Relevant bibliographies by topics / Wing-fuselage joint

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Academic literature on the topic 'Wing-fuselage joint'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Wing-fuselage joint"

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Liu, Chu Hui. "Safety Improving Technology for Finish Machining of Wing-Fuselage Joints." Advanced Materials Research 566 (September 2012): 263–66. http://dx.doi.org/10.4028/www.scientific.net/amr.566.263.

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To avoid the security problem of finish machining of wing-fuselage joints, a safety improving method for finish machining of wing-fuselage joints during digital final assembly of aircraft is studied in this paper. Before formal cutting process, automatic accurate three-coordinate measurement of wing-fuselage joints is performed on spot by machining center with a touch trigger probe installed in the spindle. A cutting allowance evaluation model of wing-fuselage joint hole is put forward based on its measured data. If some wing-fuselage joints do not meet the security condition of finish machining, the fuselage posture must be realigned.
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Liu, Chu Hui. "Large Subassembly Relocation for Finish Machining of Wing-Fuselage Joints in Digital Final Assembly of Aircraft." Advanced Materials Research 712-715 (June 2013): 2474–77. http://dx.doi.org/10.4028/www.scientific.net/amr.712-715.2474.

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During digital final assembly of some types of aircraft, the posture of fuselage or wing must be revised in the case that real cutting allowances of some wing-fuselage joint holes are insufficient for finish machining. A constrained optimization modal is proposed to gain the optimum objective posture, which will ensure that each wing-fuselage joint has enough cutting allowance and meet all other technological requirements on the posture of fuselage or wing too.
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Hart-Smith, L. J. "An Engineer'S Viewpoint on Design and Analysis of Aircraft Structural Joints." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 209, no. 2 (April 1995): 105–29. http://dx.doi.org/10.1243/pime_proc_1995_209_278_02.

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The design of structurally efficient joints in aircraft fuselage structures and wing skin splices is addressed. It is contended that the joints should be designed first and the gaps in between filled in afterwards, taking pains not to optimize the basic structure first and then discover that it either cannot be assembled or that, when it is assembled, it is full of weak-link fuses. Both adhesively bonded and mechanically fastened joints are covered. Analogies are drawn between the characteristics of both classes of joints. The aspects of static joint strength and fatigue lives are included. The work is applicable to metallic as well as composite structures, and covers both high-load wing joints which have already been tested and new ideas for fuselage splices which have not. The effects of flaws and defects are associated with the need for damage tolerance, particularly in fuselage structures.
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., Sriranga B. k. "STRESS ANALYSIS AND FATIGUE LIFE PREDICTION OF WING- FUSELAGE LUG JOINT ATTACHMENT BRACKET OF A TRANSPORT AIRCRAFT." International Journal of Research in Engineering and Technology 03, no. 15 (May 25, 2014): 818–22. http://dx.doi.org/10.15623/ijret.2014.0315154.

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Kuntjoro, Wahyu, Ibrahim Bahari, Abdul Ghani Ujang, and Assanah Mohd Mydin. "Fatigue Life Monitoring Program of RMAF MiG-29." Scientific Research Journal 5, no. 1 (June 30, 2008): 27. http://dx.doi.org/10.24191/srj.v5i1.5651.

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The Royal Malaysian Airforce (RMAF) operates one squadron of MiG-29 which were designed on Safe Life principle. RMAF conducts a fatigue life monitoring program to these airplanes. This activity is conducted based on the experience of having the fatigue life monitoring program to the RMAF F/A-18D. The fatigue life of RMAF MiG-29 is based on the wing-fuselage lug joint structure, and Low Cycle Fatigue (LCF) approach is adopted. The stress spectra of this component, is derived through mapping of g-spectra to the 1-g stress level of the lug. The g-history is obtained from the accelerator installed in the airplane, while the 1-g stress level is obtained by finite element modeling of the wing structure and lug joints. Rainflow cycle counting procedure was then applied. The fatigue characteristics (strain-life) of the lug material was obtained from the laboratory test, using the lug material sample, combined with the empirical formula of strain-life diagram. Notched effect is taken into account using Neuber theory. Mean stress effect is dealt with using Smith-Watson-Topper formula. Miner’s rule is used to calculate the fatigue damage accumulation. A fatigue life prediction software for RMAF MiG-29 which incorporates the above concepts had been developed. Currently, this software is operational with the RMAF MiG-29, and is being used as part of its Aircraft Structural Integrity Program (ASIP). This paper reports on the development of the fatigue life monitoring strategy and software for the RMAF MiG-29.
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Vargas, Erik, Diego Camarena, Alberto Morales, Hilario Hernández, and Carlos Martínez. "Numerical analysis with experimental data of the joint of fuselage with main landing gear and wing‐strut, of a two‐seat aircraft built with composites." Polymer Composites 36, no. 6 (March 21, 2015): 1072–83. http://dx.doi.org/10.1002/pc.23431.

