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Journal articles on the topic 'Aeronautic component'
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1
Wang, Xiang Fen, Cheng Gao, and Gui Cui Fu. "Multidimensional Grey Evaluation Method for Aeronautic Electronic Components & Devices Selection." Applied Mechanics and Materials 214 (November 2012): 469–74. http://dx.doi.org/10.4028/www.scientific.net/amm.214.469.
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Aeronautic electronic components & devices selection is an important means to improve the aeronautic product reliability in its development stage. This paper proposes a multidimensional grey evaluation method to evaluate the electronic components & devices selection process by four indexes after the analysis of aeronautic production contractors and component manufactures. A memory selection example was presented to prove the feasibility of the proposed method. The proposed method can avoid the evaluation error effectively due to subjective factors and help to improve the product use reliability.
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Charruau, S., F. Guerin, J. Hernández Dominguez, and J. Berthon. "Reliability estimation of aeronautic component by accelerated tests." Microelectronics Reliability 46, no. 9-11 (2006): 1451–57. http://dx.doi.org/10.1016/j.microrel.2006.07.009.
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Tommasino, Domenico, Federico Moro, Bruno Bernay, Thibault De Lumley Woodyear, Enrique de Pablo Corona, and Alberto Doria. "Vibration Energy Harvesting by Means of Piezoelectric Patches: Application to Aircrafts." Sensors 22, no. 1 (2022): 363. http://dx.doi.org/10.3390/s22010363.
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Vibration energy harvesters in industrial applications usually take the form of cantilever oscillators covered by a layer of piezoelectric material and exploit the resonance phenomenon to improve the generated power. In many aeronautical applications, the installation of cantilever harvesters is not possible owing to the lack of room and/or safety and durability requirements. In these cases, strain piezoelectric harvesters can be adopted, which directly exploit the strain of a vibrating aeronautic component. In this research, a mathematical model of a vibrating slat is developed with the modal superposition approach and is coupled with the model of a piezo-electric patch directly bonded to the slat. The coupled model makes it possible to calculate the power generated by the strain harvester in the presence of the broad-band excitation typical of the aeronautic environment. The optimal position of the piezoelectric patch along the slat length is discussed in relation with the modes of vibration of the slat. Finally, the performance of the strain piezoelectric harvester is compared with the one of a cantilever harvester tuned to the frequency of the most excited slat mode.
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del Prete, Antonio, Gabriele Papadia, and Barbara Manisi. "Computer Aided Modelling of Rubber Pad Forming Process." Key Engineering Materials 473 (March 2011): 637–44. http://dx.doi.org/10.4028/www.scientific.net/kem.473.637.
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Rubber pad forming (RPF) is a novel method for sheet metal forming that has been increasingly used for: automotive, energy, electronic and aeronautic applications [1]. Compared with the conventional forming processes, this method only requires one rigid die, according to the shape of the part, and the other tool is replaced by a rubber pad [1]. This method can greatly improve the formability of the blank because the contact surface between the rigid die and the rubber pad is flexible. By this way the rubber pad forming enables the production of sheet metal parts with complex contours and bends. Furthermore, the rubber pad forming process is characterized by a low cost of the die because only one rigid die is required [2]. The conventional way to develop rubber pad forming processes of metallic components requires a burdensome trial-and-error process for setting-up the technology, whose success chiefly depends on operator’s skill and experience [4][5]. In the aeronautical field, where the parts are produced in small series, a too lengthy and costly development phase cannot be accepted. Moreover, the small number of components does not justify large investments in tooling. For these reasons, it is necessary that, during the conceptual design, possible technological troubles are preliminarily faced by means of numerical simulation [4],[6]. In this study, the rubber forming process of an aluminum alloy aeronautic component has been explored with numerical simulations and the significant parameters associated with this process have been investigated. Several effects, depending on: stamping strategy, component geometry and rubber pad characterization have been taken into account. The process analysis has been carried out thanks to an extensive use of a commercially finite element (FE) package useful for an appropriate set-up of the process model [7],[8]. These investigations have shown the effectiveness of simulations in process design and highlighted the critical parameters which require necessary adjustments before physical tests.
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Loukopoulos, Andreas, Christos Vasilios Katsiropoulos, and Spiros G. Pantelakis. "Carbon footprint and financial evaluation of an aeronautic component production using different manufacturing processes." International Journal of Structural Integrity 10, no. 3 (2019): 425–35. http://dx.doi.org/10.1108/ijsi-07-2018-0043.
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Purpose The purpose of this paper is to quantify the environmental footprint and cost and thus compare different manufacturing scenarios associated with the production of aeronautical structural components. Design/methodology/approach A representative helicopter canopy, i.e., canopy of the EUROCOPTER EC Twin Star helicopter described in Pantelakis et al. (2009), has been considered for the carbon footprint (life cycle energy and climate change impact analysis) along with the life cycle costing analysis. Four scenarios – combinations of different manufacturing technologies (autoclave and resin transfer molding (RTM)) and end-of-life treatment scenarios (mechanical recycling and pyrolysis) are considered. Findings Using the models developed the expected environmental and cost benefits by involving the RTM technique have been quantified. The environmental impact was expressed in terms of energy consumption and of Global Warming Potential-100. From an environmental standpoint, processing the canopy using the RTM technique leads to decreased energy demands as compared to autoclaving because of the shorter curing cycles exhibited from this technique and thus the less time needed. As far as the financial viability of both processing scenarios is concerned, the more steps needed for preparing the mold and the need for auxiliary materials increase the material and the labor cost of autoclaving as compared to RTM. Originality/value At the early design stages in aeronautics, a number of disciplines (environmental, financial and mechanical) should be taken into account in order to evaluate alternative scenarios (material, manufacturing, recycling, etc.). In this paper a methodology is developed toward this direction, quantifying the environmental and financial viability of different manufacturing scenarios associated with the production of aeronautical structures.
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Astarita, A., C. Testani, F. Scherillo, A. Squillace, and L. Carrino. "Beta Forging of a Ti6Al4V Component for Aeronautic Applications: Microstructure Evolution." Metallography, Microstructure, and Analysis 3, no. 6 (2014): 460–67. http://dx.doi.org/10.1007/s13632-014-0171-3.
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Ojeda-Rodríguez, Álvaro, Pablo González-Vizuete, Joaquín Bernal-Méndez, and María A. Martín-Prats. "A Survey on Bidirectional DC/DC Power Converter Topologies for the Future Hybrid and All Electric Aircrafts." Energies 13, no. 18 (2020): 4883. http://dx.doi.org/10.3390/en13184883.
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DC-DC isolated converters allowing a bidirectional flow of energy between High-Voltage DC and Low-Voltage DC networks have been proposed to be integrated in future on board power distribution systems. These converters must meet the specially stringent efficiency and power density requirements that are typical of the aeronautic industry. This makes it specially challenging to determine which converter topology is best suited for each particular application. This work presents a thorough review of several topologies of bidirectional DC-DC power converters that are considered good candidates to meet certain important aeronautic requirements, as those related with high efficiency and high power density. We perform simulations on virtual prototypes, constructed by using detailed component models, and optimized following design criteria that are in accordance with those typically imposed by aeronautic requirements. This comparative analysis is aimed to clearly identify the advantages and drawbacks of each topology, and to relate them with the required voltage and power levels. As an outcome, we point out the topologies that, for the required power level at the chosen switching frequencies, yield higher efficiency in the whole range of required operation points and that are expected to allow more important weight reductions.
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Corrado, Andrea, and Wilma Polini. "Assembly design in aeronautic field: From assembly jigs to tolerance analysis." Proceedings of the Institution of Mechanical Engineers, Part B: Journal of Engineering Manufacture 231, no. 14 (2016): 2652–63. http://dx.doi.org/10.1177/0954405416635033.
