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 during the present study, and three critical flight Mach numbers were considered. At transonic Mach numbers, 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 by initially calculating the mean square acceleration levels induced by the fluctuating pressures distributed over an individual zone, and then summing mean square acceleration levels in one-third octave bands over all zones.
Vibration response of spacecraft shrouds to in-flight fluctuating pressures
22.04.1974
Sonstige
Keine Angabe
Englisch
Vibration response of spacecraft shrouds to in-flight fluctuating pressures
Tema Archiv | 1974
|AIAA | 1976
|AIAA | 1976
Catharpings, swifters and Bentinck shrouds
Online Contents | 2009
|Engineering Index Backfile | 1967
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