Analysis of wing flexure deformation based on ANSYS

Zhang, Xueyan; Zhao, Yan; Si, Fan

doi:10.1109/plans.2018.8373381

Cited by 5 publications

(4 citation statements)

References 4 publications

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“…The ribs are used to retain the geometrical shape of the wing section with the aim of distributing the external loads evenly on the wing skin and thereby prevent undesired wing deformation. The stringers are applied in the design to enhance the wing's rigidity (45) .…”

Section: Fem Based On Tomentioning

confidence: 99%

Wing component allocation for a morphing variable span of tapered wing using finite element method and topology optimisation – application to the UAS-S4

et al. 2021

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This 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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Section: Fem Based On Tomentioning

confidence: 99%

Wing component allocation for a morphing variable span of tapered wing using finite element method and topology optimisation – application to the UAS-S4

et al. 2021

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“…Additionally, the wing sweeps angle of an A320's is only 25 degrees. On the other hand, few reports from Zhang et al [1] and Vani, Reddy, Prasad, & Shekar [3] are characterized by the establishment of a wing model based on their objectives. This can be seen when Zhang et al, [1] established a wing based on a large-aspect-ratio prototypical.…”

Section: Wing Model Establishmentmentioning

confidence: 99%

“…On the other hand, few reports from Zhang et al [1] and Vani, Reddy, Prasad, & Shekar [3] are characterized by the establishment of a wing model based on their objectives. This can be seen when Zhang et al, [1] established a wing based on a large-aspect-ratio prototypical. This is because to evaluate the wing flexural rigidity distortion, and it is more efficient to analyze a large-aspect-ratio wing model since large deflection can be attained easily from that model.…”

Section: Wing Model Establishmentmentioning

confidence: 99%

“…Finally, the structural analysis of stress, strain, bending, torsion, and deformation data of the wing acquired from end to end transient structural analysis, which is smeared for optimization and improvement to the design of the aircraft for the future. A fatal accident can occur at the wing part of an airplane due to the influence of the complicated external flight environment, which will result in the pressure of the upper and lower wing surface with variable aerodynamic stream arenas around the wing [1].…”

Section: Introductionmentioning

confidence: 99%

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Modelling and Structural Analysis of Three-Dimensional Wing

Zakuan¹,

Aabid²,

Khan³

2019

IJEAT

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This paper attempts to discover the structural behavior of the wing imperiled to flowing loads through the voyage. The study uses a method in the form of finite element analysis of wing flexure distortion. As a first step, two wing models are established by captivating factual features, wing assembly, and plan principles into consideration. The gathering wing prototypical entails of tinny membrane, two poles, and multi-ribs. Two spars which consist of primary and secondary spars. NACA 23015 is chosen as the baseline aerofoil as this is identical alike to the tailored aerofoil being castoff in Airbus A320. Two rods mostly endure the twisting moment and trim strength, which is finished of titanium contaminant to ensure enough inflexibility. The covering and wing spars are made of aluminum amalgam to lessen the structural heaviness. Later, a static structural investigation is smeared, and the overall distortion, comparable elastic strain, and corresponding VonMises tension are obtained to analyze the mechanical behavior of the wing. Furthermore, modal investigation is being supported out to determine the natural rate of recurrence, as well as the modal shape of the three orders, which are acquired through the pre-stress modal analysis. The outcomes of the modal scrutiny aid engineers decrease excitation on the natural occurrences and avert the wing from the flurry. In view of the results obtained from the study, designers can emphasize consolidation and analysis the stress attentiveness range and huge distortion area. In conclusion, the recreation consequences indicate that the arrangement is possible and improves the information grade of the lifting surface.

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Structural analysis of three-dimensional wings using finite element method

Aabid

Zakuan

Khan

et al. 2021

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Analysis of wing flexure deformation based on ANSYS

Cited by 5 publications

References 4 publications

Wing component allocation for a morphing variable span of tapered wing using finite element method and topology optimisation – application to the UAS-S4

Wing component allocation for a morphing variable span of tapered wing using finite element method and topology optimisation – application to the UAS-S4

Modelling and Structural Analysis of Three-Dimensional Wing

Structural analysis of three-dimensional wings using finite element method

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