Theoretical analysis for the effect of static pressure differential on aeroelastic stability of flexible panel

Ye, Liuqing; Ye, Zhengyin

doi:10.1016/j.ast.2020.106428

Cited by 9 publications

(2 citation statements)

References 49 publications

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“…Another work (Dowell 1982) reported the suppressive effect of static pressure difference on the chaotic response of buckled panels. Ye & Ye (2021) theoretically studied the stability boundary of panels in supersonic airflow using the Lyapunov method, emphasising the significant role of the coupling between static deformation and aerodynamic forces in greatly enhancing the aeroelastic stability of the panel. Under the presence of shock, Visbal (2014) conducted preliminary research on three different cavity pressure cases in inviscid flow, and the results indicated that the variation of cavity pressure has a significant impact on the characteristics of the dynamical system.…”

Section: Introductionmentioning

confidence: 99%

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: Introductionmentioning

confidence: 99%

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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“…For inviscid simulations, the free-stream pressure is specified as the pressure of the backside of the panel. However, for viscous simulations, Dowell [10,11] and Ye [49] have pointed out that even small pressure differentials across the panel can lead to significant changes in the panel response.…”

mentioning

confidence: 99%

Analysis of the post-flutter aerothermoelastic characteristics of hypersonic skin panels using a CFD-based approach

Quan

Yao

et al. 2021

Aerospace Science and Technology

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Aeroelastic stability analysis of a flexible panel subjected to an oblique shock based on an analytical model

et al. 2021

Acta Mech

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Theoretical analysis for the effect of static pressure differential on aeroelastic stability of flexible panel

Cited by 9 publications

References 49 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

Analysis of the post-flutter aerothermoelastic characteristics of hypersonic skin panels using a CFD-based approach

Aeroelastic stability analysis of a flexible panel subjected to an oblique shock based on an analytical model

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