Aeroservoelastic aspects of wing/control surface planform shape optimization

Livne, Eli; Li, Weilin

doi:10.2514/3.12482

Cited by 28 publications

(7 citation statements)

References 33 publications

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“…More sophisticated methods should be used to consider the interaction between the aerodynamic and structural response. Interested readers are referred to the work of Friedmann, 14 Chattopadhyay and McCarthy, 15 Yuan and Friedmann, 16 Livne and Li, 17 The CFD solver and CSD solver do not necessarily share identical grid points at the interface; therefore, interpolations are required to allow the information exchange. Smith et al 19 evaluated suitable methods to exchange information between the CFD and CSD grids.…”

Section: Aerostructural Couplingmentioning

confidence: 99%

Aerostructural Optimization of a Transonic Compressor Rotor

Lian

Liou

2006

Journal of Propulsion and Power

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This paper presents a framework for multi-objective and multidisciplinary design optimization using highfidelity analysis tools. In this framework the aerodynamic performance is evaluated based on a Navier-Stokes equation solver, and the structure dynamics is computed using commercially available finite element software. We employ a genetic algorithm as a robust design optimization tool to facilitate the multi-objective optimization. We also use the response surface approach to tackle the difficulties associated with the organizational complexity and computational burden inherent in the multidisciplinary optimization. The coupling between the fluid solver and structural solver is realized through a thin-plate spline interpolation algorithm. The proposed approach is then used to perform aerostructural optimization of a three-dimensional transonic compressor blade. Our numerical results show that this method can improve the existing design and reduce the required computational time by orders of magnitude.

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Section: Aerostructural Couplingmentioning

confidence: 99%

Aerostructural Optimization of a Transonic Compressor Rotor

Lian

Liou

2006

Journal of Propulsion and Power

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“…Qd., = IS frfsdxdy (20) area where fr and f5 are the rth and the 5th admissible functions. The first derivatives of the admissible functions with respect to x and y are:…”

Section: Aerodynamic Force Matricesmentioning

confidence: 99%

“…Substituting these into Eq s. (19) and (20) leads to the final expression for the elements of the aerodynamic stiffness and damping matrices:…”

Section: Aerodynamic Force Matricesmentioning

confidence: 99%

“…In the effort to develop effective aeroservoelastic synthesis techniques for stressed skin aerospace structures, the area of airframe shape optimization becomes important, because of the need to make rigorous design optimization available to the designer at an early stage of the design process, where overall shape of the aircraft is still evolving. Analytic shape sensitivities have been developed for wing box structural modeling, [19], integrated wing box/panel buckling analysis in part one of this paper and unsteady aerodynamics in both subsonic and supersonic flight, [20]. This second part of the paper focuses on the integrated wing box/panel flutter analysis and sensitivity problem with emphasis on the needs of planform shape optimization.…”

Section: Introductionmentioning

confidence: 99%

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Analytic Sensitivities in Composite Wing-Shape Ynthesis Part Two: Panel Flutter Constraints

Elnomrossy

Mehanna

1999

International Conference on Aerospace Sciences and Aviation Tec

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The equivalent plate modeling formulation of composite wings, described in Part One, is extended in this paper to include the explicit analytic expressions for terms of the mass and aerodynamic matrices. Analytic sensitivities of the mass and aerodynamic matrices with respect to panel shape, thickness and fiber orientations are derived. Before proceeding in the study of analytic sensitivities using the derived expressions, the accuracy of its panel flutter analysis was numerically tested for simply supported panels of trapezoidal and skewed shape, of isotropic and composite materials and variable fiber orientations. The nondimensional critical dynamic pressure and critical frequency of flutter are compared with the results of finite element flutter analysis of composite skew panels by Chowdary, T.V.R. and al given in "Computers and Structures", (1996). The correlation of the results is good for moderate in-plane loading. Accuracy of the approximations is studied for the integration with nonlinear programming/approximation concept aeroelastic design synthesis methodology.

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“…8,9) adding DO capabilities to the ZAERO set of unsteady aerodynamic codes (Ref. 10) led the way to DO capabilities development for the ZONA Technology's ZEUS code (Refs.…”

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confidence: 99%

Towards CFD Based Aeroservoelastic Flight Vehicle Shape Optimization - New Capabilities and New Results with ZEUS-DO

Chen¹,

Zhang²,

Livne³

2012

53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials ConferenceSelf Cite

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The paper presents new developments in the capabilities of design-oriented (DO) Euler / boundary layer unsteady aerodynamic simulations to allow the accounting for static and dynamic aeroelastic constraints in the multidisciplinary shape optimization of flight vehicles. Adding to pressure distribution and generalized aerodynamic force shape derivatives as well as shape sensitivities of flutter speeds for configurations made of lifting surfaces, the new additions described in the present paper include extensions of the shape sensitivity capability to (a) configurations made of lifting surfaces and bodies, (b) linking of shape design variables to allow shape optimization of complex configurations driven by a small set of shape design variables, (c) shape sensitivity of aeroelastic static trim solutions and (d) shape sensitivities of time response to dynamic excitations. The paper also describes a designoriented implementation of a linearized Euler solver, offering computational advantages over the original approach to frequency domain generalized aerodynamic forces, which was based on system identification from CFD response time histories. Background and Motivation

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Aeroservoelastic aspects of wing/control surface planform shape optimization

Cited by 28 publications

References 33 publications

Aerostructural Optimization of a Transonic Compressor Rotor

Aerostructural Optimization of a Transonic Compressor Rotor

Analytic Sensitivities in Composite Wing-Shape Ynthesis Part Two: Panel Flutter Constraints

Towards CFD Based Aeroservoelastic Flight Vehicle Shape Optimization - New Capabilities and New Results with ZEUS-DO

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