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Abdul Jalil, Abdul Malik Hussein, and Wahyu Kuntjoro. "Wing-Fuselage Lug Stress Prediction Using Finite Element Method." Applied Mechanics and Materials 393 (September 2013): 317–22. http://dx.doi.org/10.4028/www.scientific.net/amm.393.317.

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This paper describes the methodology to predict the stress level that occurs at the wing-fuselage lugs (joints). The finite element models of the wing, the wing lugs and the fuselage lugs were developed. Finite Element Analyses were performed using NASTRAN finite element software. CQUAD4 and BAR2 elements were used to represent the individual structures of the wing such as the ribs and stringers. The applied load was based on the symmetrical level flight condition. Once the load distribution acting at the wing had been calculated and applied, reaction forces at the nodes representing the wing lugs were obtained and these values applied to the lug models where the maximum stress value acting at the lugs was obtained.
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Shin, Hye Jin, Jung Ryul Lee, and Chan Yik Park. "Loosening Monitoring of Bolted Joints Using Optical Fiber Bending Sensor for Aircraft Lug Assembly." Applied Mechanics and Materials 225 (November 2012): 540–45. http://dx.doi.org/10.4028/www.scientific.net/amm.225.540.

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Bolted joints of aircraft lug assembly play an important role in connecting the wing and fuselage of an aircraft structure. Generally, the bolted joints get loosened because they are frequently exposed to the dynamic loads induced when an aircraft is in service. For this reason, it is important to monitor the condition of the bolted joints to avoid any critical defect that will lead to any risk in human life. However, it is difficult to conduct the bolted joints’ loosening inspection by an operator. In past few decades, optical fiber based sensor has been widely used due to its advancement over a conventional piezoelectric (PZT) sensor, especially due to its small size and light weight. With regard to this, a loosening monitoring of bolted joints using optical fiber bending sensor for aircraft lug assembly is proposed in this paper. The lug assembly specimen, which consists of a stainless steel lug, CFRP/Nomex honeycomb sandwich panel, carbon-steel bolt, nut and washer, and the monitoring system, which consists of a single mode fiber with ten optical fiber bending sensor nodes and an Optical Time-domain Reflectometer (OTDR) were used to determine the bolt loosening at every 1 degree interval.
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Liu, Jintong, Anan Zhao, Zhenzheng Ke, Zhiqiang Li, and Yunbo Bi. "Investigation on the Residual Stresses and Fatigue Performance of Riveted Single Strap Butt Joints." Materials 13, no. 15 (August 4, 2020): 3436. http://dx.doi.org/10.3390/ma13153436.

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In aircraft manufacturing, riveting is one of the most important connection ways to fasten the sheet metal parts. The riveted single strap butt joints are mainly used in the load-bearing components of the aircraft such as the fuselage and wing panels. The connection quality and fatigue performance of the riveted joints directly affect the reliability and safety of the aircraft. In this paper, under the assumption of constant temperature, the fatigue strengthening mechanism of interference-fit riveting is introduced based on elastic-plastic mechanics and fracture mechanics. On this basis, the finite element (FE) models of the riveted single strap butt joints with various strap thickness and rivet sizes/arrangements are established. The residual stresses distribution around the riveted hole is analyzed. Furthermore, the fatigue tests of the riveted single strap butt joints with cyclic loading are carried out. The experimental results verified the correctness and effectiveness of the simulation model. Finally, the conclusion is drawn that increasing rivet size and strap thickness within the allowable weight range can improve the fatigue performance of the riveted single strap butt joints. The knowledge could be used to guide the structural design and optimization of the riveted butt joints against fatigue.
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Suarez, Alejandro, Pedro Grau, Guillermo Heredia, and Anibal Ollero. "Winged Aerial Manipulation Robot with Dual Arm and Tail." Applied Sciences 10, no. 14 (July 12, 2020): 4783. http://dx.doi.org/10.3390/app10144783.

