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Journal articles on the topic 'Wing stress analysis'
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1
Jemitola, P. O., J. Fielding, and P. Stocking. "Joint fixity effect on structural design of a box wing aircraft." Aeronautical Journal 116, no. 1178 (April 2012): 363–72. http://dx.doi.org/10.1017/s0001924000005261.
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Abstract A computational study was performed to compare the stress distributions in finite element torsion box models of a box wing structure that result from employing four different wing/end fin joint fixities. All considered wings were trimmed in pitch. The joint fixities refer to the type of attachment that connects the tip of the fore and aft wings to the end fin. Using loads from a vortex lattice tool, the analysis determined the best wing-joint fixity of a statically loaded idealised box wing configuration by comparing the stress distributions resulting from the different wing joints in addition to other essential aerodynamic requirements. Analysis of the wing joint fixity indicates that the rigid joint is the most suitable.
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Yu, Chun Jin, Jin Zhang, Wei Song, and Ke Hong Yi. "Deformation and Stress Analysis of Flapping Wing Aerial Vehicles Based on Composites Model." Advanced Materials Research 1006-1007 (August 2014): 7–10. http://dx.doi.org/10.4028/www.scientific.net/amr.1006-1007.7.
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Flapping wing aerial vehicles continue to be a growing field, with ongoing research into unsteady, low Reynolds number aerodynamics and micro fabrication. However research into deformation and stress of flapping wing continues to lag, especially based on composites model. One flapping cycle was divided into twelve segments, and maximum defmortion and stress were calculated in each segment. The results show that the maximum sdeformation at the beginning stages of downstroke is 19% larger than the maximum deformation at the beginning stages of upstroke, and the maximum stress at the beginning stages of downstroke is 29.9 larger than the maximum stress at the beginning stages of upstroke. This research is helpful to answer that why insect wings are so perfect through long evolution, thus improving the design of flapping-wing aerial vehicles.
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Jin, Guo Dong, Li Bin Lu, Liang Xian Gu, and Juan Liang. "Numerical Simulation Analysis on Repairing Hole of UAV Wing." Advanced Materials Research 690-693 (May 2013): 2891–95. http://dx.doi.org/10.4028/www.scientific.net/amr.690-693.2891.
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Parachute recovery of UAV is often caused of holes and other injuries on wings, that are required repair and maintenance. The surface of the patch will form the high stress area, that affects UAV using life and safety .But repair method is good or bad directly affects size of the high stress area. Based on finite element method, the broken hole repairing method was formulated and validated by ANSYS. The method could minimize the high stress area as far as possible, and economically repair broken hole of wing in certain precision and safety standards condition. It has a certain reference value for UAV repair and management, and has reference significance for extending the service life of the UAV. Key words: Finite element method; Unmanned Aerial Vehicle (UAV); Simulation; Hole of wings
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Kalavagunta, Veeranjaneyulu, and Shaik Hussain. "Wing Rib Stress Analysis of DLR-F6 aircraft." IOP Conference Series: Materials Science and Engineering 455 (December 19, 2018): 012033. http://dx.doi.org/10.1088/1757-899x/455/1/012033.
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Rabbey, M. Fazlay, Anik Mahmood Rumi, Farhan Hasan Nuri, Hafez M. Monerujjaman, and M. Mehedi Hassan. "Structural Deformation and Stress Analysis of Aircraft Wing by Finite Element Method." Advanced Materials Research 906 (April 2014): 318–22. http://dx.doi.org/10.4028/www.scientific.net/amr.906.318.
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Wing of an aircraft is lift producing component. It makes aircraft airborne by generating lift>weight. The wing must take the full aircraft weight during flying. So, it is very sophisticated task for designing a wing by keeping consideration of every design parameters simultaneously. This paper contains analysis of structural properties of wing by using finite element method. For well-organized design all the variables must be considered from the beginning of the design phase. The design phases for aircraft are: conceptual, preliminary and detail design. Until the preliminary design phase the aircraft structure is not considered. During these phases the material of the wing should be selected in such a way so that it can perform efficiently with less unexpected phenomena (drag) for which responsible properties are displacement, stress etc. Currently the most focusing area for the aero-elastic investigation is to design wing with good aerodynamic shape which will associated with less dragging structural behavior. It helps to reduce SFC (Specific Fuel Consumption) and so the cost. The analysis on that has done through Computational means as well as simulation technique to develop knowledge about the variation of aircraft wing structural properties.
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Esakkiraj, E. S., S. Anish, and V. Anish. "Static and Dynamic Analysis of Aluminium Composite in Wing Section Using ANSYS." Advanced Materials Research 984-985 (July 2014): 367–71. http://dx.doi.org/10.4028/www.scientific.net/amr.984-985.367.
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The cold of this cardboard is to abstraction and analyze the amount accustomed accommodation and weight accumulation of blended aircraft (Aluminium Silicon Carbide) addition with that of Aluminium wing and appropriately access the acceptable aircraft addition of minimum weight accomplished of address a accustomed changeless amount after failure. And also this paper presents a model and a static analysis of the aircraft wing, using the finite element software ANSYS. The geometry was created in CATIA V5 R18 and imported. The static and model analysis are carried out in analysis software ANSYS. The result of from the static analysis refers to the total deformation, equivalent stress, shear stress and shear intensity on the skin of the aircraft wing. The model analysis will be carried out to find out the first six modes of vibrations and the different mode shape in which wing can deform without the application of load. Compared to the conventional Aluminium wing, the hybridized composite wing experience far lower stresses and the aircraft wing weight nearly 40% and 50% lower stress.
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Zhu, Wen Qing, and Yang Yong Zhu. "The Vibration Response Analysis about High-Speed Train’s Braking Wing." Applied Mechanics and Materials 226-228 (November 2012): 102–5. http://dx.doi.org/10.4028/www.scientific.net/amm.226-228.102.
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With the rapid development of high-speed railway in China, the aerodynamic brake is very likely to be an important emergency braking mode of high-speed train in the future. This paper takes aerodynamic braking wing as the object, and uses the finite element software to divide the meshes, then analyses the model influenced by static stress. After simulating the vibratory frequency response of the model in the flow field, it finds that the largest deformation happens in the middle of the upper edge of the wind wing, when the wind speed gets to 500km/h and the load frequency to 4Hz. Some conclusions of this thesis can provide reference for researching the applying the aerodynamic brake in the high-speed trains and laying the foundation for solving the riding and braking safety problems.
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Alsaidi, Bashir, Woong Yeol Joe, and Muhammad Akbar. "Computational Analysis of 3D Lattice Structures for Skin in Real-Scale Camber Morphing Aircraft." Aerospace 6, no. 7 (July 7, 2019): 79. http://dx.doi.org/10.3390/aerospace6070079.
