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Автор: Grafiati

Опубліковано: 7 липня 2024

Оновлено: 7 липня 2024

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Статті в журналах з теми "Aeronautical assembly":

Atik, Hafsa, Mouhssine Chahbouni, Driss Amagouz, and Said Boutahari. "An analysis of springback of compliant assemblies by contact modeling and welding distortion." International Journal of Engineering & Technology 7, no. 1 (January 27, 2018): 85. http://dx.doi.org/10.14419/ijet.v7i1.8330.

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Due to the development of the automotive and aeronautical industries, and the impossibility of pro-typing of the flexible parts because of the large real dimension as well as the behavior of this type of parts during the assembly, the tolerance of the flexible parts become an essential step in aeronautical manufacturing. Therefore the tolerance of plates in the assembly of mechanical systems is one of the key stages in the creation of a product in the automotive and aeronautical industries. This paper deals in the first stage a presentation of the tolerance of deformable mechanisms, through the illustration of the general problem. In order to study in the second stage the model of simulation of the variation of deformable (flexible) mechanisms, using the Influence Coefficient Method taking into account the effects of contact between the surface and including welding distortion. Finally the modeling of a mechanism of this type through an example with a view to an analysis of tolerances.

Dessena, Gabriele, Dmitry I. Ignatyev, James F. Whidborne, Alessandro Pontillo, and Luca Zanotti Fragonara. "Ground Vibration Testing of a Flexible Wing: A Benchmark and Case Study." Aerospace 9, no. 8 (August 10, 2022): 438. http://dx.doi.org/10.3390/aerospace9080438.

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Beam-like flexible structures are of interest in many fields of engineering, particularly aeronautics, where wings are frequently modelled and represented as such. Experimental modal analysis is commonly used to characterise the wing’s dynamical response. However, unlike other flexible structure applications, no benchmark problems involving high-aspect-ratio flexible wings have appeared in the open literature. To address this, this paper reports on ground vibration testing results for a flexible wing and its sub-assembly and parts. The experimental data can be used as a benchmark and are available to the aeronautical and structural dynamics community. Furthermore, non-linearities in the structure, where present, were detected. Tests were performed on the whole wing as well as parts and sub-assembly, providing four specimens. These were excited with random vibration at three different amplitudes from a shaker table. The modal properties of a very flexible high-aspect-ratio wing model, its sub-assembly and parts, were extracted, non-linear behaviour was detected and the experimental data are shared in an open repository.

da Silva, Bruno Jensen Virginio, Reinaldo Morabito, Denise Sato Yamashita, and Horacio Hideki Yanasse. "Production scheduling of assembly fixtures in the aeronautical industry." Computers & Industrial Engineering 67 (January 2014): 195–203. http://dx.doi.org/10.1016/j.cie.2013.11.009.

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Mei, Biao, Weidong Zhu, Pengyu Zheng, and Yinglin Ke. "Variation modeling and analysis with interval approach for the assembly of compliant aeronautical structures." Proceedings of the Institution of Mechanical Engineers, Part B: Journal of Engineering Manufacture 233, no. 3 (February 6, 2018): 948–59. http://dx.doi.org/10.1177/0954405418755823.

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Due to small production volume in aircraft industry, the available information of variation sources is often not enough to make assumptions on their probabilistic characteristics, especially in the stage of prototype manufacturing. To deal with the problem, an assembly variation modeling and analysis method based on the elasticity mechanics and interval approach is proposed for aircraft assembly. First, variation sources are modeled as bounded convex sets, which are defined as interval structural parameters in interval arithmetic. Then, variation modeling and analysis are successively implemented using the method of influence coefficient and interval arithmetic. After that, a uniform-splitting method is applied to achieve the refinement of the interval extension in variation analysis. To reduce the complexity of the finite element analysis and assembly variation computation, part deformation forms including warpage and torsion are concisely characterized with angle instead of the deviations of isolated key points on the part. The comparison of the assembly variations estimated with the proposed variation analysis method and actual experiment results verifies the effectiveness of the constructed assembly variation model and the proposed method. The interval approach–based assembly variation analysis method is a good complement to traditional probabilistic approach–based methods for compliant assembly systems, which is suited for linear and linearized nonlinear assembly systems. The proposed method provides an improved understanding of the application of compliant assembly variation analysis methods in aircraft manufacturing.

Borreguero-Sanchidrian, T. "Scheduling of an aeronautical final assembly line: a case study." Procedia Manufacturing 13 (2017): 1167–74. http://dx.doi.org/10.1016/j.promfg.2017.09.179.

