Relevant bibliographies by topics / Aeronautic component

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Aeronautic component'

Author: Grafiati
Published: 4 June 2025
Last updated: 23 June 2025

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Journal articles on the topic "Aeronautic component"

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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7

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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Dissertations / Theses on the topic "Aeronautic component"

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Hawwari, Yasmine. "Developement of some signal processing tools for vibro-acoustic based diagnosis of aeronautic machines." Electronic Thesis or Diss., Lyon, INSA, 2022. https://theses.insa-lyon.fr/publication/2022ISAL0131/these.pdf.

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Le prétraitement des signaux de vibration dans des conditions difficiles comme celles de l'aéronautique semble être compliqué. Les conditions de fonctionnement sont nonstationnaires et le moteur présente au moins deux familles harmoniques non-linéaires liées à l'arbre à basse et haute pression. De plus, les contraintes de conception imposent un nombre réduit d'accéléromètres (généralement deux) qui est insuffisant pour détecter tous les phénomènes liés à l'arbre. Les signaux acoustiques ne sont pas soumis à cette dernière contrainte. Cependant, ils sont très bruyants par rapport aux signaux de vibration et peuvent ne pas détecter les problèmes de faible énergie. De plus, ils dépendent fortement de la position du microphone et de sa directivité. Ainsi, l'objectif de la thèse est de proposer/essayer des méthodes robustes pour principalement (i) l'interférence entre différents phénomènes linéaires et non linéaires, (ii) les conditions de fonctionnement non stationnaires et (iii) les phénomènes de bruit à large bande (lorsqu'ils ne sont pas d'intérêt). Ces difficultés scientifiques sont considérées à travers (1) une détection aveugle des pics spectraux, (2) l'estimation de la vitesse instantanée et (3) l'estimation de la composante déterministe/tonale<br>Pre-processing vibration signals in harsh conditions such as the aeronautic conditions seems a complicated task. The operating conditions are nonstationary and the motor exhibits at least two harmonic non-linear families related to low and high pressure shaft. Furthermore, the design constraints impose a reduced number of accelerometers (generally two) which is unfortunately insufficient to detect all the shaft related phenomena. The acoustic signals are not subjected to the latter constraint. However, they are very noisy in comparison to vibration signals and may not detect low energy problems and very low frequency phenomena. Besides, the obtained signals depend strongly on the microphone position and its directivity in addition to the problem of clipping with medium to high acoustic pressure values. Thus, the PhD objective is to propose methods robust to mainly (i) the interference between different linear and non-linearly related phenomena, (ii) the nonstationary operating conditions and (iii) the broadband noise phenomena. These scientific difficulties are considered through (1) a blind detection of spectral peaks, (2) the estimation of the instantaneous speed and (3) the estimation of the deterministic/tonal component
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Rubbini, Monica. "Ottimizzazione topologica di componente aeronautico." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2019.

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L’attività svolta in questa tesi prevede l’ottimizzazione topologica di un componente aeronautico. In particolare, ho effettuato lo studio su un supporto per una telecamera, che verrà poi fissato ad un elicottero utilizzato per cercare persone disperse oppure per soccorso e sorveglianza. Nella tesi è stata svolta una analisi strutturale della attuale struttura e successivamente è stata implementata l'ottimizzazione topologica sfruttando un codice di calcolo FEM a disposizione dei laboratori universitari. Il risultato ottenuto in seguito alla ottimizzazione topologica è una struttura sensibilmente più leggera di quella originale.
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VIRDIS, IRENE. "Uncertainty Quantification and Optimization of Aeronautical Components." Doctoral thesis, Università degli Studi di Cagliari, 2022. http://hdl.handle.net/11584/332668.