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Conventional or fixed wings require a certain thickness of skin material selection that guarantees structurally reliable strength under expected aerodynamic loadings. However, skin structures of morphing wings need to be flexible as well as stiff enough to deal with multi-axial structural stresses from changed geometry and the coupled aerodynamic loadings. Many works in the design of skin structures for morphing wings take the approach either of only geometric compliance or a simplified model that does not fully represent 3D real-scale wing models. Thus, the main theme of this study is (1) to numerically identify the multi-axial stress, strain, and deformation of skin in a camber morphing wing aircraft under both structure and aerodynamic loadings, and then (2) to show the effectiveness of a direct approach that uses 3D lattice structures for skin. Various lattice structures and their direct 3D wing models have been numerically analyzed for advanced skin design.
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Sun, Ya Zhen, Xiao Xing Zhai, and Jie Min Liu. "Analysis of Failure Mode and Propagation for Crack in Uniaxial Compression." Applied Mechanics and Materials 166-169 (May 2012): 2929–32. http://dx.doi.org/10.4028/www.scientific.net/amm.166-169.2929.
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This paper analyzed the failure mode for crack in uniaxial compression according to the stress intensity factor, and obtain that the failure mode for crack in uniaxial compression is compression-shear. The wing crack was deformed, after the crack tip initiate. By analyzing the dimensionless stress intensity factor, we obtain that the failure mode for wing crack in uniaxial compression is tension-shear, and we obtain that the dimensionless stress intensity factor for wing crack decreased with inclined angle increased. The inclined crack propagation in uniaxial compression was numerically studied using rock failure process analysis code (rfpa), and obtain that one inclined crack in uniaxial compression formed mode I offset crack parallel to load direction in the end. The numerical results of failure mode are accordance with stress intensity factor.
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Nabawy, M. R. A., M. M. ElNomrossy, M. M. Abdelrahman, and G. M. ElBayoumi. "Aerodynamic shape optimisation, wind tunnel measurements and CFD analysis of a MAV wing." Aeronautical Journal 116, no. 1181 (July 2012): 685–708. http://dx.doi.org/10.1017/s000192400000717x.
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Abstract The aerodynamic shape optimisation of a micro air vehicle (MAV) wing is performed to obtain the basic wing geometrical characteristics which produce the maximum range and endurance requirements. Multhopp’s method based on Prandtl’s classical lifting line theory is used for the determination of the spanwise load distribution required during the optimisation process. The obtained lift and drag characteristics are used for the derivation of the range and endurance equations of an electrically driven micro air vehicle. The optimisation process is based on the modified feasible directions gradient based optimisation algorithm. Results are validated using wind tunnel measurements showing very good agreement. Results are also compared with solutions to the Navier-Stokes equations obtained with ANSYS-CFX finite elements using different turbulence models. These include the k-ε and the shear stress transport (SST) models as well as the Reynolds stress model.
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Brzęczek, Józef, Henryk Gruszecki, Leszek Pieróg, Franciszek Deszcz, and Janusz Pietruszka. "Stress Analysis of the PZL M28’s Airframe Subjected to Repairs During Fatigue Tests." Fatigue of Aircraft Structures 2014, no. 6 (June 1, 2014): 107–12. http://dx.doi.org/10.1515/fas-2014-0011.
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AbstractThe PZL M28’s service life is determined based on the fatigue tests of the wing and wing loads-carry-through structure. During the fatigue test, the first occurrence of significance was the appearance of a in the area of the wing where loads are applied from the strut. It was demonstrated during further activities that repairs of the wing and other basic assemblies enabled, when performed at an appropriate time, the airplane’s service life to be significantly increase.In the case of each design change implemented in the airframe subject to the fatigue testing, a stress analysis of the airframe was required in order to check if local changes, i.e. local repairs, did not affect the stress level in other tested areas. This helped to avoid significant stress redistribution in the airframe after the repair, so the fatigue test was still valid for all areas of interest.
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Aird, J. C., D. T. Millett, and K. Sharples. "Fracture of Polycarbonate Brackets—A Related Photoelastic Stress Analysis." British Journal of Orthodontics 15, no. 2 (May 1988): 87–92. http://dx.doi.org/10.1179/bjo.15.2.87.
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In clinical use polycarbonate edgewise bracket designs, patterned on metallic predecessors, have demonstrated slot-wing fracture. A preliminary two-dimensional photoelastic stress investigation is described in which two bracket designs, without angles in the edgewise slot component, are subjected to simulated palatal root torque mechanics.
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Phillips, W. F., D. F. Hunsaker, and J. D. Taylor. "Minimising induced drag with weight distribution, lift distribution, wingspan, and wing-structure weight." Aeronautical Journal 124, no. 1278 (March 19, 2020): 1208–35. http://dx.doi.org/10.1017/aer.2020.24.
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ABSTRACTBecause the wing-structure weight required to support the critical wing section bending moments is a function of wingspan, net weight, weight distribution, and lift distribution, there exists an optimum wingspan and wing-structure weight for any fixed net weight, weight distribution, and lift distribution, which minimises the induced drag in steady level flight. Analytic solutions for the optimum wingspan and wing-structure weight are presented for rectangular wings with four different sets of design constraints. These design constraints are fixed lift distribution and net weight combined with 1) fixed maximum stress and wing loading, 2) fixed maximum deflection and wing loading, 3) fixed maximum stress and stall speed, and 4) fixed maximum deflection and stall speed. For each of these analytic solutions, the optimum wing-structure weight is found to depend only on the net weight, independent of the arbitrary fixed lift distribution. Analytic solutions for optimum weight and lift distributions are also presented for the same four sets of design constraints. Depending on the design constraints, the optimum lift distribution can differ significantly from the elliptic lift distribution. Solutions for two example wing designs are presented, which demonstrate how the induced drag varies with lift distribution, wingspan, and wing-structure weight in the design space near the optimum solution. Although the analytic solutions presented here are restricted to rectangular wings, these solutions provide excellent test cases for verifying numerical algorithms used for more general multidisciplinary analysis and optimisation.
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Stamatelos, Dimitriοs, and George Labeas. "Towards the Design of a Multispar Composite Wing." Computation 8, no. 2 (April 9, 2020): 24. http://dx.doi.org/10.3390/computation8020024.
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In the pursuit of a lighter composite wing design, fast and effective methodologies for sizing and validating the wing members (e.g., spar, ribs, skins, etc.) are required. In the present paper, the preliminary design methodology of an airliner main composite wing, which has an innovative multispar configuration instead of the conventional two-spar design, is investigated. The investigated aircraft wing is a large-scale composite component, requiring an efficient analysis methodology; for this purpose, the initial wing sizing is mostly based on simplified Finite Element (FE) stress analysis combined to analytically formulated design criteria. The proposed methodology comprises three basic modules, namely, computational stress analysis of the wing structure, comparison of the stress–strain results to specific design allowable and a suitable resizing procedure, until all design requirements are satisfied. The design constraints include strain allowable for the entire wing structure, stability constraints for the upper skin and spar webs, as well as bearing bypass analysis of the riveted/bolted joints of the spar flanges/skins connection. A comparison between a conventional (2-spar) and an innovative 4-spar wing configuration is presented. It arises from the comparison between the conventional and the 4-spar wing arrangement, that under certain conditions the multispar configuration has significant advantages over the conventional design.