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Cheng, Hui, Yuan Li, Kai Fu Zhang, and Feng Guo. "Deformation Analysis Method for Aeronautical Thin Walled Structures with Automated Riveting." Applied Mechanics and Materials 271-272 (December 2012): 1526–30. http://dx.doi.org/10.4028/www.scientific.net/amm.271-272.1526.

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The assembly variation of Aeronautical Thin Walled Structure (ATWS) with automated riveting is inevitable. The deformations of drilling, riveting and releasing are ralated to the final assembly variation. This paper represents a new method for deformation analysis of ATWS with automated riveting. Drilling deformation is modeled by the relationship among deflexion, strain and stress, riveting deformation is modeled by uilibrium equation, and releseaing deformation is modeled by releasing force. The comparison between computing result and expriment proves that the purposed deformation analysis method can solve the problem for ATWS automated riveting efficiently.

Kortaberria, Gorka, Unai Mutilba, Jon Eguskiza, and Joel Martins. "Simulation of an Aeronautical Product Assembly Process Driven by a Metrology Aided Virtual Approach." Metrology 2, no. 4 (October 6, 2022): 427–45. http://dx.doi.org/10.3390/metrology2040026.

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Major aircraft manufacturers are expecting the commercial aircraft market to overcome the pre-COVID levels by 2025, which demands an increase in the production rate. However, aeronautical product assembly processes are still mainly manually performed with a low level of automation. Moreover, the current industry digitalization trend offers the possibility to develop faster, smarter and more flexible manufacturing processes, aiming at a higher production rate and product customization. Here, the integration of metrology within the manufacturing processes offers the possibility to supply reliable data to constantly adjust the assembly process parameters aiming at zero-defect, more digital and a higher level of automation manufacturing processes. In this context, this article introduces the virtual metrology as an assistant of the assembly process of the Advanced Rear-End fuselage component. It describes how the assembly process CAD model is used by simulation tools to design, set up and perform the virtual commissioning of the new metrology-driven assembly methods, moving from a dedicated tooling approach to a more flexible and reconfigurable metrology-aided design. Preliminary results show that portable metrology solutions are fit-to-purpose even for hardly accessible geometries and fulfil the current accuracy demands. Moreover, the simulation environment ensures a user-friendly assembly process interaction providing further set-up time reduction.

Borreguero, T., F. Mas, J. L. Menéndez, and M. A. Barreda. "Enhanced Assembly Line Balancing and Scheduling Methodology for the Aeronautical Industry." Procedia Engineering 132 (2015): 990–97. http://dx.doi.org/10.1016/j.proeng.2015.12.587.

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Chang, Zhengping, Zhongqi Wang, Bo Jiang, Jinming Zhang, Feiyan Guo, and Yonggang Kang. "Modeling and predicting of aeronautical thin-walled sheet metal parts riveting deformation." Assembly Automation 36, no. 3 (August 1, 2016): 295–307. http://dx.doi.org/10.1108/aa-10-2015-077.

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Purpose Riveting deformation is inevitable because of local relatively large material flows and typical compliant parts assembly, which affect the final product dimensional quality and fatigue durability. However, traditional approaches are concentrated on elastic assembly variation simulation and do not consider the impact of local plastic deformation. This paper aims to present a successive calculation model to study the riveting deformation where local deformation is taken into consideration. Design/methodology/approach Based on the material constitutive model and friction coefficient obtained by experiments, an accurate three-dimensional finite element model was built primarily using ABAQUS and was verified by experiments. A successive calculation model of predicting riveting deformation was implemented by the Python and Matlab and was solved by the ABAQUS. Finally, three configuration experiments were conducted to evaluate the effectiveness of the model. Findings The model predicting results, obtained from two simple coupons and a wing panel, showed that it was a good compliant with the experimental results, and the riveting sequences had a significant effect on the distribution and magnitude of deformation. Practical implications The proposed model of predicting the deformation from riveting process was available in the early design stages, and some efficient suggestions for controlling deformation could be obtained. Originality/value A new predicting model of thin-walled sheet metal parts riveting deformation was presented to help the engineers to predict and control the assembly deformation more exactly.

Guo, Feiyan, Qingdong Xiao, Shihong Xiao, and Zhongqi Wang. "Analysis on quantifiable and controllable assembly technology for aeronautical thin-walled structures." Robotics and Computer-Integrated Manufacturing 80 (April 2023): 102473. http://dx.doi.org/10.1016/j.rcim.2022.102473.

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Дисертації з теми "Aeronautical assembly":

Haoua, Abdoulaye affadine. "Smart Machining pour l’assemblage aéronautique." Electronic Thesis or Diss., Paris, HESAM, 2023. http://www.theses.fr/2023HESAE090.

