Aeroelasticity of Plates and Shells

Dowell, Earl H.; Ashley, Holt

doi:10.1115/1.3423871

Cited by 209 publications

(139 citation statements)

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“…Among other effects, shock movements in the flow play a significant role in the destabilizing mechanisms which finally activate nonlinearities. These features can also be found in the panel flutter problem [9], which serves as our model problem. The panel flutter problem analyzed in this work consists of a plate (panel) over which a compressible fluid (air) flows at transonic speed.…”

Section: Fluid-structure Couplingmentioning

confidence: 89%

Parallel and Adaptive Methods for Fluid-Structure-Interactions

Ballmann

Behr

Brix

et al. 2010

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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The new flow solver Quadflow, developed within the SFB 401, has been designed for investigating flows around airfoils and simulating the interaction of the structural dynamics and aerodynamics. This article addresses the following issues arising in this context. After identifying proper coupling conditions and settling the well-posedness of the resulting coupled fluid-structure problem, suitable strategies for successively applying flow and structure solvers needed to be developed that give rise to a sufficiently close coupling of both media. Based on these findings the overall efficiency of numerical simulations hinges, for the current choice of structural models, on the efficiency of the flow solver. In addition to the multiscale-based grid adaptation concepts, proper parallelization concepts are needed to realize for such complex problems an acceptable computational performance on parallel architectures. Since the parallelization of dynamically varying adaptive discretizations is by far not straightforward we will mainly concentrate on this issue in connection with the above mentioned multiscale adaptivity concepts. In particular, we outline the way the multiscale library has been parallelized via MPI for distributed memory architectures. To ensure a proper scaling of the computational performance with respect to CPU time and memory, the load of data has to be well-balanced and communication between processors has to be minimized. We point out how to meet these requirements by employing the concept of space-filling curves.

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Section: Fluid-structure Couplingmentioning

confidence: 89%

Parallel and Adaptive Methods for Fluid-Structure-Interactions

Ballmann

Behr

Brix

et al. 2010

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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“…An assumption has been made that the plate layers do not sufficiently stretch during deflection, which is the case for flat plates with oscillations substantially less than the thickness 3 . For larger deflections, in the case of initial/imposed curvature or post-flutter limit cycle oscillations, the American Institute of Aeronautics and Astronautics 4 plate material may stretch, which would require the addition of a stretching potential energy.…”

Section: Governing Equationsmentioning

confidence: 99%

Flutter Analysis of the Thermal Protection Layer on the NASA HIAD

Goldman

Dowell

Scott

2013

AIAA Aerodynamic Decelerator Systems (ADS) Conference

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A combination of classical plate theory and a supersonic aerodynamic model is used to study the aeroelastic flutter behavior of a proposed thermal protection system (TPS) for the NASA HIAD. The analysis pertains to the rectangular configurations currently being tested in a NASA wind-tunnel facility, and may explain why oscillations of the articles could be observed. An analysis using a linear flat plate model indicated that flutter was possible well within the supersonic flow regime of the wind tunnel tests. A more complex nonlinear analysis of the TPS, taking into account any material curvature present due to the restraint system or substructure, indicated that significantly greater aerodynamic forcing is required for the onset of flutter. Chaotic and periodic limit cycle oscillations (LCOs) of the TPS are possible depending on how the curvature is imposed. When the pressure from the base substructure on the bottom of the TPS is used as the source of curvature, the flutter boundary increases rapidly and chaotic behavior is eliminated.

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“…К взаимодействию неустойчивостей Эйлера и Гельм-гольца близко примыкает явление дивергенции пласти-ны в потоке жидкости и газа, а также к динамиче-ской неустойчивости -явление флаттера [11][12][13]. При этом динамическое взаимодействие изгиба пластины и газовых течений рассматривается при дозвуковых и сверхзвуковых скоростях во многих случаях с учетом нелинейностей.…”

Section: Introductionunclassified

Взаимодействие Неустойчивости Эйлера, Гельмгольца, Рэлея

Ильгамов¹

2018

Журнал Технической Физики

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Aeroelasticity of Plates and Shells

Cited by 209 publications

References 0 publications

Parallel and Adaptive Methods for Fluid-Structure-Interactions

Parallel and Adaptive Methods for Fluid-Structure-Interactions

Flutter Analysis of the Thermal Protection Layer on the NASA HIAD

Взаимодействие Неустойчивости Эйлера, Гельмгольца, Рэлея

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