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Tolerance analysis represents the best way to solve assembly problems in order to improve the quality and to reduce the costs. It is a critical step to design and to build a product such as an aircraft and its importance is grown up in the past years. This work presents a method for the tolerance analysis of an assembly involving free-form surfaces with large dimensions. The assembly is a tail beam, a structural component of an aircraft that is constituted by five parts of large dimensions. The influence of the tolerances applied to the five components of the tail beam on the value of the gap at the interfaces among the parts has been deeply investigated. A set of control points have been distributed on the free-form surfaces of the tail beam; its number and its distribution have been opportunely designed. Moreover, the influence of the tolerances on the other requirements of the tail beam connected with the motion drive has been studied. Tolerance analysis has involved the choice of the assembly tools and sequence too. The assembly jigs are mated with the assembly components through pins that are inserted into tooling holes located on the assembly components. The fit conditions have been modeled and the tolerances of the tooling hole have been opportunely chosen. Each tolerance of the tail beam components has been modeled by means of a probability density function. Monte Carlo approach has been used to obtain the statistical distribution of the assembly requirements, once dimensions and geometry of the tail beam components have been perturbed inside the tolerance ranges. Monte Carlo simulation has been carried out by a well-known computer-aided tolerance software, eM-Tolmate of UGS®.
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Astarita, Antonello, Enrico Armentani, Elisabetta Ceretti, et al. "Hot Stretch Forming of a Titanium Alloy Component for Aeronautic: Mechanical and Modeling." Key Engineering Materials 554-557 (June 2013): 647–56. http://dx.doi.org/10.4028/www.scientific.net/kem.554-557.647.
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The development of Hot Stretch Forming (HSF) by the Cyril Bath Company was in response to airframe designers needing to use Titanium airframe components in new commercial aircraft. Many of the airframe component structures are designed to fit against the inside radius of the fuselage curvature. By combining traditional stretch forming technology with hot titanium forming techniques, the HSF guarantees a saving in material and machining time, which are two serious cost issues for today’s aircraft manufacturers. In addition, the process allows for consistent quality in a productively efficient manner, assuring the sustainable attainment of delivery and build schedules. The HSF is an innovative process on the cutting edge of the technologies, so focused research is needed in order to better understand this technology and develop new applications for this process. in this paper the HSF process is investigated: the machine and the different steps that characterized the process were described and the results of a preliminary experimental campaign was discussed focusing the attention on the metallurgical aspect. Moreover a modeling of the process was executed in order to study the stresses and strains undergone by the material among the deformation.
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Lionetto, Francesca, Anna Moscatello, Giuseppe Totaro, Marco Raffone, and Alfonso Maffezzoli. "Experimental and Numerical Study of Vacuum Resin Infusion of Stiffened Carbon Fiber Reinforced Panels." Materials 13, no. 21 (2020): 4800. http://dx.doi.org/10.3390/ma13214800.
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Liquid resin infusion processes are becoming attractive for aeronautic applications as an alternative to conventional autoclave-based processes. They still present several challenges, which can be faced only with an accurate simulation able to optimize the process parameters and to replace traditional time-consuming trial-and-error procedures. This paper presents an experimentally validated model to simulate the resin infusion process of an aeronautical component by accounting for the anisotropic permeability of the reinforcement and the chemophysical and rheological changes in the crosslinking resin. The input parameters of the model have been experimentally determined. The experimental work has been devoted to the study of the curing kinetics and chemorheological behavior of the thermosetting epoxy matrix and to the determination of both the in-plane and out-of-plane permeability of two carbon fiber preforms using an ultrasonic-based method, recently developed by the authors. The numerical simulation of the resin infusion process involved the modeling of the resin flow through the reinforcement, the heat exchange in the part and within the mold, and the crosslinking reaction of the resin. The time necessary to fill the component has been measured by an optical fiber-based equipment and compared with the simulation results.
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Silva, Daniel, Ricardo Rocha, Filipe Ribeiro, and Helena Monteiro. "Environmental Impact of an Innovative Aeronautic Carbon Composite Manufactured via Heated Vacuum-Assisted Resin Transfer Molding." Sustainability 16, no. 8 (2024): 3253. http://dx.doi.org/10.3390/su16083253.
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The Vacuum-Assisted Resin Transfer Molding (VARTM) process has gained popularity as a reliable and cost-effective alternative to autoclave molding for high-performance composite production, which is especially interesting for aeronautics, where weight reduction is crucial. However, to date, the environmental impact of components produced through VARTM remains relatively unknown. To address this gap, this study applied the Life Cycle Assessment (LCA) methodology to estimate the environmental impact of a thermoset composite laminate produced through heated VARTM. Aiming to support the decision, the VARTM composite part’s production was compared to conventional autoclave manufacturing, and the influence of alternative end-of-life (EoL) scenarios and energy mixes was considered, through LCA. The study found that energy consumption represented the majority of the environmental impacts of the heated VARTM component (33%), followed by carbon fibers, resins, consumables, and wastes. In terms of the comparative analysis, the autoclave manufacturing process showed better environmental results. Regarding EoL management, supercritical hydrolysis (with heat recovery) recycling emerges as the most beneficial method, reducing the impacts of the VARTM-manufactured component by 25%. This study emphasizes the importance of sustainable practices, such as reducing energy consumption, using low-carbon energy mixes, and adopting recycling methods to improve VARTM composite’s environmental performance.
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del Cuvillo, Ramón, Jose Alfonso Artero-Guerrero, Jesús Pernas-Sánchez, and Jorge López Puente. "Soft projectile impact forces measurement using Hopkinson bars: application to ice, artificial bird and rubber." EPJ Web of Conferences 250 (2021): 01008. http://dx.doi.org/10.1051/epjconf/202125001008.
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This work presents an experimental campaign of impacts of soft projectiles to measure the induced force during the impact. Three different materials acting as soft impactors that could strike against a aeronautical structural component: ice, artificial bird and rubber have been impacted at several velocities against an aluminium Hopkinson bar. This device has been instrumented with semiconductor strain gauges that allow to obtain the induced compression strain. Additionally, all the impacts were recorded using high-speed video cameras, allowing the kinematic analysis of the projectile during the impact. After the results study, it has been concluded that there is a linear dependency between the kinetic energy and the peak force for all three materials. Added to that, it has been proved that the higher peak force corresponds to ice, despite the kinetic energy, followed by rubber and finally the artificial bird. In addition, while ice and artificial bird projectiles get radially dispersed after the impact, rubber spheres rebound due to its different behaviour. The obtained data is of great interest to design structures which could be subjected to impacts of soft materials such as aeronautic structures
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Concilio, Antonio, Monica Ciminello, Bernardino Galasso, et al. "De-Bonding Numerical Characterization and Detection in Aeronautic Multi-Element Spars." Sensors 22, no. 11 (2022): 4152. http://dx.doi.org/10.3390/s22114152.
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Structural health monitoring has multifold aims. Concerning composite structures, the main objectives are perhaps reducing costs by shifting from scheduled to on-demand maintenance and reducing weight by removing redundant precautions as the insertion of chicken fasteners to for ensuring joint safety in cases of bonding layer fail. Adhesion defects may be classified along different types, for instance distinguishing between glue deficiency or de-bonding. This paper deals with a preliminary numerical characterization of adhesive layer imperfections on a representative aircraft component. The multipart composite spar is made of two plates and two corresponding C-beams, bonded together to form an almost squared boxed section beam. A numerical test campaign was devoted to extract relevant information from different defect layouts and to try to assess some parameters that could describe their peculiarities. A focus was then given to macroscopic evidence of fault effects behavior, as localization, reciprocal interference, impact on structural response, and so on. A proprietary code was finally used to retrieve the presence and size of the imperfections, correlating numerical outcomes with estimations. Activities were performed along OPTICOMS, a European project funded within the Clean Sky 2 Joint Technology Initiative (JTI).
