Relevant bibliographies by topics / Wing-fuselage joint / Journal articles

To see the other types of publications on this topic, follow the link: Wing-fuselage joint.

Journal articles on the topic 'Wing-fuselage joint'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 15 journal articles for your research on the topic 'Wing-fuselage joint.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse journal articles on a wide variety of disciplines and organise your bibliography correctly.

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

., 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.

Full text

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

SADALLAH, Y. "LINEAR FRICTION WELDING – PROCESS DEVELOPMENT AND APPLICATIONS IN AEROSPACE INDUSTRY." MATEC Web of Conferences 321 (2020): 03022. http://dx.doi.org/10.1051/matecconf/202032103022.

Full text

Abstract:

Linear Friction Welding (LFW) is a solid-state joining process very well adapted to titanium alloys, producing high integrity joints with fine grain, hot-forged microstructure and narrow heat affected zone. The first industrial application of this process was found in aircraft engines, for the manufacturing of “blisks” (“bladed disks”): linear friction welding the blades onto a disk provides economic savings and reduces the manufacturing time, compared to machining the whole blisk from solid. While the diffusion of LFW process in the blisk manufacturing market is still at the early stages and have promising growth potential, the process is now being developed for aircraft structures such as clips, brackets, hinges, fittings, and larger parts like seat rails, wing ribs, lintels and fuselage frames. The LFW process allows not only to manufacture a given part at a lower cost, it also open new part design possibilities, that were not available with traditional manufacturing processes. The manufacturing process of Ti-6Al-4V structural and engine parts by LFW is explained, highlighting advantages, limitations and part design best practices. Several LFW candidate parts are introduced and evaluated through feasibility, mass savings, post weld operations and overall cost savings.

APA, Harvard, Vancouver, ISO, and other styles

Kurdelski, Marcin, Michał Stefaniuk, Wojciech Zieliński, and Tomasz Bartoszek. "The Verification of the Technical Conditions of a Combat-Trainer Jet’s Airframe." Fatigue of Aircraft Structures 2015, no. 7 (December 1, 2015): 34–40. http://dx.doi.org/10.1515/fas-2015-0006.

Full text

Abstract:

Abstract The combat-trainer jet aircraft is an important element in the process of fighter pilot training. This type of aircraft provides a means of transition from basic training on low-speed propeller trainers to piloting high-speed and highly maneuverable fighter aircraft. Nowadays, in Poland, the PZL TS-11 “ISKRA” jet trainers, designed in 1960s, are employed for training purposes. Because of financial considerations this trainer hasn’t been yet replaced by modern aircraft that conforms to current specifications and needs. As is the case with other aircraft in service of the PLAF, the TS-11 fleet has a large reserve of remaining Hourly Service Life (HSL). This opens an opportunity to extend the Calendar Service Life (CSL), so as it matches the HSL. To this end, a series of technical and research activities needed to be undertaken. The Air Force Institute of Technology is conducting the necessary verification of airframe structural conditions in cooperation with the Military Aviation Works No. 1 J.S.C. (branch in Dęblin) responsible for the overhaul and repair operations. The AFIT’s activities in this program include: deformation analysis of the selected surface areas of the wing and the fuselage; assessment of hidden corrosion in riveted joints; non-destructive testing of selected riveted joints. This paper describes the deformation analysis. As of today, the first stage of the deformation inspection has been completed. At this stage, baseline surface measurements were obtained. Further inspections shall be performed cyclically. The future measurements will be used to establish the areas that deform due to the aircraft operation.

APA, Harvard, Vancouver, ISO, and other styles

"Wing-Fuselage Joint Design Improvement Using Nonlinear Analysis Considering Contact." Journal of the Korean Society for Aeronautical & Space Sciences 30, no. 2 (April 30, 2002): 108–14. http://dx.doi.org/10.5139/jksas.2002.30.2.108.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Chinnamahammad bhasha, A., and K. Balamurugan. "Fracture analysis of fuselage wing joint developed by aerodynamic structural materials." Materials Today: Proceedings, September 2020. http://dx.doi.org/10.1016/j.matpr.2020.07.561.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Marano, A. D., T. Polito, M. Guida, M. Barbarino, M. Belardo, A. Perazzolo, and F. Marulo. "Tiltrotor Acoustic Data Acquisition and Analysis." Aerotecnica Missili & Spazio, February 12, 2021. http://dx.doi.org/10.1007/s42496-021-00075-5.

Full text

Abstract:

AbstractPressure load measurements in operative conditions represent a fundamental parameter for improving the knowledge of the in-flight forcing generation and transmission. Furthermore, it is a fundamental step for assessing the validity and confidence of numerical methods able to predict such pressure loads, usually generated by propulsion and turbulent boundary layer. The experimental in-flight measurements and analysis and the correlation with the numerical methods are activities required as a starting point for studying the transmission mechanism through the fuselage which is responsible for the vibration and noise level which can be measured inside and for identifying potential solutions for their mitigation. The in-flight measurements have been carried out on a Leonardo Helicopter tiltrotor with the main goals to perform the validation of an experimental setup in a fully new environment and the assessment of a data analysis procedure according to the objectives of the Clean Sky 2 Fast Rotorcraft Project T-WING (CS2, Clean Sky 2 joint undertaking third amended bi-annual work plan and budget, 2018–2019).

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!