The aeroelastic equations of motion governing a hypersonic vehicle in free flight are derived. The equations of motion for a translating and rotating flexible body using Lagrange's equations in terms of quasi-coordinates are presented. These equations are simplified for the case of a vehicle with pitch and plunge rigid body degrees of freedom and small elastic displacements. The displacements are approximated by a truncated series of the unrestrained mode shapes, which are obtained using equivalent plate theory. Subsequently, the nonlinear equations of motion are linearized about the trim state, which is obtained using a rigid body trim model and steady hypersonic aerodynamics. The appropriate flutter derivatives are calculated from piston theory. Results describing mode shapes, trim behavior, and aeroelastic stability of a generic hypersonic vehicle are presented.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Aeroelastic Analysis of a Trimmed Generic Hypersonic Vehicle


    Contributors:


    Publication date :

    1999-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Aeroelastic Analysis of a Trimmed Generic Hypersonic Vehicle

    Nydick, I. / Friedmann, P. P. | British Library Online Contents | 1997



    Aeroelastic Analysis of a Trimmed Generic Hypersonic Vehicle

    Nydick, I. / Friedmann, P. / AIAA et al. | British Library Conference Proceedings | 1996


    Aeroelastic Analysis of a Trimmed Generic Hypersonic Vehicle

    Nydick, I. / Friedmann, P. P. / Confederation of European Aerospace Societies et al. | British Library Conference Proceedings | 1999