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Aerospace
Special Issues
Advanced Aircraft Composite Structure Design
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Advanced Aircraft Composite Structure Design

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: 30 November 2026 | Viewed by 632

Special Issue Editors

Dr. Wei Feng

E-Mail Website
Guest Editor
School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
Interests: composite damage; composite repair; adhesive bonding; environmental durability; similarity theory; failure mechanisms; creep; finite element modeling; impact behavior; cohesive zone model; water entry problems
Dr. Chao Zhang

E-Mail Website
Guest Editor
School of Aeronautics, Northwestern Polytechnical University, Xi'an, China
Interests: high temperature; high strain rate; ceramic matrix composites; joints; impact; dynamic damage

Special Issue Information

Dear Colleagues,

The past few decades have seen outstanding advances in the use of composite materials in the aerospace industry. Composites have revolutionized traditional design concepts and made possible an unparalleled range of new and exciting viable materials for aircraft structures.

This Special Issue, titled "Advanced Aircraft Composite Structure Design", focuses on the latest advancements and cutting-edge research that contribute to knowledge in the use of composite materials in aircraft structures. Original research papers and review articles dealing with design, research, and development studies, experimental investigations, theoretical analysis, and fabrication techniques relevant to the application of composites, ranging from individual components such as plates to complete composite structures, are welcome.

By bringing together advancements in the development, characterization, and application of composite materials, this Special Issue aims to disseminate knowledge between users, manufacturers, engineers, and researchers involved in aircraft component manufacturing using composite materials.

Dr. Wei Feng
Dr. Chao Zhang
Guest Editors

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 250 words) can be sent to the Editorial Office for assessment.

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

  • fiber-reinforced composite materials
  • functional and multi-functional composites
  • additive manufacturing of composites
  • finite modeling method
  • dynamic response of composite structures
  • composite maintenance and repair
  • hygrothermal aging
  • composite joints
  • extreme environment

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Further information on MDPI's Special Issue policies can be found here.

Published Papers (2 papers)

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Research

15 pages, 1975 KB  
Article
Post-Buckling Failure Mechanism and Optimal Tapered Termination Design for Composite Hat-Stiffened Panels
by Guofan Zhang, Chunhua Wan, Liang Chang and Xiaohua Nie
Aerospace 2026, 13(5), 467; https://doi.org/10.3390/aerospace13050467 (registering DOI) - 15 May 2026
Abstract
Composite hat-stiffened panels are widely used in civil aircraft structural design as typical closed-section stiffened components with high load-carrying efficiency. To accurately predict the post-buckling bearing capacity and optimize the tapered termination design of such panels, this paper investigates the failure process of [...] Read more.
Composite hat-stiffened panels are widely used in civil aircraft structural design as typical closed-section stiffened components with high load-carrying efficiency. To accurately predict the post-buckling bearing capacity and optimize the tapered termination design of such panels, this paper investigates the failure process of composite hat-stiffened panels with tapered ends through physical modeling and numerical analysis. A nonlinear failure analysis model is established by introducing the failure mechanisms of adhesive interfaces and composite laminates. The modeling method is verified against experimental results, showing discrepancies of 2.7% for buckling load and 3.5% for post-buckling failure load, respectively. Based on the validated numerical approach, parametric studies are carried out to analyze the effects of termination taper parameters on buckling and post-buckling mechanical behaviors. The results indicate that the termination taper design effectively adjusts the stiffness matching between stiffeners and skin and relieves local stress concentration. The optimal taper angle of 120° is recommended, where the failure load increases by 22% to 141.8 kN compared to the baseline configuration, significantly improving its post-buckling load-carrying capacity. The findings of this study can provide technical references for the design of stiffened composite panels with tapered stringer terminations in aerospace engineering. Full article
(This article belongs to the Special Issue Advanced Aircraft Composite Structure Design)
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13 pages, 12736 KB  
Article
Study on the Dynamic Mechanical Behavior of 2D C/SiC Composites at Medium Strain Rates
by Xinyue Zhang, Chao Zhang, Xiaochuan Liu, Chunyu Bai, Xulong Xi and Xiaocheng Li
Aerospace 2026, 13(2), 168; https://doi.org/10.3390/aerospace13020168 - 10 Feb 2026
Viewed by 353
Abstract
Two-dimensional C/SiC are promising candidates for use in high-temperature structures in aeroengines and thermal protection systems in the aerospace industry, which will be subjected to loads in various directions during service. In this paper, the in-plane tensile, compressive, and shear mechanical properties of [...] Read more.
Two-dimensional C/SiC are promising candidates for use in high-temperature structures in aeroengines and thermal protection systems in the aerospace industry, which will be subjected to loads in various directions during service. In this paper, the in-plane tensile, compressive, and shear mechanical properties of 2D C/SiC were investigated over a strain-rate range of 10−5 s−1 to 10 s−1. The failure mechanisms of the material under different loading conditions were analyzed. The study reveals that 2D C/SiC exhibits nonlinear stress–strain relationships under tension and shear, while it displays a linear stress–strain relationship under compression similar to the quasi-static loading state. The strain-rate strengthening effect is most pronounced under compression, whereas the effect is less significant under tensile loading. The reason for the observed increase in strength is the additional energy consumed by multiple crack initiation and propagation. A rate-dependent constitutive model was fitted, which agrees well with the experimental data for both tensile and shear loading conditions. Full article
(This article belongs to the Special Issue Advanced Aircraft Composite Structure Design)
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