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Guo, Tan, Xiao-Ping Lu, Yong-Xiong Zhang, and Keping Yu. "Neighboring Discriminant Component Analysis for Asteroid Spectrum Classification." Remote Sensing 13, no. 16 (2021): 3306. http://dx.doi.org/10.3390/rs13163306.
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With the rapid development of aeronautic and deep space exploration technologies, a large number of high-resolution asteroid spectral data have been gathered, which can provide diagnostic information for identifying different categories of asteroids as well as their surface composition and mineralogical properties. However, owing to the noise of observation systems and the ever-changing external observation environments, the observed asteroid spectral data always contain noise and outliers exhibiting indivisible pattern characteristics, which will bring great challenges to the precise classification of asteroids. In order to alleviate the problem and to improve the separability and classification accuracy for different kinds of asteroids, this paper presents a novel Neighboring Discriminant Component Analysis (NDCA) model for asteroid spectrum feature learning. The key motivation is to transform the asteroid spectral data from the observation space into a feature subspace wherein the negative effects of outliers and noise will be minimized while the key category-related valuable knowledge in asteroid spectral data can be well explored. The effectiveness of the proposed NDCA model is verified on real-world asteroid reflectance spectra measured over the wavelength range from 0.45 to 2.45 μm, and promising classification performance has been achieved by the NDCA model in combination with different classifier models, such as the nearest neighbor (NN), support vector machine (SVM) and extreme learning machine (ELM).
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Baragetti, Sergio, Riccardo Gerosa, and Francesco Villa. "Light Alloys Structural Behaviour in Severe Environmental Conditions." Key Engineering Materials 665 (September 2015): 37–40. http://dx.doi.org/10.4028/www.scientific.net/kem.665.37.
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High strength-to-mass ratio light alloys, such as 7075-T6 aluminium alloys and Ti-6Al-4V titanium alloys, are commonly adopted for high performance structural components in the aeronautic, automotive and maritime sectors. For this reason, it is crucial to investigate the effects of the external environment on their mechanical properties, to avoid dramatic component failure. In the present work, experimental tests were performed on Ti-6Al-4V and 7075-T6 light alloys. Ti-6Al-4V notched flat dogbone specimens, withKt= 1.18, were tested for quasi-static and SCC effects in a methanol-water aggressive environment at different concentrations. Rotating bendingR =-1fatigue tests were performed on 7075-T6 in air and methanol environment, to evaluate the effects of an aggressive environment on the fatigue strength at 200’000 cycles. The influence of DLC and WC/C PVD coatings on fatigue limit at 200’000 cycles has been evaluated in air and aggressive environment, to assess their mechanical and protective effects on the 7075-T6 substrate
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del Prete, Antonio, Rodolfo Franchi, and Emilia Mariano. "Nickel Superalloy Components Surface Integrity Control through Numerical Optimization." Key Engineering Materials 611-612 (May 2014): 1396–403. http://dx.doi.org/10.4028/www.scientific.net/kem.611-612.1396.
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Different parameters are used to evaluate the machined surface quality; roughness, residual stress and white layer are the most common factors that affect the surface integrity. Residual stress, in addition, are one of the main factors that influence the component fatigue life. Superficial residual stresses depend on different factors, such as cutting parameters and tool geometry. This article describes the development of an automated optimization procedure that allows the matching of a residual stress Target Profile by varying process parameters and tool geometry for a typical aeronautic superalloy, such as Waspaloy, for which a reliable numerical model has been developed for comparison to experimental data. The objective of this procedure is to maximize the Material Removal Rate under physical constraints represented by appropriate limits assigned to: Cutting Force, Thrust Force, Tool Rake Temperature and residual stress Target Profile. The developed optimization procedure has shown its effectiveness to match a given residual stress profile in accordance to process responses numerically evaluated.
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Matos, Nelson, Pedro Gamito, Margarida Pinto, Joel Ferreira, and Luis Oliveira. "Implementation of advanced technologies into Aeronautic integrated maintenance concept - Use of virtual reality in ground-floor training maintenance execution." MATEC Web of Conferences 304 (2019): 06002. http://dx.doi.org/10.1051/matecconf/201930406002.
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Aviation Maintenance industry, Repair and Overhaul (MRO) procedures need to keep up with the technological evolution and evolve from the 2D support to the 3D. The available manuals for learning and training MRO tasks rely much on old 2D drawings and lists of maintenance steps to be performed sequentially. However, these are complex actions that require and would benefit greatly from a 3D insight in order to be quickly and comprehensible absorbed. Virtual Reality (VR) apps are potentially a suitable option to turn these procedures closer to reality and, thus, improving competences and skills. Amongst the several maintenance optimization developments of the AIRMES project, which is cradled in the EU Clean Sky 2 Joint Undertaking programme, the above concept is applied to maintenance execution by developing a VR app to help practitioners in the process of carrying out specific maintenance activities as removing and positioning components into aircraft structures. The VR app runs on a mobile platform that uses a smartphone and a portable motion capture device coupled with a head mounted device allowing the practitioners to learn and to train onsite on how to proceed with the maintenance operations. The practitioners will be in an immersive and interactive environment where both the host aircraft structure section with the target component and auxiliary/peripheral systems parts are displayed and in which the 3D component can be removed by virtual hands that emulate, through the motion capture device, the hands of the user. The system developed provides a high-level training and reliable information to the technician on the maintenance operations for a dedicated situation and facilitate the identification and execution of the procedure to be applied, improving the time for repair.
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Edy, François, Viet-Duc LE, Claudia BIERE, Monica Perez, Etienne Pessard, and Franck Morel. "From the fatigue properties of Ti6Al4V produced by ALM selective laser melting process to the mechanical design of an aeronautical part." MATEC Web of Conferences 321 (2020): 03032. http://dx.doi.org/10.1051/matecconf/202032103032.
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Selective laser melting SLM is investigated through a study of redesign and characterization of an aeronautic part made of titanium Ti6Al4V. The part must ensure an excellent static and fatigue behaviour. The methodology developed hereby follows 3 main steps: First, the influence of laser power, laser speed and hatch distance on the amount/rate of porosity is performed to define optimized process parameters. Then, the influence of building process strategy, i.e. building direction or as-built surface roughness on the static and fatigue behaviour are studied and understood by following a vast experimental campaign. Obtained properties are finally used in a topology optimization study to find the best compromise between part weight and fatigue behavior . 3 prototypes of simulated part are produced and then characterized. Fatigue tests are conducted on the component and confirm the fatigue design proposed. Obtained results are encouraging and illustrate the fatigue design optimization of a complex Additive Manufacturing component.
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Masseria, Frédéric, André Berger, and Benjamin Kaiser. "Virtual Composite Manufacturing Simulation Chain." Materials Science Forum 825-826 (July 2015): 671–76. http://dx.doi.org/10.4028/www.scientific.net/msf.825-826.671.
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Composite materials have been introduced in the 90’s in the car racing, naval and aeronautic sectors for weight reduction purposes. In the automotive industry, the introduction of composite materials to reduce also the weight of the vehicles leads to additional challenges for Virtual Prototyping on top of difficulties already encountered with metallic structures modeling. The impact of manufacturing on product performance is critical for composites, as the imperfections from the process may greatly affect the statics and crash performance of the final composite component. The paper will describe the state of the art of ESI Composite Solution on global composite manufacturing simulation chain (Forming, Injection, Curing, and Distortion) and how it couples to Structure/Crash through selected industrial examples.
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Speth, Marco, Johannes Heine, Kim Rouven Riedmüller, and Mathias Liewald. "Modelling of Ceramic Particle Motion during Semi-Solid Forming of Aluminium Matrix Composites via CFD-DEM Four-Way Coupling." Key Engineering Materials 926 (July 22, 2022): 2303–11. http://dx.doi.org/10.4028/p-xz23in.
