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Aerospace
Special Issues
Fatigue Damage and Fracture Analysis of Aerospace Metal Materials
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Fatigue Damage and Fracture Analysis of Aerospace Metal Materials

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: 31 October 2025 | Viewed by 2644

Special Issue Editor

Dr. Zhixin Zhan

E-Mail Website
Guest Editor
School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China
Interests: damage mechanics; finite element analysis; mechanics of materials; solid mechanics; mechanical behavior of materials; failure analysis; plasticity; finite element modeling; fatigue of materials; fatigue; fracture analysis
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

This Special Issue seeks to delve into the advanced study of how aerospace-grade metals withstand the unique stresses and environmental conditions encountered during flight and space missions. Aerospace materials are required to perform reliably under high fatigue and immense pressures, making it critically important to understand their failure mechanisms both for safety and technological advancement. We invite researchers to submit original research articles, reviews, and technical notes that explore the intricate behaviors of metals under cyclic stress and the subsequent onset of fractures. Topics of interest include microscopic and macroscopic failure analyses, stress and strain assessments, crack propagation studies, and the influence of environmental factors such as temperature and corrosion on a material’s performance. Contributions may also include innovative approaches to improving material design, predictive modeling of life expectancy, and new methodologies for detecting and analyzing material defects. This Special Issue aims to gather groundbreaking research that can contribute to safer, more efficient aerospace designs and operations.

Dr. Zhixin Zhan
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Keywords

  • aerospace materials
  • fatigue damage
  • crack propagation
  • environmental effects
  • microstructural analysis
  • fatigue life prediction
  • non-destructive testing
  • computational modeling
  • advanced material design

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Published Papers (2 papers)

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Research

23 pages, 10747 KiB  
Article
Numerical Prediction of Fatigue Life for Landing Gear Considering the Shock Absorber Travel
by Haihong Tang, Panglun Liu, Jianbin Ding, Jinsong Cheng, Yiyao Jiang and Bingyan Jiang
Aerospace 2025, 12(1), 42; https://doi.org/10.3390/aerospace12010042 - 11 Jan 2025
Viewed by 865
Abstract
Due to the complexity of the landing gear’s (LG) structural integrity and its loads under various static or dynamic working conditions, the fatigue life assessment for LG is a highly challenging task. On the basis of the whole geometric model of a large [...] Read more.
Due to the complexity of the landing gear’s (LG) structural integrity and its loads under various static or dynamic working conditions, the fatigue life assessment for LG is a highly challenging task. On the basis of the whole geometric model of a large passenger aircraft’s main landing gear (MLG), the quasi-static finite element model (FEM) of the whole MLG is established, and the high-cycle fatigue issue of the Main Fitting (MF) is studied by considering the variation in shock absorber travel (SAT). Firstly, the ground loads under actual fatigue conditions are equivalently converted into the forces acting on the center of the left and right axles of the MLG, and based on these spatial force decompositions, the magnitude and direction of the load for 12 different basic unit load cases (ULC) are obtained. That is, the stress of the MLG under actual fatigue conditions can be obtained by superimposing these ULCs. Then, considering that the SAT of the MLG varies under different fatigue conditions, and to reduce the number of finite element (FE) simulations, this article simplifies all the SAT experienced by the MLG into seven specific values, so as to establish seven quasi-static FEMs of the MLG with the specified stroke of the shock absorber. In this way, the fatigue stress of the MLG with any actual SAT can be obtained by interpolating the stress components of the seven FEMs. Only 84 FE simulations are needed to efficiently obtain the fatigue stress spectra from the ground load spectra. Finally, according to the material S-N curve and Miner’s damage accumulation criterion, evaluate the fatigue life of the Main Fitting. The results of the stress component interpolation and superposition method show that at least five different SATs of the whole MLG’s FEM are needed to effectively convert the fatigue loads into a stress spectrum. The fatigue life prediction results indicate that the minimum lifespan of the MF is 53164 landings, which means that the fatigue life meets the requirement design. Full article
(This article belongs to the Special Issue Fatigue Damage and Fracture Analysis of Aerospace Metal Materials)
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25 pages, 13646 KiB  
Article
Chatter and Surface Waviness Analysis in Oerlikon Face Hobbing of Spiral Bevel Gears
by Jingchao Wang, Jun Qian, Kaifeng Huang, Zhentao Shang and Jianwu Yu
Aerospace 2024, 11(7), 535; https://doi.org/10.3390/aerospace11070535 - 28 Jun 2024
Viewed by 1386
Abstract
A vectorized analytical model for the cutting dynamics in the spiral bevel gear face hobbing process has been developed, which is based on machine tool kinematics and vibration vectorization. The structural modal parameters of the cutter head spindle system are obtained through experimental [...] Read more.
A vectorized analytical model for the cutting dynamics in the spiral bevel gear face hobbing process has been developed, which is based on machine tool kinematics and vibration vectorization. The structural modal parameters of the cutter head spindle system are obtained through experimental modal analysis with hammer impact testing. The analytical model is utilized to simulate the generation of simulated vibration acceleration signals during spiral bevel gear hobbing. A wavelet threshold denoising method is applied to process the simulated vibration signals of the spiral bevel gear face hobbing with added white noise. Signal processing methods, including short-time Fourier transform are employed for time-domain analysis, frequency-domain analysis, and time–frequency-domain analysis of measured signals and simulated signals, thereby extracting the corresponding statistical features. In addition to the results of the experimental modal analysis, the causes of chatter in spiral bevel gear hobbing are discussed in detail, revealing that the main factor is cutter head vibration in the Y direction of the Hunan ZDCY CNC EQUIPMENT YKA2260 machine tool used in this research. The error in the time-domain characteristic parameters between simulated signals and measured vibration acceleration signals is within 15%, with a difference of 3.5% in spectral peak values. The predicted tooth surface morphology from simulation matches the actual morphology on the workpiece, comprehensively validating the reliability of the cutting dynamics model for the spiral bevel gear face hobbing process. Another conclusion drawn from numerical simulation experiments is that the amount of tooth surface waviness of the spiral bevel gears is the ratio of tool chatter frequency to cutting fundamental frequency. Full article
(This article belongs to the Special Issue Fatigue Damage and Fracture Analysis of Aerospace Metal Materials)
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