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Les empilements hybrides composés des couches composites CFRP, du TA6V et d'alliage d'aluminium, appelés multi-matériaux, sont largement utilisés dans les composants aérospatiaux. Le perçage one-shot, au moyen d'une Unité de Perçage Automatique (UPA), de ces empilements pose des défis majeurs en raison de la différence d'usinabilité entre les différents matériaux présents dans l'empilement. Pour répondre aux exigences de qualité, améliorer la tenue des outils et atteindre une pleine productivité lors du perçage de multi-matériaux sur UPA électrique, l’adaptation des paramètres de coupe au cours de l’usinage s’impose. Cela implique une détection fiable des matériaux usinés, la détection de l'usure de l'outil, ainsi que la détection d'incidents (bris d’outil, bourrage copeaux, problème de lubrification, écaillage des arêtes de coupe). Cependant, il n’existe pas actuellement des outils permettant de répondre à ce besoin. Le travail effectué dans cette thèse propose donc des solutions basées sur l’apprentissage automatique pour le développement des méthodologies robustes et fiables d’identification des matériaux, de détection de l'usure de l'outil, ainsi que de détection des incidents pour la mise en en place des stratégies de perçage intelligent (smart-drilling) intégrant de l’usinage auto-adaptatif. Dans un premier temps, une nouvelle approche de détection des incidents a été proposée en s’appuyant sur des données industrielles non étiquetées et des algorithmes de clustering : le K-means et la classification hiérarchique ascendante. Cette approche a permis d’identifier un certain nombre d’incidents et a mis en évidence les difficultés liées au traitement des données industrielles (rareté d’incidents et absence des étiquettes) et les difficultés liées à la définition des paramètres optimaux des algorithmes d’ apprentissage automatique. Dans un second temps, des essais sur un banc expérimental multi-instrumenté dédié et sur des empilements Al7175/CFP et CFRP/Al7175 ont permis de développer et de valider une méthodologie originale d’identification des matériaux basée sur les forêts aléatoires (Random Forest ou RF). Les résultats obtenus en termes de classification par types de matériaux (Al7175, CFRP), ont permis une extension du modèle RF sur différentes configurations d’empilements (CFRP/Al7175/TA6V, TA6V/Al7175/CFRP), avec différents diamètre outils et un large domaine de conditions de coupe. Cette méthodologie permettra d’envisager la mise en œuvre d’un processus d’usinage adaptatif sur UPA électrique pour le perçage de multi-matériaux.Mots clés : Usinage auto-adaptatif, Perçage multi-matériaux, Reconnaissance des matériaux, Forêts aléatoires, Usure outil, Apprentissage non supervisé, UPA électrique, Analyse des signaux
Hybrid stacks comprising of composite CFRP layers, TA6V, and aluminum alloy, referred to as multi-material, are widely used in aerospace components. One-shot drilling, using an Automatic Drilling Unit (UPA), of these stacks poses major challenges due to the difference in machinability among the various materials within the stack. To meet quality requirements, improve tool life and achieve optimal productivity during the drilling of multi-material stacks with an electric UPA, it is essential to adapt cutting parameters during machining. However, there are currently no tools available to meet this need. This theisis conerns machine learning-based solutions for the implementation of smart drilling strategies incorporating adaptive machining. These solutions focus on the development of robust and reliable methodologies for identifying materials, detecting tool wear, and detecting multi-material drilling-related incidents (tool breakage, chip jamming, lubrication issues, cutting edges chipping). Fristly, a new approach to incident detection was proposed, based on unlabeled industrial data and clustering algorithms: K-means and hierarchical ascending classification. This approach enabled us to identify a number of incidents, and highlighted the difficulties associated with processing industrial data (rarity of incidents and absence of labels) and the difficulties associated with defining the optimum parameters for machine learning algorithms. Subsequently, experiment are performed on an specialized instrumented drilling bench and on Al7175/CFP and CFRP/Al7175 stacks. This led to the development and validation of an original material identification methodology based on Random Forest (RF). The results, in terms of material classification (Al7175, CFRP), enabled the extension of the RF model to different stack configurations with various tool diameters and a wide range of cutting conditions. This methodology will enable the implementation of an adaptive machining process on an electric UPA for multi-material drilling.Keywords : Adaptive drilling, Multi-material stacks drilling, Material recognition, Random Forest, Tool Wear, Unsupervised learning, Electric UPA, Signals analysis

Anderson, David Elliott. "Supervisory control algorithms for telerobotic space structure assembly." Thesis, Massachusetts Institute of Technology, 1988. http://hdl.handle.net/1721.1/35941.

