The Hubble Space Telescope features the most exacting line of sight jitter requirement thus far imposed on a spacecraft pointing system. Consideration of the fine pointing requirements prompted an attempt to isolate the telescope from the low level vibration disturbances generated by the attitude control system reaction wheels. The primary goal was to provide isolation from axial component of wheel disturbance without compromising the control system bandwidth. A passive isolation system employing metal springs in parallel with viscous fluid dampers was designed, fabricated, and space qualified. Stiffness and damping characteristics are deterministic, controlled independently, and were demonstrated to remain constant over at least five orders of input disturbance magnitude. The damping remained purely viscous even at the data collection threshold of .16 x .000001 in input displacement, a level much lower than the anticipated Hubble Space Telescope disturbance amplitude. Vibration attenuation goals were obtained and ground test of the vehicle has demonstrated the isolators are transparent to the attitude control system.
Workshop on Structural Dynamics and Control Interaction of Flexible Structures
1987
22 pages
Report
Keine Angabe
Englisch
Spacecraft Control/Flexible Structures Interaction Study
NTIS | 1974
|Spacecraft control/flexible structures interaction study
NTRS | 1974
|Dynamics and Control of Large Flexible Space Structures
British Library Conference Proceedings | 1996
|