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Aerospace
Special Issues
Composites in Aerospace Application
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Composites in Aerospace Application

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

Deadline for manuscript submissions: closed (30 April 2023) | Viewed by 3165

Special Issue Editor

Dr. Hyunbum Park

E-Mail Website
Guest Editor
Department of Mechanical Engineering, Kunsan National University, 558 Daehak-ro, Miryong-dong, Gunsan 54150, Jeollabuk-do, Republic of Korea
Interests: composite material; structural design and analysis; optimal design; solid mechanics; FEM analysis; impact damage; failure criteria; manufacturing; structural test
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

I am pleased to announce a new open access Special Issue of the MDPI journal Aerospace dedicated to Composites in Aerospace Applications. The aim of this Special Issue is to collect the most recent research advancements in the field of aerospace engineering considering composite applications. As Guest Editor of this Special Issue, I kindly invite you to submit full research articles and review manuscripts addressing (but not limited to) the following topics:

  • Structural design of aircraft using composites
  • Optimal design of aircraft using composites
  • Structural analysis of design results
  • FEM analysis
  • Composite damage criteria
  • Application of fiber composites for aircraft
  • Application of sandwich composites for aircraft
  • Impact damage of aerospace structures
  • Composite specimen test of structural design for aerospace structures
  • Evaluation of mechanical properties using numerical methods for composite structures
  • Evaluation of mechanical properties using specimen tests for composite structures
  • Manufacturing processes of composite structures for aerospace engineering
  • Manufacturing methods of composite structures
  • Structural testing of aircraft

Prof. Dr. Hyunbum Park
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.

Published Papers (2 papers)

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Research

14 pages, 15231 KiB  
Article
Critical Assessment of the Bonded Single Lap Joint Exposed to Cyclic Tensile Loading
by Murat Demiral, Fethi Abbassi, Abolfazl Zahedi and Salih Akpinar
Aerospace 2023, 10(5), 454; https://doi.org/10.3390/aerospace10050454 - 15 May 2023
Viewed by 1113
Abstract
Single shear or single lap joints are the most prevalent type of adhesive joints used in advanced engineering applications, where they are exposed to fatigue loadings in their services. Although their mechanical performances under static loading have been investigated extensively, the studies related [...] Read more.
Single shear or single lap joints are the most prevalent type of adhesive joints used in advanced engineering applications, where they are exposed to fatigue loadings in their services. Although their mechanical performances under static loading have been investigated extensively, the studies related to the fatigue performances were limited. For that purpose, single lap joints’ (SLJs) reaction to fatigue tensile loading was studied by varying the adherend thickness (3 mm to 6 mm) and fatigue load (3250 N to 1500 N). ABAQUS/Standard was used to create its advanced FE model. To represent the progressive damage in the adhesive layer, the fatigue damage model via the Paris Law, which links the rate of the crack expansion to the strain energy release rate (SERR), was integrated into the cohesive zone model with bi-linear traction–separation characteristics. The model was written in a UMAT subroutine. The developed model was validated using experimental data from the literature. The crack initiation cycle (Ni), the failure cycle (Nf), the fatigue load limit, the strain energy release rate, the crack propagation rate, and variation of stress components with their dependency to design parameters were investigated in depth. It was found that the service life of the SLJs with thicker adherends was more responsive to the amount of stress applied. When exposed to lesser loads, the SLJs’ life span changed more noticeably. Full article
(This article belongs to the Special Issue Composites in Aerospace Application)
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15 pages, 2236 KiB  
Article
Closed-Form Analysis of Thin-Walled Composite Beams Using Mixed Variational Approach
by Jae Seong Bae and Sung Nam Jung
Aerospace 2022, 9(10), 576; https://doi.org/10.3390/aerospace9100576 - 4 Oct 2022
Viewed by 1496
Abstract
An analytical methodology is developed for thin-walled composite beams with arbitrary geometries and material distributions. The approach uses a mixed variational theorem which sets the shell displacements, and the shear stress resultants and hoop moments as the unknowns to obtain the stiffness constants [...] Read more.
An analytical methodology is developed for thin-walled composite beams with arbitrary geometries and material distributions. The approach uses a mixed variational theorem which sets the shell displacements, and the shear stress resultants and hoop moments as the unknowns to obtain the stiffness constants at the level of Timoshenko–Vlasov beam. All the field equations and the continuity conditions that should be satisfied over the shell wall are derived in closed form as the part of the analysis. Numerical simulations are conducted to show the validity of the proposed analysis. The comparison of the predicted stresses and the stiffness constants indicates close correlation with those of the detailed finite element (FE)-based analysis and up-to-date beam approaches. Symbolically generated stiffness constants and the sectional warping deformation modes of coupled composite beams are presented explicitly to illustrate the strength of the proposed theory. Full article
(This article belongs to the Special Issue Composites in Aerospace Application)
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