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Journal articles on the topic 'Wing spar'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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1

ENNOS, A. ROLAND. "The Importance of Torsion in the Design of Insect Wings." Journal of Experimental Biology 140, no. 1 (November 1, 1988): 137–60. http://dx.doi.org/10.1242/jeb.140.1.137.

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A model insect wing is described in which spars of corrugated membrane which incorporate stiffening veins branch serially from a V-section leading edge spar. The mechanical behaviour of this model is analysed. The open, corrugated spars possess great resistance to bending, but are compliant in torsion. Torsion of the leading edge spar will result in torsion and relative movement of the rear spars. As a result camber will automatically be set up in the wing as it twists. Aerodynamic forces produced during the wing strokes will result in torsion and camber of the wing which should improve its aerodynamic efficiency. The effects of varying parameters of the wing model are examined. For given wing torsion, higher camber is given by spars branching from the leading edge at a lower angle, by spars which curve posteriorly, and by spars which diverge from each other. Wings of three species of flies were each subjected to two series of mechanical tests. Application of a force behind the torsional axis caused the wings to twist and to develop camber. Immobilizing basal regions of the leading edge greatly reduced compliance to torsion and camber, as predicted by the theoretical model. Aerodynamic forces produced during a half-stroke are sufficient to produce observed values of torsion and camber, and to maintain changes in pitch caused by inertial effects at stroke reversal.

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2

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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3

Zhou, Hong Xia, and Bin Liu. "Characteristics Analysis and Optimization of Flying-Wing Vehicle Structure." Advanced Materials Research 1077 (December 2014): 177–84. http://dx.doi.org/10.4028/www.scientific.net/amr.1077.177.

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To study structural characteristics of flying-wing vehicle, static and dynamic model of half wing span, static and dynamic model of all wing span, optimization model were established. Based on associated static test and ground resonance test data, these models were modified to implement static, dynamic and optimization analysis. Results demonstrated that structural bending and torsional deformations are mainly at outer wing surface. Torsion at inner wing is positive, while torsion at outer wing is negative. Total spar axial force along the wing span increases gradually from inner wing to outer wing and then decreases gradually after reaching the inner-outer wing interface. After axial force is transmitted to the inner wing, it is going to concentrate at the rear spar obviously. Structural bending rigidity and torsional rigidity satisfy requirements of both static force and flutter, without flutter problem of main structural mode. Viewed from the optimization size, ±45° and 0° skin at inner-outer wing turn thickens significantly. This can increase structural bending and torsional rigidity, which is good for satisfying multiple constraints comprehensively.

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4

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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5

Petrasinovic, Nikola, Danilo Petrasinovic, Bosko Rasuo, and Dragan Milkovic. "Aircraft duraluminum wing spar fatigue testing." FME Transaction 45, no. 4 (2017): 531–36. http://dx.doi.org/10.5937/fmet1704531p.

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6

Ajaj, R. M., M. I. Friswell, W. G. Dettmer, G. Allegri, and A. T. Isikveren. "Performance and control optimisations using the adaptive torsion wing." Aeronautical Journal 116, no. 1184 (October 2012): 1061–77. http://dx.doi.org/10.1017/s000192400000748x.

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Abstract This paper presents the Adaptive Torsion Wing (ATW) concept and performs two multidisciplinary design optimisation (MDO) studies by employing this novel concept across the wing of a representative UAV. The ATW concept varies the torsional stiffness of a two-spar wingbox by changing the enclosed area through the relative chordwise positions of the front and rear spar webs. The first study investigates the use of the ATW concept to improve the aerodynamic efficiency (lift-to-drag ratio) of the UAV. In contrast, the second study investigates the use of the concept to replace conventional ailerons and provide roll control. In both studies, the semi-span of the wing is split into five equal partitions and the concept is employed in each of them. The partitions are connected through thick ribs that allow the spar webs of each partition to translate independently of the webs of adjacent partitions and maintain a continuous load path across the wing span. An MDO suite consisting of a Genetic Algorithm (GA) optimiser coupled with a high-end low-fidelity aero-structural model was developed and employed in this paper.

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7

Dvorak, Milan, Miroslav Kabrt, and Milan Růžička. "The Use of Fiber Bragg Grating Sensors during the Static Load Test of a Composite Wing Structure." Applied Mechanics and Materials 486 (December 2013): 102–5. http://dx.doi.org/10.4028/www.scientific.net/amm.486.102.

