Aircraft Structures
Mostrando 1-12 de 31 artigos, teses e dissertações.
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1. A methodology to investigate the influence of the fillet radius on the buckling of integrally stiffened panels
Abstract The use of integrally stiffened panels (ISP's) in wings of small and medium-sized aircraft is frequent in aviation. These thin-walled structures are often subjected to compressive loads during their life-time and, although the finite element method has become an important tool for engineers to obtain the buckling load of structural members, some res
Lat. Am. j. solids struct.. Publicado em: 22/07/2019
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2. Analytical determination of the critical impact location for wing leading edge under birdstrike
Abstract The wing leading edge is one of the aircraft structures which are vulnerable to birdstrike. Therefore, Federal Aviation Regulation has clear requirements of anti-birdstrike performance for wing leading edge. However, the impact location is not specified in aviation regulation. The forefront of the wing leading edge is selected as a critical location
Lat. Am. j. solids struct.. Publicado em: 04/02/2019
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3. Determinación de la tenacidad a la fractura J en laminados fibra-metal del tipo CARALL con láminas de aluminio 6061 y 1050
ABSTRACT Determination of fracture toughness in hybrid composites, fiber-metal laminates, FML (Fiber Metal Laminates) is very important to perform an analysis of structural integrity to estimate damage tolerance and residual strength of the material against the propagation of a crack This evaluation should be done in both naval and aircraft structures using
Matéria (Rio J.). Publicado em: 19/07/2018
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4. Mode I Interlaminar Fracture Toughness Analysis of Co-Bonded and Secondary Bonded Carbon Fiber Reinforced Composites Joints
Aiming to reduce aircraft weight, aeronautic industry seeks alternative materials and processes used to join its different structural parts. An option to traditional methods are high performance adhesive joints, which reduce weight, number of parts and component final cost, also resulting in higher strength structures. Although, the lack of experimental data
Mat. Res.. Publicado em: 05/02/2018
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5. Electromagnetic Properties of Multifunctional Composites Based on Glass Fiber Prepreg and Ni/Carbon Fiber Veil
ABSTRACT: Multifunctional composites combine structural and other physicochemical properties, with major applications in aeronautical, space, telecommunication, automotive, and medical areas. This research evaluates electromagnetic properties of multifunctional composites based on glass fiber woven fabric pre-impregnated with epoxy resin laminated together c
J. Aerosp. Technol. Manag.. Publicado em: 2017-06
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6. Crashworthiness Analysis and Evaluation of Fuselage Section with Sub-floor Composite Sinusoidal Specimens
Abstract Crashworthiness is one of the main concerns in civil aviation safety particularly with regard to the increasing ratio of carbon fiber reinforced plastic (CFRP) in aircraft primary structures. In order to generate dates for model validations, the mechanical properties of T700/3234 were obtained by material performance tests, and energy-absorbing resu
Lat. Am. j. solids struct.. Publicado em: 2016-06
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7. Electromechanical Impedance - Based Structural Health Monitoring Instrumentation System Applied to Aircraft Structures and Employing a Multiplexed Sensor Array
ABSTRACT: The electromechanical impedance method has been seen as a promising tool for structural health monitoring regarding different types of structures and purposes. Most importantly, this method can be used in real-time applications. Frequently, massive, high-cost, single-channel impedance analyzers are used to process the time domain data, aiming at ob
J. Aerosp. Technol. Manag.. Publicado em: 2015-09
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8. Modal Shape Analysis Using Thermal Imaging
ABSTRACT: In recent years, advances in aeronautical engineering field include, among others, the development of increasingly lightweight and flexible materials, allowing better performance of systems in applications such as Unmanned Aerial Vehicles, photographic model airplanes, light weight aircraft etc. This progress, however, can cause difficulties in des
J. Aerosp. Technol. Manag.. Publicado em: 2015-06
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9. Elliptical and circular bonded composite repair under mechanical and thermal loading in aircraft structures
In this study, the three-dimensional finite element method is used to achieve a comparison between the semi circular and semi elliptical patch repairs in aircraft structures. The comparison was done by the analysis of : the mechanical and thermal stress intensity factors (SIF and TSIF) at the tip of repaired crack and the distribution of the adhesive stresse
Mat. Res.. Publicado em: 28/10/2014
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10. A new metamodel for reinforced panels under compressive loads and its application to the fuselage conception
This work presents a new metamodel for reinforced panels under compressive loads, typically used in light-weight aircraft structures. The metamodel represents a replicable cell structure of integrally machined panels. The presented formulation for conception is based on the synthesis of four stability criteria: section crippling, web buckling, flange bucklin
Lat. Am. j. solids struct.. Publicado em: 2014-03
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11. Optimal Design of a High-Altitude Solar-Powered Unmanned Airplane
ABSTRACT: This paper describes a multi-disciplinary design and optimization framework tailored for the conceptual development of high-altitude solar-powered unmanned aerial vehicles. The aircraft baseline configuration that the framework is able to handle is very similar to that of Zephyr, which is developed by the UK based company QinetiQ. The disciplines o
J. Aerosp. Technol. Manag.. Publicado em: 2013-09
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12. On the Determination of a Scatter Factor for Fatigue Lives Based on the Lead Crack Concept
ABSTRACT: The lead crack concept is adopted as the basis for a new fatigue lifeing method using the safe life philosophy. As part of its management strategy, a full-scale fatigue test is conducted to identify high-risk locations in the airframe, and for each item the time for retirement or structural repair is dictated by the safe life limit. A scatter facto
J. Aerosp. Technol. Manag.. Publicado em: 2013-06