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Bai, Yuguang, Youwei Zhang, Tingting Liu, David Kennedy, and Fred Williams. "Numerical predictions of wind-induced buffeting vibration for structures by a developed pseudo-excitation method." Journal of Low Frequency Noise, Vibration and Active Control 38, no. 2 (February 14, 2019): 510–26. http://dx.doi.org/10.1177/1461348419828248.
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A numerical analysis method for wind-induced response of structures is presented which is based on the pseudo-excitation method to significantly reduce the computational complexity while preserving accuracy. Original pseudo-excitation method was developed suitable for adoption by combining an effective computational fluid dynamic method which can be used to replace wind tunnel tests when finding important aerodynamic parameters. Two problems investigated are gust responses of a composite wing and buffeting vibration responses of the Tsing Ma Bridge. Atmospheric turbulence effects are modeled by either k–ω shear stress transport or detached eddy simulation. The power spectral responses and variances of the wing are computed by employing the Dryden atmospheric turbulence spectrum and the computed values of the local stress standard deviation of the Tsing Ma Bridge are compared with experimental values. The simulation results demonstrate that the proposed method can provide highly efficient numerical analysis of two kinds of wind-induced responses of structures and hence has significant benefits for wind-induced vibration engineering.
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Wang, Yuhui, Peng Shao, Qingxian Wu, and Mou Chen. "Reliability analysis for a hypersonic aircraft’s wing spar." Aircraft Engineering and Aerospace Technology 91, no. 4 (April 1, 2019): 549–57. http://dx.doi.org/10.1108/aeat-11-2017-0242.
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Purpose This paper aims to present a novel structural reliability analysis scheme with considering the structural strength degradation for the wing spar of a generic hypersonic aircraft to guarantee flight safety and structural reliability. Design/methodology/approach A logarithmic model with strength degradation for the wing spar is constructed, and a reliability model of the wing spar is established based on stress-strength interference theory and total probability theorem. Findings It is demonstrated that the proposed reliability analysis scheme can obtain more accurate structural reliability and failure results for the wing spar, and the strength degradation cannot be neglected. Furthermore, the obtained results will provide an important reference for the structural safety of hypersonic aircraft. Research limitations/implications The proposed reliability analysis scheme has not implemented in actual flight, as all the simulations are conducted according to the actual experiment data. Practical implications The proposed reliability analysis scheme can solve the structural life problem of the wing spar for hypersonic aircraft and meet engineering practice requirements, and it also provides an important reference to guarantee the flight safety and structural reliability for hypersonic aircraft. Originality/value To describe the damage evolution more accurately, with consideration of strength degradation, flight dynamics and material characteristics of the hypersonic aircraft, the stress-strength interference method is first applied to analyze the structural reliability of the wing spar for the hypersonic aircraft. The proposed analysis scheme is implemented on the dynamic model of the hypersonic aircraft, and the simulation demonstrates that a more reasonable reliability result can be achieved.
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Meng, Yu-shan, Li Yan, Wei Huang, and Tian-tian Zhang. "Detailed Parametric Investigation and Optimization of a Composite Wing with High Aspect Ratio." International Journal of Aerospace Engineering 2019 (July 11, 2019): 1–27. http://dx.doi.org/10.1155/2019/3684015.
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The large deformation problem of the wing with high aspect ratio cannot be avoided due to the large bending moment and poor torsional stiffness. The wing design follows the following procedure; firstly, the design indexes of high aspect ratio wing are preliminarily formulated referring to some parameters of the Predator UAV. Then, the aerodynamic analysis of the wing is performed, and the stress cloud diagram is obtained. Next, the finite element model of the wing is designed, and the static analysis is conducted in the ANSYS ACP module, and the unreasonable component size is changed. An appropriate thickness which is 12 mm is selected as the final thickness of the wing. Then, the analysis of laying methods of skin structure is conducted. Finally, the composite structure is proved to reduce the maximum deformation and maximum stress effectively compared with the metal wing.
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Yin, Zhi Ping, Jiong Zhang, Jin Guo, and Qi Qing Huang. "Crack Growth Direction Analysis Based on Elastic-Plastic Property of Material." Advanced Materials Research 217-218 (March 2011): 101–6. http://dx.doi.org/10.4028/www.scientific.net/amr.217-218.101.
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The finite element software ANSYS was employed to create a finite element model of the cracked wing beam integrated structure, and the stress field of the crack tip was got by the material nonlinearity (elastic-plastic) analysis method. Based on the maximum tensile stress theory criteria, the crack deflection angle was obtained. The crack deflection angles with different geometry parameters (crack length, wed thickness, the height-thickness ratio of the stringer, cross-sectional area, and the location of the stringer) of the wing beam integrated structure were calculated and compared with each other. So the influences of the geometry parameters of the wing beam integrated structure on the crack deflection were studied. The crack deflection angles obtained in elastic analyzing and elastic-plastic analyzing were compared to investigate the effects of the material property on the crack deflection angle.
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S. Mohamed Ali, J., Hasna Nur Fadhila, Burhani M. Burhani, and Miah Mohammed Riyadh. "Educational Software for Stress Analysis of Idealized Closed Thin Walled Sections." International Journal of Engineering & Technology 7, no. 4.36 (December 9, 2018): 368. http://dx.doi.org/10.14419/ijet.v7i4.36.28144.
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Aerospace structures are typically semi-monocoque structures that are made up of thin-walled closed section reinforced with stiffeners. Stress analysis of such closed thin-walled structures which are statically indeterminate is tedious and time consuming. An educational software which can aid students in carrying out stress analysis of such idealized thin-walled closed sections has been developed. The software enables students to select different types of wing torsion box sections with stiffeners, which may be subjected to bending, shear or torsional loads and evaluate the resulting stresses on it. The software allows the student to idealize a selected twin spar unsymmetrical wing section with multiple booms under multiple loads. Results from this software have been validated against the results in the literature. The software has been developed using MATLAB with graphical user interface (GUI) which is very user friendly.
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Liu, Cai Jun. "Finite Element Analysis of 6-Wing Synchronous Rotor in the Mixing Process." Applied Mechanics and Materials 271-272 (December 2012): 1291–95. http://dx.doi.org/10.4028/www.scientific.net/amm.271-272.1291.
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By use of finite element method to analyze the strength of 6-wing synchronous rotor, and illustrate the change of parameters regarding strain, stress and displacement etc. so as to visually see whether the designed rotor will reach the design requirements; meanwhile, through structural analysis, to provide guidance for the further optimization of designing for 6-wing synchronous rotor.
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Bushra, Abdelmunem, Mohammed Mahdi, and Mohammed A. Elhadi. "Structural Analysis of Light Aircraft Wing Components." Applied Mechanics and Materials 225 (November 2012): 201–6. http://dx.doi.org/10.4028/www.scientific.net/amm.225.201.