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The article describes process of implementation of optical Fiber Bragg Grating (FBG) sensors into the composite wing structure and their behavior during the strength test. The wing is of all-composite construction. The upper and lower skins are made of glass/epoxy composite. The spar caps are made of carbon/epoxy unidirectional composite. Optical fibers were integrated directly into the spar caps and into the adhesive joints. They were oriented in parallel with the main spar axis. The first optical fiber with chain of multiple FBG sensors was integrated into the structure of upper spar cap. Another FBG chain of FBG sensors was located in the adhesive joint of lower spar cap and shear web. The wing was instrumented with strain gages as well. Strain gages were glued to the sides of the spar caps. Static load was produced by a hydraulic actuator. Experimental results from strain gages and FBG sensors were compared with the results of the analytical analysis of the wing.

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8

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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9

Pavan, G., and N. Kishore. "Static and Fatigue Analysis on a Wing Spar Joint for a Light Jet Aircraft Structure Using 2024 T351 Material." Applied Mechanics and Materials 895 (November 2019): 244–52. http://dx.doi.org/10.4028/www.scientific.net/amm.895.244.

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The main objective of this paper is to present prototype of wing spar joint using CATIA V5 software to study the behavior of wing spar joint as per actual working condition and to perform structural analysis of the wing spar joint based on condition of cyclic loading (fatigue loading). Determining the loading modes in the spar joint is subjected to static load and fatigue loads which should be taken into account in the evaluation of the strength and fatigue life. Initially, the components were modeled with CATIA V5 and imported to MSC PATRAN; MSC NASTRAN is used as a solver. From the obtained maximum tensile stresses, fatigue analysis was carried out to find fatigue life of the spar joint with different fatigue load spectra.

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10

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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11

Iryani, Lenny, Andi M. Kadir, Yudi Irawadi, and Puguh Triwinanto. "Manufacturing Spar I Beam Profile of UAV Wing Structure Made of Composite Material." Journal of Advanced Research in Dynamical and Control Systems 11, no. 11-SPECIAL ISSUE (February 20, 2019): 556–62. http://dx.doi.org/10.5373/jardcs/v11sp11/20193066.

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12

Elelwi, M., T. Calvet, R. M. Botez, and T. M. Dao. "Wing component allocation for a morphing variable span of tapered wing using finite element method and topology optimisation – application to the UAS-S4." Aeronautical Journal 125, no. 1290 (June 7, 2021): 1313–36. http://dx.doi.org/10.1017/aer.2021.29.

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AbstractThis work presents the Topology Optimisation of the Morphing Variable Span of Tapered Wing (MVSTW) using a finite element method. This topology optimisation aims to assess the feasibility of internal wing components such as ribs, spars and other structural components. This innovative approach is proposed for the telescopic mechanism of the MVSTW, which includes the sliding of the telescopically extended wing into the fixed wing segment. The optimisation is performed using the tools within ANSYS Mechanical, which allows the solving of topology optimisation problems. This study aims to minimise overall structural compliance and maximise stiffness to enhance structural performance, and thus to meet the structural integrity requirements of the MVSTW. The study evaluates the maximum displacements, stress and strain parameters of the optimised variable span morphing wing in comparison with those of the original wing. The optimised wing analyses are conducted on four wingspan extensions, that is, 0%, 25%, 50% and 75%, of the original wingspan, and for different flight speeds to include all flight phases (17, 34, 51 and 68m/s, respectively). Topology optimisation is carried out on the solid wing built with aluminium alloy 2024-T3 to distribute the wing components within the fixed and moving segments. The results show that the fixed and moving wing segments must be designed with two spar configurations, and seven ribs with their support elements in the high-strain area. The fixed and moving wing segments’ structural weight values were reduced to 16.3 and 10.3kg from 112 to 45kg, respectively. The optimised MVSTW was tested using different mechanical parameters such as strains, displacements and von Misses stresses. The results obtained from the optimised variable span morphing wing show the optimal mechanical behaviour and the structural wing integrity needed to achieve the multi-flight missions.