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This paper presents the design and development of a winged aerial robot with bimanual manipulation capabilities, motivated by the current limitations of aerial manipulators based on multirotor platforms in terms of safety and range/endurance. Since the combination of gliding and flapping wings is more energy efficient in forward flight, we propose a new morphology that exploits this feature and allows the realization of dexterous manipulation tasks once the aerial robot has landed or perched. The paper describes the design, development, and aerodynamic analysis of this winged aerial manipulation robot (WAMR), consisting of a small-scale dual arm used for manipulating and as a morphing wing. The arms, fuselage, and tail are covered by a nylon cloth that acts as a cap, similar to a kite. The three joints of the arms (shoulder yaw and pitch, elbow pitch) can be used to control the surface area and orientation and thus the aerodynamic wrenches induced over the cloth. The proposed concept design is extended to a flapping-wing aerial robot built with smart servo actuators and a similar frame structure, allowing the generation of different flapping patterns exploiting the embedded servo controller. Experimental and simulation results carried out with these two prototypes evaluate the manipulation capability and the possibility of gliding and flying.
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Dissertations / Theses on the topic "Wing-fuselage joint"

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Sadovský, Hynek. "Návrh uzlu křídlo-trup kompozitního letounu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-232005.

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This master's thesis deals with design, strength calculation and technological solution of wing-fuselage joint for composite four-seater aeroplane certificated by CS-23. Design is focused on optimal space utilization, low weight and simple manufacturing and assembly. Main output is technical documentation consisting of drawings and technological lay-ups. Conceptual design was chosen after analysis and weight estimation. With strenght calculation for composite materials it was possible to design composition of primary parts and also specify manufacture processes. Assigment was solved by unusuall conceptual design, which claims higher precision manufacturing, but it saves weight.
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Duchoň, Peter. "Analýza spoje křídlo-trup letounu L 410 NG z hlediska filozofie konstrukce s přípustným poškozením." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2014. http://www.nusl.cz/ntk/nusl-231189.

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Master's thesis deals with the damage tolerance analysis of wing-to-fuselage joint of L 410 NG airplane. Thesis includes determination of the load distribution to the individual attachments of wing-to-fuselage joint, residual strength analysis and residual fatigue life analysis of the most loaded attachment lugs, calculation of fatigue crack growth curves in the attachment solids and inspection program proposal. This analysis was performed using FE model of the wing and central part of the fuselage and AFGROW software.
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Books on the topic "Wing-fuselage joint"

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Waters, William Allen. Failure mechanisms of laminates transversely loaded by bolt push-through. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

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Conference papers on the topic "Wing-fuselage joint"

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Ehrmayr, Robert, and Thomas M. Berens. "Numerical Investigations on an Advanced Diverterless Supersonic Inlet with a Corner Bump in a Wing-Fuselage Installation." In 2018 Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4746.

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Liu, Muran. "Damage Tolerance Analysis of Double Hole-Opposite Crack at the Wing-Fuselage Joint of Civil Aircraft." In 2020 2nd International Conference on Artificial Intelligence and Advanced Manufacture (AIAM). IEEE, 2020. http://dx.doi.org/10.1109/aiam50918.2020.00047.

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Deng, X. Y., and W. Shi. "The Study of Wing-Rock Motions of Wing/Body Model With Chined Forebody and Their Flow Mechanism." In ASME 2014 4th Joint US-European Fluids Engineering Division Summer Meeting collocated with the ASME 2014 12th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/fedsm2014-21345.