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This project was part of a wider investigation performed on a set of 200 High Pressure Turbine (HPT) blades, dismounted after several hours of flight and characterized by in-service and manufacturing variations. The main objective of this project was to determine the impact of these variations on the aerodynamic performance of the rotor and to devise a strategy to design more robust geometries, i.e, less sensitive to the given uncertainties. The initial set of data consisted of the digitized versions of the blades (GOM scans). The geometrical deviations characterizing the blades from their hub until the 70% of the span were parametrized via a set of aerodynamic Engineering Parameters belonging to PADRAM design space (EP) and quantified via an inverse mapping procedure (P2S-PADRAM-SOFT); the visual inspection of the digital twins highlighted a considerable volume loss along the blade rim (tip region) due to localized erosion: the quantification of this metal degradation was performed via in-house Python scripts and expressed as indices of volume removal rate (PADRAM Squealer Tip option). The adjoint solver and the Polynomial Chaos Expansion (PCE) were used for the Uncertainty Propagation (UP) of the first set of uncertain variables, while for the erosion parameters only PCE was selected. The sensitivity of the nominal blade with respect to the typical erosion level was found to be higher than that of the geometrical deviations occurring beneath the tip. UP was followed by a series of gradient-based robust optimizations (RO) approaches. The rotor efficiency was selected as the figure of merit to be maximized by optimizing the EP values; in the first approach, the performance of a simplified geometry (without winglet and gutter) was slightly improved driving SLSQP Python optimizer via adjoint gradients. Following this, the nominal configuration, complete with winglet and gutter, was optimized providing SLSQP with the first order derivatives calculated via PCE. The same strategy for the calculation of the derivatives was used in the third approach, only this time the erosion level, characterizing the worst damaged rim, was included. A local, gradient-based, optimization was then performed in a larger design space: the final optimized configuration is then recovered a good percentage of rotor efficiency otherwise lost when the erosion occurs, thanks to an offloading of the tip region, while also improving the nominal rotor performance.
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Mercanti, Camilla. "Progettazione bio-inspired ed ottimizzazione topologica per componenti aeronautici." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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Al fine di diminuire il peso dell’aeromobile e quindi i consumi, si cercano strutture più efficienti e quindi leggere. Le tecniche di stampa 3D, che si stanno sviluppando in questi anni, consentono di non avere più limiti sulla forma delle strutture portando a geometrie più complesse e performanti. Quindi è possibile, da una parte, ispirarsi alle strutture naturali, come lo scheletro umano, per progettare strutture leggere e allo stesso tempo robuste, dall’altra riprogettare le strutture esistenti alla luce delle nuove tecniche di produzione, attraverso l’analisi topologica. Questo lavoro di tesi ha lo scopo di definire lo stato dell’arte di queste nuove tecnologie nel campo aeronautico, in particolare per gli aeromobili commerciali di nuova generazione. Per dimostrare l’efficacia di queste nuove tecnologie si è considerato come caso di studio il supporto di un sedile aeronautico, componente strutturale secondario di un aeromobile.
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Cikrikci, Davut. "Design And Analysis Of A Structural Component Of A Heavy Transport Aircraft." Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/2/12611552/index.pdf.

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This thesis aims to present the design and analysis of a structural component of a heavy transport aircraft. The designed component is the &ldquo<br>coupling&ldquo<br>which is the interface member connecting two frames or two stringers in the fuselage assembly. The &ldquo<br>frames&rdquo<br>, which are the circumferential stiffeners, are joined together by the &ldquo<br>frame couplings&rdquo<br>. The &ldquo<br>stringers&rdquo<br>, which are the longitudinal stiffeners, are joined together by the &ldquo<br>stringer couplings&rdquo<br>. At the preliminary design phase<br>the structural design principles of the frame and the stringer coupling parts are explained<br>which are based on the company experiences that were gained from previous aircraft projects. Afterwards, conceptual design phase is performed by structural analysis of the components. The structural analysis methods are defined and illustrated by analyzing typical examples of the frame and the stringer coupling parts. Moreover, the critical load case selection process for the structural components is explained and brief information about the load cases that the structural components will be subjected to in their service life are also given in order to have a feeling about flight regime of the aircraft. The applied loads used in structural analysis of the frame coupling and the stringer coupling components are obtained from the global finite element model of the aircraft. The verification process of the part of global finite element model where the developed components are located is also explained in the thesis. Finally, the general conclusions of the thesis are specified and the recommendations for future work are proposed for similar design and analysis efforts.
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Weiss, Kathryn Anne 1979. "Component-based systems engineering for autonomous spacecraft." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/82801.

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Masters, Brett P. (Brett Peter). "Multiple degree of freedom force-state component identification." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/49916.

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Ong, Elwin 1979. "Fault protection in a component-based spacecraft architecture." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/82804.

