Frequency Analysis of Aircraft Wing Using FEM

Basutkar, Akhil; Baruah, Kunal; Kudari, S. K.

doi:10.1007/978-981-15-1124-0_46

Cited by 3 publications

(2 citation statements)

References 4 publications

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“…In the paper, the methods of the equivalence of boundary conditions in the FE model were described. Their basis is the replacement of boundary condition, bond, constraint, Similar examples for the application of equivalence methods could be found in aviation (e.g., in analysis of wings) [37][38][39][40]. These include static wing deformation, the analysis of vibration behavior, or the determination of aero-elastic stability limits of wings with regard to flutter.…”

Section: Discussionmentioning

confidence: 99%

Stiffness Estimation and Equivalence of Boundary Conditions in FEM Models

et al. 2021

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The paper deals with methods of equivalence of boundary conditions in finite element models that are based on finite element model updating technique. The proposed methods are based on the determination of the stiffness parameters in the section plate or region, where the boundary condition or the removed part of the model is replaced by the bushing connector. Two methods for determining its elastic properties are described. In the first case, the stiffness coefficients are determined by a series of static finite element analyses that are used to obtain the response of the removed part to the six basic types of loads. The second method is a combination of experimental and numerical approaches. The natural frequencies obtained by the measurement are used in finite element (FE) optimization, in which the response of the model is tuned by changing the stiffness coefficients of the bushing. Both methods provide a good estimate of the stiffness at the region where the model is replaced by an equivalent boundary condition. This increases the accuracy of the numerical model and also saves computational time and capacity due to element reduction.

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Section: Discussionmentioning

confidence: 99%

Stiffness Estimation and Equivalence of Boundary Conditions in FEM Models

et al. 2021

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“…Для забезпечення необхідної точності визначення навантажень потрібно розглянути достатню кількість тонів власних коливань конструкції. У інженерній практиці рекомендується враховувати всі суттєві тони до частоти 40 -60 Hz [17], але часто досліджують і значно більший діапазон частот (до 300 Hz) [18]. Однак тривалість модального аналізу в такому випадку буде досить значною (зростатиме за експонентою).…”

Section: стаціонарне навантаження у разі горизонтального польоту;unclassified

Influence of flight mode on loads from turbulent air

Hevko¹,

Bondar²

2022

MGS

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This paper investigated the influence of altitude and flight speed on the loads arising on the elastic wing of a turbojet aircraft of conventional layout, which falls into turbulent conditions. The aircraft structure is modeled by elastic beams with appropriate weight and stiffness distribution. Performed a modal analysis of the aircraft design and examined the influence of the number of calculated tones own oscillations on the loading of an aircraft wing. Aerodynamic forces and moments are determined by the dipole lattice and constant pressure method (DLM/CPM). Non-stationary characteristics are also taken into account, as required by certification specification. Determining the effect of flight speed showed the need to consider both the minimum and maximum speeds, because at minimum speed the end zone of the wing is loaded more, and at the cruise speed ‒ the root section. When analyzing the effect of flight altitude on the load, determined that the maximum values of transverse force and bending moment occur when flying at minimum altitude, and the torque on the wing reaches the maximum value at altitudes with the maximum Mach number. Separately highlighted loads of aircraft wing at horizontal balanced flight. Also showed that the speed of flight, namely the Mach number, significantly affects the torque that occurs on the wing.

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Optimizing Structural Integrity of Fighter Aircraft Wing Stations: a Finite Element Analysis Approach

Haider Bhutta

2024

ings

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Modern fighter aircraft are equipped with multiple stations on the fuselage and under the wings to accommodate various external stores, both jettisonable and non-jettisonable. Each configuration undergoes airworthiness certification, including structural analysis of individual stations within the carriage flight envelope. This study focuses on the structural analysis of a fighter aircraft wing station within this specified envelope. To perform this analysis, the wing station is extracted from the comprehensive global wing model, creating a sub-model with equivalent stiffness properties. Utilizing ANSYS Workbench®, Finite Element Analysis (FEA) is conducted for critical load cases to determine the Factor of Safety (FoS). The initial analysis reveals that the wing station has an FoS of 1.2 under the maximum design load. Prestressed modal and buckling analyses indicate a 10% increase in stiffness due to stress-stiffening effects. To further enhance load-carrying capacity, parametric design changes are introduced. Increasing the bolt diameter from 8 mm to 10 mm raises the FoS to 1.33, resulting in an 8% increase in the maximum load-carrying capacity of the wing station. This comprehensive approach, employing FEA, ensures the wing’s structural integrity under static load conditions within the carriage envelope. The study's findings support the wing station's enhanced performance and contribute to safer and more efficient aircraft operations.

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Frequency Analysis of Aircraft Wing Using FEM

Cited by 3 publications

References 4 publications

Stiffness Estimation and Equivalence of Boundary Conditions in FEM Models

Stiffness Estimation and Equivalence of Boundary Conditions in FEM Models

Influence of flight mode on loads from turbulent air

Optimizing Structural Integrity of Fighter Aircraft Wing Stations: a Finite Element Analysis Approach

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