Special Issue "Structural Stability of Aerospace Structures"

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

Deadline for manuscript submissions: closed (30 April 2019)

Special Issue Editor

Guest Editor
Dr. Haim Abramovich

Technion—Israel Institute of Technology, Faculty of Aerospace Engineering, 32000 Haifa, Israel
Website | E-Mail
Interests: smart structures, piezoelectricity, energy harvesting using PZT, shape memory alloys (SMA), stability, vibration, buckling, thin walled structures behavior, dynamic behavior of structures, thermal buckling, laminated composite materials

Special Issue Information

Dear Colleagues,

Aerospace structures, be it a launcher, aircraft, or a space satellite, are lightweight structures, aimed at carrying the flight loads at minimal mass, to enable a viable economical usage. Under compression and/or shear forces, those structures are liable to buckling, changing their load carrying capacity.

Those structures are built from basic components, like beams (columns), plates, shells (cylindrical, conical, spherical) and panels. Other advanced components would include stiffened panels and stiffened shells, to increase their load carrying capacity at a relatively low addition of mass. While plates have a stable post-buckling behavior, shells would present a non-stable one, with a relatively large difference between the calculated and experimental buckling loads.

From the material point of view, Aerospace Structures have evolved from metal structures to laminated composite and/or sandwich-based structures, with the latest advancement being the variable angle tow (VAT) composites structures aimed at providing an optimal layup for increased load carrying capability at a reduced weight. The proposed Special Issue addresses this broad range of topics, and would welcome manuscripts on: (i) analytical and computational stability of aerospace structures, (ii) experimental results and procedures to increase the accuracy of the predicted buckling loads, (iii) numerical and experimental results of VAT composite structures, (iv) stability of lightweight structures in the presence of cutouts; and (v) behavior of aerospace structures under combined loadings. Any other related topics will also be most welcomed.

Prof. Haim Abramovich
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 papers will be 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 550 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

  • Beams
  • columns
  • plates
  • cylindrical shells
  • conical shells
  • spherical shells
  • panels
  • stringer stiffened panels
  • curved panels
  • stringer stiffened shells
  • grid stiffened shells
  • buckling
  • post-buckling
  • collapse
  • VAT composite structures
  • metal lightweight structures
  • sandwich structures
  • laminated composite thin walled structures
  • tests
  • numerical calculations
  • FE calculation
  • high-fidelity computational calculations

Published Papers (2 papers)

View options order results:
result details:
Displaying articles 1-2
Export citation of selected articles as:

Research

Open AccessArticle
A Numerical–Analytical Approach for the Preliminary Design of Thin-Walled Cylindrical Shell Structures with Elliptical Cut-Outs
Received: 5 March 2019 / Revised: 26 April 2019 / Accepted: 29 April 2019 / Published: 6 May 2019
PDF Full-text (6571 KB) | HTML Full-text | XML Full-text
Abstract
The presence of cut-outs within thin-walled shell structures is unavoidable, holes being needed for the passage of electrical cables, fuel, or just to reduce the weight of the components. Nevertheless, the high stress concentration can lead to a premature collapse of the structure. [...] Read more.
The presence of cut-outs within thin-walled shell structures is unavoidable, holes being needed for the passage of electrical cables, fuel, or just to reduce the weight of the components. Nevertheless, the high stress concentration can lead to a premature collapse of the structure. For this reason, the preliminary design of cylindrical shell structures with holes needs a profound knowledge of the stress distribution for different loading conditions and constraints. In this paper, a parametric study of a fiber-reinforced composite shell cylinder with an elliptical cut-out has been performed. Three different loading conditions were analyzed: Tension, bending, and torsion. Ansys® script, capable of easily generating and analyzing different geometrical configurations, was used to study the dependence of the geometry on the stress distribution near the cut-out. Finally, graphical and analytical relationships were tentatively extrapolated from numerical results, aimed at linking the geometrical parameters of the cut-out to the maximum stress near the cut-out. Full article
(This article belongs to the Special Issue Structural Stability of Aerospace Structures)
Figures

Figure 1

Open AccessArticle
Computational Analysis of Compressed Stiffened Composite Panels with Impact Damage
Received: 15 November 2018 / Revised: 9 February 2019 / Accepted: 15 February 2019 / Published: 27 February 2019
PDF Full-text (4908 KB) | HTML Full-text | XML Full-text
Abstract
A complex modeling technique is presented in this paper for a numerical analysis of compressed stiffened composite panels with impact damage. The numerical technique is based on the LS-Dyna code application, which simulates both the dynamic deformation of the panel subjected to a [...] Read more.
A complex modeling technique is presented in this paper for a numerical analysis of compressed stiffened composite panels with impact damage. The numerical technique is based on the LS-Dyna code application, which simulates both the dynamic deformation of the panel subjected to a local impact and the quasi-static uniform compression of the panel within the local damage zone. The technique has been validated by both impact and compression experimental tests of the stiffened composite panel. The obtained numerical results show that impact damage to the composite panel can reduce the carrying capacity in more than 50% of damaged panels compared to undamaged panels. Full article
(This article belongs to the Special Issue Structural Stability of Aerospace Structures)
Figures

Graphical abstract

Aerospace EISSN 2226-4310 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top