Unsteady-Aerodynamic Shape Sensitivities for Airplane Aeroservoelastic Configuration Optimization

Chen, P. C.; Liu, D. D.; Livne, Eli

doi:10.2514/1.10007

Cited by 10 publications

(3 citation statements)

References 24 publications

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“…Iollo and Salas [15] used variational method to solve a two-dimensional internal flow optimization problem with embedded shock to match a pressure distribution. References [17,[28][29][30]33,34] applied variants of discrete sensitivity approaches to optimize engineering problems. Epstein and Peigin [26] used Genetic Algorithm to optimize three-dimensional lifting surfaces for wing-body aircraft configuration.…”

Section: Variational Sensitivity Analysismentioning

confidence: 99%

Variational sensitivity analysis and design optimization

Tiwari

2009

Computers & Fluids

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Section: Variational Sensitivity Analysismentioning

confidence: 99%

Variational sensitivity analysis and design optimization

Tiwari

2009

Computers & Fluids

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“…The "step-size dilemma" forces a choice between a small step size to minimize truncation error and a step not so small that errors due to subtractive cancelation do not become so dominant [1]. In light of the issues with the FDM, the complex variable differentiation (CVD) method [2] has been developed in the aerodynamic code using panel method [3].…”

mentioning

confidence: 99%

Enabling Sensitivity Analysis Capability for a CFD-Based Unsteady Aerodynamic/Aeroelastic Solver

Wang¹,

Zhang²,

Chen³

et al. 2012

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

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Unsteady aerodynamic sensitivities towards shape design variables are critical for multidisciplinary design optimization of aircraft. Sensitivity analysis using finite difference method (FDM) is not reliable due to its reliance on the step size choice. Automatic differentiation using complex variable and dual number has been enabled to a CFD-based aerodynamic solver, ZEUS. Both methods can compute the sensitivities accurately and efficiently. However, the complex variable method (CVD) requires an extreme small number be used as the perturbation to the design variable, which may slow down the computation due to floating number underflow issue. By any rate, CVD is still an approximate method, While the dual number approach theoretically gives exact sensitivity solutions. Numerical example cases on the AGARD wing configurations with the swept angle or the span as the design variable are carried out to demonstrate the validation of the CVD and dual number method implementations.

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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. 11,12), thus aiming at bringing into the early design stages of a flight vehicle CFD-based aeroelastic capabilities that would allow accounting for aeroelastic and aeroservoelastic constraints in the search for optimal shape and optimal inner structure.…”

mentioning
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 Conference
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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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Unsteady-Aerodynamic Shape Sensitivities for Airplane Aeroservoelastic Configuration Optimization

Cited by 10 publications

References 24 publications

Variational sensitivity analysis and design optimization

Variational sensitivity analysis and design optimization

Enabling Sensitivity Analysis Capability for a CFD-Based Unsteady Aerodynamic/Aeroelastic Solver

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

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