Numerical Investigation of Aeroelastic Characteristics of Grid Fin

Ye, Kun; Zhang, Yifan; Chen, Zeshuai; Ye, Zhengyin

doi:10.2514/1.j060833

Cited by 16 publications

(8 citation statements)

References 22 publications

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“…The Euler equations described by the arbitrary Lagrangian–Eulerian (ALE) method are solved in this study using a verified in-house code (Ye et al. 2022). The cell-centred finite-volume method is applied to solve the above governing equations.…”

Section: Methodsmentioning

confidence: 99%

“…To improve the calculation efficiency, a reduced-order model for unsteady aerodynamic loads based on the AutoRegressive with eXogenous input (ARX) model (Gao & Zhang 2020; Ye et al. 2022) is established through the system identification technique. The ARX model for a multi-input multi-output system can be given by where and are the output and input in the th observation, respectively; is the noise in the th observation; and are the parameter matrices to be identified; and and are the order of output and input terms, respectively, which are hyper-parameters of the model.…”

Section: Methodsmentioning

confidence: 99%

“…A comparative analysis of these errors enables us to determine the most suitable n b value. The modelling error, as defined by (4.1), quantifies the extent to which the model accurately captures the training generalised aerodynamic forces (Ye et al 2022): Figure 7 presents the variation of normalised modelling errors versus different values of n b . The modelling errors of individual modal orders are normalised using their maximum and minimum values.…”

Section: Establishment Of the Reduced-order Model For Unsteady Aerody...mentioning

confidence: 99%

“…where (5.4a,b) correspond to the output equation and state equation of the state-space model, respectively. A similar coupling method is also adopted by Gao et al (2017), Silva & Bartels (2004) and Ye et al (2022). Let the state variables be denoted as r = {e, x}.…”

Section: Linear Stability Of Fixed Pointsmentioning

confidence: 99%

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On the aeroelastic bifurcation of a flexible panel subjected to cavity pressure and inviscid oblique shock

Zhang,

Ye,

2024

J. Fluid Mech.

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The aeroelasticity of a panel in the presence of a shock is a fundamental issue of great significance in the development of hypersonic vehicles. In practical engineering, cavity pressure emerges as a crucial factor that influences the nonlinear dynamical characteristics of the panel. This study focuses on the aeroelastic bifurcation of a flexible panel subjected to both cavity pressure and oblique shock. To this end, a computational method is devised, coupling a high-fidelity reduced-order model for unsteady aerodynamic loads with nonlinear structural equations. The solution is meticulously tracked by continuous calculations. The obtained results indicate that cavity pressure plays a pivotal role in determining the bifurcation and stability characteristics of the system. First, the system exhibits hysteresis behaviour in response to the ascending and descending dynamic pressures. The evolution of hysteresis behaviour originates from the phenomenon of cusp catastrophe. Second, variations in cavity pressure induce three types of bifurcation phenomena, exhibiting characteristics akin to supercritical Hopf bifurcation, subcritical Hopf bifurcation and saddle-node bifurcation of cycles. The system's response at the critical points of these bifurcations manifests as long-period asymptotic flutter or explosive flutter. Lastly, the evolution of the dynamical system among these three types of bifurcations is an important factor contributing to the discrepancies observed in certain research results. This study enhances the understanding of the nonlinear dynamical behaviour of panel aeroelasticity in complex practical environments and provides new explanations for the discrepancies observed in certain research results.

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Section: Methodsmentioning

confidence: 99%

Section: Methodsmentioning

confidence: 99%

Section: Establishment Of the Reduced-order Model For Unsteady Aerody...mentioning

confidence: 99%

Section: Linear Stability Of Fixed Pointsmentioning

confidence: 99%

See 2 more Smart Citations

On the aeroelastic bifurcation of a flexible panel subjected to cavity pressure and inviscid oblique shock

Zhang,

Ye,

2024

J. Fluid Mech.

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“…In the current research, an in-house code called Generalized Fluid-Structure Interaction, based on the coupled CFD/CSD method, is used to simulate the aeroelastic response of panel flutter induced by oblique shock impingement. The in-house code has been extensively validated and calibrated using real experimental data in previous studies, [41][42][43] and the result of the code has also been compared to other solvers such as Fluent 43 and CFL3D. 44 The aerodynamic loads governed by Euler equations are solved in the CFD simulation, while the nonlinear structure response described by von Kármán's large deflection plate theory is solved based on Galerkin's method in the Computational Structural Dynamics simulation.…”

Section: Methodsmentioning

confidence: 99%

Mechanism of characteristic change of panel flutter caused by oblique shock impingement

Meng,

Ye,

2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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Compared to the shock-free condition, the weak shock impingement stabilizes the flexible panel, while the strong shock impingement leads to the early onset of panel flutter with a significant increase in flutter amplitude and frequency. However, the reason for this change by shock impingement remains unclear. The current research examines the mechanism of this change by an in-house code where the von Kármán’s large deflection plate theory is coupled with two-dimensional Euler equations. Compared to the shock-free condition, the oblique shock impingement leads to the change of local dynamic pressure on the panel as well as the static pressure differential across the panel. The analysis on the influence of these changes indicates that, on the one hand, the average dynamic pressure on the panel becomes larger than the shock-free condition, accelerating the onset of panel flutter. On the other hand, the change of the static pressure differential across the panel alters the coupling characteristic between different natural frequencies (modes) of the panel structure. The dynamic response of panel flutter under shock impingements is dominated by the coupling between the second and third modes instead of the first two modes for panel flutter under the shock-free condition. The combined effect of these two changes leads to the change of flutter characteristics of the panel under shock impingement. These findings provide valuable insights into the mechanism of shock-induced panel flutter.

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Wind turbine blade trailing edge crack detection based on airfoil aerodynamic noise: An experimental study

2022

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Numerical Investigation of Aeroelastic Characteristics of Grid Fin

Cited by 16 publications

References 22 publications

On the aeroelastic bifurcation of a flexible panel subjected to cavity pressure and inviscid oblique shock

On the aeroelastic bifurcation of a flexible panel subjected to cavity pressure and inviscid oblique shock

Mechanism of characteristic change of panel flutter caused by oblique shock impingement

Wind turbine blade trailing edge crack detection based on airfoil aerodynamic noise: An experimental study

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