Modal and aeroelastic analysis of trapezoidal corrugated-core sandwich panels in supersonic flow

Zhuang, Wenzheng; Yang, Chao; Wu, Zhigang

doi:10.1016/j.ijmecsci.2019.04.052

Cited by 29 publications

(7 citation statements)

References 45 publications

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“…(1) 𝐷 ( 𝜕 4 𝑤 𝜕𝑥 4 + 2 𝜕 4 𝑤 𝜕𝑥 2 𝜕𝑦 2 + 𝜕 4 𝑤 𝜕𝑦 4 ) + 𝜌ℎ 𝜕 2 𝑤 𝜕𝑡 2 = 𝑝(𝑥, 𝑦, 𝑡) Boundary conditions for x=0 or x=Lx in different support modes are defined as follows: In this study, the first order piston theory is used. In this study, it is assumed that the flow only passes through the sheet and on the other side of the sheet there is only static air pressure.…”

Section: Figure1 View Of Rectangular Sheet In Supersonic Air Flowmentioning

confidence: 99%

Aerodynamic modeling and calculating the flutter speed of a rectangular plate in supersonic air flow

nazemizadeh,

Samadi Foroushan,

mohammadi ghanaghestani

2023

MASM

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The presented paper investigates the flutter phenomenon in a rectangular-shaped plate in supersonic air flow. First, the phenomenon of flutter and its identification method based on the analysis of eigenvalues are presented. Then, using the assumptions of Kirchhoff plate, the plate motion equation is derived and coupled with the first-order piston aerodynamic model. Next, the coupled structure-fluid equation is solved in matrix form using the differential quadrature method (DQM). Using the DQM numerical method in matrix form provides advantages such as high accuracy for solving the flutter problem. The obtained results show that the first phenomenon of flutter in an aluminum plate with a length and width of 1 meter and a thickness of 5 mm with clamped-free-clamped-free boundary conditions occurs in dimensionless dynamic pressure 617 (equivalent to Mach 3.395). The presented formulation can be used as a benchmark for solving and calculating the flutter speed of various objects in the supersonic air flow.

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Section: Figure1 View Of Rectangular Sheet In Supersonic Air Flowmentioning

confidence: 99%

Aerodynamic modeling and calculating the flutter speed of a rectangular plate in supersonic air flow

nazemizadeh,

Samadi Foroushan,

mohammadi ghanaghestani

2023

MASM

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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%

“…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.…”

mentioning

confidence: 99%

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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“…Many studies on the mechanical behavior of sandwich panels and panels with corrugated cores were carried out with face sheets and cores all made of isotropic materials. [53][54][55][56][57] The very strong anisotropy and complex behavior of these structures have been pointed out and investigated in detail. Work on the nonlinear vibration of full-filled fluid FGM corrugated cylindrical shells was performed 58 using the homogeneous technique for corrugated panels of Xia et al 53 As pointed out above, there is no research studying the nonlinear buckling of the sandwich CNT-reinforced toroidal shell segments with corrugated core subjected to radial pressure in the thermal environment.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear thermo-elastic stability of corrugated-core toroidal shell segments with carbon nanotube-reinforced face sheets under radial pressure

Vu,

Do,

et al. 2023

Journal of Thermoplastic Composite Materials

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An analytical approach for nonlinear buckling and postbuckling responses of corrugated-core toroidal shell segments with carbon nanotube (CNT) reinforced face sheets in thermal environment subjected to radial pressure is reported in this work. Three distribution laws of functionally graded CNT-reinforced layers and the trapezoidal and round forms of the corrugated core are investigated. An equivalent technique for corrugated panels is improved by adding thermal forces to model the behavior of the corrugated core. The nonlinear equations are formulated by using the geometrically nonlinear Donnell shell theory considering Pasternak’s foundation. An algorithm to solve a system of nonlinear equations is established using the Ritz energy method with three shell deflection amplitudes. The postbuckling expressions between the compressive and tensile loads with maximal deflection and the critical compressive and tensile loads are determined. The numerically investigated examples present the significantly beneficial effects of corrugated core and functionally graded CNT-reinforced face sheets on nonlinear buckling responses of structures.

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Modal and aeroelastic analysis of trapezoidal corrugated-core sandwich panels in supersonic flow

Cited by 29 publications

References 45 publications

Aerodynamic modeling and calculating the flutter speed of a rectangular plate in supersonic air flow

Aerodynamic modeling and calculating the flutter speed of a rectangular plate in supersonic air flow

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

Nonlinear thermo-elastic stability of corrugated-core toroidal shell segments with carbon nanotube-reinforced face sheets under radial pressure

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