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3 edition of User"s guide to a system of finite-element supersonic panel flutter programs found in the catalog.

User"s guide to a system of finite-element supersonic panel flutter programs

User"s guide to a system of finite-element supersonic panel flutter programs

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Published by National Aeronautics and Space Administration, Langley Research Center, For sale by the National Technical Information Service in Hampton, Va, [Springfield, Va .
Written in English

    Subjects:
  • Aerodynamics, Supersonic.,
  • Flutter (Aerodynamics)

  • Edition Notes

    StatementChristine L. Woolley and John T. Batina.
    SeriesNASA technical memorandum -- 104019.
    ContributionsBatina, John T., Langley Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15355981M

    Flutter of panels can be of two possible types: single mode or coupled mode flutter. Coupled mode flutter has been thoroughly studied using piston theory, which represents air pressure acting on the plate at high Mach numbers. Single mode flutter cannot be studied using piston theory and requires potential flow theory or more complex aerodynamic theories. This type of flutter occurs at low. Flutter in the supersonic regime – wing and panel flutter Effect of nonlinearities – limit cycle oscillations Examples 12 Aeroservoelasticity Mathematical modelling of a simple aeroelastic system with a control surface Inclusion of gust terms Implementation of a control system

    This report is part of the RAND Corporation paper series. The paper was a product of the RAND Corporation from to that captured speeches, memorials, and derivative research, usually prepared on authors' own time and meant to be the scholarly or scientific contribution of individual authors to their professional fields. In high-speed aerospace vehicles, supersonic flutter is a well-known phenomenon of dynamic instability to which external skin panels are prone. In theory, the instability stage is expressed by the 'flutter critical parameter' Q(crit), which is a function of the stiffness-, and dynamic pressure parameters. For a composite skin panel, Q(crit) can be maximised by lay-up optimisation.

    A 3-DOF dynamic model is used for a 2-D airfoil with a control surface. The cubic nonlinear structural stiffness is considered in this model, and the aerodynamic load in the supersonic airflow is obtained by 3rd order Piston Theory. Nonlinear flutter happens with a phenomenon of limit cycle oscillations (LCOs) when the flight speed reaches the critical speed. In this study, aeroelastic analysis of a plate subjected to the external supersonic airflow is carried out. A 3-D rectangular plate element of variable thickness based on absolute nodal coordinate formulation (ANCF) has been developed for the structural model. In the approach to the problem, a continuum mechanics approach for the definition of the elastic forces within the finite element is.


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User"s guide to a system of finite-element supersonic panel flutter programs Download PDF EPUB FB2

Get this from a library. User's guide to a system of finite-element supersonic panel flutter programs. [Christine L Woolley; John T Batina; Langley Research Center.].

USER'S GUIDE TO A SYSTEM OF FINITE-ELEMENT SUPERSONIC PANEL PROGRAMS Christine I. Woolley John T. Batina NASA Langley Research Center Hampton, Virginia SUMMARY The utilization and operation of a set of six computer programs for the prediction of panel flutter at supersonic speeds by finite-element methods are described.

The. A finite element method is developed for studying the supersonic flutter analysis of arbitrary skewed and cracked panels. The finite element method employs a 48 degrees of freedom general plate element based on tensorial mathematics and using classical lamination theory, and linearized piston aerodynamic by:   The flutter motion shapes also reveal information on the jump behavior mechanism.

Fig. 7 depicts the shapes of the panel at pre- and post-jump condition. As already observed by Pacheco et al. for the two-bay [0 ° 90 ° 0 °] s composite panel the triggering point to the jump is the increase in rotation at the common edge between bays.

It demonstrates that the jump happens when the motion Cited by: 1. The detailed analysis for supersonic panel flutter under thermal environment with flow in arbitrary direction has been presented by Mukherjee et al [9,10].

FORMULATION FOR SUPERSONIC PANEL FLUTTER The panel configuration (a×b, thickness h) of the simply supported panel and its finite element discretization are shown in Fig 1.

FINITE ELEMENT STUDIES ON SUPERSONIC PANEL FLUTTER UNDER HIGH THE RMAL ENVIRONMENT WITH ARBITRARY FLOW DIRECTION. Analytical Formulation for Supersonic Panel Flutter 2 Basic equations 3 Solution of the differential equation 4 Finite Element Formulation for Supersonic Panel Flutter 5 Strain Energy 6 Work done due to in-plane stress resultant 6 Expression for Aerodynamic loads 7 Kinetic Energy 7.

