A generalized eigenvalue solution to the flutter stability problem with true damping: The p-L method

Quero, David; Vuillemin, Pierre; Poussot-Vassal, Charles

doi:10.1016/j.jfluidstructs.2021.103266

Cited by 8 publications

(3 citation statements)

References 37 publications

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“…This requires the partial derivatives of the aerodynamic transfer function matrix appearing in Equations ( 7), (17) and (18). They are obtained by differentiating the aerodynamic transfer function matrix of the g method, A g (s * ), defined in Equation ( 5), and by accounting for the chained partial derivative of the reduced quantities σ * , ω * to the dimensional quantities σ, ω, respectively.…”

Section: Aeroelastic Sensitivities For the G Methodsmentioning

confidence: 99%

“…Recently, the p-L method, which recovers a true aerodynamic damping representation from the values at the imaginary axis, has been presented [18]. Even though the aeroelastic eigensensitivities produced by the p-L method could be embedded in the framework presented in this work, they can also be obtained by using its corresponding generalized state-space form.…”

Section: Aerodynamic Damping Approximationsmentioning

confidence: 99%

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Effect of Aerodynamic Damping Approximations on Aeroelastic Eigensensitivities

Kaiser

Quero

2022

Aerospace

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Aeroelastic sensitivities for the flutter solution are a crucial component of the multi-disciplinary optimization methods employed in modern aircraft design. This paper derives the aeroelastic sensitivities for different aerodynamic damping approximations—the p-k method, the g method and the generalized aeroelastic analysis method—highlighting the influence of the employed aerodynamic approximation on the required derivatives. The derived formulation for the determination of aeroelastic sensitivities by means of a direct method is verified for the case of a two-degree-of-freedom typical section model, where analytical aeroelastic sensitivities can be analytically obtained. For this and for an additional model, namely the AGARD 445.6 weakened wing, the significant effect of the aerodynamic damping approximation on the aeroelastic sensitivities is shown.

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Section: Aeroelastic Sensitivities For the G Methodsmentioning

confidence: 99%

Section: Aerodynamic Damping Approximationsmentioning

confidence: 99%

Effect of Aerodynamic Damping Approximations on Aeroelastic Eigensensitivities

Kaiser

Quero

2022

Aerospace

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“…Moreover, due to the model construction method (see e.g. [51] or [50]), the E matrix may also be rank deficient. Here, due to the additional double derivative and delay structure added to accurately describe the gust disturbance effect along the fuselage, rank E = 𝑛 − 6.…”

Section: Actuatorsmentioning

confidence: 99%

Data-driven modeling and control of large-scale dynamical systems in the Loewner framework

Gosea¹,

Poussot-Vassal²,

Antoulas³

2021

Preprint

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In this contribution, we discuss the modeling and model reduction framework known as the Loewner framework. This is a data-driven approach, applicable to large-scale systems, which was originally developed for applications to linear time-invariant systems. In recent years, this method has been extended to a number of additional more complex scenarios, including linear parametric or nonlinear dynamical systems. We will provide here an overview of the latter two, together with time-domain extensions. Additionally, the application of the Loewner framework is illustrated by a collection of practical test cases. Firstly, for data-driven complexity reduction of the underlying model, and secondly, for dealing with control applications of complex systems (in particular, with feedback controller design).

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