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Today, aluminium matrix composites (AMC) are widely used for the manufacturing of lightweight, yet highly stressed components in automotive, aeronautic and electrical engineering. In order to achieve particle distributions as homogeneous as possible within these component’s volumes and thus ensure optimum component properties, efforts are being made to simulate the manufacturing process prior to production. In this paper, AMC with extremely high particle fractions of more than 25 vol.% are considered in particular, as their processing still poses significant technological challenges. To model the particle motion in a computational fluid dynamics (CFD) simulation of the semi-solid forming process of this type of materials, a Lagrangian multiphase approach combining CFD and discrete element method (DEM) was used. Here, the DEM allowed all particle-particle interactions to be considered. Thus, different parameters influencing particle agglomeration, particle distribution as well as particle interaction with the cavity can be investigated during a numerical study. More specifically, the influence particle parameters such as cohesion forces and the influence of the forming speed onto the particle distribution in the final component ́s volume was analysed. The simulations were performed for a symmetric disc geometry. A forming tool was already available for this geometry, with which components could be manufactured to validate the simulation results. In the end, the study shows that by using four-way CFD-DEM coupling, simulation predictability for the semi-solid forming process of AMC could be significantly improved.
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do Nascimento, Marcelino Pereira, Carolina Cordeiro Batista, Celso Pinto Morais Pereira, and Herman Jacobus Cornelis Voorwald. "Fatigue Behavior of Weld Repaired AISI 4130 Aeronautic Steel Used in Critical Flight Safety Structures." Advanced Materials Research 891-892 (March 2014): 1736–41. http://dx.doi.org/10.4028/www.scientific.net/amr.891-892.1736.
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Since the 1950s, fatigue is the most important project and operational consideration for both civil and military aircrafts. For some aircraft models the most loaded component is one that supports the motor: the "Motor Cradle". Because they are considered critical to the flight safety the aeronautic standards are extremely rigorous in manufacturing them by imposing a "zero index of defects" on the final weld quality (Safe Life), which is 100% inspected by Non-Destructive Testing/NDT. This study has as objective to evaluate the effects of up to four successive TIG welding repairs on the axial fatigue strength of an AISI 4130 steel. Tests were conducted on hot-rolled steel plate specimens, 0.89 mm thick, with load ratio R = 0.1, constant amplitude, at 20 Hz frequency and in room temperature, in accordance with ASTM E466 Standard. The results were related to microhardness and microstructural and geometric changes resulting fromwelding cycles.
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Rubio, Eva, María Villeta, José Valencia, and José Sáenz de Pipaón. "Cutting Parameter Selection for Efficient and Sustainable Repair of Holes Made in Hybrid Mg–Ti–Mg Component Stacks by Dry Drilling Operations." Materials 11, no. 8 (2018): 1369. http://dx.doi.org/10.3390/ma11081369.
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Drilling is one of the most common machining operations in the aeronautic and aerospace industries. For assembling parts, a large number of holes are usually drilled into the parts so that they can be joined later by rivets. As these holes are subjected to fatigue cycles, they have to be checked regularly for maintenance or repair, since small cracks or damage in its contour can quickly cause breakage of the part, which can have dangerous consequences. This paper focuses on finding the best combinations of cutting parameters to perform repair and maintenance operations of holes in stacked hybrid magnesium–titanium–magnesium components in an efficient, timely, and sustainable (without lubricants or coolants) manner, under dry drilling conditions. For the machining trials, experiments were designed and completed. A product of a full factorial 23 and a block of two factors (3 × 2) was used with surface roughness as the response variable measured as the mean roughness average. Analysis of variance (ANOVA) was used to examine the results. A set of optimized tool and cutting conditions is presented for performing dry drilling repair operations.
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Sun, Jinru, Xueling Yao, Wenjun Xu, Jingliang Chen, and Yi Wu. "Evaluation method for lightning damage of carbon fiber reinforced polymers subjected to multiple lightning strikes with different combinations of current components." Journal of Composite Materials 54, no. 1 (2019): 111–25. http://dx.doi.org/10.1177/0021998319860562.
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The aircraft lightning environment consists of four lightning current components with different parameters, which are known as lightning components A, B, C and D. The lightning damage of aeronautic carbon fiber reinforced polymer laminates subjected to multiple continuous sequential lightning current components with different timing combinations was experimentally evaluated. The experimental results indicated that the carbon fiber reinforced polymer laminates suffered serious lightning damage, including carbon fiber fracture, resin pyrolysis and delamination. Through an analysis of the lightning damage properties of carbon fiber reinforced polymers, the influential factors and evaluation methods of the lightning damage in carbon fiber reinforced polymer laminates were studied. Because the lightning damage evaluation method under a single lightning impulse was found to be inapplicable for the multiple continuous lightning strikes, a multi-factor evaluation method was proposed. In the multiple continuous lightning strike test, the damage depth was found to be closely related to lightning components A, B and D and could be estimated based on the amplitudes and rise rates of the applied lightning components. Increases in the damaged area after a lightning strike were driven by lightning component C due to its substantial thermal effects. The damaged area was evaluated on the basis of the parameters of the electrical action integral and the transfer charge. The research on the evaluation methods for carbon fiber reinforced polymer laminate lightning damage presented herein may provide experimental support and a theoretical basis for studying the lightning effect mechanism and optimizing material formulations, manufacturing processes and structural designs to achieve performance improvements for carbon fiber reinforced polymer laminates in the future.
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Wu, Ao, Ruijie Zhao, Fei Wang, Desheng Zhang, and Xikun Wang. "Effects of Coolant and Working Temperature on the Cavitation in an Aeronautic Cooling Pump with High Rotation Speed." Machines 10, no. 10 (2022): 904. http://dx.doi.org/10.3390/machines10100904.
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The centrifugal pump with high rotation speed is the key component in the cooling system of an aircraft. Because of the high rotation speed, the impeller inlet is very prone to cavitation. Two impellers with different types of blades (cylindrical and splitter) are designed, and the numerical models of the pumps are built. The authenticity of the numerical models is validated with the corresponding experiments in terms of both the hydraulic and cavitation characteristics. Then, the effects of different coolants and working temperatures on the hydraulic and cavitation performances of the prototype models are studied based on the numerical simulations. The results show that the head and efficiency of the pump for conveying water are higher than those for conveying ethylene glycol (EG) aqueous solution and propylene glycol (PG) aqueous solution (EGaq and PGaq are defined to represent the EG aqueous solution and the PG aqueous solution, respectively). The hydraulic performance in the EGaq is slightly better than that in the PGaq. The cavitation performance of water is far less than that of the EGaq and PGaq under high working temperature. The volume of cavitation in EGaq is smaller than that in PGaq, and the volume of cavitation in the splitter blades is slightly smaller than that in the cylindrical blades. It is suggested that EGaq be used as the first option. The splitter blades can improve the cavitation performance somehow while the improvement by using the splitter blades is very limited at high rotation speeds, and the design of the short blades should be careful in order to obtain a smooth internal flow field.
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Astarita, Antonello, Luigi Carrino, Massimo Durante, et al. "Experimental Study on the Incremental Forming of Coated Aluminum Alloy Sheets." Key Engineering Materials 622-623 (September 2014): 398–405. http://dx.doi.org/10.4028/www.scientific.net/kem.622-623.398.
