Finite element studies on supersonic panel flutter under high thermal environment with arbitrary flow direction

Mukherjee, Somenath and Manjuprasad, M and Avinash, R and Sakravarthini, Deepa S (2007) Finite element studies on supersonic panel flutter under high thermal environment with arbitrary flow direction. Technical Report. National Aerospace Laboratories, Bangalore, India.

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    Abstract

    Panels of re-entry vehicles are subjected to a wide range of flow conditions during ascent and re-entry phases. The flow can vary from subsonic continuum flow to hypersonic rarefied flow with wide ranging dynamic pressure and associated aerodynamic heating. One of the main design considerations is the assurance of safety against panel flutter under the flow conditions characterized by harsh thermal environment. The objectives of this work are to understand the physical principles behind panel flutter under supersonic flow and to make an estimate of the lowering of the critical dynamic pressure (flutter boundary) of the panels due to thermal distributions.13; Analytical and Finite element formulation have been developed for supersonic flutter analysis of rectangular panels subjected various thermal profiles. The piston theory is used for aerodynamic pressure computations. Panels with simply supported edges (with and13; without in-plane edge constraints) have been studied.13; The results obtained by NASTRAN for flow along panel edges are in good agreement with those obtained using the analytical method and the in-house FEM code. From the13; analysis of the results for various flow directions it has been observed that the flow along the longer sides of the panels is most critical. For simply supported panels with no in-plane edge constraints a thermal gradient can cause a drastic fall in the flutter boundary due to in-plane13; thermal stresses that effectively reduce structural stiffness. In-plane edge constraints to thermal expansion further lower the flutter boundary.The present study will be useful for the purpose of panel design in re-entry launch vehicles and supersonic fighter aircrafts.

    Item Type: Proj.Doc/Technical Report (Technical Report)
    Uncontrolled Keywords: Supersonic panel flutter;Critical dynamic pressure;Flutter speed;High thermal profile;Flow direction;In-plane loads
    Subjects: ENGINEERING > Structural Mechanics
    Division/Department: Structures Division, Structures Division, Structures Division, Structures Division
    Depositing User: M/S ICAST NAL
    Date Deposited: 19 Jan 2009
    Last Modified: 17 Jun 2010 10:33
    URI: http://nal-ir.nal.res.in/id/eprint/4645

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