Journal articles: 'Aeronautical assembly'

1

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.

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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.

3

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.

5

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.

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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.

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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.

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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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Suárez-Warden, Fernando, Eduardo González Mendívil, Alejandro Fonseca Ramírez, and Salvador García-Lumbreras. "Profit Model for Incorporating AR Technology in Assembly Tasks of Aeronautical Maintenance." Procedia Computer Science 75 (2015): 113–22. http://dx.doi.org/10.1016/j.procs.2015.12.227.

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Hagnell, M. K., B. Langbeck, and M. Åkermo. "Cost efficiency, integration and assembly of a generic composite aeronautical wing box." Composite Structures 152 (September 2016): 1014–23. http://dx.doi.org/10.1016/j.compstruct.2016.06.032.

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Khebal, Merwane, Abdelhak Abdou, Tarik Bouchala, Abderrahmane Aboura, Kamel Belkhiri, and Amor Guettafi. "Static eddy current imaging for nondestructive testing of aeronautical structures." STUDIES IN ENGINEERING AND EXACT SCIENCES 5, no. 1 (June 28, 2024): 3484–501. http://dx.doi.org/10.54021/seesv5n1-173.

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Non-destructive testing (NDT) plays a crucial role in ensuring the safety and reliability of the structures used in aeronautics as it enables the detection of defects without damaging the parts examined. In the field of aeronautics, it is necessary to ensure the structural integrity of aircraft components. Vaulted head bolts are the most commonly used in this area to assemble multi-layered structures due to their strength and ability to maintain the structural integrity of aircraft. Examining these assembly areas can be challenging and present unique hurdles for non-destructive testing due to the shape and structure of the rivet, particularly its curved surface. This curvature can result in varying lift-off distances during surface scanning and alterations in the path of swirling currents near the rivet. Consequently, the response of vortex currents may vary, complicating the precise interpretation of test outcomes. In recent years, researchers have concentrated on devising advanced techniques for vortex testing to identify defects in complex structures, particularly those found in the aerospace industry. In this study, we have devised a model employing the finite element method (FEM) using COMSOL Multiphysics for non-destructive testing via 3D imaging utilizing a grid of multi-element vortex sensors distributed across multiple layers around the rivet, without necessitating the displacement of this grid. Our investigation, which involved analyzing various changes in lift-off distances for the sensor, demonstrated the accuracy of defect detection near the rivet, irrespective of the length and width of the defect. We propose a promising solution to tackle both the rivet's shape and the issue of probe displacement during testing. The sensors' non-displacement eliminates parasitic signals, preventing errors in signal interpretation, while multiplexed powering eliminates mutual inductance between adjacent coils.

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Jghamou, Afaf, Aziz Maziri, El Hassan Mallil, and Jamal Echaabi. "SECI Model Combined with ISO 9001 2015 to Support Organizational KM for Manual Assembly Manufacturing Operations." International Journal of Knowledge Management 18, no. 1 (January 1, 2022): 1–21. http://dx.doi.org/10.4018/ijkm.305226.

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In a large number of industrial sectors, manual assembly manufacturing operations highly engage tacit knowledge at an individual level. Companies in these sectors need to effectively manage organizational knowledge since it represents a real performance and sustainability lever. Although knowledge management (KM) specialists developed several models, these latter remain difficult to implement due to several barriers and limitations related to industrial reality and models ambiguity. This paper proposes an organizational knowledge management (OKM) framework for manual assembly manufacturing operations that is based on ISO 9001:2015 and SECI conversion cycle. This framework offers guidance for implementing a KM approach within the quality management system (QMS) allows to manage knowledge differently with regards to its tacitness level and overcomes many of the most common KM limitations. An experimental application based on a single case research design in an aeronautical assembly company is conducted to confirm the applicability and effectiveness of the framework suggested.

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McDougall, N. "BAE Systems/EPSRC integrated research programme in aeronautical engineering." Aeronautical Journal 110, no. 1104 (February 2006): 121–24. http://dx.doi.org/10.1017/s000192400000107x.

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Abstract BAE Systems and the Engineering and Physical Sciences Research Council (EPSRC) have recently formed a partnership to invest in strategic research in aerospace and defence. The framework which has been developed as part of this new alliance places a strong emphasis on collaboration. This contrasts with the conventional approach to industry led research which is normally based on the establishment of ‘centres of excellence’ in specific subject areas. By using a collaborative approach, the funding partners aim to benefit from inter-disciplinary collaboration which will take place during the project, giving rise to a more effective use of the invested funds. The objective of the research programme is to develop technologies which would support the design of low cost (both to acquire and operate) flapless unmanned aerial vehicles (UAVs). This work includes fundamental aerodynamic research to provide control forces without the use of conventional flaps, coupled with developments in the areas of control systems, manufacturing engineering, structural engineering, the electromagnetic behaviour of these structures and design optimisation. The output from the research has been extended to include the design, manufacture, assembly and flight of a demonstrator vehicle, which will provide the research teams with a platform on which to evaluate the performance of their technology in a realistic flight environment. A total of fourteen research groups at ten universities are involved in the five year programme, which has a total value of £6·5M (€9·75M).

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Atik, Hafsa, Mouhssine Chahbouni, Driss Amegouz, and Said Boutahari. "Optimization tolerancing of surface in flexible parts and assembly: Influence Coefficient Method with shape defects." International Journal of Engineering & Technology 7, no. 1 (January 27, 2018): 90. http://dx.doi.org/10.14419/ijet.v7i1.8470.

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Generally, a mechanical product must fulfill particular functions in accordance with the specification provided by the customer. A designer must find a solution with lower cost to answer the functional requirements. After the design stage, come the prototyping of the parts, but in case of the large structures of automotive and aeronautical parts, this step is impossible because of the large real dimension as well as the behavior of this type of parts during the positioning and during the assembly of all the mechanism.The aim of this article is to show the influence of geometrical shape differences in the assembly of flexible components in order to optimize the tolerancing of surface in flexible parts and assembly. first a presentation of the tolerance of deformable mechanisms through the illustration of the general problem, then we propose a new approach which takes into account shape defects based on the Influence Coeficient Method, after that we compare between a case study without takes into account shape defects and another one but this time taking into account shape defects always based on the Influence Coefficient Method.