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Ouimet, Martin 1975. "A diagnostics architecture for component-based system engineering." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/17787.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004.<br>Includes bibliographical references (leaves 58-60).<br>This work presents an approach to diagnosis to meet the challenging demands of modern engineering systems. The proposed approach is an architecture that is both hierarchical and hybrid. The hierarchical dimension of the proposed architecture serves to mitigate the complexity challenges of contemporary engineering systems. The hybrid facet of the architecture tackles the increasing heterogeneity of modern engineering systems. The architecture is presented and realized using a bus representation where various modeling and diagnosis approaches can coexist. The proposed architecture is realized in a simulation environment, the Specification Toolkit and Requirements Methodology (SpecTRM). This research also provides important background information concerning approaches to diagnosis. Approaches to diagnosis are presented, analyzed, and summarized according to their strengths and domains of applicability. Important characteristics that must be considered when developing a diagnostics infrastructure are also presented alongside design guidelines and design implications. Finally, the research presents important topics for further research.<br>by Martin Ouimet.<br>S.M.
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Manfredini, Mattia. "Valutazione di codici di ingegneria inversa per la ricostruzione virtuale di componenti aeronautici." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2018.

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Valutazione dell'accuratezza dei programmi attualmente disponibili di reverse engineering basati sulla ricostruzione di componenti geometrici a partire da fotografie, al fine di una loro adozione come strumenti di supporto alle attività di un ingegnere aerospaziale. In una fase preliminare sono stati effettuati test su componenti semplici, per prendere confidenza con tali programmi e individuare quali meglio si prestassero a questo tipo di utilizzo. In seguito si è proceduto con il tentativo di ricostruzione di un modello più complesso e con un ampio range di forme geometriche diverse, con lo scopo di mettere alla prova il codice ritenuto più adatto ed individuare eventuali problematiche. I primi tentativi di ricostruzione hanno presentato livelli di accuratezza non accettabili già ad una semplice valutazione visiva; si è quindi provato a superare tale problema con la suddivisione del modello in tre elementi che successivamente sono stati uniti attraverso un software di elaborazione mesh. Il modello ottenuto da questo procedimento è risultato di qualità migliore rispetto al precedente ma non sufficientemente accurato per poter trovare un utilizzo pratico nella valutazione precisa di dimensioni lineari. Si è quindi giunti alla conclusione che tali procedure, allo stato attuale, non rappresentano un efficace strumento per l’ingegnere aeronautico, se non per svolgere valutazioni qualitative o di bassa precisione, in attesa che la rapida evoluzione dei codici di calcolo porti ad un incremento della fedeltà di rappresentazione dei componenti, tale da consentire valutazioni di ordine anche quantitativo.
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Books on the topic "Aeronautic component"

1

Borrini, Francesco. La componente spaziale nella difesa. Rubbettino, 2006.

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E, Buggele Alvin, Lepicovsky Jan, and Lewis Research Center, eds. Engine component instrumentation development facility at NASA Lewis Research Center. National Aeronautics and Space Administration, Lewis Research Center, 1992.

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Bradley, Obie H. 30th Aerospace Mechanisms Symposium: Proceedings of a symposium sponsored by the National Aeronautics and Space Administration, Washington, D.C., and Lockheed Martin Missiles and Space Company, Inc., Sunnyvale, California, and held in Hampton, Virginia, May 15-17, 1996. Langley Research Center, 1996.

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C, Oates Gordon, ed. Aerothermodynamics of aircraft engine components. American Institute of Aeronautics and Astronautics, 1985.

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Thomas, Carpenter. Comparison of straight and 15 degree vectored nozzles using a six component thrust stand: Final technical report, 10/90 - 12/91. California Polytechnic State University, m, 1991.

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Engineers, Society of Automotive, ed. SAE vehicle occupant restraint systems and components standards manual. Society of Automotive Engineers, 1993.

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Battrick, B. Impact 2000: Materials, computer hardware & software, automation & robotics, sensors & measuring techniques, mechanical components, precision mechanics & optics, communications, electronics & opto-electronics, medical. Edited by European Space Agency. ESA Publications, 1999.

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Engineers, Society of Automotive, ed. SAE vehicle occupant restraint systems and components standards manual. Society of Automotive Engineers, 1996.

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Foreman, Michael J. Flow field measuremnts of an airfoil with deflected spoiler using a two-component LDV sys. Naval Postgraduate School, 1986.

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American Institute of Aeronautics and Astronautics., ed. Managing the use of commercial off the shelf (COTS) software components for mission-critical systems: AIAA G-118-2006 guide. American Institute of Aeronautics and Astronautics, 2006.