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This paper aims to demonstrate the structure analysis of strut-braced wing of a typical manufactured Light-Aircraft by using FEM software (MSC PATRAN/NASTRAN) and determine the safety margin in all of its components, which are useful to determine the structure strength requirements. The geometrical model of the wing was created in CATIA and then exported to PATRAN, which is the modeler to build the finite element model. PATRAN model geometry was modified and prepared to create the mesh. The structural components have various functions and shapes, thus different element mesh was created. After creating the finite element model for all parts, the elements and material properties were assigned and the model was fixed at the spar root edge and strut-braced end, and loaded by distributing the inertia load and aerodynamic load, calculated using (CFD), acting on the rib edge. Then the model was submitted to NASTRAN for linear static analysis. The obtained Stress Results and Safety Margins of each part were calculated and found to be acceptable.
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Sun, Yifang, and А. А. Вендин. "АНАЛІЗ НАПРУЖЕНО-ДЕФОРМОВАНОГО СТАНУ ФІТИНГОВОГО СТИКУ ПАНЕЛЕЙ ВІД'ЄМНОЇ ЧАСТИНИ КРИЛА ТА ЦЕНТРОПЛАНА ТРАНСПОРТНОГО ЛІТАКА." Open Information and Computer Integrated Technologies, no. 91 (June 18, 2021): 97–112. http://dx.doi.org/10.32620/oikit.2021.91.07.
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Fitting joints are widely used in aircraft structures, and they are responsible for the interconnection of important components. The stress-strain state analysis of the fitting joint must be carried out before the performance analysis of the fitting joint. With the help of 3D modeling software (CATIA) and finite element analysis software (ANSYS), the stress-strain state of each component in the fitting joint of outer wing section was calculated in this paper. In the CATIA, the solid model is simplified and segmented according to the size of the cross section and the height of the center of gravity of the model. In the ANSYS, the beam elements are used to replace the simplified segmented model to obtain the internal force distribution of the solid model and to determine the magnitude and change law of the stress applied to the end of the solid model. When calculating the force transmitted by the fastener, the pre-tightening force of the bolt and the interaction between the surfaces of the component are taken into account, so as to simulate the real force situation well. Therefore, it is a very feasible method to use the CATIA and ANSYS to obtain the stress-strain state of components in the fitting joint of center wing section and outer wing section.The results show that under the working conditions of the fitting joint (130Mpa), the fitting of outer wing section with center section has a maximum stress of 245.79Mpa and a maximum strain of 0.0035, the stringer of outer wing section has a maximum stress of 293.17Mpa and a maximum strain of 0.0047, the lower panel of outer wing section has a maximum stress of 289.53Mpa and a maximum strain of 0.0042. The connecting bolts (M8 and M6) have a maximum stress of 686.81Mpa and a maximum strain of 0.0063, which meets the design requirements. In addition, according to the analysis results of the stress-strain state of the fitting joint of outer wing section, the force distribution of the bolts in the fitting joint of outer wing section with center section was obtained in this paper. It has been confirmed that due to the different positions and force areas of the bolts, the force distribution between rows of bolts is uneven, and the first row of bolts has a more force.
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Bennaceur, Mohamed Amine, Yuan-ming Xu, and Hemza Layachi. "Wing Rib Stress Analysis and Design Optimization Using Constrained Natural Element Method." IOP Conference Series: Materials Science and Engineering 234 (September 2017): 012018. http://dx.doi.org/10.1088/1757-899x/234/1/012018.
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CEJPEK, Jakub, and Jaroslav JURAČKA. "MODIFICATIONS OF A SIMPLE I-BEAM AND ITS EFFECTS ON THE STRESS STATE." Aviation 20, no. 4 (December 20, 2016): 168–72. http://dx.doi.org/10.3846/16487788.2016.1227538.
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The motivation for this work is a desire for a deeper understanding of the structural failures in a composite glider wing, which has been tested in the laboratories of the Institute of Aerospace Engineering, Faculty of Mechanical Engineering, Brno University of Technology. To understand the causes of the encountered failures, one has to consider the effects of all the stages in the design, manufacturing and testing of the wing. This paper focuses only on the design stage. The presented facts were obtained from a finite element analysis. The geometry used for the analysis is that of the tested specimens. This allows validating the results by the comparison of the deformation and strains measured during the laboratory tests. The analysis starts with a simple I-beam loaded by three-point-bending. In the next step a cantilever is added. Several more modifications follow, changing the I-beam to the wing. The case evaluation considers the interaction between normal (material direction 1) and inter-laminar shear stresses in the upper flange. The goal of this paper is to quantify the effect of each design change in the wing structure and loading on the stress plane σ1-τ31.
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Yang, Zheng Ran, Yi Jiang, and Cong Huang. "The Thickness of an Aircraft Wing Skins Optimization Based on ABAQUS." Applied Mechanics and Materials 716-717 (December 2014): 679–81. http://dx.doi.org/10.4028/www.scientific.net/amm.716-717.679.
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Wing skins play a vital role on the wing structure as well as the inherent characteristics of the wing. The thickness of the wing skins affects many of the key parameters of the wing. To study the impact of the thickness of the wing skins on the modal characteristics of the wing, and to preferable for the thickness of the wing skins, a certain type of aircraft wing model as an example, we carried out on the wing modal analysis and preferable the thickness of the wing skins based on Abaqus. The calculations show that the thickness of the wing skins are all affected on each wing modal frequencies, modal size of displacement and stress.
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Dong, Wen Jun, and Qin Sun. "Airfoil Design and Numerical Analysis for Morphing Wing Structure." Advanced Materials Research 228-229 (April 2011): 169–73. http://dx.doi.org/10.4028/www.scientific.net/amr.228-229.169.
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This paper investigates an unconventional honeycomb cellular structure featuring a negative Poisson’s ratio with the ability to undergo large overall displacements with limited straining of its solid material in the spanwise direction. Numerical analyses are performed to exploit such properties in the design of a morphing airfoil. The commercial simulation software ANSYS is used to carry on these processes. The cellular structure is designed to satisfy the requirements of configuration changing occurred while wing morphing. Finally, detailed numerical models of the structures are presented as a possible approach to evaluate the stress distribution of the structure. According to simulation results, the airfoil designed in this paper has the property of negative Poisson’s ratio, which is useful to the morphing wing aircraft design.
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Liu, Hao, Xia Sheng Sun, and Xiao Dong Li. "Modal Analysis of Wing Considering Transient Thermal Effects." Applied Mechanics and Materials 444-445 (October 2013): 1400–1406. http://dx.doi.org/10.4028/www.scientific.net/amm.444-445.1400.