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Superficial coatings are widely used in industrial applications in order to improve the superficial properties of metallic components. In particular, in the aeronautic field, all the components are coated in order to prevent both corrosion and wear. In this field, heat treatable aluminum alloys, in age hardened condition, are used; consequently, superficial coatings must be carried out through “cold” processes, i.e. coating processes in which the component to be coated remains at low temperatures, below 100°C. Cold gas dynamic spray technique (CGDS) is a process of deposition that consists in the realization of surface coatings with high-velocity metal particles sprayed on the substrate at temperature significantly lower than the melting one of the substrate itself and at relatively low temperatures if compared to other spray techniques. When processing conditions are optimized, the process can produce near fully dense coatings. This technique could be particularly useful in the coating of rolled sheets, needing of successive cold plastic deformations. One of the cold plastic processes is incremental forming, a high flexible process for rapid manufacturing of complex sheet metal part shapes; it presents the potential to be easy to automate and particularly attractive for small batches and customized parts. In this process, a simple tool describes a path that allows to locally deform the sheet clamped along its periphery. The aim of this paper is to study the evolution and behaviour of aluminum coating deposed by CGDS on AA 2024-T3 sheets carried out by an incremental forming process. This evaluation is carried out by characterizing the cold sprayed coating after the forming process for different wall angles of simples geometries.
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Encalada-Dávila, Ángel, Lenín Pardo, Yolanda Vidal, Efraín Terán, and Christian Tutivén. "Conceptual Design of a Vibration Test System Based on a Wave Generator Channel for Lab-Scale Offshore Wind Turbine Jacket Foundations." Journal of Marine Science and Engineering 10, no. 9 (2022): 1247. http://dx.doi.org/10.3390/jmse10091247.
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Structural health monitoring (SHM) systems are designed to continually monitor the health of structures (e.g., civil, aeronautic) by using the information collected through a distributed sensor network. However, performing tests on real structures, such as wind turbines, implies high logistic and operational costs. Therefore, there is a need for a vibration test system to evaluate designs at smaller scales in a laboratory setting in order to collect data and devise predictive maintenance strategies. In this work, the proposed vibration test system is based on a lab-scale wind turbine jacket foundation related primarily to an offshore environment. The test system comprises a scaled wave generator channel, a desktop application (WTtest) to control the channel simulations, and a data acquisition system (DAQ) to collect the information from the sensors connected to the structure. Various equipment such as accelerometers, electrodynamic shaker, and DAQ device are selected as per the design methodology. Regarding the mechanical part, each component of the channel is designed to be like the wave absorber, the mechanical multiplier, the piston-type wavemaker, and the wave generator channel. For this purpose, the finite element method is used in static and fatigue analysis to evaluate the stresses and deformations; this helps determine whether the system will work safely. Moreover, the vibration test system applies to other jacket structures as well, giving it greater utility and applicability in different research fields. In sum, the proposed system is compact and has three well-defined components that work synchronously to develop the experimental simulations.
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Astarita, Antonello, Luca Giorleo, Fabio Scherillo, Antonino Squillace, Elisabetta Ceretti, and Luigi Carrino. "Titanium Hot Stretch Forming: Experimental and Modeling Residual Stress Analysis." Key Engineering Materials 611-612 (May 2014): 149–61. http://dx.doi.org/10.4028/www.scientific.net/kem.611-612.149.
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Titanium alloys, due to their high mechanical properties coupled with light weight and high corrosion resistance, are finding a widespread use in the aeronautic industry. The use of titanium in replacing the conventional alloys, such as aluminum alloys and steel, is reduced by both the high cost of the raw material (it costs anywhere from 3 to 10 times as much as steel or aluminium) and the machining costs (at least 10 times that to machine aluminium). For such a reason new technologies have been studied and developed. In particular many researchers are searching for technologies, such as the precision hot forming, that allows to obtain components with a low buy to fly ratio. Many of the airframe component structures are designed to fit against the inside radius of the fuselage curvature. By combining traditional stretch forming technology with hot titanium forming techniques, the HSF guarantees a saving in material and machining time, which are two serious cost issues for todays aircraft manufacturers. In addition, the process allows for consistent quality in a productively efficient manner, assuring the sustainable attainment of delivery and build schedules. In order to develop and improve the HSF process a modeling of the process itself was executed in order to study the stresses and strains undergone by the material among the deformation. The FEM model was validated through the residual stresses, and in particular the residual stresses provided by the model were compared with the ones experimentally measured using the hole drilling technique. Good agreement, in terms of stress range, was recorded both for the maximum and the minimum stress.
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Silva, Leandro Soares, Henrique Fernandes, Michael Schwarz, Hans-Georg Herrmann, and Aldemir Cavalini. "Numerical and Non-Destructive Analysis of an Aluminum-CFRP Hybrid 3D Structure." Metals 11, no. 12 (2021): 1938. http://dx.doi.org/10.3390/met11121938.
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Advanced materials are widely used in many industries. They play an important role especially in the aeronautic and automotive sectors where weight reduction is required in order to reduce fuel consumption. Composite materials have a high strength to weight ratio and are applied in airplane construction. Nevertheless, sometimes it is not viable to replace all metal parts by composite ones due to the cost factor. In this sense, hybrid structures are highly welcome. In order to ensure the safety of these hybrid components during their entire life cycle, non-destructive testing evaluation (NDT&E) methods are used and sometimes they are the only option. In this study, we use infrared thermography (IRT) to inspect an aluminum-composite hybrid structure with a 3D shape. The sample has a composite part with a small metal inlay (EN AW-6082) overmolded with a thermoplastic layer. The inlay is bended to reach the desired 3D geometry. This sample was design to be used for the connection between an A- or B-pillar and a car roof made of carbon fiber reinforced polymer (CFRP). A dual-band infrared camera is used in order to capture images in two different spectral ranges. In addition, two data processing techniques for infrared images are applied to enhance the images: principal component thermography (PCT) and partial least squares thermography (PLST). Then, a signal-to-noise ratio analysis is performed with three randomly chosen previous known defects to assess the quality of the images and detected defects. Results showed that principal component thermography has a slight advantage over partial least squares thermography in our specific experiments. Specifically, for the long-wave infrared band, PCT presented, among the defects analyzed, PCT presented a mean value 12.5% higher while the standard deviation was almost three times lower than PLST. In parallel to the non-detructive analysis, a numerical finite element model was formulated in ANSYS® to analyze the total deformations to which the metal-composite-hybrid structure is subjected during a possible use. Results obtained with the numerical model indicate that the interface region between composite and metal parts is where the highest degree of deformation occur, which indicates possible regions where defects and failures may occur in real use cases.
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Gloria, Antonio, Roberto Montanari, Maria Richetta, and Alessandra Varone. "Alloys for Aeronautic Applications: State of the Art and Perspectives." Metals 9, no. 6 (2019): 662. http://dx.doi.org/10.3390/met9060662.
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In recent years, a great effort has been devoted to developing a new generation of materials for aeronautic applications. The driving force behind this effort is the reduction of costs, by extending the service life of aircraft parts (structural and engine components) and increasing fuel efficiency, load capacity and flight range. The present paper examines the most important classes of metallic materials including Al alloys, Ti alloys, Mg alloys, steels, Ni superalloys and metal matrix composites (MMC), with the scope to provide an overview of recent advancements and to highlight current problems and perspectives related to metals for aeronautics.
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Silva, António José Ramos, P. M. G. Moreira, Mario A. P. Vaz, and Joaquim Gabriel. "Temperature profiles obtained in thermoelastic stress test for different frequencies." International Journal of Structural Integrity 8, no. 1 (2017): 51–62. http://dx.doi.org/10.1108/ijsi-04-2016-0016.