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Lin, Jia, Sun Jin, Cheng Zheng, Zhimin Li, and Yinhua Liu. "Compliant assembly variation analysis of aeronautical panels using unified substructures with consideration of identical parts." Computer-Aided Design 57 (December 2014): 29–40. http://dx.doi.org/10.1016/j.cad.2014.07.003.

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Giublin, B., J. A. Vieira, T. G. Vieira, L. G. Trabasso, and C. A. Martins. "Experimental analysis of the automated process of sanding aircraft surfaces." Aeronautical Journal 118, no. 1199 (January 2014): 53–64. http://dx.doi.org/10.1017/s0001924000008927.

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Abstract ITA and EMBRAER are currently executing the research project Automation of Aircraft Structural Assembly (AASA) whose goal is to implement a robotic cell for automating the riveting process of aeronautical structures. The proposal described herein complements the AASA project, adds other manufacturing processes, namely sanding and polishing of aircraft surfaces. To implement the additional processes AASA project resources and facilities were used (robots and metrology systems) and devices designed and /or acquired to allow sharing of these resources. Among these, an Automatic Tooling Support for AERonautics structures (ATS_AER) was designed and built; also, a robot tool changer with high load capacity was acquired. The outcome of this research project is the evaluation of the feasibility of automating the processes of sanding and polishing metal surfaces in the aircraft manufacture using robots. The operating method adopted for surface treatment employed the ‘U’ type trajectory optimised to be run by a KUKA robot KR 500. The sanding process has been applied to aluminum metal sheet specimen sized 2•18ft2 (0•20m2) and used commercial 600 and 800 sandpaper. The automated sanding process yielded an average value of RA 0•48 ± 0•08 which is 25% more efficient when compared to the traditional, manual process whose average value of RA is 0•75 ± 0•51.

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Ma, Tianxiang, Shengqi Yang, Yongsen Xu, Dachuan Liu, Jinghua Hou, and Yunqing Liu. "Analysis and Correction of Measurement Error of Spherical Capacitive Sensor Caused by Assembly Error of the Inner Frame in the Aeronautical Optoelectronic Pod." Sensors 22, no. 23 (December 6, 2022): 9543. http://dx.doi.org/10.3390/s22239543.

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The ball joint is a multi-degree-of-freedom transmission pair, if it can replace the inner frame in the aviation photoelectric pod to carry the optical load, which will greatly simplify the system structure of the photoelectric pod and reduce the space occupied by the inner frame. However, installation errors in ball joint siting introduce nonlinear errors that are difficult to correct and two degree of freedom angular displacement of the ball joint is difficult to detect, which limits application in the precision control of two degrees of freedom systems. Studies of spherical capacitive sensors to date have not tested sensors for use in an inner frame stabilisation mechanism nor have they analysed the influence of installation error on sensor output. A two-axis angular experimental device was designed to measure the performance of a ball joint capacitive sensor in a frame stabilisation mechanism in an aeronautical optoelectronic pod, and a mathematical model to compensate for ball joint capacitive sensor installation error was created and tested. The experimental results show that the resolution of the capacitive sensor was 0.02° in the operating range ±4°, the repeatability factor was 0.86%, and the pulse response time was 39 μs. The designed capacitive sensor has a simple structure, high measurement accuracy, and strong robustness, and it can be integrated into ball joint applications in the frames of aeronautical photoelectric pods.

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Liu, Han Wu, Nan Li, Qiao Nan Tian, and De Chao Dong. "Microstructure Changes and Computer Simulation of K4169 Superalloy Using Chemical Grain Refinement Casting." Advanced Materials Research 189-193 (February 2011): 3954–59. http://dx.doi.org/10.4028/www.scientific.net/amr.189-193.3954.

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As an important aeronautical assembly materials, such as aeronautical gas turbine and turbine plate et al, K4169 alloy has enough high ability of resistance to high temperature deformation and a long low-period fatigue life when working, and its grain structure should be equiaxed dendrite as fine as possible in casting. Chemical grain refinement method was used to refine K4169 alloy to satisfy the demands mentioned above. By using new intermetallic compound grain refiners, chemical grain refinement casting technology was carried out to refine K4169 superalloy. The results show that the grain morphology has been transformed from dendrite to granulation, the average principal axis length of the primary dendrites has been shorted and the segregation ratios of main alloy elements mitigate with the decrease of grain size in fine-grained castings, which indicates the remarkable effects of grain refinement. In addition, basing on the model of equiaxed dendrite growth solute diffusion, continuous nucleation model, dendrite tip growth kinetics model and cellular automata (CA) technique to coupled simulate the grain structure formation process of K4169 alloy in chemical grain refinement casting, which agreed very well with experiments results, this will do much contribution to the theoretic base for studying high temperature mechanics performance and performance of resistance to corrosion of K4169 superalloy.

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Hou, Renluan, Qing Wang, Jiangxiong Li, and Yinglin Ke. "Modified Fourier–Galerkin Solution for Aerospace Skin-Stiffener Panels Subjected to Interface Force and Mixed Boundary Conditions." Materials 12, no. 17 (August 30, 2019): 2794. http://dx.doi.org/10.3390/ma12172794.

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Aeronautical stiffened panels composed of thin shells and beams are prone to deformation or buckling due to the combined loading, functional boundary conditions and interface forces between joined parts in the assembly processes. In this paper, a mechanical prediction model of the multi-component panel is presented to investigate the deformation propagation, which has a significant effect on the fatigue life of built-up structures. Governing equations of Kirchhoff–Love shell are established, of which displacement expressions are transformed into Fourier series expansions of several introduced potential functions by applying the Galerkin approach. This paper presents an intermediate quantity, concentrated force at the joining interface, to describe mechanical interactions between the coupled components. Based on the Euler–Bernoulli beam theory, unknown intermediate quantity is calculated by solving a 3D stringer deformation equation with static boundary conditions specified on joining points. Compared with the finite element simulation and integrated model, the proposed method can substantially reduce grid number without jeopardizing the prediction accuracy. Practical experiment of the aircraft panel assembly is also performed to obtain the measured data. Maximum deviation between the experimental and predicted clearance values is 0.193 mm, which is enough to meet the requirement for predicting dimensional variations of the aircraft panel assembly.

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Dimitrescu, A., C. Babiş, and A. M. Rugescu. "Comparisons between Assembly Technologies by Welding and Brazing of Aluminium Alloys from the Sight of Assembly Quality." IOP Conference Series: Materials Science and Engineering 1303, no. 1 (March 1, 2024): 012033. http://dx.doi.org/10.1088/1757-899x/1303/1/012033.