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Gralla, Erica Lynn. "Strategies for launch and assembly of modular spacecraft." Thesis, Massachusetts Institute of Technology, 2006. http://hdl.handle.net/1721.1/37886.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2006.
Includes bibliographical references (p. 97-101).
NASA's human lunar and Mars exploration program requires a new transportation system between Earth and the Moon or Mars. In recent years, unfortunately, human space exploration programs have faced myriad political, technical, and financial difficulties. In order to avoid such problems, future human space exploration programs should be designed from the start for affordability. This thesis addresses one aspect of affordable exploration programs by tackling the issue of high costs for access to space. While launch vehicle trades for exploration programs are relatively well understood, on-orbit assembly has been given much less attention, but is an equally important component of the infrastructure enabling human access to space. Two separate but related perspectives on in-space assembly of modular spacecraft are provided: first, the coupling between launch vehicle selection, vehicle design, and on-orbit assembly is explored to provide a quantitative understanding of this combined tradespace; and second, a number of on-orbit assembly methods are analyzed in order to understand the potential value of a reusable assembly support infrastructure.
(cont.) Within the first topic, a quantitative enumeration of the launcher-assembly tradespace (in terms of both cost and risk) is provided based on a generalizable process for generating spacecraft modules and launch manifests from a transportation architecture. An optimal module size and launcher capability is found for a sample architecture at 82 metric tons; a 28-mt EELV emerges as another good option. The results show that the spacecraft design, assembly planning, and launcher selection are highly coupled and should be considered together, rather than separately. Within the second topic, four separate assembly strategies involving module self-assembly, tug-based assembly, and in-space refueling are modeled and compared in terms of mass-to-orbit requirements for various on-orbit assembly tasks. Results show that the assembly strategy has a significant impact on overall launch mass, and reusable space tugs with in-space refueling can significantly reduce the required launch mass for on-orbit assembly. This thesis thus examines a broad but focused set of issues associated with on-orbit assembly of next-generation modular spacecraft.
by Erica Lynn Gralla.
S.M.

Koonmen, James P. (James Patrick). "Implementing precision assembly techniques in the commercial aircraft industry." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/12120.

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Hedgecock, Judson C. "Implementation of distributed processing for the beam assembly teleoperator." Thesis, Massachusetts Institute of Technology, 1990. http://hdl.handle.net/1721.1/43021.

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Katz, Jacob G. "Estimation and control of flexible space structures for autonomous on-orbit assembly." Thesis, Massachusetts Institute of Technology, 2009. http://hdl.handle.net/1721.1/50599.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2009.
Includes bibliographical references (p. 135-139).
The ability to autonomously assemble large structures in space is desirable for the construction of large orbiting solar arrays, interplanetary spacecraft, or space telescopes. One technique uses free-flying satellites to manipulate and connect elements of the structure. Since these elements are often flexible and lack embedded actuators and sensors, the assembly robot must use its own actuators and onboard measurements to suppress vibrations during transportation maneuvers. This thesis will examine the dynamic modeling of a free-flying robot attached to a flexible beam-like element, vision-based estimation of vibrational motion, and trajectory control for assembly of a space structure.
by Jacob G. Katz.
S.M.

Bunn, Jason Chrisotopher. "Evaluation of assembly simulators used in closed loop attitude control system testing." Thesis, Massachusetts Institute of Technology, 1997. http://hdl.handle.net/1721.1/47403.

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McCarthy, Bryan Patrick. "Flight hardware development for a space-based robotic assembly and servicing testbed." Thesis, Massachusetts Institute of Technology, 2014. http://hdl.handle.net/1721.1/90780.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2014.
Cataloged from PDF version of thesis. "This material is declared a work of the United States Government and is not subject to copyright protection in the United States."
Includes bibliographical references (pages 161-165).
Robotic assembly and servicing missions in space are becoming increasingly attractive for their potential to expand space capabilities and save money. Future missions may construct large systems on-orbit, service existing space assets, or remove retired satellites from valuable locations in the Geosynchronous orbit, among other things. Due to the high-risk nature of these missions, rigorous test facilities are a necessity. This thesis examines the existing testbeds for robotic assembly and servicing technologies and argues that a new, space-based testbed is necessary. It presents initial ground testing results for applicable control concepts, which also indicate that the dynamic authenticity associated with a six-degree-of-freedom on-orbit testbed is crucial for further development. This thesis then presents the requirements for such a testbed and describes the SPHERES Facility on the International Space Station. The facility, created by members of MIT's Space Systems Laboratory, has many of the desired testbed characteristics and can be easily expanded to meet the requirements through a hardware augmentation known as the Halo. The thesis develops the requirements for the Halo and then steps through the conception, design, and implementation of that hardware, along with the planned operations aboard the International Space Station.
by Bryan Patrick McCarthy.
S.M.