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13

Trappe, Volker. "Fatigue life evaluation of composite wing spar cap materials." Materials Testing 61, no. 12 (December 2, 2019): 1135–39. http://dx.doi.org/10.3139/120.111431.

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14

Tatarnikov, O. V., W. A. Phyo, and Lin Aung Naing. "Multi-Criteria Optimization of a Two-Spar Composite Wing for a Light Aircraft." Proceedings of Higher Educational Institutions. Маchine Building, no. 5 (734) (May 2021): 76–87. http://dx.doi.org/10.18698/0536-1044-2021-5-76-87.

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The article considers the results of optimization of the two-spar composite wing for the K-8 training aircraft. The geometric characteristics of the main structural elements of the wing such as spars, ribs and skin; orientation angles of the reinforcing layers and their thicknesses for each wing structural element, as well as the type of composite material and cost were selected as optimization parameters. The proposed optimization procedure includes several steps; each step uses a multi-criteria approach. The minimum deflection, weight, and cost are taken as optimization criteria. All the necessary calculations for selecting the optimal optimization parameters were performed using nonlinear static finite element analysis in the FEMAP software package.

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15

Babcock, J., and R. Lind. "Aeroelastic effects of battens on the flight dynamics of a MAV." Aeronautical Journal 118, no. 1207 (September 2014): 985–1008. http://dx.doi.org/10.1017/s0001924000009714.

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Abstract Wing flexibility is well established as providing gust rejection and delayed onset of stall for micro air vehicles. As such, many designs adopt wings of a flexible material mounted onto a skeleton comprised of a stiff leading-edge spar and stiff chordwise strips, called battens. These battens are shown to provide additional strength at localised regions of the wing and thus improve the gust rejection and delay stall; however, their effect on the flight dynamics is less studied. Using a numerical modeling approach, this paper explores a design space of vehicles with a varied number of wing battens mounted onto a baseline vehicle with a flexible wing. The battens are modelled as stepwise changes in torsional stiffness along the wing span. The resulting trim characteristics, static stability metrics and flight dynamics are evaluated. The battens are shown to improve gust rejection but otherwise have a complicated effect across the design space. A reduction in the number of battens improves the longitudinal static stability derivative slightly but lowers the lateral and directional static stability. The damping is decreased for the short period mode and increased for the phugoid and dutch roll modes as the number of battens is reduced.

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16

Park, Sang-Wook, Jeong-Woo Shin, Mu-Hyoung Lee, and Tae-Uk Kim. "Non-linear Structural Analysis of Main Wing Spar of High Altitude Long Endurance UAV." Journal of the Korean Society for Aviation and Aeronautics 23, no. 1 (March 31, 2015): 24–29. http://dx.doi.org/10.12985/ksaa.2015.23.1.024.

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17

Ciminello, Monica, Angelo De Fenza, Ignazio Dimino, and Rosario Pecora. "Skin-Spar Failure Detection of a Composite Winglet Using FBG Sensors." Archive of Mechanical Engineering 64, no. 3 (September 1, 2017): 287–300. http://dx.doi.org/10.1515/meceng-2017-0017.

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Abstract Winglets are introduced into modern aircraft to reduce wing aerodynamic drag and to consequently optimize the fuel burn per mission. In order to be aerodynamically effective, these devices are installed at the wing tip section; this wing region is generally characterized by relevant oscillations induced by flights maneuvers and gust. The present work is focused on the validation of a continuous monitoring system based on fiber Bragg grating sensors and frequency domain analysis to detect physical condition of a skin-spar bonding failure in a composite winglet for in-service purposes. Optical fibers are used as deformation sensors. Short Time Fast Fourier Transform (STFT) analysis is applied to analyze the occurrence of structural response deviations on the base of strain data. Obtained results showed high accuracy in estimating static and dynamic deformations and great potentials in detecting structural failure occurrences.

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18

Eldwaib, Khalid, Aleksandar Grbović, Gordana Kastratović, and Mustafa Aldarwish. "Design of Wing Spar Cross Section for Optimum Fatigue Life." Procedia Structural Integrity 13 (2018): 444–49. http://dx.doi.org/10.1016/j.prostr.2018.12.074.

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19

Diaz, I. Carbia, Y. Jin, and E. Ares. "Cycle time study of wing spar assembly on aircraft factory." Procedia Manufacturing 13 (2017): 1019–25. http://dx.doi.org/10.1016/j.promfg.2017.09.107.

