Structural Optimization of Internal Structure of Aircraft Wings with Curvilinear Spars and Ribs

De, Shuvodeep; Jrad, Mohamed; Kapania, Rakesh K.

doi:10.2514/1.c034818

Cited by 20 publications

(11 citation statements)

References 36 publications

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“…It can also include topological optimization of the structure. For example, optimal rib and spar distribution were investigated by Stanford et al [12,13] while De et al [14] and Zhao and Kapanta [15] investigated topology optimization using curvilinear spars and ribs.…”

Section: Subscriptsmentioning

confidence: 99%

Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Sodja

Werter

Breuker

2021

Journal of Aircraft

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Section: Subscriptsmentioning

confidence: 99%

Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Sodja

Werter

Breuker

2021

Journal of Aircraft

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“…Verification and Validation is a very important and essential field where the computational models [1][2][3][4][5][6][7][8][9][10][11][12][13][14] are tested for their credibility. Computer simulations are used to predict real-life outcomes, control vehicles precisely, design light-weight structures etc.…”

Section: Assumptions In Computational Modelsmentioning

confidence: 99%

Verification and Validation in Computational Mechanics

De¹

2022

Preprint

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Decades ago, when computational was expensive and limited, the structural design was mostly performed by hand calculations using simple mathematical models. For example, it was a common practice to design a structure as complex as the wing of an aircraft by simple beam analysis. However, ever since the classic paper by Turner et al., due to a rapid increase in computational, more complex mathematical models are being used to simulate the physical behavior of complex structural components. To solve intractable problems unsolvable by hand calculations, numerical techniques like Finite Element Analysis (FEA), Computational Fluid Dynamics (CFD), Finite Difference Method etc. are being employed. In fact, the availability of these methods has led to the development of an entirely new area of research known as Multidisciplinary Design Optimization (MDO) where various disciplines are considered in an optimization problem. The most important question while using a mathematical model to represent practical industrial problems is to what extent these models represent the real-life situation. Computational models are always built on upon assumptions. Simply at looking at the simulation outcomes i.e. the graphical and numerical results, it is often very difficult to ensure if the underlying assumption holds and that the results are reliable. This has led to the development of another field of research known as Verification and Validation (called V&V in short).

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“…Composite structures are increasingly being used for such applications due to their high strength and stiffness to weight ratios. Additionally, such structures when used in combination with curvilinear stiffeners provide an enhanced design space due to the possibility of tailoring geometric curvature, placement, orientation and material characteristics [3,4].…”

Section: Introductionmentioning

confidence: 99%

Free Vibration analysis of Curvilinearly Stiffened Composite plates with an arbitrarily shaped cutout using Isogeometric Analysis

Devarajan¹

2021

Preprint

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This paper focuses on the isogeometric vibration analysis of curvilinearly stiffened composite panels. The stiffness matrices and the mass matrices are derived using the first-order shear deformation theory (FSDT). The present method models the plate and the stiffener separately, which allows the stiffener element nodes to not coincide with the plate shell-element nodes. The stiffness and mass matrices of a stiffener are transformed to those of the plate through the displacement compatibility conditions at the plate-stiffener interface by interpolation using NURBS basis functions. Cutouts are modeled using a single NURBS patch generated by creating a ruled surface between two curves. The proposed formulation is first validated by comparing it with available literature. The effects of width-to-thickness ratio, fiber orientation, ply layups, shape and size of the cutouts and the boundary conditions on the response of stiffened composite plates are then analyzed and the numerical results are used to derive useful conclusions.

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Structural Optimization of Internal Structure of Aircraft Wings with Curvilinear Spars and Ribs

Cited by 20 publications

References 36 publications

Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Verification and Validation in Computational Mechanics

Free Vibration analysis of Curvilinearly Stiffened Composite plates with an arbitrarily shaped cutout using Isogeometric Analysis

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