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第十届动力学与控制学术会议

作者： YAN Zhi-miao RAGAB Saad HAJJ Muhammad School of Astronautics Harbin Institute of Technology (HIT) Department of Biomedical Engineering and Mechanics Virginia Tech

In this work, we performed numerical simulations to investigate the effectiveness of a nonlinear energy sink in the control of transonic flutter. To simulate the transonic flow around the airfoil, we chose the solver rho Central Foam of Open Foam because of the free on-line open source and convenience to be revised. We briefly discussed the governing equations and assumptions used in this solver. To validate the solver rho Central Foam, we use two classical transonic experimental cases: steady RAE-2822 and oscillating NACA64A010. In the oscillatory case, we discuss the merits of dynamic zone of mesh used in the sixDoFRigid BodyMotion and revised them for our simulation boundary conditions. In both cases, we noted that the solver rho Central Foam was very effective and accurate to simulate transonic flow around the airfoil. Then, we proposed the model for typical section airfoil with nonlinear energy sink as shown in Figure 1. We chose the classical transonic-dip case of NACA64A010 and found that the NES to be a very effective mean to suppress the transonic flutter of the airfoil. We also quantified the effects of the NES damping and stiffness coefficients on the wing’s response. Furthermore, we examined the effects of the initial conditions.

关键词： Nonlinear Energy Sink transonic flutter Passive control Open FOAM FluidStructure interaction

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A TVD Uncertainty Quantification Method with Bounded Error Applied to transonic Airfoil flutter

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Communications in Computational Physics 2009年第7期6卷 406-432页

作者： Jeroen A.S.Witteveen Hester Bijl Faculty of Aerospace Engineering Delft University of TechnologyKluyverweg 12629HS DelftThe Netherlands

The Unsteady Adaptive Stochastic Finite Elements(UASFE)approach is a robust and efficient uncertainty quantification method for resolving the effect of random parameters in unsteady *** this paper,it is shown that the underlying Adaptive Stochastic Finite Elements(ASFE)method for steady problems based on Newton-Cotes quadrature in simplex elements is extrema diminishing(ED).It is also shown that the method is total variation diminishing(TVD)for one random parameter and for multiple random parameters for first degree Newton-Cotes *** is proven that the interpolation of oscillatory samples at constant phase in the UASFE method for unsteady problems results in a bounded error as function of the phase for periodic responses and under certain conditions also in a bounded error in *** two methods are applied to a steady transonic airfoil flow and a transonic airfoil flutter problem.

关键词： Total variation diminishing extrema diminishing error bounds stochastic finite elements uncertainty quantification transonic flow transonic flutter

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Oscillation quenching and physical explanation on freeplay-based aeroelastic airfoil in transonic viscous flow

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Chinese Journal of Aeronautics 2023年第10期36卷 124-136页

作者： Yayun SHI Shun HE Gaowei CUI Gang CHEN Yan LIU State Key Laboratory for Strength and Vibration of Mechanical Structures School of Aerospace EngineeringXi’an Jiaotong UniversityXi’an 710049China School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China Beijing Institute of Structure and Environment Engineering Beijing 100076China Shenyang Aircraft Design Institute Shenyang 110036China

Limit Cycle Oscillation(LCO)quenching of a supercritical airfoil(NLR 7301)considering freeplay is investigated in transonic viscous *** Fluid Dynamics(CFD)based on Navier-Stokes equations is implemented to calculate transonic aerodynamic forces.A loosely coupled scheme with steady CFD and an efficient graphic method are developed to obtain the aerodynamic *** quenching phenomenon is observed from the nonlinear dynamic aeroelastic response obtained by using time marching *** the airspeed increases,LCO appears then quenches,forming the first LCO *** the quenching region,LCO occurs again and sustains until the divergence of the response,forming the second LCO *** quenching of LCOs was addressed physically based on the aerodynamic preload and the linear flutter ***“island”of stable region is observed in the flutter boundary,*** flutter speed versus the mean Angle of Attack(AoA).The LCO quenches when the aerodynamic preload crosses this stable region with the increasing of *** LCO quenching of this model in transonic flow is essentially induced by destabilizing effect from aerodynamic preload,since the flutter speed is sensitive to AoA due to aerodynamic nonlinearity.

关键词： Freeplay Nonlinear aeroelasticity Supercritical airfoil transonic flutter Unsteady flow

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