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Abstract Aluminum and its alloys are finding use in more and more industrial fields. Since the early 1970s, when many companies in the automotive, pharmaceutical and aeronautical industries replaced the classic components of iron alloys with those of aluminum alloys, they faced various difficulties in the non-removable assembly of designed components. The first assembly technologies used were welding, followed in the 1980s by brazing. Due to its economic advantages, in many cases brazing technologies are preferred by manufacturers. The present paper aims to make a comparative study, based on experimental data, between the non-removable assembly technology by welding and brazing for aluminum alloys of group 6000. Due to the high costs of materials and labor, it is preferable to use relevant non-destructive control methods that can indicate any discontinuities that may occur in welded or brazed structures. These defects can provide valuable information and may indicate either non-compliance with the required technological conditions or the wrong choice of assembly method. Non-destructive testing methods that can highlight interior defects, such as radiographic control with penetrating radiation and ultrasound will be used, as well as less expensive equipment and labor methods that may highlight surface defects or which communicates with the surface such as the method of control with penetrating liquids. Thus, the joint areas of the base and filler materials will be analyzed, as well as the areas in the immediate vicinity that have been thermally influenced. The experimental results will be able to lead to pertinent conclusions in the way of choosing the non-removable assembly technology, results that can be easily generalized in the industrial fields. Thus, each company will be able to choose according to the conditions imposed by the product specifications a certain technology that will satisfy its requirements.

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Schwaiger, Meinhard, and David Wills. "D-Dalus VTOL – efficiency increase in forward flight." Aircraft Engineering and Aerospace Technology 88, no. 5 (September 5, 2016): 594–604. http://dx.doi.org/10.1108/aeat-04-2015-0104.

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Purpose This paper aims to provide the international aeronautical community with details of the development of a new disruptive technology for aircraft propulsion. Design/methodology/approach This paper describes the results achieved by a small Austrian aeronautical innovations company in developing a cyclogyro propulsion system capable of vertical launch and efficient forward flight. The research team progressed from concept definition and simulation (2004-2006), through experimental validation and concept demonstration (2006), component optimization (2006-2012), full system demonstration (2012-2014) and examination of ability to scale (both larger and smaller) (2015 onwards). This paper provides details of the results of each of these stages. Findings The research team proved that cyclogyro propulsion can be used for the vertical launch, and that, in forward flight, it has the potential to achieve efficiency beyond the range of conventional fixed wing and rotorcraft. Research limitations/implications This research indicates that the efficiency increases with forward speed within the range achieved in standard wind tunnels (up to 35 m/s). This efficiency appears to be caused by a unique chamber effect within the cyclogyro rotor assembly. Future research should be conducted to analyse this chamber effect in greater detail and to test the cyclogyro rotor for speeds beyond 35 m/s. Practical implications This work indicates that cyclogyro propulsion could have the potential to provide vertical launch, high speed and highly efficient aircraft that have reduced wing span, no external rotors and exceptional agility. This technology could therefore be feasible for vertical take-off and landing aircraft that can safely form densely packed swarms. Social implications It could be researched as an efficiency increase in forward flight completely different to existing propulsion systems. This could open a way for a more efficient air traffic in future and faster reduction of CO2 and NOX emission an allow an environment-friendlier air travelling. Originality/value This paper provides the details of the first cyclogyro aircraft to have flown and will serve the aeronautical community by stimulating the debate on this new disruptive technology.

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Lettera, Gaetano, and Ciro Natale. "An Integrated Architecture for Robotic Assembly and Inspection of a Composite Fuselage Panel with an Industry 5.0 Perspective." Machines 12, no. 2 (February 1, 2024): 103. http://dx.doi.org/10.3390/machines12020103.

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Aeronautical robotic applications use quite large, heavy robots with huge end effectors that are frequently multifunctional. An assembly jig to hold a fuselage panel and two medium-sized six-axis robots fixed on linear axes, referred to as the internal and the external robot with respect to the curvature of the panel, make up the Lean robotized AssemBly and cOntrol of composite aeRostructures (LABOR) work cell. A distributed software architecture is proposed in which individual modules are developed to execute specific subprocesses, each implementing innovative algorithms that solve the main drawbacks of state-of-the-art solutions. Real-time referencing adopts a point-cloud-based strategy to reconstruct and process the part before drilling, avoiding hole positioning errors. Accurate concentric countersink diameters are made possible through the automatic adjustment of the drilling tool with respect to the skin panel, which guarantees its orthogonality, as well as the implementation of process parameter optimization algorithms based on historical results that compensate for the wear of the drilling bits. Automatic sealing and fastening strategies that involve the measurement of the main fastener quality parameters allow for the complete verification of the entire assembly process of each part. Additionally, an advanced multimodal perception system continuously monitors the collaborative workspace to ensure safe human–robot collaboration (HRC) tasks. Through this integrated architecture, LABOR substantially reduces expenses and facilitates maintenance and programming.

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Teng, Hsing Ming, Ming Chang Wu, Jin Yi Kao, Chun Yao Hsu, and Chung Chen Tsao. "The Effect of Thrust Force in Drilling Composite Materials Using a New Step Core-Ball Drill." Key Engineering Materials 830 (February 2020): 77–84. http://dx.doi.org/10.4028/www.scientific.net/kem.830.77.

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Compared with conventional metal materials, composite materials can sustain more loads under lower weight and lower space, which is more suitable to use in high strength environment for structure parts application in aerospace, military, transportation and leisure. The enormous aeronautical components and structures of composite materials require assembly and machining. Drilling is the most important making-hole process in the final assembly. However, conventional drill cannot avoid delamination in drilling composite materials effectively depending on tool geometry only. Delamination caused by drilling thrust has been showed as one of the most problematic defects after drilling composite laminates. Drilling of composite plates using a new step core-ball drill (NSCBD), which is a special drill to improve the chip flow and reduces the thrust force (delamination) at the exit of hole, is studied and compared to the traditional step core-ball drill (TSCBD). The thrust force of new step core-ball drill in drilling composite materials was investigated in this study. The theoretical analysis and experimental results show that the NSCBD can improve the thrust force (delamination) and efficiency than TSCBD in drilling composite materials.