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Purpose Maintenance is one of the most critical and expensive operations during the life cycle of metallic structures, in particular in the aeronautic industry. However, early detection of fatigue cracks is one of the most demanding operations in global maintenance procedures. In this context, non-destructive testing using image techniques may represent one of the best solutions in such situations, especially thermal stress analyses (TSA) using infrared thermography. The purpose of this paper is to access and characterize the main stress profile calculated through temperature variation, for different load frequencies. Design/methodology/approach In this paper, a cyclic load is applied to an aluminum sample component while infrared thermal image is being acquired. According to the literature and experiments, a cyclic load applied to a material results in cyclic temperature variation. Findings Frequency has been shown to be an important parameter in TSA evaluations, increasing the measured stress profile amplitude. The loading stimulation frequency and the maximum stress recorded show a good correlation (R2 higher than 0.995). It was verified that further tests and modeling should be performed to fully comprehend the influence of load frequency and to create a standard to conduct thermal stress tests. Originality/value This work revealed that the current infrared technology is capable of reaching far more detailed thermal and spatial resolution than the one used in the development of TSA models. Thus, for the first time the influence of mechanical load frequency in the thermal profiles of TSA is visible and consequentially the measured mechanical stress.
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Meng, Fanjuan, Carl Labergere, Pascal Lafon, Mathieu Duguy, and Laurent Daniel. "Multi-objective optimization based on meta-models of an aeronautical hub including the ductile damage constraint." International Journal of Damage Mechanics 23, no. 8 (2014): 1055–76. http://dx.doi.org/10.1177/1056789514544481.
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In forging process, geometric design of initial billet and tools is very important. Traditionally, engineers use their knowledge and experience to design and optimize the geometric model of forging process by using trial-and-error methods. Such methods are time consuming and cost expensive. It is therefore interesting to design an automatic tools builder based on optimization methodology coupled with virtual finite element simulations, thus helping engineers to improve products and reduce cost. In this article we describe a meta-model based multi-objective optimization methodology for forging process designed to build the theoric Pareto optimal front of the mechanical problem. We go through a four-step process: building parametric computer-aided design geometry model, simulating the forging process according to the DOE, fitting meta-models, and optimizing the process by using an advanced algorithm. Two different meta-models, including polynomial and kriging methods, are constructed, based on the simulation values for different responses. Then optimization algorithms NBI-NLPQLP and NSGA-II are applied to find the optimum solutions based on each different meta-model. In order to drive this procedure automatically we use ModeFRONTIER® software. Using this environment, several macro commands are used to connect the geometry modelling (made with CATIA V5™) and numerical simulation process. As an industrial example, a two-step forging of an aeronautic component shows the efficiency of the proposed methodology. That shows contributions of research in dealing with optimization design of die geometry taking into account technological interactions related to the process and the ductile damage inside the deformed part. A set of solutions selected in particular points of the optimal Pareto front are also presented and analysed.
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Biagio, Marco San, Carlos Beltrán-González, Salvatore Giunta, Alessio Del Bue, and Vittorio Murino. "Automatic inspection of aeronautic components." Machine Vision and Applications 28, no. 5-6 (2017): 591–605. http://dx.doi.org/10.1007/s00138-017-0839-1.
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Loukopoulos, Andreas, Christos Katsiropoulos, and Spiros Pantelakis. "Life cycle assessment and cost analysis evaluation of a helicopter's canopy production using different manufacturing processes." MATEC Web of Conferences 188 (2018): 01020. http://dx.doi.org/10.1051/matecconf/201818801020.
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In the present work, Life Cycle analysis (LCA) and Life cycle costing (LCC) models were developed in order to quantify the environmental footprint and cost and thus compare different manufacturing scenarios associated with the production of aeronautical structural components. To validate the models developed, they were implemented for the case of a helicopter's canopy processed by two techniques commonly used in aeronautics, namely the autoclave and the Resin Transfer moulding (RTM). The canopy was assumed to be made of a carbon fiber reinforced thermosetting material. Using the models developed the expected environmental and cost benefits by involving the RTM technique have been quantified.
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Wu, Jiajun, Zhihu Zhou, Xingze Lin, Hongchao Qiao, Jibin Zhao, and Wangwang Ding. "Improving the Wear and Corrosion Resistance of Aeronautical Component Material by Laser Shock Processing: A Review." Materials 16, no. 11 (2023): 4124. http://dx.doi.org/10.3390/ma16114124.
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Since the extreme service conditions, the serious failure problems caused by wear and corrosion are often encountered in the service process for aeronautical components. Laser shock processing (LSP) is a novel surface-strengthening technology to modify microstructures and induce beneficial compressive residual stress on the near-surface layer of metallic materials, thereby enhancing mechanical performances. In this work, the fundamental mechanism of LSP was summarized in detail. Several typical cases of applying LSP treatment to improve aeronautical components’ wear and corrosion resistance were introduced. Since the stress effect generated by laser-induced plasma shock waves will lead to the gradient distribution of compressive residual stress, microhardness, and microstruture evolution. Due to the enhancement of microhardness and the introduction of beneficial compressive residual stress by LSP treatment, the wear resistance of aeronautical component materials is evidently improved. In addition, LSP can lead to grain refinement and crystal defect formation, which can increase the hot corrosion resistance of aeronautical component materials. This work will provide significant reference value and guiding significance for researchers to further explore the fundamental mechanism of LSP and the aspects of the aeronautical components’ wear and corrosion resistance extension.
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Agüero Bruna, A., J. Álvarez Alba, F. J. García de Blas Villanueva, and P. Valles González. "Recubrimientos protectores para componentes de turbinas de aviación y de generación de energía depositados por proyección por plasma." Boletín de la Sociedad Española de Cerámica y Vidrio 39, no. 4 (2000): 540–47. http://dx.doi.org/10.3989/cyv.2000.v39.i4.815.
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Bassi, Stefano, Matteo Scafe, Enrico Leoni, Claudio Mingazzini, Narayan Jatinder Bhatia, and Andrea Rossi. "Development of recyclable Fibre Metal Laminates (FML), their mechanical characterization and FE modelling, aiming at structural application in aeronautics." MATEC Web of Conferences 349 (2021): 01010. http://dx.doi.org/10.1051/matecconf/202134901010.
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This study concerns with the optimisation of a fibre-reinforced composite material ply book and application to an aeronautical component. The presented material solution is a recyclable FML (Fibre Metal Laminate). Recyclable and structural PMCs (Polymeric Matrix Composites) developed up-to now in ENEA had to be improved to satisfy the high-demanding fire characteristics requirements in aeronautics, particularly for the case considered in ongoing project FireMat (www.firemat.it), namely a turbine-bonnet production. FireMat project objective is the combination of weight reduction and fire resistance, maximizing the use C2C recyclable, secondary and biomass derived raw materials. Aluminium layers were introduced inside the lamination, to act as oxygen barriers and improve fire-retardancy. FML were obtained starting from a fire-retardant biobased resin, which was associated with aeronautical grade basalt-derived mineral fabric, processed in the form of a prepreg and then coupled with aluminium foils. FE modelling was based on performed mechanical characterization of the single layers and inter- layer adhesive strength of the ply stack: a composite sandwich structure (including aluminium honeycomb) was optimised.
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Bintoro, Atik. "LENDUTAN STRUKTUR TWIN BOOM PESAWAT TERBANG NIR AWAK LSU-05 PADA SAAT MENERIMA BEBAN TERBANG (DEFLECTION OF LSU-05 UAV TWIN BOOM STRUCTURE ON RECIEVING THE FLIGHT LOAD)." Jurnal Teknologi Dirgantara 14, no. 2 (2017): 91. http://dx.doi.org/10.30536/j.jtd.2016.v14.a2386.
