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Aerospace
Special Issues
Crashworthiness Design for Aviation Safety
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Crashworthiness Design for Aviation Safety

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

Deadline for manuscript submissions: closed (31 July 2020) | Viewed by 31298

Special Issue Editors

Dr. Michele Guida

E-Mail Website
Guest Editor
Department of Industrial Engineering - Aerospace Branch, University of Naples Federico II, Via Claudio, 21 80125 Naples, Italy
Interests: crashworthiness; dynamic impact; biomechanics; structural dynamic; multibody and vehicle dynamics
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Francesco Marulo

E-Mail Website
Guest Editor
Department of Industrial Engineering, Aerospace Division, University of Naples “Federico II”, Via Claudio 21, 80125 Naples, Italy
Interests: vibroacoustics, noise control, damping, crashworthiness; impact dynamics; bird strike; biomechanics; structural dynamic; multibody and vehicle dynamics

Special Issue Information

Dear Colleagues,

The subject of this Special Issue is dedicated to the important topics of the passenger’s passive safety and the research for the improvement of aeronautical structures in presence of high dynamic transient loads. Papers eligible for this Special Issue should refer to the development and validation of advanced crashworthiness concepts and design methods able to increase the level of safety. Special attention will also be devoted to papers dealing with advanced crashworthiness research able to improve safety with minimal cost and weight increases and compliant with a specified certification process. The focus can be extended to materials and their capability to absorb deformation energy, design methods allowing deformation paths which save the passenger, and restraint systems that save human lives and avoid fatal injuries to occupants. These objectives may be obtained through a strong numerical and experimental correlation considering the passenger and their safety as the main reference parameter.

Authors are invited to submit full research articles and review manuscripts addressing (but not limited to) the following topics:

  • Biomechanical investigation;
  • Design of energy-dissipating structure;
  • Modelling strategies for numerical simulation;
  • Identification of optimal topologies for crashworthiness;
  • Numerical study of injury prevention for the occupants seated in aircraft.

Dr. Michele Guida
Prof. Dr. Francesco Marulo
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. 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

  • aerospace
  • automotive
  • crashworthiness
  • low-velocity impact
  • high-velocity impact
  • bird strike
  • aircraft safety certification issue

Published Papers (5 papers)