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The severe aerodynamic heating on the surface of modern hypersonic flight vehicle, that can bring high temperature and large temperature gradients in the structure of the vehicle, will be a challenge for the vehicles design and multidisciplinary optimization. The transient thermal environment consists of high temperature and large temperature gradients will generate two important problems related to vehicle structure, namely: 1) the material property, such as elastic modulus, will be degraded at elevated temperature, and 2) the non-uniform thermal stress cased by large temperature gradients will change the stiffness distribution of wing structure, which can make the modal frequencies and shapes of structure changed remarkably. Firstly, the theory and methodology of structure modal analysis in transient thermal environment is outlined. Subsequently, the transient temperature field of structure considering aerodynamic heating is obtained by employing computational technology of aerodynamic heating/structure heat transfer coupling program. Finally, the modal frequencies and shapes of vehicle structure under transient temperature field is calculated based on finite element method (FEM). Based on the analysis and investigation of the simulation results, the influence of the transient thermal environment on structure modal frequency and shape is determined. Furthermore, the investigation of wing structure modal analysis considering aerodynamic heating is an important basis of aerothermoelastic simulation.
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Witek, Lucjan. "Stress and Fatigue Analysis of Modified Wing-Fuselage Connector for the Agricultural Aircraft." Journal of Aircraft 43, no. 3 (May 2006): 773–78. http://dx.doi.org/10.2514/1.14122.
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Yu, Chunjin, Daewon Kim, and Yi Zhao. "Stress Analysis of Membrane Flapping-Wing Aerial Vehicle Based on Different Material Models." Journal of Applied Mathematics and Physics 02, no. 12 (2014): 1023–30. http://dx.doi.org/10.4236/jamp.2014.212116.
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Kong, Chang Duk, Hyun Bum Park, Jae Huy Yoon, and Kuk Jin Kang. "Conceptual Design on Carbon-Epoxy Composite Wing of a Small Scale WIG Vehicle." Key Engineering Materials 334-335 (March 2007): 353–56. http://dx.doi.org/10.4028/www.scientific.net/kem.334-335.353.
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Conceptual structural design of the main wing for the 20 seats WIG(Wing in Ground Effect)flight vehicle, which will be a high speed maritime transportation system for the next generation in Rep. of Korea, was performed[1,2]. The high stiffness and strength Carbon-Epoxy material was used for the major structure and the skin-spar with a foam sandwich structural type was adopted for improvement of lightness and structural stability. As a design procedure for this study, firstly the design load was estimated through the critical flight load case study, and then flanges of the front and the rear spar from major bending loads and the skin structure and the webs of the spars from shear loads were preliminarily sized using the netting rule and the rule of mixture[4,5]. In order to investigate the structural safety and stability, stress analysis was performed by commercial Finite Element code such as NASTRAN/PATRAN. From the stress analysis results, it was confirmed that the upper skin structure between the front spar and rear spar was weak for the buckling. Therefore in order to solve this problem, a middle spar and the foam sandwich structure at the upper skin and the web were added. After design modification, even thought the designed wing weight was a little bit heavier than the target wing weight, the structural safety and stability of the final design feature was confirmed. In addition to this, the insert bolt type structure with six high strength bolts to fix the wing structure at the fuselage was adopted for easy assembly and removal. As well as consideration of the fatigue limit load for more than 20 years fatigue life.
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Castro, Xabier, and Zeeshan A. Rana. "Aerodynamic and Structural Design of a 2022 Formula One Front Wing Assembly." Fluids 5, no. 4 (December 9, 2020): 237. http://dx.doi.org/10.3390/fluids5040237.
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The aerodynamic loads generated in a wing are critical in its structural design. When multi-element wings with wingtip devices are selected, it is essential to identify and to quantify their structural behaviour to avoid undesirable deformations which degrade the aerodynamic performance. This research investigates these questions using numerical methods (Computational Fluid Dynamics and Finite Elements Analysis), employing exhaustive validation methods to ensure the accuracy of the results and to assess their uncertainty. Firstly, a thorough investigation of four baseline configurations is carried out, employing Reynolds Averaged Navier–Stokes equations and the k-ω SST (Shear Stress Transport) turbulence model to analyse and quantify the most important aerodynamic and structural parameters. Several structural configurations are analysed, including different materials (metal alloys and two designed fibre-reinforced composites). A 2022 front wing is designed based on a bidimensional three-element wing adapted to the 2022 FIA Formula One regulations and its structural components are selected based on a sensitivity analysis of the previous results. The outcome is a high-rigidity-weight wing which satisfies the technical regulations and lies under the maximum deformation established before the analysis. Additionally, the superposition principle is proven to be an excellent method to carry out high-performance structural designs.
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Li, Kui, Yuan Ying Qiu, and Ying Sheng. "Multi-Objective Optimization of a Large-Span Wing Analog Beam with Variable Cross-Sections." Applied Mechanics and Materials 215-216 (November 2012): 735–40. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.735.
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Aiming at the difficulty with structure and parameter design for a wing analog beam under a large deformation condition, a large-span cantilever truss model with Pro/e is designed. Then a mathematical model of the wing beam based on the Multi-objective Genetic Algorithm is proposed. Thereby the sizing optimization and shape optimization for the wing analog beam are conducted with the finite element analysis and meanwhile two main objectives minimizing the maximum von Mises stress and the mean-square error of the deformation displacement curve fitting are satisfied. A Pareto optimal solution aggregate is obtained after the optimization. Finally an optimal structure is concluded via the multi-objective optimization design, which improves the curve fitting accuracy of the wing and satisfies the stress strength requirement as well.
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Mohammadzadeh, Behzad, Sunghoon Jung, Tae Hyung Lee, Quyet Van Le, Joo Hwan Cha, Ho Won Jang, Sea-Hoon Lee, Junsuk Kang, and Mohammadreza Shokouhimehr. "Manufacturing ZrB2–SiC–TaC Composite: Potential Application for Aircraft Wing Assessed by Frequency Analysis through Finite Element Model." Materials 13, no. 10 (May 12, 2020): 2213. http://dx.doi.org/10.3390/ma13102213.
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This study presents a new ultra-high temperature composite fabricated by using zirconium diboride (ZrB2), silicon carbide (SiC), and tantalum carbide (TaC) with the volume ratios of 70%, 20%, and 10%, respectively. To attain this novel composite, an advanced processing technique of spark plasma sintering (SPS) was applied to produce ZrB2–SiC–TaC. The SPS manufacturing process was achieved under pressure of 30 MPa, at 2000 °C for 5 min. The micro/nanostructure and mechanical characteristics of the composite were clarified using X-ray diffraction (XRD), field-emission scanning electron microscopy (FESEM), and nano-indentation. For further investigations of the product and its characteristics, X-ray fluorescence (XRF) analysis and X-ray photoelectron spectroscopy (XPS) were undertaken, and the main constituting components were provided. The composite was densified to obtain a fully-dense ternary; the oxide pollutions were wiped out. The mean values of 23,356; 403.5 GPa; and 3100 °C were obtained for the rigidity, elastic modulus, and thermal resistance of the ZrB2–SiC–TaC interface, respectively. To explore the practical application of the composite, the natural frequency of an aircraft wing considering three cases of materials: (i) with a leading edge made of ZrB2–SiC–TaC; (ii) the whole wing made of ZrB2–SiC–TaC; and (iii) the whole wing made of aluminum 2024-T3 were investigated employing a numerical finite element model (FEM) tool ABAQUS and compared with that of a wing of traditional materials. The precision of the method was verified by performing static analysis to obtain the responses of the wing including total deformation, equivalent stress, and strain. A comparison study of the results of this study and published literature clarified the validity of the FEM analysis of the current research. The composite produced in this study significantly can improve the vibrational responses and structural behavior of the aircraft’s wings.