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The twin-boom structure is a component of LSU-5 unmanned aireal vehicle (UAV) construction wich was produced by Aeronautic Technology Center of LAPAN. This structure serves as a stabilizer UAV movements. In operations, the structure will recieve flight load which could result as the structure deflection. Through analytical methods involving the mission, dimensions and configuration of the structure of the twin-boom LSU 05 UAV, has done research to determine the extent of the ability of the structure in the fligth load, so the resulting deflection. From this research it was known that at flighting during 130 minutes, starting from take off the beginning of the flight until cruising with maximum velocity in 130 km/h, the maximum deflection that occurred in the structure only reaches 5.593 x 10-6 m, with a safety factor of 1.3, it’s means that the structure was relatively save. While at the landing on a relatively save was velocity below 14 km/h. If landing at the velocity exceeding 20 km/h can be believed that the twin-boom structure suffered severe damage, because the stress occurs already exceeded from 650 MPa as the yield strenght of e-glass composite materials. Abstrak:Struktur twin boom merupakan salah satu komponen konstruksi pesawat terbang nir awak LSU-05 hasil karya Pusat Teknologi Penerbangan - LAPAN. Struktur ini berfungsi sebagai penyetabil gerakan pesawat. Dalam operasionalnya, struktur menerima beban terbang yang dapat mengakibatkan timbulnya lendutan. Melalui metode analitis yang melibatkan misi, dimensi dan konfigurasi struktur twin boom pesawat LSU-05, telah dilakukan penelitian untuk mengetahui sejauh mana kemampuan struktur dalam menerima beban terbang, sehingga mengakibatkan lendutan tersebut. Dari penelitian ini diketahui bahwa pada saat penerbangan, selama 130 menit mulai dari tinggal landas di awal penerbangan sampai dengan terbang jelajah pada kecepatan maksimal 130 km/jam, lendutan maksimal yang terjadi pada struktur hanya mencapai 5,593 x 10-6 m, dengan faktor keamanan sebesar 1,3 berarti struktur relatif aman. Sedangkan untuk pendaratan, kecepatan yang relatif aman dapat dilakukan di bawah 14 km/jam. Jika mendarat pada kecepatan melebihi 20 km/jam, struktur twin boom tersebut mengalami kerusakan parah, karena tegangan yang terjadi sudah melebihi 650 MPa sebagai tegangan ijin bahan struktur yakni komposit e-glass.
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Viscardi, Massimo, Maurizio Arena, Liberata Guadagno, Luigi Vertuccio, and Giuseppina Barra. "Multi-functional nanotechnology integration for aeronautical structures performance enhancement." International Journal of Structural Integrity 9, no. 6 (2018): 737–52. http://dx.doi.org/10.1108/ijsi-11-2017-0060.
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Purpose The purpose of this paper is to evaluate the applicative potentiality of functional/self-responsive materials in aeronautics. In particular, the study aims to experimentally validate the enhancement of structural performances of carbon fibers samples in the presence of nanofillers, as multi-walled carbon nanontubes or microcapsules for the self-healing functionality. Design/methodology/approach The paper opted for a mechanical study. Experimental static and dynamic tests on “blank” and modified formulations were performed in order to estimate both strength and damping parameters. A cantilever beam test set-up has been proposed. As a parallel activity, a numerical FE approach has been introduced to assess the correct modeling of the system. Findings The paper provides practical and empirical insights about how self-responsive materials react to mechanical solicitations. It suggests that reinforcing a sample positively affects the samples properties since they, de facto, improve the global structural performance. This work highlights that the addition of carbon nanotubes strongly improves the mechanical properties with a simultaneous slight enhancement in the damping performance. Damping properties are, instead, strongly enhanced by the addition of self-healing components. A balanced combination of both fillers could be adopted to increase electrical conductivity and to improve global performance in damping and auto-repairing properties. Practical implications The paper includes implications for the use of lightweight composite materials in aeronautics. Originality/value This paper fulfills an identified need to study new lightweight self-responsive smart materials for aeronautical structural application.
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Ye, Hai Chao, Guo Hua Qin, Cong Kang Wang, and Dong Lu. "A Simulation Study on the End Milling Operation with Multiple Process Steps of Aeronautical Frame Monolithic Components." Applied Mechanics and Materials 66-68 (July 2011): 569–72. http://dx.doi.org/10.4028/www.scientific.net/amm.66-68.569.
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Machining deformation has always been a bottleneck issue in the manufacturing field of aeronautical monolithic components. On the base of finite element method, the effect of the process steps and tool paths on the workpiece stiffness and the redistribution of residual stress in the machining process of aeronautical frame monolithic component was investigated under the given fixturing scheme. Thus, the prediction of the workpiece deformation can be carried out in reason. The proposed simulation approach to deformation analysis can be used to observe the true characteristic of milling forces and machining deformations. Therefore, the proposed method can supply the theoretical basis for the determination of the optimal process parameters.
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Belkhiria, Chama, Atlal Boudir, Christophe Hurter, and Vsevolod Peysakhovich. "EOG-Based Human–Computer Interface: 2000–2020 Review." Sensors 22, no. 13 (2022): 4914. http://dx.doi.org/10.3390/s22134914.
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Electro-oculography (EOG)-based brain–computer interface (BCI) is a relevant technology influencing physical medicine, daily life, gaming and even the aeronautics field. EOG-based BCI systems record activity related to users’ intention, perception and motor decisions. It converts the bio-physiological signals into commands for external hardware, and it executes the operation expected by the user through the output device. EOG signal is used for identifying and classifying eye movements through active or passive interaction. Both types of interaction have the potential for controlling the output device by performing the user’s communication with the environment. In the aeronautical field, investigations of EOG-BCI systems are being explored as a relevant tool to replace the manual command and as a communicative tool dedicated to accelerating the user’s intention. This paper reviews the last two decades of EOG-based BCI studies and provides a structured design space with a large set of representative papers. Our purpose is to introduce the existing BCI systems based on EOG signals and to inspire the design of new ones. First, we highlight the basic components of EOG-based BCI studies, including EOG signal acquisition, EOG device particularity, extracted features, translation algorithms, and interaction commands. Second, we provide an overview of EOG-based BCI applications in the real and virtual environment along with the aeronautical application. We conclude with a discussion of the actual limits of EOG devices regarding existing systems. Finally, we provide suggestions to gain insight for future design inquiries.
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Martin, Paul, Gildas Guillemot, Michel Bellet, et al. "Solidification path for rapid solidification – Application to multicomponent alloys for L-PBF." IOP Conference Series: Materials Science and Engineering 1281, no. 1 (2023): 012062. http://dx.doi.org/10.1088/1757-899x/1281/1/012062.
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Abstract Laser Powder Bed Fusion (L-PBF) is seen as a process of interest by aeronautical industry to develop new engine components. Nevertheless, the reliability and durability of parts produced by L-PBF depend on the possibility to suppress the occurrence of defects. Among them, hot cracking represents a key issue. These cracks are due to the liquid film remaining between grains at the end of the solidification stage combined with stresses and strains endured by the mushy domain. A microsegregation model providing relevant prediction of the solidification path during L-PBF is thus required for coupling with a thermomechanical analysis. As an answer to the industrial need, a new model is proposed and applied in cooling conditions encountered in L-PBF. It includes the initial solidification conditions and follows the phases, and their composition in the interdendritic liquid region to predict the brittle temperature range. Both dendrite tip growth model and kinetic phase diagram due to non-equilibrium interface phenomena are considered. Cross-diffusion of solute species in the liquid phase is accounted for, as well as thermodynamic coupling with CALPHAD. The model will be applied to IN718, a nickel-based superalloy widely used in the aeronautic industry.
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Escaffre, Jérémy, Yann Lefaux, and Astrid Lenain. "The orbital friction welding process for engines components in aeronautic." MATEC Web of Conferences 321 (2020): 04024. http://dx.doi.org/10.1051/matecconf/202032104024.
