Modeling and Simulation in Aerospace Composites

A special issue of Journal of Composites Science (ISSN 2504-477X). This special issue belongs to the section "Composites Modelling and Characterization".

Deadline for manuscript submissions: closed (15 February 2024) | Viewed by 1876

Special Issue Editors


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Guest Editor
1. Mare Engineering Group SPA, Via Ex Aeroporto s.n.c. c/o Consorzio Il Sole Lotto XI, 80038 Pomigliano d’Arco, NA, Italy
2. Department of Engineering, University of Campania “L. Vanvitelli”, Via Roma 29, 81031 Aversa, Italy
Interests: innovative vehicles; airworthiness; qualification methods; composites structure; aeroelasticity; crashworthiness; noise; MDO

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Guest Editor
Department of Airframe Design and Dynamics, The Italian Aerospace Research Centre (CIRA), 81043 Capua, CE, Italy
Interests: structures; composites; tiltrotors; structural modeling; aircraft & structures design; aeroelasticity

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Guest Editor

Special Issue Information

Dear Colleagues, 

Today, the use of composite materials and structures is a common practice in aerospace, especially in aeronautics. Modeling and simulation (M&S) have been widely used and increasingly improved over the years with the aims of supporting a more reliable design practice and to aid the products’ final qualification with respect to the authorities’ rules and guidelines. Scientists and engineers are constantly looking for a more digital qualification and certification exploring M&S advancements and high-fidelity approaches in several disciplines (structure strength, aeroelasticity clearance, internal noise, thermal effects, EMC, crashworthiness, etc.). Advanced M&S methods have demonstrated the ability to simulate highly complex composite systems’ behaviors, reducing the amount of physical testing. Such an approach requires the development of a credibility assurance framework (CAF) to support risk-informed applications of advanced M&S. This is a crucial research and innovation stream to make viable the M&S advanced methods for practical applications in aerospace composite. In addition, the current aerospace innovation topics are devoted to the development of greener aircraft and new systems for space exploration; thus, the M&S methods are required to take into account technical issues never considered before such as onboard cryogenic H2 tanks for greener aircraft and new type of ceramic composite for the thermal protections of spacecraft. 

We are pleased to invite you to contribute to this Special Issue your original and beyond state-of-the-art studies, methods, techniques, results and V&V experiences in aeronautical and space composite to improve the M&S methods for theoretical, numerical and practical point of views, with the aim of supporting the worldwide aerospace communities in making the whole development pathway of composite aircraft and spacecraft more reliable and affordable. 

This Special Issue aims to collect original and state-of-the-art studies, methods, techniques, and results including V&V experiences in aeronautical and space composite. 

In this Special Issue, original research articles and reviews are welcome. Research areas may include (but are not limited to) the following:

  1. Structures strength and buckling;
  2. Aeronautical virtual certification;
  3. Credibility assurance framework;
  4. Aeroelasticity and dynamics;
  5. Crashworthiness;
  6. Numerical formulations;
  7. Noise detection and reduction;
  8. Impact loads (e.g., bird strike and space debris);
  9. Hot structures and protection systems for re-entry spacecraft;
  10. Multi-disciplinary optimization;
  11. Electromagnetic compatibility;
  12. Lighting protection;
  13. Stealth capabilities;
  14. Low-weight structures. 

We look forward to receiving your contributions. 

Dr. Luigi Di Palma
Dr. Marika Belardo
Dr. Alessandro De Luca
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 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. Journal of Composites Science 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 1800 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

  • composites
  • structure
  • aeronautics
  • spacecraft
  • virtual certification
  • credibility assurance framework
  • aeroelasticity
  • dynamics
  • crashworthiness
  • FEM
  • BEM
  • FVM
  • noise
  • impact loads
  • bird strike
  • debris impact
  • hot structures
  • re-entry spacecraft
  • multi-disciplinary optimization
  • electromagnetic compatibility
  • lighting protection
  • stealth capabilities
  • low-weight structures

Published Papers (1 paper)

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Research

22 pages, 9294 KiB  
Article
Non-Linear Analysis in Post-Buckling Regime of a Tilt Rotor Composite Wing Structure Using Detailed Model and Robust Loading Approach
by Antonio Chiariello, Pasquale Vitale, Marika Belardo, Francesco Di Caprio, Mauro Linari, Claudio Pezzella, Jacopo Beretta and Luigi Di Palma
J. Compos. Sci. 2024, 8(1), 4; https://doi.org/10.3390/jcs8010004 - 22 Dec 2023
Viewed by 1434
Abstract
The design and development of a wing for a completely brand-new aircraft represents, in aeronautics, one of the highest challenges from an engineering point of view. The present work describes a novel methodology devoted to execute numeric simulation in a non-linear post-buckling regime [...] Read more.
The design and development of a wing for a completely brand-new aircraft represents, in aeronautics, one of the highest challenges from an engineering point of view. The present work describes a novel methodology devoted to execute numeric simulation in a non-linear post-buckling regime to verify the composite wing compliance under the design load conditions. The procedure was developed as part of a wing design and research activity and was motivated by the need to have more realistic results, without standard conservatisms like the no-buckling up to ultimate load, to be of use for achieving further weight savings. To carry this out, it was obviously necessary to ensure that the structural integrity was also guaranteed in the post-buckling regime, above the limit load, and therefore in a highly non-linear regime. The present work illustrates a numerical approach based on non-linear finite element analysis which uses the inertia relief option in order to have a more realistic representation of the structural response of the wing in its real context. All that represents a novelty since, at present, the commercial FE codes allow us to use the inertia relief option exclusively for linear analysis. Obviously, the approach can be applied to any other structural component with similar needs. The obtained results show that the differences between linear and non-linear regime are not negligible and, above all, that it is possible to design a wing (or other structural components) considering, at the same time, the large deformation due to the post-buckling regime, the material non-linearities due to the failures and any other non-linearities in order to achieve the challenging weight requirement of the new aircraft generation. Full article
(This article belongs to the Special Issue Modeling and Simulation in Aerospace Composites)
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