Aeroelastic analysis of foam-filled composite corrugated sandwich plates using a higher-order layerwise model

Zhuang, Wenzheng; Yang, Chao; Wu, Zhigang

doi:10.1016/j.compstruct.2020.112996

Cited by 7 publications

(4 citation statements)

References 46 publications

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“…As shown in Figure 16, Zhuang et al 239,240 employed an analytical mathematical model to analyze the flutter characteristics of a trapezoidal corrugated core sandwich panel and a foam‐filled composite corrugated sandwich panel under supersonic airflow. The corrugated core was homogenized as an equivalent orthotropic layer and the overall sandwich panel was divided into three sections through thickness.…”

Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

“…(A) A foam‐filled corrugated core sandwich panel in supersonic airflow, and (B) the effects of corrugation orientation on flutter bounds of the panel with variable reference Mach numbers. Reproduced with permission 239 . Copyright 2021, Elsevier…”

Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

“…Khorshidi and Karimi238 presented an analytical model to study the aeroelastic behaviors of sandwich panels with functionally graded face sheets under the combined action of the aerodynamic pressure and thermal load. The effects of parameters including the aspect ratio, temperature change, and power law index on the flutter bounds of the sandwich panels were analyzed.As shown in Figure16, Zhuang et al239,240 employed an analytical mathematical model to analyze the flutter characteristics of a trapezoidal corrugated core sandwich panel and a foam-filled composite corrugated sandwich panel under supersonic airflow. The corrugated core was homogenized as an equivalent orthotropic layer and the overall sandwich panel was divided into three sections through thickness.…”

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confidence: 99%

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Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

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Flutter is a self-excited vibration under the interaction of the inertial force, aerodynamic force, and elastic force of the structure. After the flutter occurs, the aircraft structures will exhibit limit cycle oscillation, which will cause catastrophic accidents or fatigue damage to the structures. Therefore, it is of great theoretical and practical significance to study the aeroelastic characteristics and flutter control for improving the aeroelastic stability of aircraft structures. This paper reviews the recent advances in aeroelastic analysis and flutter control of wings and panel structures. The mechanism of aeroelastic flutter of wings and panels is presented. The research methods of aeroelastic flutter for different structures developed in recent years are briefly summarized. Various control strategies including the linear and nonlinear control algorithms as well as the active flutter control results of wings and panels are presented. Finally, the paper ends with conclusions, which highlight challenges of the development in aeroelastic analysis and flutter control, and provide a brief outlook on the future investigations. This study aims to present a comprehensive understanding of aeroelastic analysis and flutter control. It can also provide guidance on the design of new wings and panel structures for improving their aeroelastic stability.

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Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

Section: Research Status Of Aeroelastic Analysismentioning

confidence: 99%

mentioning

confidence: 99%

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Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

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“…Also, the only aeroelastic analysis of foam-filled composite corrugated sandwich plates was done recently. 12 Zhang et al 13 studied an investigation on the vibrations and flutter of a honeycomb sandwich plate with zero Poisson’s ratio under supersonic airflow. Therefore, developing innovative ways to improve the aeroelastic properties of aerospace high-speed vehicle panels is essential.…”

Section: Introductionmentioning

confidence: 99%

Aeroelastic analysis of a lightweight topology-optimized sandwich panel

Najafi,

Ferreira,

Marques

2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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Sandwich structures with lattice cores are novel, lightweight composite structures and are widely used in the aerospace industry. Besides, the aeroelastic behavior of sandwich panels in a supersonic flow regime still needs to be thoroughly studied. This work investigates the supersonic flutter of a sandwich panel whose core is topology-optimized. A finite element model of a sandwich panel based on the layerwise theory, coupled with the first-order piston theory, is presented. The sandwich panel core is assessed using a topology optimization approach with flutter loading constraints. The subsequent analytical homogenization scheme is developed to provide the equivalent mechanical properties of the topology-optimized panel. The modeling approach is fully validated, and the results demonstrate that the sandwich panel is capable of enlarging the flutter-free operational flight range when compared with other conventional panel designs. A parametric analysis of the topology-optimized sandwich panel regarding the critical flutter conditions is performed.

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