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Shin, Jeong Woo, Sang Wook Park, Mu-Hyoung Lee, and Tae-Uk Kim. "Light Wing Spar Design for High Altitude Long Endurance UAV." Journal of the Korean Society for Aviation and Aeronautics 22, no. 2 (June 30, 2014): 27–33. http://dx.doi.org/10.12985/ksaa.2014.22.2.027.

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21

Solovyev, Pavel, Andrey Gomzin, Yuriy Pervushin, Fanil Musin, and Sergey Galyshew. "Structure determination and composite wing spar stress-strain state estimation." MATEC Web of Conferences 129 (2017): 02040. http://dx.doi.org/10.1051/matecconf/201712902040.

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22

Whiteside, J. B., R. J. DeIasi, and R. L. Schulte. "Measurement of preferential moisture ingress in composite wing/spar joints." Composites Science and Technology 24, no. 2 (January 1985): 123–45. http://dx.doi.org/10.1016/0266-3538(85)90055-7.

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23

Kim, Ki-Hoon, and Kyo-Nam Koo. "Design and Analysis of Section-divided Circular Composite Wing Spar." Journal of the Korean Society for Aeronautical & Space Sciences 47, no. 10 (October 31, 2019): 687–94. http://dx.doi.org/10.5139/jksas.2019.47.10.687.

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Pecho, Pavol, Paulína Magdolenová, Michal Hrúz, Pavel Kováčik, and Iveta Škvareková. "Study of reinforcement design h-profile of aircraft wing spar." AEROjournal 16, no. 2 (2020): 9–14. http://dx.doi.org/10.26552/aer.c.2020.2.2.

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In today's world, with ever-increasing safety requirements, there is a growing demand to maintain or reduce production costs. In aviation, in addition to factors like weight and related variables such as resistance to vibration, corrosion, temperature and other are also considered. The task of this paper is to analyse unconventional designs of wing beams with respect to the current requirements of the aviation industry. In the article, the authors analyse the possibilities of design modification either by adding ribs to the profile, or by changing the cross-section of the profile itself. In practice, such design changes would increase weight, production time and finances, but also increase strength and thus safety. All proposed changes were subjected to strength analyses by FEM (Finite element method) computer simulations. The article output is the selection of suitable designs for further observation and experimental verification to ensure comprehensive results for the possibility of implementation in practice. Despite the non-traditional shapes of the proposed wing beam cross-sections, the authors assume that traditional beam shapes will be gradually modified more efficiently.

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25

Zhou, Yu Hua, Yu Tao Ju, and Chang Sheng Zhou. "Design of Flexible Wing with Embedded Piezoelectric Actuator." Applied Mechanics and Materials 325-326 (June 2013): 951–55. http://dx.doi.org/10.4028/www.scientific.net/amm.325-326.951.

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This paper introduces a new kind of flexible wing with embedded piezoelectric actuator as framework for Micro Air Vehicles (MAV), which was fixed spar in the previous flexible wing. This made it a controllable flexible wing because the new flexible wing can not only works as previous model without control, but also can change its wing profiles in our purpose by using the embedded piezoelectric actuator when its necessary. The mathematical model of the deformation of piezoelectric actuator under control has developed. with which the structure of the flexible wing was designed. The simulation of dynamic characteristic of the flexible wing with embedded piezoelectric actuator has been done with ANSYS software.

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26

ENNOS, A. ROLAND, and ROBIN J. WOOTTON. "FUNCTIONAL WING MORPHOLOGY AND AERODYNAMICS OF PANORPA GERMANICA (INSECTA: MECOPTERA)." Journal of Experimental Biology 143, no. 1 (May 1, 1989): 267–84. http://dx.doi.org/10.1242/jeb.143.1.267.