A review of various analytical methods and experimental results of supersonic and hypersonic panel flutter is presented.

The analytical methods are categorized into two main methods. The first category is the classical methods, which include Galerkin in conjunction with numerical integration, harmonic balance and perturbation methods.

Finite element supersonic flutter analysis of low aspect ratio stiffened wing 4 September | Journal of Vibration and Control, Vol. 19, No. 14 A study on the aero-elastic flutter of stiffened laminated composite panel in the supersonic flow. Dowell, E. [] “ Panel flutter: A review of the aeroelastic stability of plates and shells,” AIAA Journal 8(3), – Crossref, Google Scholar; Gordnier, R.

and Fithen, R. [] “ Coupling of a nonlinear finite element structural method with a Navier-Stokes solver,” Computers and Structu.

A finite element formulation (employing the Kirchoff plate C1 bending element) has been developed here for supersonic flutter analysis of simply supported rectangular panels without in-plane edge.

Supersonic panel Flutter characteristic Piston theory Assumed mode method Finite element method Elastically restrained boundary 1 Introduction Flutter, a kind of self-excited oscillation, is caused by the coupling effect of the aerodynamic load, the elastic force as well as the inertial force of the structure.

Aeroelastic analysis and active flutter suppression of an electro-rheological sandwich cylindrical panel under yawed supersonic flow Aerospace Science and Technology, Vol. 42 Nonlinear Thermal Flutter Analysis of Supersonic Composite Laminated Panels Using Differential Quadrature Method.

Accurate Prediction of Panel Flutter Applicable to Supersonic or High Lift Flight: Results and Comparison to NASA Wind Tunnel Data. Avoiding flutter of an aircraft's skin is important for safe and robust operation.

Traditional panel flutter prediction tools fall short for conditions where the boundary layer thickness varies. The problem of panel flutter in a supersonic flow is treated in three parts. In the first the flutter of a simply supported rectangular plate is studied.

Only small deflections are considered so that linear plate theory may be used. The flutter mode is described by a series expansion in terms of the normal modes of oscillation of the plate in a vacuum. Hybrid finite element method in supersonic flutter analysis of circular cylindrical shells F.

Sabri1, of panel flutter modelling has been addressed in his monograph [6]. Amabili and Pellicano [7] developed a model considering the geometric nonlinearities to study the supersonic flutter of the circular cylindrical shell.

They also applied the. The system is discretized by Galerkin method and is investigated by using a model involving up to 22 degrees-of-freedom, allowing for travelling-wave flutter around the shell and axisymmetric contraction of the shell.

Asymmetric and axisymmetric geometric imperfections of circular cylindrical shells are taken into account. Supersonic flutter analysis of laminated composite curved panels is investigated using doubly-curved, quadrilateral, shear flexible, shell element based on field-consistency approach.

The model adopted the von Karman large deflection plate theory for the geometrical nonlinearity, and the third order piston theory for the supersonic aerodynamic loads. Convergence and accuracy studies were carried out to verify the proposed approach.

Finally, the nonlinear thermal flutter characteristics of a supersonic composite panel were. nonlinear supersonic panel flutter using SMA.

The finite element system equations of motion for a composite panel embedded with prestrained SMA at supersonic speeds and elevated temperatures are derived. The von Karman large-deflection strain-displacement relations and the laminated composite plate theory are employed.

The flutter instability of stiffened composite panels subjected to aerodynamic forces in the supersonic flow is investigated. Based on Hamilton’s principle, the aeroelastic model of the composite panel is established by using the von Karman large deflection plate theory, piston theory aerodynamics and the quasi-steady thermal stress theory.

Then, using the finite element method along with.Brief reviews on suppressing panel flutter vibrations by various active control strategies as well as utilization tunable electrorheological fluids (ERFs) for vibration control of structural systems are presented.

Active suppression of the supersonic flutter motion of a simply supported sandwich panel with a tunable ERF interlayer, and coupled to an elastic foundation, is subsequently.curved panels under a yawed supersonic flow. In the sixties and early seventies researchers have investigated the effect of yawing flows on the flutter stability boundaries of isotropic and orthotropic flat rectangular panels at supersonic speeds.

Several review articles devoted sections to the influence of yaw flow angle [1, 2] on panel flutter.