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An experimental investigation was conducted to obtain behaviors of wing-rock motions over a wing-body model with a chined fuselage and reveal corresponding flow mechanisms. Free-to-roll technique was used to acquire motion behaviors at fixed angles of attack in a wind tunnel at Reynolds number of 1.87×105. Eight dynamic regimes of uncommanded lateral motions can be divided with increasing angle of attack. There is no lateral motion if the angle of attack is low (in A region, α ≤ 20°) or high (in H region, α ≥ 65°) enough. In the other six regions (from B region to G region), wing-rock motions are mainly generated and developed by the wing vortices evolved with angles of attack, which are induced by chined forebody asymmetric vortices. Some new physical concepts are found and proposed in present paper. There are two kind of asymmetric vortices: one is generated by hydrodynamic instability at large enough angle of attack (α > 20°), which can generate the uncommanded lateral motion, the other is created from symmetric vortices over a model with asymmetric boundary condition (ϕ ≠ 0°), which can’t generate any lateral motions. Non-determinacy of asymmetric vortices over the forebody is at ϕ = 0° only, and if ϕ ≠ 0°, the asymmetric vortices are determinant. Based on those concepts the fluid mechanism of the very complicated uncommanded lateral motions can be analyzed and revealed.
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Fisher, Emily, Anton Bauhofer, Christine Beauchene, Brian Dress, Stephen Marshall, Cory McCraw, Christopher Mehrvarzi, et al. "A Bio-Inspired Aircraft Design Concept." In ASME 2012 Fluids Engineering Division Summer Meeting collocated with the ASME 2012 Heat Transfer Summer Conference and the ASME 2012 10th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/fedsm2012-72431.

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The goal of the research has been to design a robotic bird that utilizes principles of nature to optimize flight. Seagulls were the preferred model for the robot because they have a large wing span that provides a more steady flight and sheds a continuous wake vortex, creating lift on both the upstroke and down-stroke of flight [1]. Research has been done on the architecture of a seagull’s wing as well as the aerodynamic features of its comprising airfoils. The robotic wings developed will capture the architecture of the seagull wings with a variety of airfoils that improve lift and reduce drag and joints that enable bending on the upstroke in the flapping motion. A main focus of this research was to study how the seagull uses air flow to improve its flight performance. The fluid mechanics of the wing was analyzed for steady and unsteady flight using Fluent code to see how seagull adapts to different flow conditions. Using the developed robotic model of the wing attempts were made to achieve the necessary wing positioning that fully complied with that of the seagull during flight. Actuation of the wings was achieved using servo motors. Fabrication of the robotic prototype involved material selection for the fuselage, wing surface and skeletal structure. At completion of the prototyping, trials were performed using stereovision to study the complex effects of unsteady flow, and to verify the computational analyses undertaken.
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Bolick, Ronnie L., Ajit D. Kelkar, Jeremy A. Taylor, and Jitendra S. Tate. "Performance Evaluation of Unstitched, Stitched and Z-Pinned Textile Composites Under Static Loading." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-81053.

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Advances in conventional tape laminates and textile composites provide aircraft manufacturers important technology, but the industry lacks the confidence to use these composites to manufacture wing and fuselage structures due to high cost and low damage tolerance. In order to overcome the high cost and to improve the damage tolerance of composites, researchers have developed new through-the-thickness reinforcement techniques, such as stitching through the thickness. This reinforcement technique can be used to join the skin, stiffeners, ribs and spars to form an integral structure. The structures are typically more damage tolerant, contain fewer fasteners and are less expensive to manufacture than conventional composite or metallic structures. Furthermore, stitching reduces the manufacturing time and labor compared to drilling holes for fasteners, and may eliminate the problems of fatigue and/or corrosion from galvanic reactions with metal fasteners. Woven composites with through the thickness reinforcements such as stitching have good properties not only in mutually orthogonal directions but also in the transverse direction and more balanced properties than traditional tape laminates. They are also expected to have better fatigue and impact resistance due to the interlacing. Another benefit is reduced manufacturing cost by reducing part count. Because of these potential benefits, these composites are being considered for various applications including primary/secondary components for aerospace structures. The objective of this effort is to develop experimental tools for comparing the performance of these composites reinforced by stitching to unstitched composites. Identification of damage mechanisms and forces available to grow damage is essential for identifying the primary parameters that determine performance. Accurate determination of the driving forces will require extensive manufacturing and experimentation. However, once the reinforcement techniques are well understood, it is anticipated that simplified experiments can be developed that could be used routinely by designers to evaluate the effects of the reinforcements on damage tolerance. This paper specifically addresses the performance evaluation of stitched low cost manufactured composites subjected to static loading. Static tension and compression testing was conducted to determine the Ultimate Tensile and Compressive Strengths, Young’s Moduli and Poisson’s Ratio. Two different stitch patterns or stitch densities were used for comparison. The first density was five rows of stitching per inch of width, with eight stitches per inch over the entire length. The second density was three rows of stitching per inch of width, with four stitches per inch over the entire length.
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