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The functional wing morphology of the wings of the scorpion fly Panorpa germanica L. was investigated using a combination of light microscopy, high-speed cinematography, wing manipulation and mechanical testing In rising forward flight the wings are flapped 40° out of phase along a shallow stroke plane, the forewings leading. Aerodynamic analysis suggests that unsteady effects are important in flight During the downstroke, both wings are straight and cambered, the chord being parallel to the body axis, which is angled 45° upwards from horizontal. Both wings are supinated at lower stroke reversal, the hindwing to a much greater extent, and flex ventrally halfway along their length for the first half of the upstroke. Flexion is parallel to the chord in the hindwing, but is oblique in the forewing, so distal forewing areas are supinated relative to proximal areas The behaviour of the wings is related to their structure. Spars at the leading and trailing edges of both wings support the wing during the downstroke, and flexion during the upstroke is facilitated by buckling of the weak ventral thyridium region. The oblique flexion seen in the forewing is due to its relatively longer leading edge spar The differences between the wings are, in turn, related to their pitch control mechanisms. The forewing has a well-developed clavus, like that of the forewing of a locust, and pitch is altered by relative movement of this and the leading edge, but only within a narrow range. Oblique flexion is necessary to invert the aerofoil. The weaker and less well-developed clavus of the hindwing, more similar to that of the Diptera, allows a greater degree of supination, effected largely by wing inertia. No oblique flexion is necessary

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27

Grbović, Aleksandar, Gordana Kastratović, Aleksandar Sedmak, Khalid Eldweib, and Snezana Kirin. "Determination of optimum wing spar cross section for maximum fatigue life." International Journal of Fatigue 127 (October 2019): 305–11. http://dx.doi.org/10.1016/j.ijfatigue.2019.06.019.

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Ji, Zhe, Bin Liu, and Fei Xu. "Wing Structural Design of a High Altitude Long Endurance Solar-Powered Platform." Advanced Materials Research 753-755 (August 2013): 1287–90. http://dx.doi.org/10.4028/www.scientific.net/amr.753-755.1287.

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The solar-powered platform has great application prospects with its unique characteristics of high cruising altitude and long endurance. This paper presents a high-aspect-ratio long straight composite wing structure. A 3D FEM model is used to study the mechanical performance of the wing under gust, by applying nonlinear analytical method. The wing optimization is focused on high stiffness and light weight. A wing structure of feasible strength and stiffness is obtained. Through analysis, several engineering conclusions are obtained. In addition, the instability features of the main spar are included as well.

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29

Triani, Suciari Dewi, Moh Ardi Cahyono, and Lazuardy Rahendra Pinandhita. "STRUCTURE ANALYSIS AND MANUFACTURING OF WINGS TRAINER-5774." Vortex 1, no. 2 (January 26, 2021): 107. http://dx.doi.org/10.28989/vortex.v1i2.894.

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Unmanned Aerial Vechicle (UAV) is one of the types an aircraft. Trainer is part of an airplane where the aircraft is controlled by a remote control for its flight. One of the things that must be considred in design an airplane is strength and and resistance of the wing structure in accepting distributed aircraft loads. In addition to the structural design and load, the material to be used can have an effect. The process is starting from modification of the aircraft wing using CATIA V5R20 which is then carried out analysis of the wing structure by being given the aircraft load using ANSYS 19. The largest structural value is in the Joiner section of 7,967 with manuvering load and smallest value is 0,026 on the Spar section. Margin of safety smallest value in the spar when its manuver. After analysis it is continued with the manufacturing process according to the design that has been made.

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30

A, Mugeshwaran, Guru Prasad Bacha, and Rajkumar S. "Design and experimental analysis of morphing wing based on biomimicry." International Journal of Engineering & Technology 7, no. 3.3 (June 8, 2018): 239. http://dx.doi.org/10.14419/ijet.v7i2.33.14160.

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In this paper narrate about the study of aerodynamics in the multi-section morphing wing variation of baseline configuration to camber con-figuration. In particularly NACA 0012, section tried to morph as NACA 9312 camber section to achieve the lift to drag ratio in the flight condition based on the bio-mimicry. The CAD model and fabricated morphing wing in geometry scale of 20 cm chord and a 36 cm wing-span, with aluminum material ribs divided into 6 sections. Each section was able to rotate approximately 6 degrees without causing a discon-tinuity in the wing surface and also in order avoid the control surface based on the bio mimicry the morphing wing was designed and tested. DC-motor located at main spar with the two equal gear ratio the rib section used to morph the wing through the linear mechanical linkages. The aluminum ribs section are made through the EDM-Wire cut machining process for capable to actuate the morphing wing. In each sec-tion morphing wing can able provide up to 10 percent variation in the symmetrical airfoil to the cambered airfoil. The experimental test of the morphing was carried out in the cascade tunnel by force balancing method and the lift and drag output are compared.

