Topology Optimization of a Reinforced Wing Box for Enhanced Roll Maneuvers

Gomes, Alexandra A.; Suleman, Afzal

doi:10.2514/1.23028

Cited by 31 publications

(21 citation statements)

References 20 publications

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“…The SIMP method has also been used to optimize individual ribs (Krog et al 2004). The spectral level set method has been applied to optimize the reinforcement of a wing upper skin to maximize aileron reversal dynamic pressure (Gomes and Suleman 2008). Topology optimization has also been applied to the design of plate-like wings, through varying the thickness of the plate (Stanford and Beran 2011;De Leon et al 2012) or varying the distribution of different materials (Stanford and Ifju 2009).…”

Section: Topology Optimization In Aircraft Designmentioning

confidence: 99%

“…The application of the level set method for wing structure optimization has been limited to local regions (Gomes and Suleman 2008) or did not account for the aerostructural coupling (James and Martins 2012). In our previous work, the level set method was used to optimize the internal structure of a 3D wing box and included the effect of aerostructural interaction through coupled analysis and coupled sensitivities .…”

Section: Level Set Topology Optimizationmentioning

confidence: 99%

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Coupled aerostructural topology optimization using a level set method for 3D aircraft wings

Dunning

Stanford

Kim

2014

Struct Multidisc Optim

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The purpose of this work is to develop a level set topology optimization method for an unstructured threedimensional mesh and apply it to wing box design for coupled aerostructural considerations. The paper develops fast marching and upwind schemes suitable for unstructured meshes, which make the level set method robust and efficient. The method is applied to optimize a representative wing box internal structure for the NASA Common Research Model. The objective is to minimize the total compliance of the wing box. The trim condition that aerodynamic lift must balance the total weight of the aircraft is enforced by allowing the root angle of attack to change. The adjoint method is used to obtain the coupled shape sensitivities required to perform aerostructural optimization of the wing box. Optimum solutions for several aerodynamic and body force load cases, as well as a ground load case, are presented.

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Section: Topology Optimization In Aircraft Designmentioning

confidence: 99%

Section: Level Set Topology Optimizationmentioning

confidence: 99%

Coupled aerostructural topology optimization using a level set method for 3D aircraft wings

Dunning

Stanford

Kim

2014

Struct Multidisc Optim

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“…This corresponds to maximize the speed at which the aileron ceases to provide additional lift. Gomes and Suleman [42] tried to maximize the aileron reversal speed of a wing torsion box by reinforcing its upper skin. Chen et al [24] optimized the roll rate by replacing the existing wing spars with an adaptive-structure.…”

Section: Reviews Of Previous Workmentioning

confidence: 99%

“…Especially a good fit of the lift-curve slope data in the limited range 7 6 10 2 Re 10 2     is given by Eqn. (42). Results from XFOIL are compared with the 86 experimental data, which is generated directly from Eqn.…”

Section: Two-dimensional Airfoil Characteristics With/without Closedmentioning

confidence: 99%

Enhancement of Roll Maneuverability Using Post-Reversal Design. Part I: Nonlinear Analysis

Li¹,

Hodges²

2010

51st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…5 The spectral level set method has been applied to optimize the reinforcement of a wing upper skin to maximize aileron reversal dynamic pressure. 6 Topology optimization has also been applied to the design of plate-like wings, through varying the thickness of the plate 7,8 or varying the distribution of different materials. 9 The motivation for this work is to consider the entire 3D wing box space as the design domain for topology optimization to explore novel configurations for the entire wing box structure.…”

Section: Introductionmentioning
confidence: 99%

Aerostructural Level Set Topology Optimization for a Common Research Model Wing
Dunning
¹
,
Stanford
²
,
Kim
³

2014
10th AIAA Multidisciplinary Design Optimization Conference
17
0
19
0
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The purpose of this work is to use level set topology optimization to improve the design of a representative wing box structure for the NASA common research model. The objective is to minimize the total compliance of the structure under aerodynamic and body force loading, where the aerodynamic loading is coupled to the structural deformation. A taxi bump case was also considered, where only body force loads were applied. The trim condition that aerodynamic lift must balance the total weight of the aircraft is enforced by allowing the root angle of attack to change. The level set optimization method is implemented on an unstructured three-dimensional grid, so that the method can optimize a wing box with arbitrary geometry. Fast matching and upwind schemes are developed for an unstructured grid, which make the level set method robust and efficient. The adjoint method is used to obtain the coupled shape sensitivities required to perform aerostructural optimization of the wing box structure. NomenclatureA = sensitivity factor for angle of attack a = vector of Doublet Lattice Method (DLM) box areas b = vector defining influence of wing deformed shape on lift C = compliance of the structure c p = pressure coefficient vector D = aerodynamic influence coefficient matrix E = material property tensor e = number of elements attached to a node f a = aerodynamic load vector f g = body force load vector f t = total load vector g = acceleration due to gravity h = element edge length i, j = indices K = global structural stiffness matrix K c = stiffness matrix of an element cut by the boundary K E = stiffness matrix of a finite element k = iteration number 1 Research Scholar, peter.d.dunning@nasa.gov, AIAA Member. 2 Research Aerospace Engineer, Aeroelasticity Branch, bret.k.stanford@nasa.gov, AIAA Member. 3 Senior Lecturer, Department of Mechanical Engineering, h.a.kim@bath.ac.uk, AIAA Senior Member. Downloaded by PURDUE UNIVERSITY on July 30, 2015 | http://arc.aiaa.org | 2 L = total lift force L c = lift force from built-in twist and camber Lα = lift force from unit angle of attack N = load factor n = unit normal vector p = adjoint state vector q = dynamic pressure Q = aerodynamic stiffness matrix S = force transfer matrix T = displacement transfer matrix t = fictitious time variable u = displacement field or vector V n = velocity function v = virtual displacement W b = wing box weight W c = fixed aircraft weight w = downwash dependent on deformed wing shape w c = constant downwash from built-in camber x = point in the design domain z = column vector of 1's α = angle of attack β c = volume of a cut element that lies inside the structure β E = volume of an element γ = small number Γ = structural boundary Γ D = part of boundary subject to displacement boundary conditions Γ N = part of boundary subject to aerodynamic loads Γ 0 = part of boundary free from boundary conditions and aerodynamic loads Δt = time step ε = strain tensor θ = arbitrary vector (shape derivative auxiliary variable) ρ = material density φ = implicit function Ω ...

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Topology Optimization of a Reinforced Wing Box for Enhanced Roll Maneuvers

Cited by 31 publications

References 20 publications

Coupled aerostructural topology optimization using a level set method for 3D aircraft wings

Coupled aerostructural topology optimization using a level set method for 3D aircraft wings

Enhancement of Roll Maneuverability Using Post-Reversal Design. Part I: Nonlinear Analysis

Aerostructural Level Set Topology Optimization for a Common Research Model Wing

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