Jefferson, Thomas G. "Reconfigurable assembly system design methodology for aerospace wing structures." Thesis, University of Nottingham, 2017. http://eprints.nottingham.ac.uk/42778/.

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The aerospace industry is facing new challenges to meet burgeoning customer demand. An unprecedented number of orders for commercial aircraft has placed great urgency on aerospace manufacturers to make gains in production efficiency. Wing assembly is one such area where cycle times are in the order of hundreds of hours and commissioning cells can take several years which has led to a significant order backlog. In light of these challenges, new techniques are required to bring about greater agility to respond to market changes. Aerospace manufacturers must seize the opportunity to innovate and readdress approaches to ensure their prosperity. Recent research advocates Reconfigurable Assembly Systems (RAS) as a viable solution. A RAS is designed at the outset to change in structure to modify production capacity and functionality to meet new requirements. Yet, adding reconfigurability further increases design complexity. Despite the increased complexity, few formal methodologies exist to support RAS design for aerostructures. A novel RAS design methodology is presented to address the design complexity and the specific needs of Airbus. The methodology is a systems design approach consisting of reconfigurability principles, Axiomatic Design and Design Structure Matrices. Customer needs and existing knowledge are used to systematically specify scalable and customisable functionalities from the outset. These requirements and constraints are then translated into physical system designs modelled using CATIA, a 3D modelling software suite. The design methodology is applied in two case studies for wing assembly to produce full-scale factory designs. The designs are compared with current Airbus baselines in production ramp-up scenarios. The RAS demonstrate capability to change in structure for rapid increase in capacity at comparable cost to fixed systems. Greater capacity and shortened ramp-up time evidently reduces backlog compared to current systems. The first case study focused on technical development of a RAS and found potential ramp-up reduction of 88% and 10% less Capital Expenditure (CapEx) over 10 years. The second case study for a current wing scenario found reductions of 50% to ramp-up and 41% less tooling CapEx compared to a pulse line for a 12-year production cycle. The designs and scenarios were validated in formal Airbus design reviews. The case studies present the first instances of production-scale RAS for aerostructures. The RAS designs are made possible by designing from the outset using a novel design methodology which sets a precedent for the future of aerostructure assembly and opens up new possibilities for future research.

Shah, Ankit Jayesh. "Planning for manipulation of interlinked deformable linear objects with applications to aircraft assembly." Thesis, Massachusetts Institute of Technology, 2016. http://hdl.handle.net/1721.1/105640.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2016.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 83-87).
Manipulation of deformable linear objects (DLO) has potential applications in the fields of aerospace and automotive assembly. In this paper, we introduce a problem formulation for attaching a set of interlinked DLOs to a support structure using a set of clamping points. The formulation describes the manipulation planning problem in terms of known clamping locations; pre-determined ideal clamping locations on the cables, called "reference points", and a set of finite gripping points on the DLOs. We also present a prototype algorithm that generates a solution in terms of primitive manipulation actions. The algorithm guarantees that no interlink constraints are violated at any stage of manipulation. We incorporate gravity in the computation of a DLO shape and propose a property linking geometrically similar cable shapes across the space of cable length and stiffness. This property allows for the computation of solutions for unit length and scaling of these solutions to appropriate length, potentially resulting in faster shape computation.
by Ankit Jayesh Shah.
S.M.

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Книги з теми "Aeronautical assembly":

Service, Iowa General Assembly Committee on Air. Committee on Air Service report to the General Assembly. s.l: Iowa Dept. of Transportation, 2000.

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California. Legislature. Assembly. Select Committee on Aviation. The state's role in aviation safety: Interim hearing conducted by Assembly Select Committee on Aviation, October 20, 1986, State Capitol, Sacramento, California. Sacramento, CA (Box 90, State Capitol, Sacramento 95814): Joint Publications Office, 1986.

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United States. National Aeronautics and Space Administration., ed. Final test report for the qualification of the gristblast assembly and process for the inside diameter of the RSRM forward and aft domes. Brigham City, UT: Thiokol Corporation Space Operations, 1992.

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Meeting, COSPAR Plenary. Laboratory planetology: Proceedings of the B2 Symposium of COSPAR Scientific Commission B which was held during the Thirtieth COSPAR Scientific Assembly, Hamburg, Germany, 11-21 July, 1994. Oxford: Published for the Committee on Space Research [by] Pergamon, 1995.

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Assembly, COSPAR Scientific. Anticipating a solar probe: Proceedings of the D1.2 meeting of COSPAR Scientific Commission D, which was held during the thirtieth COSPAR Scientific Assembly, Hamburg, Germany, 11-21 July, 1994. Oxford, England: Published for the Committee on Space Research [by] Pergamon, 1995.