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31

James, Polagnagu, Kotresh Gaddikeri, Byji Varughese, and M. Subba Rao. "Realisation of Shear Flow at Crucial Spar Splice Joints of Composite Wing in Idealised Wing Test Box." Procedia Engineering 86 (2014): 718–26. http://dx.doi.org/10.1016/j.proeng.2014.11.090.

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Ajaj, R. M., M. I. Friswell, W. G. Dettmer, A. T. Isikveren, and G. Allegri. "Roll control of a MALE UAV using the adaptive torsion wing." Aeronautical Journal 117, no. 1189 (March 2013): 299–314. http://dx.doi.org/10.1017/s0001924000008009.

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Abstract This paper assesses the feasibility of the Adaptive Torsion Wing (ATW) concept to replace conventional ailerons and enhance the manoeuvrability of a MALE UAV. The ATW concept is a thin-walled closed section two-spar wingbox whose torsional stiffness can be adjusted through the chord-wise position of the front and rear spar webs. The reduction in torsional stiffness allows external aerodynamic loads to induce aeroelastic twist that can be used as a function of the flight conditions to obtain a desired roll control authority. Modelling of the concept was performed using a conceptual design tool developed in MATLABTM. The variation of structural figures of merit are evaluated and discussed. Finally, an MDO study was performed to have in-depth assessments of the potential benefits of the ATW in replacing ailerons and providing sufficient roll control.

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Bolinches, M., A. J. Keane, A. I. J. Forrester, J. P. Scanlan, and K. Takeda. "Design, analysis and experimental validation of a morphing UAV wing." Aeronautical Journal 115, no. 1174 (December 2011): 761–65. http://dx.doi.org/10.1017/s0001924000006503.

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Abstract The design of wings with morphing capabilities is known to give aerodynamic benefits. These aero-dynamic benefits come from both the use of hinge-less surfaces and the greater adaptability to flight conditions. This paper describes the structural design of a twisting wing to be used for an unmanned air vehicle (UAV) and presents finite element analysis and experiment results. This is part of a research project carried out at the University of Southampton in which one of the goals is to compare different novel wing designs and technologies to determine which one of them gives the best performance. The twisting capability provides roll control without hinged surfaces hence providing aerodynamic improvement. The wing is manufactured using polystyrene foam and is cut out of block of this material using a hot wire machine. In order to link this foam structure to a main spar, ABS plastic inserts were manufactured using a 3D printer. The mechanisms used to actuate the wing are also made from this material. A full scale UAV wing has been manufactured and tested in order to compare with FEA results.

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Dr. S. Elangovan et al.,, Dr S. Elangovan et al ,. "Design and Analysis of Aircraft Wing Spar with Different Materials using ANSYS." International Journal of Mechanical and Production Engineering Research and Development 9, no. 3 (2019): 613–18. http://dx.doi.org/10.24247/ijmperdjun201966.

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Anton, Steven R., Alper Erturk, and Daniel J. Inman. "Multifunctional Unmanned Aerial Vehicle Wing Spar for Low-Power Generation and Storage." Journal of Aircraft 49, no. 1 (January 2012): 292–301. http://dx.doi.org/10.2514/1.c031542.

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Aston, G., and F. W. Williams. "Simplified methods for the buckling analysis of composite multi-spar wing boxes." Composite Structures 28, no. 2 (January 1994): 215–23. http://dx.doi.org/10.1016/0263-8223(94)90050-7.

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Bourchak, M., R. M. Ajaj, E. I. Saavedra Flores, M. Khalid, and K. A. Juhany. "Optimum design of a PID controller for the adaptive torsion wing." Aeronautical Journal 119, no. 1217 (July 2015): 871–89. http://dx.doi.org/10.1017/s0001924000010964.