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Rosenzveig, Guillaume, François Louf, and Laurent Champaney. "A FE model updating method for the simulation of the assembly process of large and lightweight aeronautical structures." Finite Elements in Analysis and Design 111 (April 2016): 56–63. http://dx.doi.org/10.1016/j.finel.2015.12.006.

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Guo, Feiyan, Qingdong Xiao, Shihong Xiao, and Zhongqi Wang. "Assembly technology for aeronautical CFRP structures under the collaborative constrains of geometric shape, physical performance and service stability." Composite Structures 318 (August 2023): 117071. http://dx.doi.org/10.1016/j.compstruct.2023.117071.

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Kumar, R., and M. Balasubramanian. "Comparative Study of Ti Alloy and Stainless Steel 304L Friction Welded Joint with Different Interlayer Process Methods." Applied Mechanics and Materials 766-767 (June 2015): 739–44. http://dx.doi.org/10.4028/www.scientific.net/amm.766-767.739.

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Rotary Friction welding is a process of solid state joining, broadly in shaft and pipe weld, in the field of automobile, defence, aeronautical, chemical and nuclear environment assembly pipe lines. Due to its some distinctive advantages similar to ease of fabricate, environmentally sociable, high fabrication value and appropriate for similar, dissimilar metal joint. Now a day’s Titanium alloy and stainless steel materials are very popular material in industrial application due to its high mechanical potency, and non-corrosive in nature. In this study an attempt was made to join commercial rod of Ti-6Al-4V and Stainless steel304L with some methods and evaluates the joint strength. Different intermediate metals are taking on in this process and the outcomes are witnesses. From that study the best method of in-between metal was analyzed by carry out mechanical and metallurgical test.

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Micol, Alexandre, Adrien Zéanh, Olivier Dalverny, and Moussa Karama. "Identification of the Sn96.5Ag3.5 Law Behavior with the Scatter of the Parameters - Study of Aeronautical Application in Power Module." Advanced Materials Research 112 (May 2010): 83–92. http://dx.doi.org/10.4028/www.scientific.net/amr.112.83.

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This work studies the reliability of power electronic component in aeronautical environment to the ageing eect of the thermal cycling. The structure fatigue is sensitive to the process assembly conditions especially of the soldering process. To correclty evaluate the reliability of the power module, the identication of the solder behavior is one of the rst steps. Anand Model is here identied. Experimental test have to be established to evaluate the parameters of the law. A srt study is made to evaluate the indetiability of the law according to the dierent experimantal test. Then, the scatter of the parameters is evaluated in a context of time series. In the end, the scatter of the parameters is included in a nite element model to understand the inuence of this scatter on the evaluation of the number of cycle before failure.

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Teng, Hsing-Ming, and Chung-Chen Tsao. "The effect of thrust force in drilling composite materials using step core-ball drill." MATEC Web of Conferences 185 (2018): 00016. http://dx.doi.org/10.1051/matecconf/201818500016.

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Composite materials have gained increasing popularity over the past few decades due to their superior mechanical properties, such as high strength-to-weight ratio, fighting against high temperature and corrosion resistance. The assembly of enormous aeronautical components and structures require the machining of composite materials. Drilling is the most important hole-making process in the final assembly. When drilling composite materials, a number of defects are generating. Delamination caused by drilling thrust has been showed as one of the most problematic defects after drilling composite laminates. With a pressing need for decreased delamination, many studies are turning more and more toward tool geometry and machining parameters. Drilling of composite plates using a step core-ball drill, which is a special drill to improve the chip flow and reduces the thrust force at the exit of hole, is investigated in this study. The experimental results found that the step core-ball drill was efficient in drilling of carbon fiber reinforced plastic (CFRP) and did not produce loading on the drill exit at the proper drilling conditions. The results obtained from this study feeding back for fundamental research efforts could steer future studies on the drilling composite materials in the most promising direction.

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Petitprez, Matthieu, and Katia Mocellin. "Numerical Study of a Crimped Assembly Mechanical Strength." Key Engineering Materials 554-557 (June 2013): 1037–44. http://dx.doi.org/10.4028/www.scientific.net/kem.554-557.1037.

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Electrical contact crimping is a mechanical fastening process commonly used in aeronautical and aero spatial applications. In order to ensure the perfect electrical conduction and acceptable mechanical properties, the assembly have to fullfil some drastic holding force criteria. This outfit is directly dependent on the indentation depth at the end of crimping. The feedback generally reveals that an over crimping will lead to the cable breakage whereas an under crimping will be characterized by the cable sliding into the contact during pulling. The optimal behavior is a combinaison of both phenomena : the cable must become thinner before slipping into the contact. Numerical simulation is an efficient tool to limit the tedious experimental tests. It is the main topic of our work. This paper deals with prediction of the failure type and the force level required to tear out a contact crimped on multistrand cable for different indentation depths. The determination of optimal crimping condition is determined. In order to simulate the contact tensile test, crimping simulation has to be performed. The first step is then to be able to simulate accurately the crimping stage by using appropriate behavior laws and realistic conditions. One difficulty is linked to the small size of our objects. The first one is a 19 strands cable, in which each strand is about 0.15 mm diameter. The second sample is a 1 mm diameter cylindrical copper contact measuring 7 mm long. Adapted testing devices are described. Geometries and mechanical fields are obtained and then exported in the mechanical holding model to ensure realistic prediction [1]. Impact of crimping conditions on the pulling results is discussed. Pulling simulation results are compared to experimental values. The prediction of breakage mechanisms is also studied. Keywords: Crimping process, mechanical fastening operation, finite element computations, mechanical strength, breakout force, tensile test. [1] Fayolle, S., 2008, Etude de la modélisation de la pose et de la tenue mécanique des assemblages par déformation plastique : application au rivetage auto poinçonneur, Thèse de l'Ecole des Mines de Paris.

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Caggiano, Alessandra, Xavier Rimpault, Roberto Teti, Marek Balazinski, Jean-François Chatelain, and Luigi Nele. "Machine learning approach based on fractal analysis for optimal tool life exploitation in CFRP composite drilling for aeronautical assembly." CIRP Annals 67, no. 1 (2018): 483–86. http://dx.doi.org/10.1016/j.cirp.2018.04.035.

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Ruiz, Leandro, Manuel Torres, Alejandro Gómez, Sebastián Díaz, José M. González, and Francisco Cavas. "Detection and Classification of Aircraft Fixation Elements during Manufacturing Processes Using a Convolutional Neural Network." Applied Sciences 10, no. 19 (September 29, 2020): 6856. http://dx.doi.org/10.3390/app10196856.

