Results are presented for the vibration response of a spacecraft shroud to a range of in-flight fluctuation pressures. An Atlas-Agena 15 degree cone-cylinder shroud was analyzed, and three critical flight Mach numbers were considered. At transonic Mach numbers considered during this investigation (M;=0.7 and M;=0.8), the aerodynamic flow over the shroud is complex, involving zones of regular attached flow, separated flow, shock wave oscillation and modified attached flows induced by local thickening of the boundary layer. The overall shroud vibration levels for a particular Mach number were determined. Over most of the frequency range of interest, the vibration levels induced during transonic flight are considerably higher than the vibration levels induced during maximum dynamic pressure (qmax) at M;=2.0. At frequencies well above the ring frequency of the shroud, however, this situation is reversed, and vibration levels during qmax are higher than those during transonic flight. This is shown to be due to hydrodynamic coincidence effects where matching between the flexural and pressure wavelengths results in a number of near-coincident modes contributing significantly to the vibration levels. A discussion is given of the relative effects of the various fluctuating pressure environments distributed over discrete zones on the shroud surface


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    Title :

    Vibration response of spacecraft shrouds to in-flight fluctuating pressures


    Additional title:

    Schwingungsverhalten von Raumfahrzeug-Ummantelungen gegenueber schwankenden Druecken waehrend des Fluges


    Contributors:

    Published in:

    Publication date :

    1974


    Size :

    , 23 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English