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Book chapters on the topic "Aeronautic component"

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Fedele, Lorenzo, and Massimo Tronci. "Neural Networks for Aeronautical Components Maintenance and Management." In Probabilistic Safety Assessment and Management. Springer London, 2004. http://dx.doi.org/10.1007/978-0-85729-410-4_207.

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Gringoz, F., F. Thiébaut, C. Lartigue, and B. Soufflet. "Free-State Shape of Aeronautical Components for Assembly Simulation." In Advances on Mechanics, Design Engineering and Manufacturing II. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-12346-8_20.

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Ben Khalifa, Romdhane, and Noureddine Ben Yahia. "Development of STEP-NC Compliant Manufacturing for Machining Strategies of Aeronautical Components." In Lecture Notes in Mechanical Engineering. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-52071-7_13.

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Thomas, Johney, Antonio Davis, and Mathews P. Samuel. "Quality-Reliability-Risk-Safety Paradigm—Analyzing Fatigue Failure of Aeronautical Components in Light of System Safety Principles." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-4779-9_18.

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Al Risi, Al Reem Majid Ali, Fatma Hassan Khamis Al-Zaabi, Azza Marwan Salim Al Washahi, Raqiya Khalid Mohammed Al-Maaini, and Murali Krishna Boddu. "Machine Learning Algorithm Based Condition Monitoring of Electrical Components of Solar PV Plant with Ultraviolet Image Processing Observed Through Unmanned Aerial Vehicle." In Proceedings of the First International Conference on Aeronautical Sciences, Engineering and Technology. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-7775-8_16.

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Baumeister, Jan, Bernd Finkbeiner, Florian Kohn, et al. "Monitoring Unmanned Aircraft: Specification, Integration, and Lessons-Learned." In Computer Aided Verification. Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-65630-9_10.

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AbstractThis paper reports on the integration of runtime monitoring into fully-electric aircraft designed by Volocopter, a German aircraft manufacturer of electric multi-rotor helicopters. The runtime monitor recognizes hazardous situations and system faults. Since the correct operation of the monitor is critical for the safety of the aircraft, the development of the monitor must follow strict aeronautical standards. This includes the integration of the monitor into different development environments, such as log-file analysis, hardware/software-in-the-loop testing, and test flights. We have used the stream-based monitoring framework RTLola to generate monitors for a range of requirements. In this paper, we present representative monitoring specifications and our lessons learned from integrating the generated monitors. Our main finding is that the specification and the integration need to be decoupled, because the specification remains stable throughout the development process, whereas the different development stages require a separate integration of the monitor into each environment. We achieve this decoupling with a novel abstraction layer in the monitoring framework that adapts the monitor to each environment without affecting the core component generated from the specification. The decoupling of the integration has also allowed us to react quickly to the frequent changes in the hardware and software environment of the monitor due to the fast-paced development of the aircraft in a startup company.
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Suárez-Warden, Fernando, Yocelin Cervantes-Gloria, and Eduardo González-Mendívil. "Sample Size Estimation for Statistical Comparative Test of Training by Using Augmented Reality via Theoretical Formula and OCC Graphs: Aeronautical Case of a Component Assemblage." In Lecture Notes in Computer Science. Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-22024-1_10.

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Fistas, Nikos. "Future Aeronautical Communications: The Data Link Component." In Future Aeronautical Communications. InTech, 2011. http://dx.doi.org/10.5772/29899.

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de Oliveira, Ítalo Romani, Ricardo Alexandre Veiga Gimenes, and Jorge Rady de Almeida Jr. "Component-Based Development of Aeronautical Software." In Computational Models, Software Engineering, and Advanced Technologies in Air Transportation. IGI Global, 2010. http://dx.doi.org/10.4018/978-1-60566-800-0.ch014.

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Modern aircraft heavily relies on software to fly and operate, which lessens pilot workload, increases flight stability and fuel efficiency, and provides several other benefits. However, the more automated an aircraft is, the more prone to complexity its software modules are, raising special safety issues to be considered in the project. This chapter presents an overview of the Verification and Validation requirements for safety-critical software in aeronautics and, given the high costs to meet them, explains in detail a component-based methodology which can contribute to reduce the overall costs of software development and, at the same time, provide enhanced safety.
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Tassin Alan, Le Diraison Yohan, and Joubert Pierre-Yves. "A Comparative Study of Source Separation Techniques for the Detection of Buried Defects in the EC NDE of Aeronautical Multi-Layered Lap-Joints." In Studies in Applied Electromagnetics and Mechanics. IOS Press, 2008. https://doi.org/10.3233/978-1-58603-896-0-125.