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The aerospace sector is one of the main economic drivers that strengthens our present, constitutes our future and is a source of competitiveness and innovation with great technological development capacity. In particular, the objective of manufacturers on assembly lines is to automate the entire process by using digital technologies as part of the transition toward Industry 4.0. In advanced manufacturing processes, artificial vision systems are interesting because their performance influences the liability and productivity of manufacturing processes. Therefore, developing and validating accurate, reliable and flexible vision systems in uncontrolled industrial environments is a critical issue. This research deals with the detection and classification of fasteners in a real, uncontrolled environment for an aeronautical manufacturing process, using machine learning techniques based on convolutional neural networks. Our system achieves 98.3% accuracy in a processing time of 0.8 ms per image. The results reveal that the machine learning paradigm based on a neural network in an industrial environment is capable of accurately and reliably estimating mechanical parameters to improve the performance and flexibility of advanced manufacturing processing of large parts with structural responsibility.

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Mozetic, Halston, Rafael Pandolfo Da Rocha, Matheus Henrique Riffel, and Lirio Schaeffer. "Application of the process of joining sheet by mechanical cold forming (clinching) using dissimilar materials." OBSERVATÓRIO DE LA ECONOMÍA LATINOAMERICANA 21, no. 12 (December 27, 2023): 27717–34. http://dx.doi.org/10.55905/oelv21n12-228.

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In the metalworking industry in general, the need to join components made of sheet metal is very common. The automotive sector, for example, needs to join components made of sheet metal to assemble vehicle bodies. The aeronautical sector needs to join sheets, mainly aluminum, when assembling aircraft. In white goods, there is a need to join low-carbon steel sheets that make up a wide range of household appliances, as well as other sectors such as metal structures, packaging and others. The joining of sheet metal components can be done through some permanent joining process, such as welding and riveting; or by some type of detachable connection, made by screw, nut, stud, pin, among others. A joining technique that has been gaining ground in the industry is plastic deformation joining. Groche et al. (2014) reviewed this technique and present the various existing variations. The most common is known as clinching union. According to Varis (2006), it emerged in the 1980s in an automotive industry in the assembly of chassis. The technique consists of cold joining sheets through the action of a punch that plastically deforms the sheets against a die. The deformation produces an interlook region that joins the sheets, giving the appearance of a spot weld. Sarmento and Pereira (2012) cite the main advantages of this technique: (I) it allows joining a vast amount of materials including metals with non-metals; (II) lower distortions, embrittlement and residual stress; (III) high process repeatability and simple quality control, and (IV) safe working environment.

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K'nevez, Jean Yves, Olivier Cahuc, Philippe Darnis, and Raynald Laheurte. "Mathematical Cutting Model Based on Experimental Approach: Drilling Application." Applied Mechanics and Materials 62 (June 2011): 77–84. http://dx.doi.org/10.4028/www.scientific.net/amm.62.77.

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The object of this work research tasks relates to the improvement of the cutting tools in drilling within the industrial framework of the aeronautical assembly. The stakes of the study consist in optimizing the lifespan of the tools according to a criterion of respect of geometrical quality and surface quality of the bored holes. This optimization relates to the geometry of the cutting part of the drills. The discussion thread of work thus tends to set up methods which make it possible to bind the geometry of the tools to the final quality of borings carried out. The study was divided into three stages differentiated and complementary to modeling of the physical phenomena induced by the process of drilling. The first stage [1] lies in describing the real geometrical parameters according to the parameters of grinding of the tool. While being based on the modeling of the geometry, the experimental cutting model enables to identify the mechanical actions of cut along the edge. Lastly, the phenomenological [2] aspect of the process associates the parameters of cut the final quality of the bored holes. [3].

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Ruiz-Garcia, Raul, Pedro Mayuet Ares, Juan Vazquez-Martinez, and Jorge Salguero Gómez. "Influence of Abrasive Waterjet Parameters on the Cutting and Drilling of CFRP/UNS A97075 and UNS A97075/CFRP Stacks." Materials 12, no. 1 (December 30, 2018): 107. http://dx.doi.org/10.3390/ma12010107.

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The incorporation of plastic matrix composite materials into structural elements of the aeronautical industry requires contour machining and drilling processes along with metallic materials prior to final assembly operations. These operations are usually performed using conventional techniques, but they present problems derived from the nature of each material that avoid implementing One Shot Drilling strategies that work separately. In this work, the study focuses on the evaluation of the feasibility of Abrasive Waterjet Machining (AWJM) as a substitute for conventional drilling for stacks formed of Carbon Fiber Reinforced Plastic (CFRP) and aluminum alloy UNS A97050 through the study of the influence of abrasive mass flow rate, traverse feed rate and water pressure in straight cuts and drills. For the evaluation of the straight cuts, Stereoscopic Optical Microscopy (SOM) and Scanning Electron Microscopy (SEM) techniques were used. In addition, the kerf taper through the proposal of a new method and the surface quality in different cutting regions were evaluated. For the study of holes, the macrogeometric deviations of roundness, cylindricity and straightness were evaluated. Thus, this experimental procedure reveals the conditions that minimize deviations, defects, and damage in straight cuts and holes obtained by AWJM.

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Graneix, Jeremie, Jean Denis Beguin, Joël Alexis, and Talal Masri. "Weldability of Superalloys Hastelloy X by Yb: YAG Laser." Advanced Materials Research 1099 (April 2015): 61–70. http://dx.doi.org/10.4028/www.scientific.net/amr.1099.61.

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Hastelloy X is a commercially available nickel-chromium-molybdenum superalloy with a good oxidation resistance, a good mechanical properties at high temperature and a significant formability; sine qua criteria for the choice of materials for the production of chambers turbojet combustion which is part of this study [1]. Arc welding technique is commonly used for the manufacturing of parts but the aeronautical requirements becoming increasingly severe especially in terms of reproducibility of geometry and metallurgical grade fillet weld. Laser welding is a viable method of assembly to meet these new demands by its automation to replace longer term the manual TIG welding. The high power CO2laser is extensively used for practical applications such as cutting and welding laser welding. The CO2laser is very used in the industry with regard to Yb:YAG laser which until now was not rather powerful but this changes. The aim of this study was to evaluate the effect of Yb:YAG laser beam parameters on the microstructure and mechanical properties of the laser beam welded superalloys Hastelloy X to define a field of weldability. The implementation of an experimental design approach is required due to the multitude of input parameters and the complexity of the phenomena involved [2-3].

