Local Piston Theory with Viscous Correction and Its Application

Luo, Wen; Zhang, Chen-An; Han, Han-Qiao; Wang, Famin

doi:10.2514/1.j055207

Cited by 26 publications

(13 citation statements)

References 16 publications

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“…13 that the flutter boundaries computed via the PROM are in good agreement with the results computed via the direct CFD. It is noted that the obtained degradation phenomenon of the hypersonic flutter Mach with the increase of the angle of attack is consistent with that reported in Liu et al (2016b) and Zhang et al (2009). Limit-cycle oscillation (LCO) is a major nonlinear aeroelastic phenomenon induced by the structural nonlinearities due to aerodynamic heating.…”

Section: Verification Of the Hypersonic Aerodynamic Modeling Methodssupporting

confidence: 86%

Active Disturbance Rejection Control for Hypersonic Flutter Suppression Based on Parametric ROM

Chen

Zhao

2020

J. Aerosp. Eng.

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This paper presents an active disturbance rejection control algorithm (ADRC) to suppress the hypersonic flutter of a three-degreesof-freedom (3-DOF) two-dimensional (2D) airfoil operating in multiparameters space. In this study, two key issues need to be addressed. The first one is the construction of the reduced-order model (ROM) of quasi-steady aerodynamic forces in multiparameter space. To solve this problem, a parametric reduced-order model (PROM) based on the adaptive proper orthogonal decomposition (POD) is developed to efficiently predict the quasi-steady aerodynamic forces at an arbitrary point in the given multiparameters space. The accuracy of the PROM is validated by the direct computational fluid dynamics (CFD) computations for flutter and limit cycle oscillation (LCO) prediction. The second issue is the design of the control law for an aeroservoelastic (ASE) system constructed by a parametric black-box aerodynamic model. Considering the black-box characteristics of a controlled object, we use an error-based feedback control law named ADRC to suppress the flutter instability of the system. Furthermore, in order to improve the rapidity in responses and the robustness of the ASE system, we propose an SVM-ADRC strategy that features embedding the least squares support vector machine (LS-SVM) into the ADRC controller. Hypersonic ASE simulation results show that the proposed SVM-ADRC controller can effectively suppress the hypersonic flutter over a wide range of parameter variations, and is more robust than the standard ADRC controller.

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Section: Verification Of the Hypersonic Aerodynamic Modeling Methodssupporting

confidence: 86%

Active Disturbance Rejection Control for Hypersonic Flutter Suppression Based on Parametric ROM

Chen

Zhao

2020

J. Aerosp. Eng.

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“…The advantages of local piston theory (LPT) relative to CPT have been demonstrated previously [3]. Typically, LPT has been used to perturb a mean-steady solution obtained from the Euler equations, and recently, from the NavierStokes equations [4]. The applications of LPT in the literature have been limited to first-order LPT [5][6][7].…”

Section: Introductionmentioning

confidence: 99%

Role of Higher-Order Terms in Local Piston Theory

Meijer

Dala

2019

Journal of Aircraft

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“…33 The same method was applied by Liu et al. 34 to investigate the flutter boundary of a 2D airfoil as well as a waverider. Compared to Euler equations, a better agreement with N-S equations was found by using this method.…”

Section: Introductionmentioning

confidence: 99%

Analysis on location of maximum vibration amplitude in panel flutter

Meng

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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When the panel is under limit cycle oscillation, the location of maximum vibration amplitude always locates at 0.75 of panel length under different dynamic pressure. However, this conclusion is drawn from engineer practice without further investigations on its theoretical basis. Thus, the current study focuses on the theoretical and mathematical basis of this problem. The pattern of the location of maximum amplitude is verified at first by using three numerical methods. Then, based on the law of energy conservation, the displacement function of linear panel oscillation is derived for theoretical investigation. The linear panel consists of two structural modes. Theoretical analysis shows that, under critical dynamic pressure, the generalized displacement responses of two structural modes have opposite phase, the same vibration amplitude and the same vibration frequency. As a result, the superposition of displacement function of two structural modes, which is the displacement function of panel, leads to the occurrence of maximum vibration amplitude at 0.7 of panel length. With more structural modes considered, the location of maximum moves to 0.75 of panel length.

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Local Piston Theory with Viscous Correction and Its Application

Cited by 26 publications

References 16 publications

Active Disturbance Rejection Control for Hypersonic Flutter Suppression Based on Parametric ROM

Active Disturbance Rejection Control for Hypersonic Flutter Suppression Based on Parametric ROM

Role of Higher-Order Terms in Local Piston Theory

Analysis on location of maximum vibration amplitude in panel flutter

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