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The authors present a multi-coil EC sensor dedicated to the rapid inspection of aeronautical riveted lap joints, and compare the efficiency of two signal processing methods based on principal component analysis and independent component analysis, to enhance the detection of buried defects appearing next to the rivets.
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Conference papers on the topic "Aeronautic component"

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Gaverina, Ludovic, Pierre Beauchêne, Stanislas Lech, and Jean-Michel Roche. "Multiscale inspection flying spot thermography for enhanced detection of fatigue cracks in aeronautical components." In Thermosense: Thermal Infrared Applications XLVII, edited by Giovanni Ferrarini, Fernando López, and Peter Spaeth. SPIE, 2025. https://doi.org/10.1117/12.3053993.

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Putnam, Jacob, Justin Littell, Nathaniel Gardner, and Matlock Mennu. "Component Characterization of an eVTOL Reference Model for Crashworthiness Studies." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1059.

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Researchers at the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) have conducted a series of structural component and seat level tests to improve finite element model (FEM) characterization of a representative vertical take-off and landing (eVTOL) test article developed by NASA. A full-scale dynamic test was conducted on the representative eVTOL test article in November of 2022. The test article represented a high wing, six passenger eVTOL design concept and is referred to as the lift plus cruise (LPC) test article. The full-scale test identified limitations in the analytical models used to predict aircraft structural response, in particular the composite material models did not effectively capture brittle failure of the structure which were measured during dynamic loading. To better understand the mechanism behind the composite material failure mechanisms observed and to improve the FEM, intact sample specimens of the composite airframe structure were recovered from the test article post-test and used in material characterization testing. In addition, the seat configurations used in the LPC test article were further studied using isolated seat and anthropomorphic test device (ATD) drop tower testing. Dynamic compression tests and three-point bend tests, conducted at varied impact speeds, were performed on the recovered frame section specimens. Additional testing was conducted to characterize the material properties of the forming foam, which remained in the frames after fabrication. These tests were used to improve characterization of the damage and failure parameters of the composite material model used in the FE model of the LPC test article. Seat level tests were conducted on the seats used in the LPC test article using acceleration pulses inclusive of current general aviation and rotorcraft certification load levels as well as conditions representative of those measured at the seat base during the LPC test. The structural material models and seat environment models of the LPC test article FEM were calibrated using the generated component test data. The updates made to these models were then integrated into the LPC FEM and simulated in the full-scale test condition. Results demonstrated the effectiveness of component testing to improve predictive capability of composite aerospace structural models within the crash and dynamic loading environments. Demonstration of the LPC FEM response across an accumulation of coupon, component, seat environment, and full-scale test levels provides confidence in the predictive capability of this model for future use in the study of occupant safety within eVTOL relevant crash environments.
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Perotto, Filipo, Anthony Pires, Jean-Loup Farges, et al. "Thinking the Certification Process of Embedded ML-Based Aeronautical Components Using AIDGE, a French Open and Sovereign AI Platform." In International Conference on Cognitive Aircraft Systems. SCITEPRESS - Science and Technology Publications, 2024. http://dx.doi.org/10.5220/0012965100004562.

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Lewis, Pattie L., and Jerome P. Curran. "Environmentally Preferable Corrosion Protection of Structural Steel." In CORROSION 2008. NACE International, 2008. https://doi.org/10.5006/c2008-08217.

