A Volterra Kernel Reduced-Order Model Approach for Nonlinear Aeroelastic Analysis

Munteanu, Sorin; Rajadas, John; Nam, Changho; Chattopadhyay, Aditi

doi:10.2514/6.2005-1854

Cited by 13 publications

(4 citation statements)

References 13 publications

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“…The outline idea of modified POD method is to construct POD kernel with snapshots of primary system and dual system. Consider an n order state-space system and its dual system defined in (11), (12) x Ax Bu…”

Section: Pod With Balanced Modificationmentioning

confidence: 99%

Aerodynamic System Modeling based on Proper Orthogonal Decomposition

Yao¹,

Xu²,

Wang³

2011

IJITCS

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The main goal of present paper is to construct an efficient reduced order model (ROM) for aerodynamic system modeling. Proper Orthogonal Decomposition (POD) is presented to address the problem. First, the snapshots are collected to form the POD kernel, and then Singular Values Decomposition (SVD) is used to obtain POD modes, finally POD-ROM can be constructed by projecting full order aerodynamic system to POD modes subspace. Two problems are addressed: (1) aerodynamic data inverse design; (2) aeroelastic structure active control. For the second problem, POD method with balanced modification is introduced to improve the robustness of original POD method. Results in problem (1) suggest POD method works efficiently not only for interpolation inverse design but also for extrapolation problems. The results in problem (2) demonstrate POD method with balanced modification is efficient and accurate enough for aeroelastic system analysis.

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Section: Pod With Balanced Modificationmentioning

confidence: 99%

Aerodynamic System Modeling based on Proper Orthogonal Decomposition

Yao¹,

Xu²,

Wang³

2011

IJITCS

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“…For an aircraft in flight, strong interactions can occur between the flexible aircraft structures and the surrounding flow resulting in aeroelastic problems [1,2]. The emphasis of the study is the discipline of displacement and load of the flexible structure under the unsteady aerodynamic.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic Analysis of a Supersonic Fin Based on CFD/CSD Coupling

Cai

Guo

et al. 2010

2010 2nd International Conference on Information Engineering and Computer Science

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The main goal of this paper is to analyze the flutter boundary and dynamic load of a supersonic fin. Reduced order mode (ROM) based on Volterra Series is presented to calculate the flutter boundary, and CFD/CSD coupling is used to compute the transient aerodynamic load. The Volterra-based ROM is obtained using the derivative of unsteady aerodynamic stepresponse, and the infinite plate spline is used to perform interpolation of physical quantities between the fluid and the structural grids. The results show that inertia force plays a significant role in the dynamic load, the moment cause by inertia force is lager than the aerodynamic force, because of the huge dynamic load, structure may be broken by aeroelasticity under the flutter dynamic pressure.

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“…Computational aeroelasticity is one of the most challenging fields for aircraft. For an aircraft in flight, strong interactions can occur between the flexible aircraft structures and the surrounding flow resulting in aeroelastic problems [1,2]. The emphasis of the study is the discipline of displacement and load of the flexible structure under the unsteady aerodynamic.…”

Section: Introductionmentioning

confidence: 99%

CFD-based Analysis of Aeroelastic behavior of Supersonic Fins

Cai¹,

Xu²,

Yao³

2011

IJISA

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The main goal of this paper is to analyze the flutter boundary, transient loads of a supersonic fin, and the flutter with perturbation. Reduced order mode (ROM) based on Volterra Series is presented to calculate the flutter boundary, and CFD/CSD coupling is used to compute the transient aerodynamic load. The Volterra-based ROM is obtained using the derivative of unsteady aerodynamic stepresponse, and the infinite plate spline is used to perform interpolation of physical quantities between the fluid and the structural grids. The results show that inertia force plays a significant role in the transient loads, the moment cause by inertia force is lager than the aerodynamic force, because of the huge transient loads, structure may be broken by aeroelasticity below the flutter dynamic pressure. Perturbations of aircraft affect the aeroelastic response evident, the reduction of flutter dynamic pressure by rolling perturbation form 15.4% to 18.6% when Mach from 2.0 to 3.0. It is necessary to analyze the aeroelasticity behaviors under the compositive force environment.

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A Volterra Kernel Reduced-Order Model Approach for Nonlinear Aeroelastic Analysis

Cited by 13 publications

References 13 publications

Aerodynamic System Modeling based on Proper Orthogonal Decomposition

Aerodynamic System Modeling based on Proper Orthogonal Decomposition

Aeroelastic Analysis of a Supersonic Fin Based on CFD/CSD Coupling

CFD-based Analysis of Aeroelastic behavior of Supersonic Fins

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