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Office, General Accounting. Space station: Cost to operate after assembly is uncertain : report to Congressional requesters. Washington, D.C. (P.O. Box 37050, Washington, D.C. 20013): The Office, 1999.

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Assembly, COSPAR Scientific. Near-earth radiation environment including time variations and secondary radiation: Proceedings of the meetings of F2.6 and F2.7 of COSPAR Scientific Commission F, which was held during the thirtieth COSPAR Scientific Assembly, Hamburg, Germany, 11-21 July, 1994. Oxford, England: Published for the Committee on Space Research [by] Pergamon, 1995.

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COSPAR. Panel on Technical Problems Related to Scientific Ballooning. PSB Meeting. Scientific ballooning: Proceedings of the PSB Meeting of the COSPAR Panel on Technical Problems Related to Scientific Ballooning which was held during the Thirtieth COSPAR Scientific Assembly, Hamburg, Germany, 11-21 July 1994. Oxford: Published for the Committee on Space Research [by] Pergamon, 1995.

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Assembly, COSPAR Scientific. Life and gravity: Physiological and morphological responses : proceedings of the F1.1 meeting of COSPAR Scientific Commission F, which was held during the thirtieth COSPAR Scientific Assembly, Hamburg, Germany, 11-21 July, 1994. Oxford, England: Published for the Committee on Space Research [by] Pergamon, 1995.

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Virginia. Dept. of State Police. Use of funds provided from the Rescue Assistance Fund for aviation (Med Flight) operations: Report of the Virginia Department of State Police to the Governor and the General Assembly of Virginia. Richmond, Va: Commonwealth of Virginia, 2005.

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Частини книг з теми "Aeronautical assembly":

Mozzillo, Rocco, Ferdinando Vitolo, Paola Iaccarino, and Pasquale Franciosa. "Tolerance Prediction for Determinate Assembly Approach in Aeronautical Field." In Lecture Notes in Mechanical Engineering, 229–40. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-31154-4_20.

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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, 203–12. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-12346-8_20.

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Pichon, Guillaume, Alain Daidie, Adeline Fau, Clément Chirol, and Audrey Benaben. "Cold Working Process on Hard Metal Stacked Assembly." In Lecture Notes in Mechanical Engineering, 41–47. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-70566-4_8.

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AbstractDesigned for aeronautical and automotive applications, the split sleeve cold expansion process is used to improve the fatigue life of bolted metallic parts. Although its application has been well tested on aluminum assemblies, hard metal applications are still being studied. This paper presents experimental results of double bolt joint assemblies under double shear fatigue tests after stacked split sleeve cold expansion. The behaviors of two sizes of assemblies with different degrees of expansion are investigated. S-N curves are the main indicators of this study but thermal aspects are also investigated to observe fretting in the specimens as bolts are preloaded. Bolt tension is a major parameter in assembly regarding fatigue life. Interference between those two phenomena is at the heart of this paper. The first results show that stacked cold expansion has a negative effect on mechanical performances, as it deteriorates the fatigue life of the assembly. However, an examination of these results provides a coherent explanation for the loss of performance that occurs.

Morales-Palma, Domingo, Ignacio Eguía, Manuel Oliva, Fernando Mas, and Carpóforo Vallellano. "Managing Maturity States in a Collaborative Platform for the iDMU of Aeronautical Assembly Lines." In Product Lifecycle Management and the Industry of the Future, 667–76. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-72905-3_59.

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Nuñez, Alex Aquieta, Anouck Chan, Alberto Donoso-Arciniega, Thomas Polacsek, and Stéphanie Roussel. "A Collaborative Model for Connecting Product Design and Assembly Line Design: An Aeronautical Case." In Lecture Notes in Business Information Processing, 267–80. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-91279-6_19.

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Mas, Fernando, Alejandro Gómez, José Luis Menéndez, and José Ríos. "Proposal for the Conceptual Design of Aeronautical Final Assembly Lines Based on the Industrial Digital Mock-Up Concept." In Product Lifecycle Management for Society, 10–19. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-41501-2_2.

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Cugini, Umberto. "Feature-Based Assembly for Aeronautics." In CAD Tools and Algorithms for Product Design, 31–46. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-04123-9_3.

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Tardieu, Hubert. "Role of Gaia-X in the European Data Space Ecosystem." In Designing Data Spaces, 41–59. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-93975-5_4.

