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Pomigliano d'Arco, Italy

Iannone M.,Alenia Aeronautica
AIP Conference Proceedings | Year: 2010

Cooling rate of semicrystalline thermoplastic (PEEK) based composite parts has been assessed by means of a thermal flow model. Cold tool thermoforming was found suitable for thin parts, but the use of a preheated tool is suggested. Cooling rate is critical for automated lay-up; consequently the optimization of this technique requires the use of a complex apparatus, able to provide both heating of the part during lay-up and a control of the cooling rate. Alternatively a modified cooling rate vs. crystallinity behavior of the material must be achieved. © 2010 American Institute of Physics. Source

Feminella F.,Alenia Aeronautica
SAE International Journal of Aerospace | Year: 2011

This paper presents a model of semi-quantitative analysis for risks and their associated impact caused by aeronautical suppliers in charge of specific work-packages (WP). Considering that many approaches to supply chain risk evaluation are qualitative (consequently subjective) and restricted to few functional areas of the supplier, the paper defines fifteen areas of functionality (production, finance, quality human resources etc.) for the supplying company. It then identifies specific risks for each area and measures them through predictive indicators. Therefore, taking in account the WP characteristics (size, technology, delivery and quality constraints, etc.), drivers are defined to evaluate the impact associated with each risk. The model is applied to the case of a supplier delivering structural parts. Finally, contingency actions to overcome the identified risks are illustrated and discussed. © 2011 SAE International. Source

Zammit Mangion D.,University of Malta | Becouarn L.,Thales Alenia | Dominici J.,Thales Alenia | Fabbri M.,Alenia Aeronautica | Bader J.,Diehl Aerospace
11th AIAA Aviation Technology, Integration,and Operations (ATIO) Conference, including the AIAA Balloon Systems Conference and 19th AIAA Lighter-Than-Air Technology Conference | Year: 2011

This paper presents a cockpit display concept that proposes to make use of rear-projection technology to generate a single, seamless end-to-end display on the aircraft's main instrument panel, extending to the front of the central pedestal in its central section. In this way, a greater percentage of the area than that currently utilized on state-of-the-art aircraft can be employed productively for human machine interaction. Although this paper focuses on commercial and business jet aircraft, the concept could be adapted to other platforms such as military aircraft or helicopters. It eliminates the limitation of functional compartmentalization introduced by the physical limitations of the individual displays and employs multi-touch capability over the whole display surface, thus affording the pilots with enhanced display and input functionality, which may then form the basis of new cockpit HMI concepts. The paper also discusses a simple concept of use to illustrate the salient capabilities of the single interactive display concept. © 2011 by The ODICIS Consortium. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Source

Guida M.,University of Naples Federico II | Marulo F.,University of Naples Federico II | Meo M.,University of Bath | Russo S.,Alenia Aeronautica
International Journal of Impact Engineering | Year: 2013

The objective of this paper was to design, manufacture and test a composite leading edge, without ribs, able to satisfy birdstrike requirements specified by certification authorities. The leading edge configuration was validated through an extensive campaign of experimental tests performed firstly on small sample to determine the mechanical properties [1], then through the analysis and testing of a small representative structures of the wing leading edge [2,3]. The explicit finite element software MSC.Dytran® [4] was chosen for the numerical investigation and a validated simulation methodology was developed to predict the birdstrike scenario. The evaluation of numerous birdstrike scenarios allowed an improved design efficiency and safety and led to a significant reduction of certification costs. The most important achievement was a ribless wing leading edge made of FML, aluminium and honeycomb able to satisfy the birdstrike resistance test specified by the Federal Aviation Regulation [5]. This configuration allowed a considerable reduction in weight and manufacturing costs. © 2012 Elsevier Ltd. All rights reserved. Source

Iaccarino P.,University of Naples Federico II | Leone C.,University of Naples Federico II | Durante M.,University of Naples Federico II | Caprino G.,University of Naples Federico II | Lamboglia A.,Alenia Aeronautica
Journal of Sandwich Structures and Materials | Year: 2011

Three-point bending tests in the elastic domain were carried out on sandwich specimens with the facings made of unidirectional T800H/3900-2 laminates, and the core of a soft and thin viscoelastic layer, varying the slenderness ratio. A closed-form formula available in the literature, developed for sandwich beams with thick facings, was used to predict the rigidities in flexure, adopting three different methods for the calculation of the shear rigidity. The best results were obtained by the classical sandwich theory, which provided reasonably good correlation with the experimental results, slightly overestimating the actual values. A finite element model consisting of three layers, made of standard CQUAD4 and CHEXA8 elements for facings and core, respectively, was developed, accurately predicting beam bending behavior. From the numerical results, the inability of classical sandwich theory to correctly estimate the bending rigidity is correlated with the through-the-thickness shear deformation of facings, not accounted for in the analysis. © The Author(s) 2010. Source

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