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AbstractThis paper presents the optimum design of a PID controller for the Adaptive Torsion Wing (ATW) using the genetic algorithm (GA) optimiser. The ATW is a thin-wall, two-spar wingbox whose torsional stiffness can be adjusted by translating the spar webs in the chordwise direction inward and towards each. The reduction in torsional stiffness allows external aerodynamic loads to deform the wing and maintain its shape. The ATW is integrated within the wing of a representative UAV to replace conventional ailerons and provide roll control. The ATW is modelled as a two-dimensional equivalent aerofoil using bending and torsion shape functions to express the equations of motion in terms of the twist angle and plunge displacement at the wingtip. The full equations of motion for the ATW equivalent aerofoil were derived using Lagrangian mechanics. The aerodynamic lift and moment acting on the aerofoil were modelled using Theodorsen’s unsteady aerodynamic theory. The equations of motion are then linearised around an equilibrium position and the GA is employed to design a PID controller for the linearised system to minimise the actuation power require. Finally, the sizing and selection of a suitable actuator is performed.

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Al-Arabe, A. M. F., E. V. Markova, and T. V. Denisova. "OPTIMIZATION OF THE ASSEMBLY OF THE FRONT WING SPAR OF A TRANSPORT AIRCRAFT." RUSSIAN ELECTRONIC SCIENTIFIC JOURNAL 37, no. 3 (October 1, 2020): 8–25. http://dx.doi.org/10.31563/2308-9644-2020-37-3-8-25.

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This article is to optimize the assembly of the front wing spar of a transport aircraft. Particular attention is paid to reducing the complexity, assembly cycle and other parameters that determine the efficiency of the process. According to experts, the domestic civil aviation fleet today is characterized as obsolete both morally and physically. The most important advantage of new products is the increased resource provided by the use of new materials, new design and technological solutions. One of such solutions is the widespread use of bent profiles from promising aluminum sheet materials. The presence of a cladding layer, a more uniform structure provides an increased resource. An important part of the production process of an aircraft manufacturing enterprise is assembly work, which largely determines the quality of the product. The main ways to increase the efficiency of assembly work, preparation of production, reduce costs is to increase the manufacturability of products, the creation of new means of production, the wider use of mechanization and automation, as well as the selection of optimal technological processes and means of equipping assembly work in technological design.

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Wong, B. Stephen, Xin Wang, Chen Ming Koh, Chen Guan Tui, Chingseong Tan, and Jian Xu. "Crack detection using image processing techniques for radiographic inspection of aircraft wing spar." Insight - Non-Destructive Testing and Condition Monitoring 53, no. 10 (October 1, 2011): 552–56. http://dx.doi.org/10.1784/insi.2011.53.10.552.

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McKenna, Vincent, Yan Jin, Adrian Murphy, Michael Morgan, Rao Fu, Xuda Qin, Caroline McClory, Rory Collins, and Colm Higgins. "Cost-oriented process optimisation through variation propagation management for aircraft wing spar assembly." Robotics and Computer-Integrated Manufacturing 57 (June 2019): 435–51. http://dx.doi.org/10.1016/j.rcim.2018.12.009.

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Jacob Olaitan, AKINDAPO, JOHNSON-ANAMEMENA Nnaemeka, and GARBA Danladi King. "Graphite-epoxy Composite Design for Aircrcaft Wing Spar Using Computational Techniques – Part I." American Journal of Mechanical Engineering 5, no. 4 (August 26, 2017): 117–27. http://dx.doi.org/10.12691/ajme-5-4-2.

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42

Belabbaci, Madjid, Zakaria Imine, Tewfik Ghomari, and Bachir Imine. "Mechanical properties of an aluminium-carbon fiber composite for aircraft wing spar applications." Indian Journal of Science and Technology 14, no. 22 (June 15, 2021): 1905–13. http://dx.doi.org/10.17485/ijst/v14i22.51.

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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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Yang, Kang, Liguo Zhang, Shude Ji, Yumei Yue, and Wang Ji. "Static Testing and Analysis of Composite Wing of a Two-Seater Aircraft Powered by Li-Ion Battery Electric Propulsion." Advanced Composites Letters 25, no. 6 (November 2016): 096369351602500. http://dx.doi.org/10.1177/096369351602500601.