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Research

21 pages, 8036 KiB  
Article
A Numerical Investigation on Stress Modal Analysis of Composite Laminated Thin Plates
by Yadong Zhou, Youchao Sun and Weili Zeng
Aerospace 2021, 8(3), 63; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace8030063 - 04 Mar 2021
Cited by 6 | Viewed by 2661
Abstract
Because of the light weight and high strength, composite laminates have many advantages in aircraft structures; however, they are frequently subjected to severe dynamic loadings during flight. To understand the dynamic properties of composite laminated thin plates at the stress scale, this paper [...] Read more.
Because of the light weight and high strength, composite laminates have many advantages in aircraft structures; however, they are frequently subjected to severe dynamic loadings during flight. To understand the dynamic properties of composite laminated thin plates at the stress scale, this paper studies the stress modal analysis (SMA) of composite laminated thin plates by finite element method (FEM). Firstly, the basic theory on SMA of composite laminates was given from the classical displacement modal analysis. Secondly, a square laminated thin plate was numerically studied to obtain some distribution laws of the stress mode shapes (SMSs) from the layup and stress component perspectives. Then, based on the characteristics of SMSs in different plies, a modified layup configuration was conducted for possible lower magnitude and more uniform distributions of SMSs. Results indicate that ±45° layups can improve the performance of SMSs of the square plate, without excessively decreasing the modal frequencies. Such fact manifests that ±45° layups are critically vital for the dynamic stress reduction of the square composite laminated plates. Modal participation factor and strain energy were evaluated to assist the determination of critical modes. Lastly, the aspect ratio of the composite plate on layup design was considered. Numerical investigation in this study can serve as a preliminary step of SMSs perspective for the analysis and optimization of dynamic composite laminates. Full article
(This article belongs to the Special Issue Crashworthiness Design for Aviation Safety)
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25 pages, 13661 KiB  
Article
Interface Failure of Heated GLARETM Fiber–Metal Laminates under Bird Strike
by Md.Zahid Hasan
Aerospace 2020, 7(3), 28; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace7030028 - 17 Mar 2020
Cited by 9 | Viewed by 4011
Abstract
Many high-strength composite materials have been developed for aircraft structures. GLAss fiber REinforced aluminum (GLARE) is one of the high-performance composites. The review of articles, however, yielded no study on the impact damage of heated GLARE laminates. This study, therefore, aimed at developing [...] Read more.
Many high-strength composite materials have been developed for aircraft structures. GLAss fiber REinforced aluminum (GLARE) is one of the high-performance composites. The review of articles, however, yielded no study on the impact damage of heated GLARE laminates. This study, therefore, aimed at developing a numerical model that can delineate the continuum damage of GLARE 5A-3/2-0.3 laminates at elevated temperatures. In the first stage, the inter-laminar interface failure of heated GLARE laminate had been investigated at room temperature and 80 °C. The numerical analysis employed a three-dimensional GLARE 5A-3/2-0.3 model that accommodated volumetric cohesive interfaces between mating material layers. Lagrangian smoothed particles populated the projectile. The model considered the degradation of tensile and shear modulus of glass fiber reinforced epoxy (GF/EP) at 80 °C, while incorporated temperature-dependent critical strain energy release rate of cohesive interfaces. When coupled with the material particulars, an 82 m/s bird impact at room temperature exhibited delamination first in the GF/EP 90°/0° interface farthest from the impacted side. Keeping the impact velocity, interface failure propagated at a slower rate at 80 °C than that at room temperature, which was in agreement with the impact damage determined in the experiments. The outcomes of this study will help optimize a GLARE laminate based on the anti-icing temperature of aircraft. Full article
(This article belongs to the Special Issue Crashworthiness Design for Aviation Safety)
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14 pages, 4921 KiB  
Article
SPH-FEM Design of Laminated Plies under Bird-Strike Impact
by Yadong Zhou, Youchao Sun and Tianlin Huang
Aerospace 2019, 6(10), 112; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace6100112 - 07 Oct 2019
Cited by 15 | Viewed by 6124
Abstract
Composite laminates can potentially reduce the weight of aircrafts; however, they are subjected to bird strike hazards in civil aviation. To handle their nonlinear dynamic behaviour, in this study, the impact damage of composite laminates were numerically evaluated and designed by means of [...] Read more.
Composite laminates can potentially reduce the weight of aircrafts; however, they are subjected to bird strike hazards in civil aviation. To handle their nonlinear dynamic behaviour, in this study, the impact damage of composite laminates were numerically evaluated and designed by means of smoothed particle hydrodynamics (SPH) and the finite element method (FEM) to simulate the interaction between bird projectiles and the laminates. Attention was mainly focused on the different damage modes in various laminates’ plies induced by bird impact on a square laminated plate. A continuum damage mechanics approach was exploited to simulate damage initiation and evolution in composite laminates. Damage maps were computed with respect to different ply angles, i.e., 0°, 45° and −45°. The damage distributions were comparatively investigated, and then the ply design was considered for crashworthiness improvement. The results aim to serve as a design guideline for future prototype-scale bird strike studies of complex laminated structures. Full article
(This article belongs to the Special Issue Crashworthiness Design for Aviation Safety)
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12 pages, 2220 KiB  
Article
Development of a Head Injury Criteria-Compliant Aircraft Seat by Design of Experiments
by Giuseppe Lamanna, Amalia Vanacore, Michele Guida, Francesco Caputo, Francesco Marulo, Bonaventura Vitolo and Salvatore Cicatiello
Aerospace 2019, 6(9), 95; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace6090095 - 03 Sep 2019
Cited by 9 | Viewed by 6822
Abstract
This paper deals with the redesign of an aircraft passenger seat, placed at the first seat row, which was not compliant with Federal Aviation Regulations FAR 25.562 “Emergency landing dynamic conditions” regulation (due to a high value for the Head Injury Criterion (HIC)) [...] Read more.
This paper deals with the redesign of an aircraft passenger seat, placed at the first seat row, which was not compliant with Federal Aviation Regulations FAR 25.562 “Emergency landing dynamic conditions” regulation (due to a high value for the Head Injury Criterion (HIC)) and related guidelines. Starting from an accurate analysis of some results obtained via an experimental seat sled test, a numerical procedure was developed in order to improve the passenger safety with respect to head injury. Specifically, the proposed numerical procedure, using the advantages of a Finite Element (FE) model and a Design of Experiment (DoE) approach for simulation modeling, was aimed at identifying a new design solution to avoid the impact between the passenger’s head and the bulkhead. The redesign of the passenger seat was validated against an experimental test carried out at Geven S.p.A. Company by demonstrating, consequently, the compliance of the modified seat-belt system with the regulations. Full article
(This article belongs to the Special Issue Crashworthiness Design for Aviation Safety)
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14 pages, 7294 KiB  
Article
An Insight on the Crashworthiness Behavior of a Full-Scale Composite Fuselage Section at Different Impact Angles
by Aniello Riccio, Salvatore Saputo, Andrea Sellitto, Angela Russo, Francesco Di Caprio and Luigi Di Palma
Aerospace 2019, 6(6), 72; https://0-doi-org.brum.beds.ac.uk/10.3390/aerospace6060072 - 18 Jun 2019
Cited by 30 | Viewed by 10603
Abstract
In the present paper, advanced numerical methodologies have been adopted to investigate the influence of impact angle on the crashworthiness behavior of a composite fuselage section. The analyzed fuselage section, made of unidirectional fiber-reinforced material, woven fabric material, and aluminum material, is representative [...] Read more.
In the present paper, advanced numerical methodologies have been adopted to investigate the influence of impact angle on the crashworthiness behavior of a composite fuselage section. The analyzed fuselage section, made of unidirectional fiber-reinforced material, woven fabric material, and aluminum material, is representative of a regional aircraft fuselage. Two different angles of impact with rigid ground have been investigated and reported: Perpendicularly to the ground and with a pitch angle of 3 degrees with respect to the ground. The adopted numerical models have been preliminarily validated with experimental data from a drop test on a full-scale fuselage section, in terms of deformations and failure location and progression. The correlation between the numerical model and the experimental test has enabled evaluation of the effect of the impact angle on the deformation and damage in the sub-cargo floor area. Full article
(This article belongs to the Special Issue Crashworthiness Design for Aviation Safety)
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