Structural Deformation and Stress Analysis of Aircraft Wing by Finite Element Method

Rabbey, M. Fazlay; Rumi, Anik Mahmood; Nuri, Farhan Hasan; Monerujjaman, Hafez M.; Hassan, M

doi:10.4028/www.scientific.net/amr.906.318

Cited by 4 publications

(3 citation statements)

References 1 publication

(1 reference statement)

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“…The applied computational techniques based on finite element method and achieved results have been presented in dozens of papers or monographs issued in last several years; among them newest are described in Refs. [11][12][13] In particular, the approaches and examples proposed for solutions regarding parameterization and optimization of FEMs are innovative and useful Refs. [14][15][16][17]…”

Section: Introduction To the Problemmentioning

confidence: 99%

Finite element analysis of the underslung carrier rocket effect on stress and strain distribution in a structure of the MiG-29 aircraft

Olejnik

Kachel

Zalewski

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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The paper presents selected aspect of the analytical-conceptual research project entitled: Airborne-Rocket Launch System for Delivering Satellite Payloads into Low Earth Orbit – Feasibility Study. The aim of the project is to conduct series of aerodynamic, strength, and aeroelastic simulations of Polish aging combat aircraft (Mig-29 and Su-22) to explore applicability of both fighters as an airborne platform for carrying out carrier rockets with a detachable satellite payload. This work presents exemplary analyses in the area of airframe loads and structural strength and deformability of MiG-29 for predicted operational variants with carrier rockets put to the hardpoints under fuselage. The numerical simulations were conducted for a structural discrete model of the aircraft prepared for finite element analysis in MSC Software. Model development involved such aspects as precise discretization of geometric model, declaration of material constants, identification of structural properties, introduction of suitable merging connections for included airframe assemblies, and final validation of model mass and stiffness. The model was analyzed in MSC Nastran software with application of linear “Statics” solution. External flight loads introduced into the model were calculated for specific points of the flight envelope—the highest values of load factor were taken into consideration ( n=9). The counterpart aerodynamic force distribution in a form of a set of equivalent lumped forces was calculated. Then, the aerodynamic and weight loads were added to the model as a set of forces applied to specific structural nodes. Additionally, weights of applicable carrier rockets were taken into account as concentrated forces applied to under-fuselage suspension hardpoints. Calculations were performed for several rockets of mass values between 250 and 1200 kg. Parametric dependencies were investigated as an effect of missile mass and size on stress and strain distribution over the whole structure. The areas of stress cumulations were identified. On the basis of static structural deformation, maximum wing tip displacements were assessed.

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Section: Introduction To the Problemmentioning

confidence: 99%

Finite element analysis of the underslung carrier rocket effect on stress and strain distribution in a structure of the MiG-29 aircraft

Olejnik

Kachel

Zalewski

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The blade structure and aerodynamics are the critical parameters for any aircraft [1], in our research these parameters are considered for the purpose of design initiation. Design aspects of various composite structures and wind turbine blades have been observed [2][3] which are used for CAD modeling of the propeller blade carried out in this research.…”

Section: Introductionmentioning

confidence: 99%

Design and Structural Mechanics of a Modified Wood – Composite Integrated Propeller Blade

Jangam¹,

Verma²,

Ramesha³

2021

Proceedings of the Fist International Conference on Advanced Scientific Innovation in Science, Engineering and Technology, ICA

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Aircraft Propellers are the key components of turboprop type engines which are used for thrust generation for the aircraft. Metallic propellers which are in use for long time are being replaced by composite type equivalent propeller due to their high specific strength and modulus. Composite material is used in combination with engineered wooden core offers refined dynamic characteristics with enhanced damping as well as greater stiffness Better damping characteristics reduces the vibrations due to external excitation sources resulting in higher fatigue life. In this study, effort will be made to design and analyze a composite bladed propeller for a typical light transport aircraft. Scope of the work in this project includes design, modeling and detailed finite element analysis of an integrated composite-engineered wood propeller blade. The structural analysis includes static structural and modal analysis for induced stresses, deformations, its natural frequencies and associated mode shapes.

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“…The finite element method can be used to analyze stress in certain aircraft components, e.g. wings [11,12]. FEM can also be used for an aeroelasticity analysis of an aircraft [13,14].…”

Section: Introductionmentioning

confidence: 99%

Numerical analysis of the support platform for an unmanned aerial vehicle

Czyż¹,

Suwała²,

Karpiński

et al. 2021

J. Phys.: Conf. Ser.

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The study investigates a thin-walled support platform for an unmanned aerial vehicle, i.e. aluminum beams connected by flat bars and angle irons. The construction is a kind of frame for a propulsion unit of the designed aircraft which is a combination of a multi-copter and a gyrocopter. This construction was tested for various load patterns to investigate the stresses and strains its profiles are connected. The load patterns correspond to different operation modes of the propulsion system, and the finite element method (FEM) and the SolidWorks software were used for the numerical calculations. The research was done for elastic operation of the individual components of the support platform. The analysis enabled to verify the state of stresses on the critical spots of the construction and to develop a construction for ground and flight tests to verify the correct operation of the propulsion control system and optimize its operation in different flight states.

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Structural Deformation and Stress Analysis of Aircraft Wing by Finite Element Method

Cited by 4 publications

References 1 publication

Finite element analysis of the underslung carrier rocket effect on stress and strain distribution in a structure of the MiG-29 aircraft

Finite element analysis of the underslung carrier rocket effect on stress and strain distribution in a structure of the MiG-29 aircraft

Design and Structural Mechanics of a Modified Wood – Composite Integrated Propeller Blade

Numerical analysis of the support platform for an unmanned aerial vehicle

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