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Trujillo Vilches, Francisco Javier, Sergio Martín Béjar, Carolina Bermudo Gamboa, Manuel Herrera Fernández, and Lorenzo Sevilla Hurtado. "Influence of Tool Wear on Form Deviations in Dry Machining of UNS A97075 Alloy." Metals 11, no. 6 (June 13, 2021): 958. http://dx.doi.org/10.3390/met11060958.

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Geometrical tolerances play a very important role in the functionality and assembly of parts made of light alloys for aeronautical applications. These parts are frequently machined in dry conditions. Under these conditions, the tool wear becomes one of the most important variables that influence geometrical tolerances. In this work, the influence of tool wear on roundness, straightness and cylindricity of dry-turned UNS A97075 alloy has been analyzed. The tool wear and form deviations evolution as a function of the cutting parameters and the cutting time has been assessed. In addition, the predominant tool wear mechanisms have been checked. The experimental results revealed that the indirect adhesion wear (BUL and BUE) was the main tool-wear mechanism, with the feed being the most influential cutting parameter. The combination of high feed and low cutting speed values resulted in the highest tool wear. The analyzed form deviations showed a general trend to increase with both cutting parameters. The tool wear and the form deviations tend to increase with the cutting time only within the intermediate range of feed tested. As the main novelty, a relationship between the cutting parameters, the cutting time (and, indirectly, the tool wear) and the analyzed form deviations has been found.

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Liu, Yuxuan, Wuxiang Zhang, Junyan Liu, Yingchun Guan, and Xilun Ding. "Study on microstructures and mechanical performance of laser transmission welding of poly-ether-ether-ketone (PEEK) and carbon fiber reinforced PEEK (CFR-PEEK)." Journal of Laser Applications 34, no. 4 (November 2022): 042037. http://dx.doi.org/10.2351/7.0000823.

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The reliable assembly of poly-ether-ether-ketone (PEEK) and carbon fiber-reinforced PEEK (CFR-PEEK) is crucial to effective load transfer within lightweight and high-stiffness structures, which are commonly demanded in aeronautical, automobile, and medical industries. In this work, laser transmission welding of PEEK and CFR-PEEK has been performed by using a 1070 nm Nd:YAG fiber laser. The effects of process parameters including laser power, laser scanning speed, and clamping pressure on joining quality have been investigated via mechanical, morphological, and thermal characterization. Results show that strong bonds have been formed by entanglements of polymer chains at the joining interface and the mechanical embedment between carbon fibers and PEEK. The formation mechanisms of bubble defects have been classified into three types. One of them was eliminated by scanning the joints twice, which significantly improved joints' mechanical performance and hermeticity with the maximum joining strength reaching 11.6 MPa. Also, a comparative study between PEEK/PEEK and PEEK/CFR-PEEK joints shows that the existence of carbon fibers within the CFR-PEEK significantly increased joints' decomposition threshold, joining region, and strength due to their great thermal conductivity. Besides, the influence of the welding process on the crystallinity of PEEK was analyzed, which was then improved from 11.7% to 34.1% through annealing.

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Mayuet, Pedro, Pedro Arroyo, Alberto Portal, Miguel Álvarez, Severo Raúl Fernández-Vidal, and Mariano Marcos Bárcena. "Comparison of Diameter and Area Change Based Methods for Evaluating Break-IN and Break-OUT Damages in Dry Drilled Holes of Aeronautical Carbon Fiber Composites." Materials Science Forum 797 (June 2014): 35–40. http://dx.doi.org/10.4028/www.scientific.net/msf.797.35.

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Currently, Carbon Fiber Reinforced Non-Metal Composites (CFRC) are commonly applied in structural components of aircrafts. Frequently, these elements need to be drilled for their assembly in the final product. Chips close to powder are formed when this kind of material is machined. Because of this, drilling processes are mostly performed in absence of cutting fluids. High quality requirements are demanded for holes due to the fact than those elements are placed in key components of the aircrafts. The most relevant defects that can be produced in the dry drilling of CFRC are located in the both tool input and tool output. These defects are known as Break-IN (B-IN) and Break-OUT (B-OUT). This paper reports on the results of a comparative study of different methodologies for evaluating those defects. First of them is based on the analysis of the diameter deviation. Second procedure is based on the damaged area. Both parameters have been measured making use of image analysis techniques. Obtained results have revealed that damaged area based method is more sensitive to hole changes.

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Kone, Tenon Charly, Sebastian Ghinet, Raymond Panneton, and Anant Grewal. "Broadband low frequency noise attenuation using thin acoustic metamaterials for aircraft cabin noise mitigation." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 268, no. 5 (November 30, 2023): 3223–31. http://dx.doi.org/10.3397/in_2023_0463.

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Broadband noise attenuation at low frequencies is a challenge for the aeronautical, ground transportation and construction industries. In the past few decades, various low frequency noise control solutions, based on acoustic metamaterials designs, have been presented in the literature. The proposed technologies showed promising acoustic performance and are considered as better solutions when compared to conventional sound insulation materials in application fields such as aerospace, where the available space for their integration is extremely limited. The noise attenuation of typical metamaterials is characterized by very narrow resonant frequency maxima which represent a good solution for tonal noise. However, in practical applications, the slight variations of the tonal noise frequencies may render a metamaterial ineffective. This paper presents a thin acoustic metamaterial design for improved broadband noise attenuation at low frequencies. The geometry is an assembly of structured materials arranged in parallel and embedded in a layer of fiberglass. The two structured materials are designed such that their resonant frequencies are optimally regrouped to create a resonant frequency band of maximum attenuation at low frequencies. A thermo-viscous acoustics approach was solved numerically with COMSOL Multiphysics in the frequency domain to predict the sound absorption coefficient and the normal incidence sound transmission loss of the proposed metamaterial design. The results obtained show a wide frequency band noise attenuation for this metamaterial at low frequencies.

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Guo, Feiyan, Qingdong Xiao, Shihong Xiao, and Zhongqi Wang. "Corrigendum to “Assembly technology for aeronautical CFRP structures under the collaborative constrains of geometric shape, physical performance and service stability” [Compos. Struct. 318 (2023) 117071]." Composite Structures 319 (September 2023): 117145. http://dx.doi.org/10.1016/j.compstruct.2023.117145.