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AbstractThe Gaia-X project was initiated in 2019 by the German and French Ministers of Economy to ensure that companies would not lose control of their industrial data when it is hosted by non-EU cloud service providers.Since then, Gaia-X holds an international association presence in Belgium with more than 334 members, representing both users and providers across 20 countries and 16 national hubs and 5 candidate countries.The Association aims to increase the adoption of cloud services and accelerate data exchanges by European businesses through the facilitation of business data sovereignty with jointly approved (user and provider) policy rules on data portability and interoperability.Although for many enterprises, data sovereignty is seen as a prerequisite for using the cloud, a significant driver to boost the digital economy in business is incentivizing business data sharing. Two decades of cost optimization have constrained business value creation, driving many companies to neglect the opportunity to create shared value within a wider industry ecosystem.Now, thanks to the participation of large numbers of cloud users in the domains of Finance, Health, Energy, Automotive, Travel Aeronautics, Manufacturing, Agriculture, and Mobility, among others, Gaia-X is ideally positioned to help industries define appropriate data spaces and identify/develop compelling use cases, which can then be jointly deployed to a compliant-by-design platform architecture under the Gaia-X specifications, trust, and labeling frameworks.The creation of national Gaia-X hubs that act as independent think tanks, ambassadors, or influencers of the Association further facilitates the emergence of new data spaces and use/enabler cases at a country level, before these are subsequently extended to a European scope and beyond. Gaia-X partners share the view that data spaces will play a similar role in digital business as the web played 40 years ago to help the Internet take off.The Gaia-X Working Groups are at the core of the Gaia-X discussions and deliverables. There are three committees: the Technical, the Policies and Rules, and the Data Spaces and Business.The Technical Committee focus on key architectural elements and their evolution, such as and not limited to: Identity and Access Management: bridge the traditional X509 realm and new SSI realm, creating a decentralized network of identity federations Service Composition: how to assemble services in order to create new services with higher added value Self-Description: how to build digital trust at scale with measurable and comparable criteria The Policy and Rules Committee creates the deliverables required to develop the Gaia-X framework (compliance requirements, labels and qualification processes, credentials matrix, contractual agreements, etc.): The Labels and Qualification working group defines the E2E process for labels and qualification, from defining and evolving the levels of label, the process for defining new labels, and identifying and certifying existing CABS. The Credentials and Trust Anchors working group will develop and maintain a matrix of credentials and their verification methods to enable the implementation of compliance through automation, contractual clauses, certifications, or other methods. The Compliance working group collects compliance requirements from all sources to build a unique compliance requirements pool. The Data Spaces Business Committee helps the Association expanding and accelerating the creation of new Gaia-X service in the market: The Finance working group focuses on business modeling and supports the project office of the Association. The Technical working group analyzes the technical requirements from a business perspective. The Operational Requirements working group is the business requirements unit. The Hub working groups hold close contact with all Gaia-X Hubs and support the collection and creation of the Gaia-X use and business cases. These working groups maintain the international list of all use cases and data spaces and coordinate the Hubs.

Caggiano, Alessandra, Luigi Nele, and Roberto Teti. "Drilling of Fiber-Reinforced Composite Materials for Aeronautical Assembly Processes." In Characterizations of Some Composite Materials. IntechOpen, 2019. http://dx.doi.org/10.5772/intechopen.80466.

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Megnafi, Hicham, and Walid Yassine Medjati. "Quadrotor-Type UAVs Assembly and Its Application to Audit Telecommunications Relays." In Aeronautics - New Advances. IntechOpen, 2022. http://dx.doi.org/10.5772/intechopen.104254.

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Field inspection process of the cellular network infrastructures is an important step during Radio Network Optimization. It allows the collection of all physical data of needed relays to efficiently optimize the network performances. The human-based performed inspection is initiated after the raise of a set of issues. The initiated operation is intended to resolve the cited issues as the errors in physical parameters extraction of relays, human safety issues as burns and falls, etc. This work revolves around an assembly and configuration of quadrotor drones in telecommunication relays inspections because of their easiest construction and their rapidly services. The user of the realized UAV can control and initiate the operation so intuitive thanks to its graphic control interface.

Тези доповідей конференцій з теми "Aeronautical assembly":

Da Costa, Sylvain J. "FACAI - A Flexible Assembly Cell for Aeronautical Industry." In Aerofast Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1993. http://dx.doi.org/10.4271/931770.

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Leila, Troudi, and Jelassi Khaled. "Assembly defect detection using rivets in aeronautical structures." In 2021 18th International Multi-Conference on Systems, Signals & Devices (SSD). IEEE, 2021. http://dx.doi.org/10.1109/ssd52085.2021.9429521.

