A Doublet-Lattice Method Correction Approach for High Fidelity Gust Loads Analysis

Valente, Carmine; Lemmens, Yves; Wales, Christopher J A; Jones, Dorian P; Gaitonde, Ann L; Cooper, Jonathan E.

doi:10.2514/6.2017-0632

Cited by 10 publications

(3 citation statements)

References 11 publications

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“…While higher-order structural and aerodynamic methods are sometimes used [24], the computational expense currently limits the application to individual cases of interest rather than large numbers of computations over the whole envelope. Despite the development of aerodynamic reduced order models (ROMs) [25] and corrections to established methods [26,27], the work in this paper is focused on the industrial implications of structural nonlinearities, and as such, a strip theory approach coupled with a nonlinear beam solver is deemed to be sufficient to capture important phenomena without modelling extraneous details.…”

Section: Fig 1 Future Harw Aircraft Conceptsmentioning

confidence: 99%

Industrially Inspired Gust Loads Analysis of Various-Aspect-Ratio Wings Featuring Geometric Nonlinearity

Cook

Calderon

Cooper

et al. 2020

Journal of Aircraft

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Section: Fig 1 Future Harw Aircraft Conceptsmentioning

confidence: 99%

Industrially Inspired Gust Loads Analysis of Various-Aspect-Ratio Wings Featuring Geometric Nonlinearity

Cook

Calderon

Cooper

et al. 2020

Journal of Aircraft

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“…Especially, the aircraft has to be designed to withstand loads resulting from gusts. Unsteady gust analyses rely usually on linear techniques in frequency domain, based on simple Doublet Lattice Methods (DLM) for the aerodynamic flow prediction [1], [2]. These techniques are valid for subsonic flows, but could sometimes be not accurate enough to get realistic responses in the transonic regime, characterized by strong nonlinearities such as shocks and flow separation.…”

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigations of a 2D aeroelastic airfoil encountering a gust in transonic conditions

2019

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In order to make substantial progress in reducing the environmental impact of aircraft, a key technology is the reduction of aircraft weight. This challenge requires the development and the assessment of new technologies and methodologies of load prediction and control. To achieve the investigation of the specific case of gust load, ONERA defined a dedicated research program based on both wind tunnel test campaigns and high fidelity simulations.To reach the experimental objectives, a set-up was designed, manufactured and implemented within the ONERA S3Ch transonic wind tunnel facility. The first component, called gust generator, consists of two oscillating airfoils installed upstream of the wind tunnel test section and allows to produce air flow deflections. The second component, the test model, is a two degrees-of-freedom aeroelastic model of a supercritical airfoil. A test campaign has been performed leading to the generation of databases for high fidelity tools validation.These databases have been used in order to assess the capabilities of the elsA code (ONERA-Airbus-Safran property) using its aeroelastic module and a gust model based on the Field Velocity Method. A validation process has been defined in order to move from experimental results obtained in the wind tunnel with wall boundaries to industrial modeling computed with farfield boundaries. The full process was applied to a transonic case with sine gust excitation signals.

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“…However, this method presents limitations in terms of its approximations due to the use of linearized potential equations, therefore not describing essential effects for aerodynamic analysis, such as geometry thickness, fluid viscosity, or shockwave formation, often resulting in overprediction of lift in aerodynamic surfaces [94]. Considering the DLM limitations in estimating aerodynamic coefficients, it is a common procedure in the industry to match the steady results at zero frequency with a higher order model by using correction factors, such as computed with CFD analysis or validated with steady-state wind tunnel data, in order to guarantee a good compromise between performance and accuracy in the results [95].…”

Section: Aerodynamic Modelmentioning

confidence: 99%

Dynamic Aeroelastic Response Attenuation of Aerospace Structures Employing Passive Tuned Mass Dampers

Gasparetto¹

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This thesis proposes an optimization procedure to achieve the best configuration of Multiple Degrees of Freedom (MDOF) tuned mass dampers (TMD) to mitigate the global dynamic aeroelastic response of aerospace structures. The TMD design parameters are investigated in terms of their individual mass, stiffness, damping, and location on the target structure. In order to determine the optimum sets of TMD, a Multi-Objective design optimization employing Genetic Algorithm (MOGA) is implemented, where the selected fitness functions for the analysis are the minimization of the total mass included with the resonators and concurrent minimization of the peak displacement at a specific structural nodes in space.Two case studies are presented where the method proposed is tested to minimize the pointing error of large Earth-based radio antenna structures. Fourteen different operational scenarios of wind gust are considered employing two models of atmospheric disturbances, namely, the Power Spectral Density (PSD) represented by the Davenport spectrum (DS), and the Tuned Discrete Gust (TDG) where the dynamic aeroelastic response of the structure is analyzed in the frequency and the time domains, respectively.In the first case study, the inclusion of multiple-TMD in the antenna structure is analyzed and compared with different placement configurations of the multiple-TMD devices. Here, the performance of the antenna structure in the form of its pointing error and the corresponding multiple-TMD inclusion are discussed at length. It is found that the placement of the multiple-TMD in the primary reflector of the antenna provides a maximum reduction in the pointing error of the antenna of 62.0% and 39.2% while subject to PSD and TDG gust disturbances , respectively. iv In the second case study, a single-TMD configuration is investigated to concurrently attenuate the aeroelastic response of all 14 operational cases considering the frequency and time-domain gust models. It is found that the optimal solutions are capable of reducing the structural response by an average of 66% and 50% for the PSD and TDG gust excitation scenarios, respectively, with a mass inclusion of 1% of the total mass of the antenna structural.Finally, this study proposes an advanced framework to estimate the optimal parameters of TMD attenuation devices, under complex loadings conditions, as an initial step in the direction of the use of such passive systems in applications that commonly employ active or semi-active attenuation solutions.

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A Doublet-Lattice Method Correction Approach for High Fidelity Gust Loads Analysis

Cited by 10 publications

References 11 publications

Industrially Inspired Gust Loads Analysis of Various-Aspect-Ratio Wings Featuring Geometric Nonlinearity

Industrially Inspired Gust Loads Analysis of Various-Aspect-Ratio Wings Featuring Geometric Nonlinearity

Experimental and numerical investigations of a 2D aeroelastic airfoil encountering a gust in transonic conditions

Dynamic Aeroelastic Response Attenuation of Aerospace Structures Employing Passive Tuned Mass Dampers

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