Informed Fatigue Life Prediction for Shallow Shell Structures
This study introduces a Bayesian-informed framework for fatigue life prediction in shallow shell structures. The methodology focuses on inferring the Equivalent Initial Flaw Size Distribution (EIFSD), a critical parameter for structural durability. Bayesian inference, combined with a Co-Kriging…
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Artikel Jurnal
On the Application of Laser Shock Peening as a Manufacturing and Repair Process to Improve the Fatigue Performance of Refill Friction Stir Spot-Welded AA2024-T3 Joints
The refill friction stir spot welding (refill FSSW) process is an innovative solid-state spot-welding method, which has evolved from the concept of friction stir welding. Compared to riveting, the process has the advantage of avoiding stress concentration by eliminating holes. In addition, weight…
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Artikel Jurnal
Residual Strength Analysis of a Composite Stiffened Panel After a Stiffener Debonding Using an Industrial Numerical Damage Model
The increasing demand for greener aviation technology has driven the adoption of advanced composite materials in aircraft structures, offering significant weight saving and fuel efficiency improvements. Wing structures made of torsion boxes composed of stiffened panels have shown over the decades…
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Artikel Jurnal
Fem Analysis of Residual Stresses in Welded Aluminum and Polyamide 6
Thermoplastic composites enable weldable, recyclable aircraft structures, but thermal mismatch between metals and polymers can introduce detrimental residual stresses. This study develops a finite element method (FEM) framework to predict residual stress fields in resistance-welded joints between…
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Artikel Jurnal
Baseline-Free Detection of Progressive Fatigue Damage Using Nonlinear Ultrasonic Guided Waves
Detecting fatigue-induced progressive damage under varying environmental conditions remains a major challenge in structural health monitoring (SHM). This study investigates a baseline-free nonlinear guided wave method, which extracts nonlinear parameters to detect fatigue cracks without requiring…
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Artikel Jurnal
Development of an Open-Source Robotic NDT Solution for Automated Composite Repair Testing
Non-destructive testing (NDT) plays an important role in aircraft maintenance and repair processes, ensuring the structural integrity necessary for safe operation. The paper presents the design and evaluation of an animated, low-cost robotic NDT system tailored for inspecting composite bonding…
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Artikel Jurnal
Investigating the Effects of Crack Orientation and Defects on Pipeline Fatigue Life Through Finite Element Analysis
In response to the steady rise in global demand for energy resources such as gas and oil, there is a pressing need to enhance the efficiency and safety of pipeline transportation systems. These systems, integral for transferring vast amounts of energy, must operate under increasingly higher…
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Artikel Jurnal
Using Corrosion Health Monitoring Systems to Detect Corrosion: Real-Time Monitoring to Maintain the Integrity of the Structure
This study investigates the use of Corrosion Health Monitoring (CHM) systems to detect and manage corrosion in aviation environments, with a specific focus on enclosed areas within aircraft structures. Corrosion poses significant risks to airport facilities and aircraft, and CHM systems offer…
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Artikel Jurnal
Some Comments Concerning the Preparation of and Fatigue Testing of the Aircraft’s Cable-Control System
The currently accepted rules that are applied to the aircraft cable-control systems’ operational use are based on the reactive maintenance idea and the comparative tests, inspections, and diagnostics performed at the mandatory intervals. Fatigue tests of the aviation cables are commonly conducted…
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Artikel Jurnal
Dynamic Testing and Fatigue Analysis of the I-31P Nose Landing Gear
The landing gear is a critical safety component of any aircraft, playing a key role in managing the significant loads experienced during landing and ground maneuvers. In the case of the I-31P aircraft, a redesign of the I-23 landing gear system, required comprehensive testing to validate its…
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Artikel Jurnal
Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer Aircraft
Military aircraft are subjected to highly variable and unpredictable loads due to diverse mission profiles, armament configurations, and individual piloting styles. This variability complicates the definition of precise load spectra, particularly in cases where data loss occurs due to Flight Data…
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Artikel Jurnal
X-Ray Diffraction Measurements for Inconel 718 Alloy Elements Created by Incremental Methods
The work presented is the result of the implementation of diffraction measurements: phase composition and stresses resulting from additive manufacturing process of nickel superalloy Inconel 718 components print. With the help of diffraction methodologies, the key parameters from the point of view…
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Artikel Jurnal
High-Temperature Fatigue Testing of Turbine Blades
This paper evaluates the efficacy of a patented grip for high-temperature fatigue testing by establishing the S-N curve for full-scale nickel-based turbine blades under simulated environmental conditions. Initially, a bending test assessed the stress-displacement characteristics of the component…