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Abstract The U.S. space program is responsible for a number of facilities with metallic structural and nonstructural components in highly and moderately corrosive environments. To protect against the effects of corrosion, such structures are commonly covered with a coating system consisting of a zinc primer, intermediate coating, and topcoat. The most common topcoats used in such systems are polyurethanes that contain isocyanates and other hazardous materials. Their use, however, is being threatened by safety and environmental concerns and increasing regulations. In order to ensure mission readiness while reducing environmental and safety risks, the National Aeronautics and Space Administration (NASA) partnered with Headquarters Air Force Space Command (AFSPC) to demonstrate/validate environmentally preferable coating systems for use on steel substrates used on launch pads, test stands, and ground support equipment. This paper will present the results and conclusions from the laboratory and field testing. The study revealed at least two isocyanate-free coating systems that performed similar or better than the control coatings.
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Prete, Antonio Del, Rodolfo Franchi, Fabrizio Antermite, and Iolanda Donatiello. "Development of an automatic procedure for machining distortions improvement on an aeronautic axisymmetric component." In PROCEEDINGS OF THE 22ND INTERNATIONAL ESAFORM CONFERENCE ON MATERIAL FORMING: ESAFORM 2019. AIP Publishing, 2019. http://dx.doi.org/10.1063/1.5112616.

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Arcuri, R. "Neural networks for the identification of degraded components of aircraft fuel quantity system." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-15.

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Abstract. The physical and software architecture design of the fuel system of high-performance aircrafts is very complex and represents a challenging topic for aeronautic engineers. Among the main functionalities, there is the calculation of the on board fuel quantity, consisting in data computed by the fuel gauging sub-system, shown to the pilot on the cockpit display and used by the flight control system for aircraft controllability. Due to the large number of sensors and to a strongly ramified calculation code, faults and performance degradation of components, are difficult to be detected/isolated, since the operation would require an invasive investigation on the aircraft. To reduce the impact of the fault detection and isolation process in terms of time and costs, a digital twin of the fuel system has been developed and coupled with a condition-monitoring algorithm based on machine-learning methods. It is thus possible to quickly replicate the mission profiles during which the faults can occur, to calculate the residual fuel mass in parallel with the fuel computer and to precisely identify which component caused the system failure. A neural network, trained on experimental flight data, has been developed to provide reliable data. Once validated , the neural network is coupled with a 0D model that simulates the movement of the fuel inside the tank. In this way, it is possible to obtain the mass of fuel, simulating any flight mission profile. This approach optimizes the analysis of system malfunctions in terms of time and costs, highlighting unexpected mass values, otherwise undetectable. The reliability of the neural network can clearly be increased by training the algorithm with additional flight data, which can be derived from experimental or virtual flights simulated using the 0D model. The versatility of this process makes it applicable for different aircrafts as well as for further developments.
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Baila, Diana Irinel, Razvan Pacurar, and Ancuta Pacurar. "MECHANICAL BEHAVIORS OF POLYESTER RESINS REINFORCED WITH UNIFILO FIBERGLASS." In 22nd SGEM International Multidisciplinary Scientific GeoConference 2022. STEF92 Technology, 2022. http://dx.doi.org/10.5593/sgem2022/6.1/s24.05.

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In the last years, composite materials are increasingly used in automotive, aeronautic, aerospace, construction applications. Composite materials have been used in aerospace in applications such as engine blades, brackets, interiors, nacelles, propellers/rotors, single aisle wings, wide body wings. The fields of use of composite materials have multiplied with the improvement of material properties, such as stability and adaptation to the environment, mechanical tests, wear resistance, moisture resistance, etc. The composite materials are classified concerning type of matrix materials, as metallic, polymeric and ceramic based composites and are grouped according to the reinforcement type as fibre, obtaining particulate and laminate composites. Production of a better material is made more likely by combining two or more materials with complementary properties. The best combination of strength and ductility may be accomplished in solids that consist of fibres embedded in a host material. Polyester is a suitable component for composite materials, as it adheres so readily to the particles, sheets, or fibres of the other components. The important properties of the reinforcing fibres are their high strength and high modulus of elasticity. For applications, as in automotive or in aeronautical domain, in which a high strength-to-weight ratio is important, non-metallic fibres such as fiberglass have a distinct advantage because of their low density. In general, the glass fibres content varied between 9 to 33% wt. in the composites. In this article, high-performance types of composite materials glass-epoxy and glasspolyester used in automotive domain will be analyzed, performing tensile and flexural tests and SEM analyzes.
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Rouser, Kurt P., Caitlin R. Thorn, Aaron R. Byerley, Charles F. Wisniewski, Scott R. Nowlin, and Kenneth W. Van Treuren. "Integration of a Turbine Cascade Facility Into an Undergraduate Thermo-Propulsion Sequence." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94744.