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Harchouche, Zine El Abidine, Abdelkader Lousdad, Mothtar Zemri, Nabila Dellal, and Foudil Khelil. "Modeling and Simulation Based Analysis of the Matter Flow During Friction Stir Welding Process." Journal Européen des Systèmes Automatisés 54, no. 2 (April 27, 2021): 363–69. http://dx.doi.org/10.18280/jesa.540219.

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Friction Stir Welding (FSW) is a recent assembly process which has been developed at the British Welding Institute (TWI) at the beginning of the 90's. This welding process has gone a rapid development and an increasing success. Many remarkable industrial applications achieved mainly in spatial, aeronautical, automobile, railways, marine and naval industries.... The translation and the rotation of the tool during the FSW process generate the flow and plastic deformation of the material which had been often differently interpreted in contradictory manner. In this paper, an analytical model is proposed to describe the flow of matter in the vicinity of the FSW tool pin during the welding process. Analytical solutions are elaborated on the basis of conventional fluid mechanics theory which is used to solve the associated equation to the mentioned problem based on the Laurent's series (called also Laurent's development). The knowledge of the material flow around the tool pin can lead to a better understanding of the metallurgical phenomena which have a significant effect on the mechanical properties of the welded joint and allows a better description of the speed fields which is worth full for the thermal modelisation since the great part of the thermal power is generated by auto-heating energy. The results obtained on the effect of the speeds on the material flow are in good accordance with the experimental results found in the literature. The study highlights and gives a better understanding of the material flow phenomenon during the Friction Stir Welding process.

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de Vasconcelos, Luiz Eduardo Guarino, Nelson Paiva Oliveira Leite, André Yoshimi Kusumoto, Leandro Roberto, and Cristina Moniz Araujo Lopes. "Store Separation: Photogrammetric Solution for the Static Ejection Test." International Journal of Aerospace Engineering 2019 (January 13, 2019): 1–18. http://dx.doi.org/10.1155/2019/6708450.

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The process of developing and certifying aircraft and aeronautical systems requires the execution of experimental flight test campaigns to determine the actual characteristics of the system being developed and/or validated. In this process, there are many campaigns that are inherently dangerous, such as the store separation. In this particular case, the greatest risk is the collision of the store with the fuselage of the aircraft. To mitigate the risks of this campaign, it is necessary to compare the actual trajectory of a separation with its simulated estimates. With such information, it is possible to decide whether the next store release can be done with the required safety and/or whether the model used to estimate the separation trajectory is valid or not. Consequently, exact determination of the trajectory of the separation is necessary. Store separation is a strategic, relevant, and complex process for all nations. The two main techniques for determining the quantitative store trajectory data with 6DoF (six degrees of freedom) are photogrammetry and instrumented telemetry packages (data obtained from inertial sensors that are installed in the store). Each presents advantages and disadvantages. In regard to photogrammetry, several market solutions can be used to perform these tests. However, the result of the separation trajectory is only obtained after the test flight, and therefore, it is not possible to safely carry out more than one on the same flight. In this context, the development and validation of a solution that will allow the realization of near real-time separation analysis are in fact an innovative and original work. This paper discusses the development and validation, through actual static ejection tests, of the components that will compose a new onboard optical trajectory system for use in store separation campaigns. This solution includes the implementation of a three-dimensional (3D) calibration field that allows calibration of the optical assembly with just one photo per optical assembly, development of a complete analytical model for camera calibration, and development of specific software for identification and tracking of targets in two-dimensional (2D) coordinate images and three-dimensional (3D) coordinate trajectory calculation. In relation to the calibration, the analytical model is based on a pinhole type camera and considers its intrinsic parameters. This allowed for a mean square error smaller than ±3.9 pixels @1σ. The 3D analysis software for 6DoF trajectory expression was developed using photogrammetry techniques and absolute orientation. The uncertainty associated with the position measurement of each of the markers varies from ±0.02 mm to ±8.00 mm @1σ, depending on the geometry of the viewing angles. The experiments were carried out at IPEV (Flight Test Research Institute)/Brazil, and the results were considered satisfactory. We advocate that the knowledge gained through this research contributes to the development of new methods that permit almost real-time analysis in store separation tests.

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Morard, Adrien, Jean-Christophe Riou, and Gabriel Pares. "Flip chip reliability and intermetallic compounds for SIP module." International Symposium on Microelectronics 2018, no. 1 (October 1, 2018): 000029–36. http://dx.doi.org/10.4071/2380-4505-2018.1.000029.

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Abstract In the aeronautical field, the electronic integration roadmaps show that the weight and the volume dedicated to on-board electronics must be reduced by a factor of 4 to 10 compared to the existing ones for the most recurrent functions in the next years. This work is an opening to new technological solutions to increase our ability to save space while improving the overall reliability of the system. The first part of this work is dedicated to the study of “system in package” (SiP) solutions based on different substrates, namely organic or silicon. Generally speaking a SIP is composed by several active and passive components stacked on an interposer. Benchmarks done by our laboratory have demonstrated that in terms of substrate, embedded die technology leads to several advantages compared to 3D TSV or TGV based packaging approaches. The benefits provided by this substrate is the possibility to embed some surface mount technologies (SMT), some bare chips or some integrated passives devices (IPD) banks directly above or below the stacked active components. This way, top and bottom surface of the substrate can be used to integrate several heterogeneous dies side by side while using low profile flip-chip assemblies on the C4 side. Finally, in this kind of 3D architecture, this embedded technology enable a gain of integration, without using costly TSV connections. Substrates of high quality allow a reduction of I/Os interconnection pitches leading to very aggressive integration down to 50μm. Secondly, a 3D stack with 3 levels of components, as described above, leads to 2 or 3 REACH compliant sequential assembly processes, depending of the needs. In order to consider all the solutions for an optimized overall integration with high reliability, this work focuse on the study one simple SIP which includes the top die assembled by flip-chip. For the flip chip hybridization on organic interposers copper pillars technologies will be studied. The objective is to understand in depth the processes and to obtain information on the reliability aspect after thermal cycling stress of the flip chip assembly. Thirdly, we built many silicon test chips with different characteristics with a dedicated daisy chain test vehicle. The different parameters are: chip's thicknesses (50 to 200 μm), chip's sizes (2 to 8 mm), bump structures (diameter), the pitches of the interconnection (from 50 to 250 μm) and the number of interconnection rows. Designs were chosen in order to fit real operational configurations. Moreover, these configurations are interesting to build a comprehensive model in order to understand the failure mechanisms. These chips are then stacked by flip chip on the silicon and on the organic substrate. We are also designing the both configurations of substrates. Only the production of the organics part is outsourced. Fourth, for all assemblies thermos-cycling test results will be evaluated with thermo mechanical simulations done by finite elements. 3D models will take into account the different geometries in order to understand and quantify the various key parameters. The analysis will mainly focus on 3D interconnections. Design rules based on the results will be derivated. The aim is to obtain dimensional criteria based on stress versus deformation responses. Lastly intermetallic formation will be evaluated using EBSD analysis to obtain better understanding of copper pillar failures for this specific bumps size. Issued information's will be exploited for designing the future functional SIP. The ultimate goal of this work is finally to define mechanical design rules that can then be used in functional SiP modules.