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Titanium alloys are key materials in engines due to their low density, their high mechanical properties and their good resistance to corrosion and oxidation. Titanium engine parts are manufactured most of the time by forging, giving good mechanical properties associated with the possibility to optimize final microstructures of the parts. Due to design challenges consisting of making parts more robust and lighter, new processes are emerging. For some parts, friction welding can give opportunities to achieve those objectives because these assemblies are characterised by very good mechanical properties, generally higher than the raw unwelded materials [1]. As a consequence, the friction welding process is finding increasing applications as a manufacturing technology for the production of titanium alloy Ti-6Al-4V aerospace components [2]. Among those processes, the Orbital Friction Welding (OFW) technology is under study for low pressure compressors manufacturing. The BLuM® (Bladed drum, Figure 1), is constituted of a drum comprising several stages of friction-welded blades. Such architecture allows an important weight saving and performances improvement compared to current design. The objective of the article consists of addressing the orbital friction welding process, through the description of its characteristics, the key process parameters, the microstructures and the way of ensuring good integrity of the interface. The objective of the article consists of addressing the orbital friction welding process, through the description of its characteristics, the key process parameters, the microstructures and the way of ensuring good integrity of the interface.
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Cianetti, Ciotti, Palmieri, and Zucca. "On the Evaluation of Surface Fatigue Strength of a Stainless-Steel Aeronautical Component." Metals 9, no. 4 (2019): 455. http://dx.doi.org/10.3390/met9040455.
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In this paper, a novel method for the evaluation of the surface fatigue strength of a stainless-steel component is proposed. The use of stainless steel is necessary indeed, whenever a component has to work in a particularly aggressive environment that may cause an oxidation of the component itself. One of the major problems that affect stainless-steel components is the possible wear of the antioxidant film that reduces the antioxidant properties of the component itself. One of the main causes that can lead to wear is related to the surface corrosion that occurs every time two evolving bodies are forced to work against each other. If the antioxidant film is affected by surface fatigue problems, such as pitting or spalling, the antioxidant capacities of this type of steel may be lost. In this context, it is, therefore, necessary to verify, at least, by calculation that no corrosion problems exist. The method proposed in this activity is a hybrid method, numerical-theoretical, which allows to estimate the surface fatigue strength in a very short time without having to resort to finite element models that often are so complex to be in contrast with industrial purposes.
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González Ojeda, Itzel De Jesús, Pablo Bengoa, Aitor Ibarguren, et al. "Robot Coordination: Aeronautic Use Cases Handling Large Parts." Designs 6, no. 6 (2022): 116. http://dx.doi.org/10.3390/designs6060116.
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The coordination of two collaborative robots to handle and hold huge parts is the main topic of this research. This study shows how flexible systems may accommodate large-volume components while situating components with a displacement precision between robots of no more than 10 mm into the parts, with the assistance of a single operator. The robots must be able to keep the parts in place while coordinating their movements to handle the parts and reducing external stressors. This paper suggests using collaborative robots to integrate flexible tools for adaptability to various elements in order to accomplish this goal without endangering the operators. The software architecture is described in full in this paper, including machine states to choose task executions, robot referencing in the workspace, remote monitoring via the digital twin, generation paths, and distributed control using a high-level controller (HLC).
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Lu, Xufei, Michele Chiumenti, Miguel Cervera, Hua Tan, Xin Lin, and Song Wang. "Warpage Analysis and Control of Thin-Walled Structures Manufactured by Laser Powder Bed Fusion." Metals 11, no. 5 (2021): 686. http://dx.doi.org/10.3390/met11050686.
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Thin-walled structures are of great interest because of their use as lightweight components in aeronautical and aerospace engineering. The fabrication of these components by additive manufacturing (AM) often produces undesired warpage because of the thermal stresses induced by the manufacturing process and the components’ reduced structural stiffness. The objective of this study is to analyze the distortion of several thin-walled components fabricated by Laser Powder Bed Fusion (LPBF). Experiments are performed to investigate the sensitivity of the warpage of thin-walled structures fabricated by LPBF to different design parameters such as the wall thickness and the component height in several open and closed shapes. A 3D-scanner is used to measure the residual distortions in terms of the out-of-plane displacement. Moreover, an in-house finite element software is firstly calibrated and then used to enhance the original design in order to minimize the warpage induced by the LPBF printing process. The outcome of this shows that open geometries are more prone to warping than closed ones, as well as how vertical stiffeners can mitigate component warpage by increasing stiffness.
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Deloison, Dominique, Claudie Darcourt, Albert Abisror, Christophe Decker, and Bertrand Journet. "Recent Advances in Welding Simulation of Aeronautical Components." Revue Européenne des Éléments Finis 13, no. 3-4 (2004): 377–89. http://dx.doi.org/10.3166/reef.13.377-389.
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Soprano, Alessandro, Alfonso Apicella, Luigi D'Antonio, and Francesco Schettino. "Application of durability analysis to glare aeronautical components." International Journal of Fatigue 18, no. 4 (1996): 265–72. http://dx.doi.org/10.1016/0142-1123(96)00009-6.
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Sow, Cheikh Tidiane, Grégoire Bazin, Thomas Heuzé, and Guillaume Racineux. "Electromagnetic flanging: from elementary geometries to aeronautical components." International Journal of Material Forming 13, no. 3 (2020): 423–43. http://dx.doi.org/10.1007/s12289-020-01547-y.
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Rauch, Matthieu, Jean-Yves Hascoët, and Manjaiah Mallaiah. "Repairing Ti-6Al-4V aeronautical components with DED additive manufacturing." MATEC Web of Conferences 321 (2020): 03017. http://dx.doi.org/10.1051/matecconf/202032103017.
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Direct Energy Deposition (DED) processes are Additive Manufacturing (AM) processes that provide new perspectives for the manufacturing industry. In particular the area of component repair could highly benefit from these processes. It is consequently necessary to ensure the ability of DED processes, so that the repaired component can provide the same level of service than a new one. This paper focuses on the repair of Ti-6Al-4V parts by powder based LMD AM and investigates its accuracy, repeatability and reliability. At first, an experimental campaign has been carried out to evaluate the characteristics of as-built material. Optimal process parameter selection is made by a porosity and macrostructure analysis. Tensile properties, Low Cycle Fatigue and crack propagation studies have been done on as-built samples (100% AM) and interface samples (50% AM / 50% substrate). The results compare to wrought alloy and validate the relevance of LMD to produce sound repaired parts. In a second section, the paper proposes a semi automatic repair method of Ti-6Al-4V components: the defect geometry and the CAD model of the part to repair are identified from 3D scanning operations. Adapted additive and machining tool paths are then generated on the selected equipment.
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Tomaszek, Henryk, Józef Żurek, and Sylwester Kłysz. "A Method to Estimate Operational Fatigue Life of Aeronautical Structural Components and Experimental Verification Thereof - An Outline." Research Works of Air Force Institute of Technology 23, no. 1 (2008): 77–88. http://dx.doi.org/10.2478/v10041-008-0020-4.
Full textAbstract:
A Method to Estimate Operational Fatigue Life of Aeronautical Structural Components and Experimental Verification Thereof - An OutlineThe study presents an attempt to estimate fatigue life of structural components with further verification of the applied method by means of testing the specimens taken. Therefore, it has been assumed that a specimen subjected to tests is a structural component of a real system, and operational loads have been simulated in the form of a predefined loading scheme. All parameters necessary for the method have been derived from the analyses of both the specimens subjected to tests and properties of the preset load spectrum.The applied method of fatigue life estimation represents a probabilistic approach based on the Paris formula for the crack growth rate, and on difference equations that after some transformation result in an equation of the Fokker-Planck type. A probability density function of a crack length is a solution to this equation and depends on either the total time of operating the component in question or the number of load cycles applied.The probability density function of a crack length has been used to find out a formula for the probability of not exceeding the permissible crack length against the number of load cycles. The derived relationship has been applied after normalization to estimate fatigue life as based on results of experimental examination of specimens made from titanium alloy.The nomenclature of the aeronautical engineering is used throughout the paper due to the assumption that the component exposed to tests represents a part of an aircraft. This, in turn, has been intended to show some specific application(s) of the formulated model.