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Zhang, Da Qian, Ze Peng Zhu, and Xiao Dong Tan. "Lightweight Design of Outer Wing Based on Importance Evaluation Factor." Applied Mechanics and Materials 532 (February 2014): 461–65. http://dx.doi.org/10.4028/www.scientific.net/amm.532.461.
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The static and dynamic performance index is constraint condition to establish the mathematical model for optimization design of wing. Basically,the analysis of weighted sensitivity of objective function and state variable imports an importance evaluation factor of wing lightweight design to determine the optimization design variables, then using finite element software , with a optimization design module, to carry out a optimization design. As a result, the analysis of the outer wing shows that the premise of the maximum stress, maximum displacement and low modal frequency are better meet the operating requirements, which the wing weight cumulative reduce to 4.02%. Simultaneously, it proves the efficient and effective of such method.
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Wang, Peiyan, Shile Yao, Xinmei Wang, and Zhufeng Yue. "Experimental Research and Numerical Simulation of Wing Boxes under Pure Bending Load." Advances in Mechanical Engineering 6 (January 1, 2014): 274748. http://dx.doi.org/10.1155/2014/274748.
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Two full-scale wing boxes with different types of butt joints were investigated under pure bending load, and numerical methods, including global analysis and detailed analysis, were proposed to determine the reasons for failure of the wing boxes. Wing boxes were tested under bending loads applied by a multichannel force control system. The experimental results showed that the region of the butt joint was the weakest location of the wing boxes, and the damage loads were far less than the design load. The global analysis and detailed analysis were carried out on the wing boxes, focusing on the region of the butt joint, to determine the reasons for failure. Global analysis in explicit dynamic modulus was adopted to simulate the loading process of the two wing boxes. Meanwhile, detailed finite element models created in Patran/Nastran were used to evaluate the stability. Comparing experimental results with numerical counterparts, it is shown that the failure of the wing boxes is induced by local buckling occurring around the butt joint. In addition, the wing box that uses butt joints with lap jointed sheets is more rigid than that without lap jointed sheets, and the stress distribution is more uniform. The numerical analysis proposed by the paper can help with structure design in preliminary assessment.
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Tian, Yuan, Zhende Zhu, Xinyu Liu, and Yanxin He. "Experiment and Failure Analysis of Rock-Like Material Affected by Different Excavation Depths." Shock and Vibration 2021 (February 9, 2021): 1–15. http://dx.doi.org/10.1155/2021/6633367.
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In order to increase the understanding of the strength and failure mechanism of rock mass during tunnel excavation, a series of uniaxial compression tests were conducted on mortar specimen with cracks and holes by using a rock mechanics servo-controlled testing system. And by monitoring the experimental process, the initiation, propagation, and coalescence process of cracks were observed and characterized. According to the experimental results, the influences of the excavation depth on the mechanical parameters and fracture characteristics of mortar specimens with single hole and the ones with single-hole crack were analyzed in detail. In the specimens with single hole, the peak strength decreases with the increase of hole depth, but the peak strain and elastic modulus have no obvious linear correlation with the hole depth. And the position and angle of initial crack change differently with the increase of the hole depth. The position of initial crack moves from the side of the hole to the top of the hole. When the hole depth exceeds 50%, the crack initiation angle is no longer inclined to the axial stress direction, but parallel to the axial stress direction. In the specimens with single prefabricated crack, the wing-shaped secondary cracks are generated at the tip of the precrack, and the antiwing-shaped secondary cracks are generated at the tip when approaching the peak stress. However, in the specimens with single-hole crack, no antiwing-shaped crack appears. And when the hole depth reaches 80%, two wing-shaped cracks appear at the precrack tip. One of the new wing-shaped cracks appears in the direction of the extension line of the precrack.
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Edwards, Tim, and Jeremy Thompson. "Spar Corner Radius Integrity for the A400M Wing." Applied Mechanics and Materials 3-4 (August 2006): 197–204. http://dx.doi.org/10.4028/www.scientific.net/amm.3-4.197.
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The paper focuses on the structural integrity of the corner radius of the carbon fibre composite, ‘C’-section spar for the Airbus A400M wing. The corner radius is subject to opening moments generated by internal wing box fuel pressures. The low inter-lamina strength of composites makes de-lamination of the corner of prime concern. The paper describes initial development of analytical techniques to calculate the through-thickness tensile stresses and inter-lamina shear stresses developed in a corner radius under applied bending moments and transverse shear forces. A test programme is also described, aimed at the determination of the failure moment of curved laminates under pure bending moments. Using the analytical expressions developed, a through-thickness failure stress is calculated from the failure moments. A variation of the failure stress with specimen thickness is indicated, showing that thicker specimens fail at higher inter-lamina stresses – a characteristic that must be exploited in the design of the spar. Using finite element analysis of the test configuration, in conjunction with virtual crack extension techniques, it is demonstrated that, at the failure load, a constant rate of strain energy release accompanies inter-lamina crack growth in the different test specimens. A critical energy release rate for uncontrolled crack growth is thus established, which is used, in conjunction with further finite element analysis, to predict the failure stress of specimens with different values of thickness and corner radius. It is concluded that this fracture mechanics approach to integrity can be applied to the A400M spar corner and to similar aircraft structures. Recommendations for further testing and correlation with analysis are proposed to strengthen the theoretical basis for such integrity assessments.
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Stamoulis, Konstantinos, Dimitrios Panagiotopoulos, George Pantazopoulos, and Spyros Papaefthymiou. "Failure analysis of an aluminum extrusion aircraft wing component." International Journal of Structural Integrity 7, no. 6 (December 5, 2016): 748–61. http://dx.doi.org/10.1108/ijsi-10-2015-0050.
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Purpose The purpose of this paper is to deal with the failure analysis of a fractured spar stiffener, extruded from 7075-T6 aluminum alloy, which was found in the central wing, trailing edge structure of a military transport aircraft. The previous loading history and the dominant environmental factors (corrosive and humid atmosphere, water entrapment, etc.) suggest corrosion and fatigue as the principal failure modes, synergistically acting on the wing component. Design/methodology/approach This study presents the failure analysis concentrated on finding evidence of failure mechanisms and plausible root-cause(s) of the fractured spar stiffener. Chemical analysis, stereo and scanning electron microscopy, as well as finite element analysis employed as the main analytical tools for material characterization and failure investigation. Findings The overall evaluation of the findings suggest that the failure caused by a synergy of two mechanisms; a crack initiated in the longitudinal, extrusion direction by an environmentally assisted corrosion attack, then propagated by the superimposed transverse stress field, branched/deflected due to a low crack driving force and extended in a transverse path through a high cycle fatigue process. Finally, the complete fracture occurred as fast fracture, resulted by a ductile overload. Originality/value This paper deals with an industrial damage case study, providing analysis and modeling from structural engineering standpoint. The aforementioned findings concerning the fractured aircraft component allow gaining a deeper knowledge about the mechanisms of crack initiation and propagation which, in turn, can produce a valuable feedback to design, inspection and maintenance procedures. This includes a modified heat treatment from T6 to T73 temper for the redesigned component.