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Hosokawa, Keisuke, Susumu Saito, Jun Sakai, Ichiro Tomizawa, Hiroyuki Nakata, Toru Takahashi, Michi Nishioka, et al. "Observations of sporadic E using aeronautical navigation radio waves." In XXXVth URSI General Assembly and Scientific Symposium. Gent, Belgium: URSI – International Union of Radio Science, 2023. http://dx.doi.org/10.46620/ursigass.2023.1493.mhft6662.

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Saito, Susumu, Maho Nakamura, Takayuki Yoshihara, Minh Le Huy, Thang Nguyen Chien, Slamet Supriadi, Prayitno Abadi, and Dwiko Unggul Prabowo. "Characterization of Ionospheric Spatial Decorrelation for GNSS-based Aeronautical Navigation Systems." In XXXVth URSI General Assembly and Scientific Symposium. Gent, Belgium: URSI – International Union of Radio Science, 2023. http://dx.doi.org/10.46620/ursigass.2023.2042.rwcc5650.

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Tabuchi, Shumpei, Keisuke Hosokawa, Susumu Saito, Jun Sakai, Ichiro Tomizawa, Toru Takahashi, and Hiroyuki Nakata. "Observation of sporadic E using aeronautical navigation radio for instrument landing system." In XXXVth URSI General Assembly and Scientific Symposium. Gent, Belgium: URSI – International Union of Radio Science, 2023. http://dx.doi.org/10.46620/ursigass.2023.1618.vfqi6822.

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Bordegoni, Monica, and Umberto Cugini. "Feature-Based Assembly Design: Concepts and Design Environment." In ASME 1997 Design Engineering Technical Conferences. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/detc97/cie-4266.

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Abstract The design of mechanical assemblies is mainly done after having modeled single parts. Most of the CAD systems are still weak for what concerns assembly. For example, they do not support the manipulation or the modification of the part geometry or the mating conditions once the assembly is made. The introduction of a feature-based approach in assembly design, successfully used in the design of single parts, would offer several advantages. This paper describes some results of the research work done within a project funded by the European Union aiming at extending the use of features, to help in the solution of assembly problems in the aeronautical applications.

Mozzillo, Rocco, Paola Iaccarino, Ferdinando Vitolo, and Pasquale Franciosa. "Design and development of jigless assembly process: the case of complex aeronautical systems." In 2019 II Workshop on Metrology for Industry 4.0 and IoT (MetroInd4.0&IoT). IEEE, 2019. http://dx.doi.org/10.1109/metroi4.2019.8792874.

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Lourenco, E. J., M. Oliva, M. A. Estrela, and A. J. Baptista. "Multidimensional Design Assessment Model for eco-efficiency and efficiency in aeronautical assembly processes." In 2019 IEEE International Conference on Engineering, Technology and Innovation (ICE/ITMC). IEEE, 2019. http://dx.doi.org/10.1109/ice.2019.8792641.

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Otto, A. J., R. P. Millenaar, C. Van der Merwe, T. Abbott, S. Tshongweni, and A. R. Botha. "Aeronautical radio frequency interference characterisation for the square kilometre array." In 2017 XXXIInd General Assembly and Scientific Symposium of the International Union of Radio Science (URSI GASS). IEEE, 2017. http://dx.doi.org/10.23919/ursigass.2017.8104497.

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Lin, Jia, Sun Jin, Cheng Zheng, Fuyong Yang, and Siyi Ding. "Variation Analysis of Accumulative Stresses in Multistep Assembly Processes Using Output Transformation Matrices." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-71215.

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Geometric variation produces gaps or interferences between the mating features of parts when assembling them. To accomplish the operation, forces need to be applied to deform the parts; while as a price, stresses arise around the structure and accumulate as the assembly process proceeds, which could impair the structural reliability. A tool modeling and analyzing the accumulation of assembly stresses can help us predict and control it. Associated with geometric variation, the levels of assembly stresses are variables as well, thus variation analysis of them is required rather than a single case analysis; however, research on assembly variation analysis has focused mainly on the geometric variation itself. In a previous study, we developed a compliant assembly variation analysis method which is based on a Finite Element (FE) model condensation technique of substructuring (Lin J, et al. “Compliant assembly variation analysis of aeronautical panels using unified substructures with consideration of identical parts.” Computer-Aided Design, 2014.). In this paper, by introducing Output Transformation Matrices (OTMs) into the unified substructure system, we add the analysis of assembly stresses onto that of assembly deviations: no extra modeling work is needed, but the assembly stresses within a part are recovered from its assembly deviations by OTMs. Though these OTMs need to be generated in advance, this one-off effort will be relatively small when the assembly process to be analyzed involves multiple steps. A case study on an aeronautical panel assembly is presented to illustrate the proposed method and investigate the characteristics of assembly stresses.