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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 (March 7, 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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Khebal, Merwane, Abdelhak Abdou, Tarik Bouchala, Abderrahmane Aboura, Abdelhadi Bachir, and Guettafi Amor. "Non-destructive rapid defect testing around curved head rivets without displacement of eddy current sensors." STUDIES IN ENGINEERING AND EXACT SCIENCES 5, no. 1 (May 21, 2024): 2040–62. http://dx.doi.org/10.54021/seesv5n1-101.

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In the field of aeronautics, it is essential to ensure the structural integrity of aircraft components. Non-destructive testing (NDT) plays a crucial role in ensuring the safety and reliability of structures used in aeronautics as it enables the detection of defects and imperfections without damaging the inspected parts. Domed head rivets are commonly used in aeronautics to assemble multilayer structures due to their strength and ability to maintain the structural integrity of aircraft. However, inspecting these assembly areas can be challenging and presents unique challenges in terms of non-destructive testing due to the curved surface of the rivet, resulting in lift-off variation during surface scanning and a modification of the trajectory of eddy currents near the rivet. This can lead to changes in the response of eddy currents, complicating the accurate interpretation of test results. In recent years, researchers have focused on developing advanced eddy current testing methods to detect defects in complex structures, such as those found in aeronautics. In this work, we propose a promising solution to address both the shape of the rivet and the probe displacement issue during testing. We have developed a model based on the finite element method (FEM) using COMSOL Multiphysics for non-destructive testing through 3D imaging using a matrix of multiplexed multi-element eddy current sensors distributed over multiple layers around the rivet without the need for the displacement of this matrix and capable of adapting to the variation in the diameter of the domed head rivet. The non-displacement of the sensors eliminates parasitic signals that can lead to errors in the interpretation of obtained signals, and the multiplexed powering of the sensors eliminates the mutual inductance effect between adjacent coils.

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Bordegoni, Monica, and Umberto Cugini. "Feature-based assembly in aeronautics design: from concepts development to formalisation." International Journal of Vehicle Design 21, no. 2/3 (1999): 228. http://dx.doi.org/10.1504/ijvd.1999.005578.

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Highlander, Sarah K., Jason M. Wood, John D. Gillece, Megan Folkerts, Viacheslav Fofanov, Tara Furstenau, Nitin K. Singh, et al. "Multi-faceted metagenomic analysis of spacecraft associated surfaces reveal planetary protection relevant microbial composition." PLOS ONE 18, no. 3 (March 22, 2023): e0282428. http://dx.doi.org/10.1371/journal.pone.0282428.

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The National Aeronautics and Space Administration (NASA) has been monitoring the microbial burden of spacecraft since the 1970’s Viking missions. Originally culture-based and then focused 16S sequencing techniques were used, but we have now applied whole metagenomic sequencing to a variety of cleanroom samples at the Jet Propulsion Lab (JPL), including the Spacecraft Assembly Facility (SAF) with the goals of taxonomic identification and for functional assignment. Our samples included facility pre-filters, cleanroom vacuum debris, and surface wipes. The taxonomic composition was carried out by three different analysis tools to contrast marker, k-mer, and true alignment approaches. Hierarchical clustering analysis of the data separated vacuum particles from other SAF DNA samples. Vacuum particle samples were the most diverse while DNA samples from the ISO (International Standards Organization) compliant facilities and the SAF were the least diverse; all three were dominated by Proteobacteria. Wipe samples had higher diversity and were predominated by Actinobacteria, including human commensals Cutibacterium acnes and Corynebacterium spp. Taxa identified by the three methods were not identical, supporting the use of multiple methods for metagenome characterization. Likewise, functional annotation was performed using multiple methods. Vacuum particles and SAF samples contained strong signals of the tricarboxylic acid cycle and of amino acid biosynthesis, suggesting that many of the identified microorganisms have the ability to grow in nutrient-limited environments. In total, 18 samples generated high quality metagenome assembled genomes (MAG), which were dominated by Moraxella osloensis or Malassezia restricta. One M. osloensis MAG was assembled into a single circular scaffold and gene annotated. This study includes a rigorous quantitative determination of microbial loads and a qualitative dissection of microbial composition. Assembly of multiple specimens led to greater confidence for the identification of particular species and their predicted functional roles.

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Batista, M., D. Piñero, M. Ramírez, P. F. Mayuet, R. Bienvenido, and J. M. Vazquez. "Defectology Characterization of FDM Drilled Parts." IOP Conference Series: Materials Science and Engineering 1193, no. 1 (October 1, 2021): 012054. http://dx.doi.org/10.1088/1757-899x/1193/1/012054.

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Abstract Since its emergence, the industry has made great efforts to implement additive manufacturing processes in its production systems. However, to achieve this use, the precision of the parts must also be guaranteed. But it is not yet possible to achieve the characteristics required in certain industrial sectors like the aeronautical where highly rigorous requirements are related to the assembled parts. In this way, alternatives arise, such as the use of machining to obtain the precision required. This concept has been applied for some time to metal parts obtained through additive manufacturing, but not so much to polymer parts. For this reason, given that it is expected that polymeric parts will be used in aeronautical structures, these will have to be machined to obtain the required geometric characteristics. Therefore, in this article, a parametric study of the quality of the holes made in parts obtained by Fused Deposition Modelling (FDM) will be carried out.

Journal articles on the topic 'Aeronautical assembly'

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