Aeroelastic analysis of an idealized landing gear door in subsonic potential flow

Morris, Benjamin; Davis, R. Benjamin

doi:10.1016/j.jfluidstructs.2020.103163

Cited by 2 publications

(1 citation statement)

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“…Li et al (2020) studied the nonlinear dynamics of the rectangular honeycomb sandwich panel. Based on piston theory a great number of papers studied the supersonic aeroelastic behavior of different structures (Morris and Davis, 2020; dos Santos and Marques, 2021; Khalafi and Fazilati, 2018; Wang et al, 2021). Li et al (2020) carried out a nonlinear vibration analysis of cylindrical shells with the points-supported condition.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear aeroelastic analysis of sandwich composite cylindrical panel with auxetic core subjected to the thermal environment

Karimiasl

Alibeigloo

2022

Journal of Vibration and Control

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In this study, nonlinear aeroelastic instability of a composite sandwich panel subjected to a supersonic airflow and thermal loading is investigated. The sandwich panel is composed of three-phase composites with polymer/Graphene platelet/fiber skins at the top and bottom surfaces and an auxetic honeycombs core layer with a negative Poisson’s ratio. The motion equations of the panel within the framework of higher-order shear deformation theory (HSDT) and von Kármán nonlinearity are driven. In addition to Krumhaar’s modified supersonic piston, unsteady aerodynamic pressure in the supersonic flow regime is considered. The governing equations of the sandwich panel are derived by implementing Hamilton’s principle and solved by the generalized differential quadrature method (GDQM). Validation of the present formulation is assessed by comparing the numerical results with those available in the open literature. Then, the effects of several parameters such as geometric parameters, volume fraction, Mach number, different boundary conditions, yaw angle, and different inclined angles on the nonlinear aeroelastic stability of sandwich panels are examined. Finally, it was found that the ratio of core thickness, inclined angle, and Mach number have significant effects on aerodynamic pressure.

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