Large-Amplitude Finite Element Flutter Analysis of Composite Panels in Hypersonic Flow

Gray, C. E.; Mei, Chuh

doi:10.2514/3.49051

Cited by 71 publications

(26 citation statements)

References 21 publications

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“…The first-order piston theory can suitably describe the aerodynamic pressure loads acting on the panel under sufficiently high supersonic Mach number ( √ 2 < M ∞ < 5) [1][2][3][4]8,9,12,13]. This theory relates the aerodynamic pressure and panel transverse deflection as follows:…”

Section: Aerodynamic Loadsmentioning

confidence: 99%

“…Spatial discretization is performed using four-node rectangular C 1 conforming plate elements [1][2][3]. There are two inplane degrees of freedom (u 0 , v 0 ) and four bending degrees of freedom (w, w x , w y , w xy ) at each node and one electrical degree of freedom () per piezoelectric layer per element, that is, electric potential is assumed to be constant over an element piezoelectric layer and applied or detected in the center of each element piezoelectric layer.…”

Section: Finite Element Discretizationmentioning

confidence: 99%

“…Gray et al [1] gave an excellent survey on various theoretical considerations for the investigation of nonlinear panel flutter up to 1991. Mei et al [2] presented an extensive review of the developments and advances in nonlinear panel flutter analysis and experiment up to 1999.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Finite element analysis and design of control system with feedback output using piezoelectric sensor/actuator for panel flutter suppression

Moon

2006

Finite Elements in Analysis and Design

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Section: Aerodynamic Loadsmentioning

confidence: 99%

Section: Finite Element Discretizationmentioning

confidence: 99%

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Finite element analysis and design of control system with feedback output using piezoelectric sensor/actuator for panel flutter suppression

Moon

2006

Finite Elements in Analysis and Design

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“…These are the harmonic balance technique [48], perturbation method [49], finite element method [28,29,38,39,50], direct numerical integration technique (DNIT) [26,40,47,[51][52][53][54][55][56][57][58], pseudo-arc length continuation method that complements the DNIT [32,59] and recently the Lyapunov first quantity (LFQ) [8,31,60]. Galerkin's method [72] and DNIT will be considered to solve the integro-differential equation (Eq.…”

Section: Galerkin Methods and Direct Numerical Integration Techniquementioning

confidence: 99%

A parametric study on supersonic/hypersonic flutter behavior of aero-thermo-elastic geometrically imperfect curved skin panel

et al. 2011

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In this paper, the effect of the system parameters on the flutter of a curved skin panel forced by a supersonic/hypersonic unsteady flow is numerically investigated. The aeroelastic model investigated includes the third-order piston theory aerodynamics for modeling the flow-induced forces and the Von Kármán nonlinear strain-displacement relation in conjunction with the Kirchhoff plate hypothesis for the panel structural modeling. Structural non-linearities are considered and are due to the non-linear coupling between out-of-plane bending and in-plane stretching. The effects of thermal degradation and Kelvin's model of structural damping independent on time and temperature are also considered. The aero-thermo-elastic governing equations are developed from the geometrically imperfect non-linear theory of infinitely long two-dimensional curved panels. Computational analysis and discussion of the finding along with pertinent conclusions are presented.

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“…The first group consists of studies focusing on panel flutter, which is a localized aeroelastic problem representing a small portion of the skin on the surface of the hypersonic vehicle. [5][6][7][8][9][10] The second group of studies in this area was motivated by a previous hypersonic vehicle, namely the NASP. [11][12][13][14][15][16][17] However, some of these studies dealt with the transonic regime, because it was perceived to be quite important.…”

Section: Nomenclaturementioning

confidence: 99%

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

McNamara

Friedmann

Powell

et al. 2005

46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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The aeroelastic and aerothermoelastic behavior of three-dimensional configurations in hypersonic flow regime are studied. The aeroelastic behavior of a low aspect ratio wing, representative of a fin or control surface on a generic hypersonic vehicle, is examined using third order piston theory, Euler and Navier-Stokes aerodynamics. The sensitivity of the aeroelastic behavior generated using Euler and Navier-Stokes aerodynamics to parameters governing temporal accuracy is also examined. Also, a refined aerothermoelastic model, which incorporates the heat transfer between the fluid and structure using CFD generated aerodynamic heating, is used to examine the aerothermoelastic behavior of the low aspect ratio wing in the hypersonic regime. Finally, the hypersonic aeroelastic behavior of a generic hypersonic vehicle with a lifting-body type fuselage and canted fins is studied using piston theory and Euler aerodynamics for the range of 2.5 ≤ M ≤ 28, at altitudes ranging from 10,000 feet to 80,000 feet. This analysis includes a study on optimal mesh selection for use with Euler aerodynamics. In addition to the aeroelastic and aerothermoelastic results presented, three time domain flutter identification techniques are compared, namely the moving block approach, the least squares curve fitting method, and a system identification technique using an Auto-Regressive model of the aeroelastic system. In general, the three methods agree well. The system identification technique, however, provided quick damping and frequency estimations with minimal response record length, and therefore offers significant reductions in computational cost. In the present case, the computational cost was reduced by 75%. The aeroelastic and aerothermoelastic results presented illustrate the applicability of the CFL3D code for the hypersonic flight regime.

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Large-Amplitude Finite Element Flutter Analysis of Composite Panels in Hypersonic Flow

Cited by 71 publications

References 21 publications

Finite element analysis and design of control system with feedback output using piezoelectric sensor/actuator for panel flutter suppression

Finite element analysis and design of control system with feedback output using piezoelectric sensor/actuator for panel flutter suppression

A parametric study on supersonic/hypersonic flutter behavior of aero-thermo-elastic geometrically imperfect curved skin panel

Three-dimensional Aeroelastic and Aerothermoelastic Behavior in Hypersonic Flow

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