Special Issue "Modern Aerospace Materials"

A special issue of Metals (ISSN 2075-4701).

Deadline for manuscript submissions: 30 November 2018

Special Issue Editor

Guest Editor
Prof. Dr. Guillermo Requena

Department of Metallic Structures and Hybrid Materials Systems, Institute for Materials Research, German Aerospace Centre, Linder Höhe, 51147, Cologne, Germany
Website | E-Mail
Interests: light alloys; metals for additive manufacturing; three-dimensional material characterization; synchrotron tomography; high energy synchrotron diffraction; aluminum alloys; titanium alloys; magnesium alloys; titanium aluminides; metal matrix composites; phase transformations; relationships microstructure-properties; thermo-mechanical behavior of metals

Special Issue Information

Dear Colleagues,

Aerospace materials are a wide family, characterized by their applications under some of the most demanding mechanical, thermal, and thermo-mechanical service conditions. As such, their development has been accompanying technological breakthroughs along the last two centuries, e.g., the development of damage tolerant lightweight alloys contributed to the massification of civil air transport, superalloys are a must in modern jet engines and high temperature alloys are found in all rocket propulsion systems.

Nowadays, current trends in the frame of the so-called “Industry 4.0 revolution”, as well as strict regulations to decrease the ecological footprint of aircrafts, together with new space travel technologies such as reusable entry vehicles are further pushing the development of metal-based aerospace materials and structures and their corresponding manufacturing methods. This Special Issue is devoted to disseminate scientific and technological efforts in this context and it is, therefore, my pleasure to invite you to submit contributions dealing with the processing and behavior under service-relevant conditions of metal-based aerospace materials.

Prof. Dr. Guillermo Requena
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. Metals 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 1200 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

  • high temperature alloys
  • superalloys
  • lightweight alloys
  • fibre metal laminates
  • automatic manufacturing
  • additive manufacturing

Published Papers (3 papers)

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Research

Open AccessArticle An Equivalent Calculation Method for Press-Braking Bending Analysis of Integral Panels
Metals 2018, 8(5), 364; https://doi.org/10.3390/met8050364
Received: 17 April 2018 / Revised: 6 May 2018 / Accepted: 15 May 2018 / Published: 18 May 2018
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Abstract
Press-braking bending is widely applied in the manufacture of aircraft integral panels because of the advantages of strong adaptability to different contours, simplicity of bending tools, short manufacturing time and low process cost. However, a simulation of bending process requires long-time calculation and
[...] Read more.
Press-braking bending is widely applied in the manufacture of aircraft integral panels because of the advantages of strong adaptability to different contours, simplicity of bending tools, short manufacturing time and low process cost. However, a simulation of bending process requires long-time calculation and consumes extensive computational resources. Considering the factors that the original model (ORM) of an integral panel is large and the press-braking bending is used only for the local area of integral panels with heavy thickness in practice, an equivalent calculation method for press-braking bending analysis of integral panels is proposed. The local bending area of an integral panel is simplified to a model of plate in this method. An exponential strengthening model is used to derive the equations of stress, strain and forming radius of the ORM and its simplified model (SPM). Meanwhile, the equivalent parameters of the SPM are determined and deduced based on three principles: that the material begin to be yielded simultaneously, the ultimate stress of the ORM is the same as that of the SPM at the same punch displacement, and the forming radii of neutral surfaces of the ORM and the SPM are identical after springback. The distribution of the stress and strain determined by finite element (FE) simulations are compared, and the FE simulations indicate that the contour curve of the SPM is in fairly good agreement with the profile of the ORM under the same bending process parameters, and the maximum difference is 13.17%. The computational efficiency is increased by more than 48%. Therefore, the proposed approach is quite suitable for industrial applications to improve the bending quality and efficiency of integral panels. Full article
(This article belongs to the Special Issue Modern Aerospace Materials)
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Figure 1

Open AccessArticle Microstructure and Properties of Friction Stir Welded 2219 Aluminum Alloy under Heat Treatment and Electromagnetic Forming Process
Metals 2018, 8(5), 305; https://doi.org/10.3390/met8050305
Received: 25 March 2018 / Revised: 21 April 2018 / Accepted: 21 April 2018 / Published: 28 April 2018
PDF Full-text (3992 KB) | HTML Full-text | XML Full-text
Abstract
Among available processing technologies of heat-treatable aluminum alloys such as the 2219 aluminum alloy, the use of both friction stir welding (FSW) as joining technology and electromagnetic forming (EMF) for plastic formation technology have obvious advantages and successful applications. Therefore, significant potential exists
[...] Read more.
Among available processing technologies of heat-treatable aluminum alloys such as the 2219 aluminum alloy, the use of both friction stir welding (FSW) as joining technology and electromagnetic forming (EMF) for plastic formation technology have obvious advantages and successful applications. Therefore, significant potential exists for these processing technologies, both of which can be used on the 2219 aluminum alloy, to manufacture large-scale, thin-wall parts in the astronautic industry. The microstructure and mechanical properties of 2219 aluminum alloy under a process which compounded FSW, heat treatment, and EMF were investigated by means of a tensile test as well as via both an optical microscope (OM) and scanning electron microscope (SEM). The results show that the reduction of strength, which was caused during the FSW process, can be recovered effectively. This can be accomplished by a post-welding heat treatment composed of solid solution and aging. However, ductility was still reduced after heat treatment. Under the processing technology composed of FSW, heat treatment, and EMF, the forming limit of the 2219 aluminum alloy decreased distinctly due to the poor ductility of the welding joint. A ribbon pattern was found on the fractured surface of welded 2219 aluminum alloy after EMF treatment, which was formed due to the banded structure caused by the FSW process. Because of the effects of induced eddy current in the EMF process, the material fractured, forming a unique structure which manifested as a molten surface appearance under SEM observation. Full article
(This article belongs to the Special Issue Modern Aerospace Materials)
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Graphical abstract

Open AccessArticle Electromagnetic Forming Rules of a Stiffened Panel with Grid Ribs
Metals 2017, 7(12), 559; https://doi.org/10.3390/met7120559
Received: 11 October 2017 / Revised: 15 November 2017 / Accepted: 7 December 2017 / Published: 12 December 2017
Cited by 1 | PDF Full-text (10888 KB) | HTML Full-text | XML Full-text
Abstract
Electromagnetic forming (EMF), a technology with advantages of contact-free force and high energy density, generally aims at forming parts by using a fixed coil and one-time discharge. In this study, multi-stage EMF is introduced to form a panel with stiffened grid ribs. The
[...] Read more.
Electromagnetic forming (EMF), a technology with advantages of contact-free force and high energy density, generally aims at forming parts by using a fixed coil and one-time discharge. In this study, multi-stage EMF is introduced to form a panel with stiffened grid ribs. The forming rules of the stiffened panel is revealed via analyzing the distribution and evolution of the simulated stress and strain in the ribs and web, where the grid-rib panels were decomposed as the flat panel and two panels with uni-directional ribs (ribs only in X direction or Y direction). It is shown that the forming depth is mainly attributed to the forces on the web, although electromagnetic force is applied on both the ribs and the web, especially, large force on the ribs. The ribs are subjected to uniaxial stress parallel to their directions, and the web is subjected to plane stress in the deformation region. Furthermore, the change of the uniaxial stress characteristic in the X-direction ribs is influenced by the electromagnetic force, reverse bend and inertial effect. The plastic deformation mainly occurs in the Y-direction ribs of the deformation region under a three-direction strain state. Full article
(This article belongs to the Special Issue Modern Aerospace Materials)
Figures

Figure 1a

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