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Lai, Hui Fen, and Wu Zheng Xiao. "The Analysis on the Typical Parts in F1 Race Car." Applied Mechanics and Materials 215-216 (November 2012): 1136–39. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.1136.
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This document explains and demonstrates how to analyze the stress of the axle, modify the rear wing and SolidWorks dynamic simulation analysis for the F1 Race Car. It offers a variety of results visualization tools that allow investigators to gain valuable insight into the design of the F1 race car, and makes it easy to share analysis results effectively with everyone involved in the F1 race car product development process.
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KATRŇÁK, Tomáš, and Jaroslav JURAČKA. "Topometry FEM optimization of the wing structure of the transport aircraft." Aviation 21, no. 1 (March 27, 2017): 29–34. http://dx.doi.org/10.3846/16487788.2016.1266819.
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The article presents the topometry optimization of the critical semi-shell wing structure of the aircraft in the Commuter category of the CS-23 regulation standard (EASA 2012). Modern finite element (FE) optimization methods are used. The main outcome is that the milled integral lower wing panel allows significant weight savings due to an optimization of the thickness of each skin segment. The FE model validation with the analytical software and the selection of structural constraints and requirements for the optimization are described in this article. Also, a final stress analysis and a complex load capacity analysis validate required properties of designed structural modifications with an optimal stress distribution. Additionally the analysis of weight savings and elongation of the fatigue durability according to the Damage tolerance methodology was done.
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Жиряков, Дмитрий Юрьевич. "АНАЛІЗ КОНСТРУКТИВНИХ ОСОБЛИВОСТЕЙ З'ЄДНАНЬ СИЛОВИХ ЕЛЕМЕНТІВ КРИЛА ЛІТАКІВ ТРАНСПОРТНОЇ КАТЕГОРІЇ." Open Information and Computer Integrated Technologies, no. 86 (February 14, 2020): 139–51. http://dx.doi.org/10.32620/oikit.2019.86.10.
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Ensuring the fatigue life of the aircraft structure is a requirement for flight safety, and for a cost-effective aircraft. A plane with a long lifetime can perform more flights, reduce routine maintenance costs and increase airline profits. Market trends in the aviation industry show the interest of airlines in long life aircraft. Structural elements of the wing are joined by fasteners. The wing structure fatigue is determined by the endurance of regular zones. Regular zones include longitudinal, transverse joints. The fatigue life of the wing irregular zones should be no less than the fatigue life of the regular zone. The article provides an analysis of the design features of the wing structural element joints performing short and medium flights, ANTONOV and Boeing, which have reached a high level in this field of research. Structural schemes of the wings, location and execution of the joints of the wing structural parts using facilities that improve take-off and landing characteristics (such as ailerons, flaps, slats and spoilers) are analyzed. The types, diameters and materials of fasteners that vary within the wing limits are considered. Attention was focused on such important indicators as the edge tolerance, distance between the fasteners (spacing), wing and fastener construction materials. The wing is made of a prefabricated structure, to ensure safety requirements for permissible destruction. In turn, this leads to an increase in the amount of fasteners. Since fatigue life is affected not only by the kinds of materials, parameters of fasteners, rated stresses, but also the degree of load transferring between parts. The constructive execution of the longitudinal and transverse connections of the load-bearing elements was analyzed to further study the degree of load transfer in a difficult - stressed state. The materials of the article provide an opportunity for further in-depth research on the general and local stress-strain state of the wing.
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Chun, Young Chal, Yun Jung Jang, Tae Jin Chung, and Ki Weon Kang. "Stress Spectrum Algorithm Development for Fatigue Crack Growth Analysis and Experiment for Aircraft Wing Structure." Transactions of the Korean Society of Mechanical Engineers A 39, no. 12 (December 1, 2015): 1281–86. http://dx.doi.org/10.3795/ksme-a.2015.39.12.1281.
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Yang, Jia, and Wen Jun Qi. "Effect of Extreme Temperature on the Performance of Wind Turbine Blade." Key Engineering Materials 522 (August 2012): 457–61. http://dx.doi.org/10.4028/www.scientific.net/kem.522.457.
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According to the Dabancheng wing farm weather conditions from 1971 to 2000, and its extreme temperature conditions, the performance change of 750KW wind turbine blade with them was researched in the article. Import UG Modeling to ANSYS, then achieve the static structural analysis and the heat-structure interaction analysis respectively. The results show that comparing aerodynamic-temperature loads with aerodynamic loads, the stress, strain and displacement of the blade is increased by 13.89%, 10.29% and 0.20%. Therefore, temperature changes have a certain impact on the blade performance. In the future, the temperature will be a necessary consideration during design of blade structure.
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Kuntjoro, Wahyu. "Development of a Lightweight Box Structure for Static Structural Experiments." International Journal of Mechanical Engineering Education 35, no. 4 (October 2007): 324–35. http://dx.doi.org/10.7227/ijmee.35.4.7.
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It is important to expose university students to practical experiments. In this way, they will appreciate more the subjects which they learn. This paper reports on the development of a lightweight box structure with which students can perform static structural experiments. The box simulates the wing box of a two-spar wing structure, and is intended for aeronautics engineering undergraduate students in a practical laboratory. All materials were purchased from high-street shops. To determine the characteristics of the sheet metal aluminum alloy that was purchased, tensile tests were performed. A preliminary analysis was performed to obtain the stress of the box for a certain loading. Further analysis was conducted using the finite element method. Manufacturing of the box consisted of conventional sheet metal cutting, metal forming, and sheet metal assembly. The box was then tested to obtain the stress due to static tip loading. The stresses were obtained through strain gauge readings. The readings were then compared with the theoretical and finite element analysis. The data from these analyses were then used as part of the practical laboratory.
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Imumbhon, Johnson O., Mohammad D. Alam, and Yiding Cao. "Design and Structural Analyses of a Reciprocating S1223 High-Lift Wing for an RA-Driven VTOL UAV." Aerospace 8, no. 8 (August 5, 2021): 214. http://dx.doi.org/10.3390/aerospace8080214.