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The present paper studied the strength and deformation characteristics of a composite wing of a two-seater aircraft powered by Li-ion battery electric propulsion. In order to get the airworthiness certificate, the static testing is indispensable. The primary wing structure component includes upper and lower skins, leading edge, trailing edge, a root rib and main spar. The main purpose of static testing is to examine the bending strength of the wing. The testing results are in good agreement with the FE analysis results and the bending strength of wing is strong enough to support the limit loads (the maximum loads to the expected in service) without detrimental and permanent deformation, and without failure for at least 3s under the ultimate loads (limit loads multiplied by prescribed factors of safety), which meets ASTM F2245-11(Standard Specification for Design and Performance of a Light Sport Airplane) enough.

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Sun, Shiyong, Rui Yang, Zibin Yan, and Wei Qian. "Effect of Interfacial Debonding on the Strength of Composite Structure-Similarity Scale Model for the Wing-Box." International Journal of Aerospace Engineering 2015 (2015): 1–8. http://dx.doi.org/10.1155/2015/473926.

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Based on the wing-box structure, a model was established to analyze the strength of the scale model for the composite wing. Firstly, different failure criteria were set to determine damage onset of the components. The continuum damage variables were adopted in the stiffness degradation rule. Secondly, the interface elements were placed along the interface between the beam flange and the skin to investigate the effects of bonding strength on the ultimate load-carrying capacity of the wing-box. The failure modes of the wing-box structure were studied by using the nonlinear finite element method. The effect of flange’s width on the strength of wing-box was discussed based on the prediction method. The results indicated that the ultimate load-carrying capacity varied distinctly with the change of flange’s width. However, the bonding strength had limited effect on the model strength as the flange’s width increases to the critical value. The research methods and results of the study can serve as reference for the strength analysis on the scale model of composite wing as well as the determination of principles adopted in the design of the scale model for wing spar.

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Liu, Zhiwei, Xiaojun Yan, Mingjing Qi, Dawei Huang, Xiaoyong Zhang, and Liwei Lin. "Electrostatic flapping-wing actuator with improved lift force by the pivot-spar bracket design." Sensors and Actuators A: Physical 280 (September 2018): 295–302. http://dx.doi.org/10.1016/j.sna.2018.07.054.

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Fleuret, Clément, Anne-Sophie Andreani, Éric Lainé, Jean-Claude Grandidier, Sylvain L’héritier, and Anne-Laure Gorge. "Complex wing spar design in carbon fiber reinforced composite for a light aerobatic aircraft." Mechanics & Industry 17, no. 6 (2016): 614. http://dx.doi.org/10.1051/meca/2016032.

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Xia, Tianxiang, Weixing Yao, Lipu Xu, and Jun Zou. "Metamodel-based optimization of the bolted connection of a wing spar considering fatigue resistance." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 230, no. 5 (August 10, 2015): 805–14. http://dx.doi.org/10.1177/0954410015598792.

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Wang, Ya, and Daniel J. Inman. "Experimental Validation for a Multifunctional Wing Spar With Sensing, Harvesting, and Gust Alleviation Capabilities." IEEE/ASME Transactions on Mechatronics 18, no. 4 (August 2013): 1289–99. http://dx.doi.org/10.1109/tmech.2013.2255063.

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Bennett, S. Christopher. "New interpretation of the wings of the pterosaur Rhamphorhynchus muensteri based on the Zittel and Marsh specimens." Journal of Paleontology 89, no. 5 (September 2015): 845–69. http://dx.doi.org/10.1017/jpa.2015.68.

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AbstractThe Zittel wing of Rhamphorhynchus muensteri is reinterpreted as preserving negative impressions of closely spaced broad flat actinofibrils that were replaced by calcite but were prepared away by the specimen’s finder. The Marsh specimen preserves positive impressions of the dorsal and ventral surfaces of the wing, which show that the skin was smooth with fine wrinkles and that actinofibrils were not on the wing surface. Based on comparisons of those specimens, the dactylopatagium consisted of dorsal and ventral skins of epidermis and dermis surrounding a common hypodermis core, and keratinous actinofibrils developed in place within the dorsal epidermis adjacent to a layer of linear collagen fibers in the dorsal dermis. The actinofibrils and linear collagen fibers together formed the main functional structure of the dactylopatagium. That structure made the dactylopatagium somewhat stiff and essentially inextensible so that it folded up along discrete fold lines that probably were genetically determined. A pneumatic retrophalangeal wedge behind the antebrachium through at least wing phalanx 3 streamlined the transition between the thick wing spar and thin patagium.

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