Multidisciplinary multifidelity optimisation of a flexible wing aerofoil with reference to a small UAV

Berci, Marco; Торопов, В. В.; Hewson, Robert; Gaskell, Philip

doi:10.1007/s00158-014-1066-2

Cited by 31 publications

(14 citation statements)

References 30 publications

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“…It is interesting to note that the decrease of the aerodynamic critical pressure with the growth of the fiber orientations (the angle-ply configuration is considered) is almost insensitive to the form of boundary condition and the orthotropy ratio A lot of papers studied the influence of the fiber orientations, stacking sequences, and fiber mechanical properties on critical aerodynamic speed [21,[59][60][61][62][63][64][65][66][67][68]. Hertz et al [69] called the above process as aeroelastic tailoring, i.e., the design that makes use of the directional properties of fibrous composite materials in wing skins and orients these materials in optimum directions-see also References [70][71][72][73][74][75][76][77][78][79][80][81][82][83][84][85][86][87][88]. In different papers the dominant role of the bending stiffness D11 is observed.…”

Section: Composite Materialsmentioning

confidence: 99%

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

2019

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Aeroelastic optimization has become an indispensable component in the evaluation of divergence and flutter characteristics for plated/shell structures. The present paper intends to review the fundamental trends and dominant approaches in the optimal design of engineering constructions. A special attention is focused on the formulation of objective functions/functional and the definition of physical (material) variables, particularly in view of composite materials understood in the broader sense as not only multilayered laminates but also as sandwich structures, nanocomposites, functionally graded materials, and materials with piezoelectric actuators/sensors. Moreover, various original aspects of optimization problems of composite structures are demonstrated, discussed, and reviewed in depth.

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Section: Composite Materialsmentioning

confidence: 99%

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

2019

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“…[14] used a finite element (FE) model to optimize wing stiffnesses with aeroelastic constraints. [4,6] optimized a flexible wing airfoil using a 2D model and considering flutter and divergence. [15] used bacterial foraging optimization for the aeroelastic tailoring of a composite wing.…”

Section: Related Workmentioning

confidence: 99%

Composite stacking sequence optimization for aeroelastically tailored forward-swept wings

Bach

Jebari

Viti

et al. 2016

Struct Multidisc Optim

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A method for stacking sequence optimization and aeroelastic tailoring of forward-swept composite wings is presented. It exploits bend-twist coupling to mitigate aeroelastic divergence. The method proposed here is intended for estimating potential weight savings during the preliminary aircraft design stages. A structural beam model of the composite wingbox is derived from anisotropic shell theory and the governing aeroelastic equations are presented for a spanwise discretized forward swept wing. Optimization of the system to reduce wing mass is undertaken for sweep angles of -35 • to 0 • and Mach numbers from 0.7 to 0.9. A subset of lamination parameters (LPs) and the number of laminate plies in each pre-defined direction (restricted to {0 • ,±45 • , 90 • }) serve as design variables. A bi-level hybrid optimization approach is employed, making use of a genetic algorithm (GA) and a subsequent gradientbased optimizer. Constraints are implemented to match lift requirements and prevent aeroelastic divergence, excessive deformations, airfoil stalling and structural failure. A permutation GA is then used to match specific composite ply stacking sequences to the optimum design variables with a limited number of manufacturing constraints considered for demonstration purposes. The optimization results in positive bend-twist coupling and

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“…Efficient aeroelastic methods and tools [1][2] based on reduced-order complexity [3][4][5][6] are increasingly sought for the preliminary multidisciplinary design and optimisation (MDO) [7][8] of flexible subsonic wings [9][10][11][12][13][14]. A semi-analytical model for the aeroelastic behavior of a thin straight wing in unsteady incompressible flow is hence here presented.…”

Section: Introductionmentioning

confidence: 99%

Semi-Analytical Reduced-Order Models for the Aeroelastic Behavior of Subsonic Flexible Wings via Generalised Plate and Beam Formulations

Berci¹

2017

Proceedings of the 6th International Conference on Computational Methods in Structural Dynamics and Earthquake Engineering (COM

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Multidisciplinary multifidelity optimisation of a flexible wing aerofoil with reference to a small UAV

Cited by 31 publications

References 30 publications

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

Optimal Design of Plated/Shell Structures under Flutter Constraints—A Literature Review

Composite stacking sequence optimization for aeroelastically tailored forward-swept wings

Semi-Analytical Reduced-Order Models for the Aeroelastic Behavior of Subsonic Flexible Wings via Generalised Plate and Beam Formulations

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