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In the design stage of an aircraft, structural analyses are commonly employed to test the integrity of the aircraft components to demonstrate the capability of the structural elements to withstand what they are designed for, as well as predict potential failure of the components. This research focused on the structural design and analysis of a high-lift, low Reynolds number airfoil profile, the Selig S1223, under reciprocating inertial force loading, to determine the feasibility of its use in a new reciprocating airfoil (RA) driven VTOL UAV. The material selected for the wing structures including ribs, spars, and skin, was high-strength carbon fiber. The wing was designed in SolidWorks, while finite element analysis was performed with ANSYS mechanical in conjunction with the inertia forces due to the reciprocating motion of the wing and the lift and drag forces that were derived from the aerodynamic wing analyses. The structural stress and strain determined under the loading conditions were satisfactory and the designed wing could sustain the high reciprocating inertia forces in the RA-driven VTOL UAV module. The results of this study indicate that the Selig S1223 airfoil profile, due to its superior performance at low Reynolds numbers, high-lift, and reduced noise characteristics at low angles of attack, combined with the use of the high strength carbon fiber, proves to be an excellent choice for this RA-driven aircraft application.
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Zhang, Xiao Yu, Feng Ming Liu, and Gang Chen. "Geo-Stress Measurement and its Application in the Yangchangwan Coal Mine." Applied Mechanics and Materials 353-356 (August 2013): 398–402. http://dx.doi.org/10.4028/www.scientific.net/amm.353-356.398.
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The initial stress of rock is a basic parameter, which can be used for surrounding rock stability analysis, exploitation and support design. By utilizing stress relief method of hollow inclusion with its characters of high precision and obtaining three dimensional stress at one time, we have measured three dimensional stress magnitude and direction in north wing roadway (-850m) and 710 open-off cut (-1000m), respectively. The results show that the horizontal tectonic stress is obvious in this coal area.
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Rośkowicz, Marek, Michał Jasztal, Piotr Leszczyński, and Szymon Wszelaki. "Geometrical Optimisation of a Wing Strut Joint. Part I." Journal of KONBiN 49, no. 4 (December 1, 2019): 1–26. http://dx.doi.org/10.2478/jok-2019-0072.
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Abstract This paper provides the result of the geometrical optimisation of a wing strut joint of an aircraft. The objective of the geometrical optimisation was to modify the geometry of the wing strut joint components to meet an optimisation criterion defined as yield strength determined by static tensile testing. The geometrical optimisation was processed on a computer model of the wing strut joint using FEM (finite element method). The design variables assumed in this geometrical optimisation were the load option and boundary conditions of interaction between the wing strut joint components. An analysis carried out as part of the geometrical optimisation was based on proposing modifications to the geometry of the joint features at their maximum stress levels. The geometry optimisation results will be applied in the preparation and performance of validation strength testing of the wing strut joint assembly.
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Freakley, P. K., and S. R. Patel. "Internal Mixing: A Practical Investigation of the Flow and Temperature Profiles during a Mixing Cycle." Rubber Chemistry and Technology 58, no. 4 (September 1, 1985): 751–73. http://dx.doi.org/10.5254/1.3536091.
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Abstract From the results of mixing trials with a highly instrumented BR Banbury and biconical rotor rheometry of mixed batches, a detailed analysis of flow and mixing characteristics in the region of a rotor wing has been undertaken. An ‘angled spreader blade’ analogy of the rotor wing is proposed as being a viable basis for mathematical modelling. A one-dimensional flow analysis is used, in which power-law flow behavior and isothermal conditions are assumed. Dispersive mixing, which depends on the stress levels generated during mixing, is shown to occur throughout the entire mass of material swept in front of the rotor wing and not simply at the rotor tip. In addition, the stress levels depend more strongly on batch temperature than on rotor speed. High rotor speeds tend to lead to reduced stress levels as a result of the associated rapid rise in batch temperature, although choosing an appropriate fill factor can minimize temperature rise by promoting efficient heat transfer to the cooling water. During each rotor revolution, the rotor wing collects a mass of material from the reservoir between the rotors. This mass of material is then progressively reduced by leakage flow under the rotor tip and flow around the end of the wing, until the revolution is completed by the return of a residue to the reservoir. The flow around the end of the rotor is shown to be consistently greater than the leakage flow, although the ratio can be influenced by both fill factor and rotor speed. At high rotor speeds and low fill factors, it appears that material is retained in the regions of the side frames of the mixer and may give batch inhomogeneity through poor distribution mixing.
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Tanaskovic, Marija, Zorana Kurbalija-Novicic, Bojan Kenig, Savic Veselinovic, Marina Stamenkovic-Radak, and Marko Andjelkovic. "Synergistic effect of environmental and genomic stress on wing size of drosophila subobscura." Genetika 48, no. 3 (2016): 1039–52. http://dx.doi.org/10.2298/gensr1603039t.
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Growing anthropogenic influence on every aspect of environment arise important issues regarding the ability of populations and species to adapt to variant pressures. Lead is one of the most present contaminants in the environment with detrimental influence on organisms and populations. In combination with genomic stress, lead may act synergistically, leading to reduction in adaptive values. We sampled two Drosophila subobscura populations, from ecologically different habitats and established differences in genetic backgrounds and population histories. In order to establish different levels of genome heterozygosity, series of intra-line, intra-population and between population crosses were made. The progeny was reared on a standard Drosophila medium and a medium with 200?g/mL of lead acetate and right wing of approximately 4000 individuals was used for geometric morphometric analysis of wing size. Results showed that lead significantly reduces wing size and that magnitude of this reduction is dependent on genetic background, indicating synergistic effect of genomic and environmental stress. There is also an indication of strong female origin influence on the outcome of hybridization when source of environmental stress is lead. Our results showed that the genetic structure of populations is of great importance for population fitness in anthropogenic induced stressful conditions. Further studies of synergistic effect of genetic and environmental stress are needed, as well as studies of its outcome in natural populations.
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Jain, Prathik S. "2 Way Fluid-Structure Interaction Study of a Wing Structure." International Journal for Research in Applied Science and Engineering Technology 9, no. 8 (August 31, 2021): 2593–606. http://dx.doi.org/10.22214/ijraset.2021.37834.
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Abstract: In this paper a scaled down model of a wing of rectangular planform is designed and the static analysis on the wing is carried out to determine the aerodynamics forces, stresses acting on it and the frequency of various modes. The iteration for the analysis is carried out for three materials namely, Aluminium 7075 T-6, Glass Fibre Reinforced Polymer and Aluminium Metal Matrix Composite. The analysis in the coupled mode is conducted and compared with the results obtained from that of static analysis to observe the changes in the flow pattern and how the structure behaves when the wing is considered to be flexible. In the coupled mode analysis 2 Way Fluid Structure Interaction analysis is carried out. The material properties and the results obtained from the analysis is compared to select the best out of the three materials. The change in the aerodynamic properties of the wing when it is considered to be flexible is also highlighted by a method of comparison. From the results obtained, it is observed that Aluminium Metal Matrix Composite has the least deformation for the same loading and can withstand higher stress. Hence, Aluminium Metal Matrix Composite exhibits better characteristics in comparison with Glass Fibre Reinforced Polymer and Aluminium 7075 T-6. Additionally, it is noticed that the aerodynamic properties of the wing is reduced when it is considered as a flexible structure. This can be highlighted by the 5.42% decrease in the L/D ratio between the CFD analysis and the 2 Way FSI analysis results. Keywords: Fluid Structure Interaction; Flexible Wing; CFD; Coupled Mode Analysis;