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The Department of Aeronautics at the United States Air Force Academy utilizes a closed-loop, two-dimensional turbine cascade wind tunnel to reinforce a learning-focused undergraduate thermo-propulsion sequence. While previous work presented in the literature outlined the Academy thermo-propulsion sequence and the contextual framework for instruction, this current paper addresses how the Academy turbine cascade facility is integrated into the aeronautical engineering course sequence. Cadets who concentrate in propulsion are to some extent prepared for each successive course through their contact with the cascade, and ultimately they graduate with an exposure to experimental research that enhances their grasp of gas turbine engine fundamentals. Initially, the cascade is used to reinforce airfoil theory to all cadets in the Fundamentals of Aeronautics course. Aeronautical engineering majors take this course during the first semester of their sophomore year. The next semester all aeronautical engineering majors take Introduction to Aero-thermodynamics. In this course, the closed-loop aspect of the cascade facility is used to reinforce concepts of work addition to the flow. Heat transfer is also discussed, using the heat exchanger that regulates test section temperature. Exposure to the cascade also prepares cadets for the ensuing Introduction to Propulsion and Aeronautics Laboratory courses, taken in the junior and senior year, respectively. In the propulsion course, cadets connect thermodynamic principles to component analysis. In the laboratory course, cadets work in pairs on propulsion projects sponsored by the Air Force Research Laboratory, including projects in the cascade wind tunnel. Individual cadets are selected from the cascade research teams for summer internships, working at an Air Force Research Laboratory turbine cascade tunnel. Ultimately, cadet experiences with the Academy turbine cascade help lay the foundation for a two-part senior propulsion capstone sequence in which cadets design a gas turbine engine starting with the overall cycle selection leading to component-level design. The turbine cascade also serves to integrate propulsion principles and fluid mechanics through a senior elective Computational Fluid Dynamics course. In this course, cadets may select a computational project related to the cascade. Cadets who complete the thermo-propulsion sequence graduate with a thorough understanding of turbine engine fundamentals from both conceptual and applied perspectives. Their exposure to the cascade facility is an important part of the process. An assessment of cadet learning is presented to validate the effectiveness of this integrated research-classroom approach.
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Russo, A. "A numerical parametric study on delamination influence on the fatigue behaviour of stiffened composite components." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-82.

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Abstract. This paper investigates the fatigue phenomenon in Carbon Fibre Reinforced Plastic (CFRP) composite materials. Fatigue is a major problem in composite materials, due to their complex microstructures and inhomogeneous properties. In composite materials, fatigue is caused by cyclic loading, which leads to the accumulation of damage and eventually failure. This is related to several factors such as material properties, geometry, loading conditions, and environmental conditions. The fatigue life of composite materials is usually much lower than that of metals, and it is often catastrophic and unpredictable. Therefore, it is mandatory to understand behaviour of composite materials subjected to cyclic loading condition and to develop strategies to improve their fatigue performance. To this end, a Paris Law-based module has been implemented in the well-establish SMart-time XB (SMXB) procedure, being able to accurately numerically simulate the delamination growth caused by cyclic loads in complex composite structures. This process, which takes advantages of the mesh and load independency of the SMXB method in the evaluation of the delamination growth, has been implemented in the Ansys Parametric Design Language to create a highly versatile and parametric procedure. A numerical parametric study has been carried out to investigate the behaviour of a pre-existing circular delamination under cyclic loading, to assess the influence of delamination radius and thickness on the delamination growth. The results of this study will provide important insights into how delamination radius and thickness affect the delamination growth and the durability of composite structures. This study will help to inform the design of composite structures for various applications.
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Garofano, A. "On the use of double-double design philosophy in the redesign of composite fuselage barrel components." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-83.

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Abstract. Mass minimization and mechanical performance maximization constitute the basic aspects of the structural optimization processes. In particular, the laminate redesign in terms of thickness and lay-up grants the main approach for the optimization of composite components. The innovative Double-Double laminate concept provides an effective approach to design composite components for weight and strength requirements, overcoming the use of the conventional 0°, 90° and ±45° ply orientations. In Double-Double designed components, 4-plies building blocks are stacked one upon the other to constitute a laminate. Each building block is made up of four [±Φ, ±Ψ] oriented plies. In the present work, the Double-Double approach has been adopted in the redesign of the composite lay-up and thickness profile of frames in a composite fuselage barrel. The DD optimized frames achieved a total mass reduction by up to 35% while ensuring mechanical performances comparable to the starting configuration.
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