Volterra series approach for nonlinear aeroelastic response of 2-D lifting surfaces

2005

Nonlinear Dyn

180

The identification of nonlinear aeroelastic systems based on the Volterra theory of nonlinear systems is presented. Recent applications of the theory to problems in computational and experimental aeroelasticity are reviewed. Computational results include the development of computationally efficient reduced-order models (ROMs) using an Euler/Navier-Stokes flow solver and the analytical derivation of Volterra kernels for a nonlinear aeroelastic system. Experimental results include the identification of aerodynamic impulse responses, the application of higher-order spectra (HOS) to wind-tunnel flutter data, and the identification of nonlinear aeroelastic phenomena from flight flutter test data of the active aeroelastic wing (AAW) aircraft.

Section: Higher-order Spectra (Hos)mentioning

confidence: 99%

“…Analytical derivation of frequency-domain, nonlinear aeroelastic Volterra kernels is presented by Marzocca et al [58,59]. Aeroelastic systems with one (plunge) and two (plunge and pitch) degrees of freedom with linear aerodynamic equations but with nonlinear structural parameters were defined.…”

Section: Analytical Derivation Of Volterra Kernelsmentioning

confidence: 99%

Identification of Nonlinear Aeroelastic Systems Based on the Volterra Theory: Progress and Opportunities

2005

Nonlinear Dyn

180

“…17 Some very interesting and fundamental applications using the frequency-domain Volterra theory 18,19 and experimental applications of Volterra methods 20, 21 are providing new "windows" on the world of nonlinear aeroelasticity.…”

Section: Higher-order Spectramentioning

confidence: 99%

Higher-Order Spectral Analysis of F-18 Flight Flutter Data

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

Dunn²

2005

Self Cite

Royal Australian Air Force (RAAF) F/A-18 flight flutter test data is presented and analyzed using various techniques. The data includes high-quality measurements of forced responses and limit cycle oscillation (LCO) phenomena. Standard correlation and power spectral density (PSD) techniques are applied to the data and presented. Novel applications of experimentally-identified impulse responses and higher-order spectral techniques are also applied to the data and presented. The goal of this research is to develop methods that can identify the onset of nonlinear aeroelastic phenomena, such as LCO, during flutter testing.

“…12 Some very interesting and fundamental applications using the frequency-domain Volterra theory 13,14 and experimental applications of Volterra methods 15,16 are providing new "windows" on the world of nonlinear aeroelasticity.…”

Section: Higher-order Spectramentioning

confidence: 99%

Higher-Order Spectral Analysis of a Nonlinear Pitch and Plunge Apparatus

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

Strganac

Hajj³

2005

Self Cite

Simulated aeroelastic responses of a nonlinear pitch and plunge apparatus are analyzed using various statistical signal processing techniques including higher-order spectral methods. A MATLAB version of the Nonlinear Aeroelastic Testbed Apparatus (NATA) at the Texas A&M University is used to generate various aeroelastic response data including limit cycle oscillations (LCO). Traditional and higher-order spectral (HOS) methods are applied to the simulated aeroelastic responses. Higher-order spectral methods are used to identify critical signatures that indicate the transition from linear to nonlinear (LCO) aeroelastic behavior.