Some aspects of cylindrical shell panel flutter.

Carter, L. L.; Stearman, Ronald O.

doi:10.2514/3.4438

Cited by 32 publications

(7 citation statements)

References 4 publications

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“…For the further increasing the pressure, the shell loses stability by coupled-mode flutter once the imaginary part of complex frequency crosses the zero value. Prediction of critical freestream static pressure by using equation (12) is closer to the experimental results than evaluating pressure field by equation (13). The complex frequencies for the case that aerodynamic pressure is evaluated using equation (13) are plotted in fig.…”

Section: Numerical Results and Discussionmentioning

confidence: 99%

Hybrid finite element method in supersonic flutter analysis of circular cylindrical shells

Sabri

Lakis

Toorani³

2009

Mesh Reduction Methods

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This study is focused on the aeroelastic behaviour of circular cylindrical shells in a supersonic airflow. The development is based on a combination of Sanders' thin shell theory and the classical finite element method. Potential and piston theory with and without the correction factor for shell curvature is applied to derive the aerodynamic damping and stiffness matrices. The influence of stress stiffness due to the shell internal pressure and axial loading is also taken into account. Aeroelastic equations in hybrid finite formulation are derived and solved numerically. The effect of shell boundary conditions; geometry and flow parameters on the structure response is investigated. In all study cases, the shell loses its stability by coupled-mode flutter where a travelling wave is observed during this dynamic instability. The results are compared with existing experimental data, other analytical and finite element solutions. The present study shows efficient and reliable results that can be applied for the aeroelastic design of shell structures used for aerospace vehicles.

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Section: Numerical Results and Discussionmentioning

confidence: 99%

Hybrid finite element method in supersonic flutter analysis of circular cylindrical shells

Sabri

Lakis

Toorani³

2009

Mesh Reduction Methods

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“…A complete description of panel flutter modeling is given in his book [2]. A study by Carter and Stearman [9] showed that agreement between the theory and experiments reported in the literature exists in cases that involve a small amount of static preload acting on the shell. Amabili and Pellicano [10] included geometric nonlinearities in their study of the supersonic flutter of a circular cylindrical shell.…”

Section: Introductionmentioning

confidence: 94%

Numerical Investigation of the Flutter of a Spherical Shell

Menaa

Lakis

2013

Journal of Vibration and Acoustics

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In this study, aeroelastic analysis of a spherical shell subjected to external supersonic airflow is carried out. The structural model is based on a combination of the linear spherical shell theory and the classic finite element method (FEM). In this hybrid method, the nodal displacements are found from the exact solution of shell governing equations rather than approximated by polynomial functions. Therefore, the number of elements chosen is a function of the complexity of the structure. Convergence is rapid. It is not necessary to choose a large number of elements to obtain good results. Linearized first-order potential (piston) theory with the curvature correction term is coupled with the structural model to account for pressure loading. The linear mass, stiffness, and damping matrices are found using the hybrid finite element formulation. Aeroelastic equations are numerically derived and solved. The results are validated using the numerical and theoretical data available in literature. The analysis is accomplished for spherical shells with different boundary conditions, geometries, flow parameters, and radius to thickness ratios. the results show that the spherical shell loses its stability through coupled-mode flutter. This proposed hybrid FEM can be used efficiently for the design and analysis of spherical shells employed in high speed aircraft structures.

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“…For this case, the finer mesh is chosen for the zones close to the fluid free surface and clamped boundary condition, and the converged results are obtained by n x = 12 and n y = 88. It is important to note that several studies, such as the study conducted by Carter and Stearman, 6 considered different values for L = 16 in (0.406 m), E = 13 × 10 6 psi (8.96 × 10 10 N/m 2 ), and = 0.33. As mentioned by Sabri and Lakis, 13 the former is referred to as Case I, and the latter is called Case II.…”

Section: Vibration Analysis Of a Partially Liquid-filled Circular Cylmentioning

confidence: 99%

“…3 To capture the circumferentially traveling wave flutter mode observed during the experimental test, Evensen and Olson 1,5 conducted a study by including geometric nonlinearities in the theoretical model by applying a four-mode expansion for the shell deflection. In a work that aimed to account for the discrepancies between theory and experiment observations reported in the literature, Carter and Stearman 6 found that a preflutter configuration did not notably influence the flutter boundary. It was also found that the agreement between theory and experiment existed only for a small amount of static preload.…”

Section: Introductionmentioning

confidence: 97%

Sloshing effects on supersonic flutter characteristics of a circular cylindrical shell partially filled with liquid

Zarifian

Ovesy

Firouz-Abadi

2018

Numerical Meth Engineering

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Summary This paper aims to revisit the effect of sloshing on the flutter characteristics of a partially liquid‐filled cylinder. A computational fluid‐structure interaction model within the framework of the finite element method is developed to capture fluid‐structure interactions arising from the sloshing of the internal fluid and the flexibility of its containing structure exposed to an external supersonic airflow. The internal liquid sloshing is represented by a more sophisticated model, referred to as the liquid sloshing model, and the shell structure is modeled by Sanders' shell theory. The aerodynamic pressure loading is approximated by the first‐order piston theory. The initial geometric stiffness due to prestresses in the initial configuration stemming from the fluid hydrostatic pressure, internal pressure, and axial compression load is also considered. The obtained results reveal that the sloshing of the internal fluid has little influence on the supersonic flutter boundary of a cylinder partially filled with liquid, at least for the case considered here. It is also shown that the critical freestream static pressure predicted by the sloshing model is negligibly larger than that calculated by the hydroelastic model of the internal fluid, which means that the sloshing of the internal fluid slightly overestimates the flutter boundary.

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Some aspects of cylindrical shell panel flutter.

Cited by 32 publications

References 4 publications

Hybrid finite element method in supersonic flutter analysis of circular cylindrical shells

Hybrid finite element method in supersonic flutter analysis of circular cylindrical shells

Numerical Investigation of the Flutter of a Spherical Shell

Sloshing effects on supersonic flutter characteristics of a circular cylindrical shell partially filled with liquid

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