Instrument-induced pointing stability and jitter are significant design drivers for the Earth Observing System (EOS) AM spacecraft. Techniques for determining the rigid and flexible body pointing jitter contributions have been developed and applied to the EOS AM spacecraft. The contribution of each instrument on itself, on the spacecraft and on other instruments is addressed. Rigid body effects are separated from flexible body effects to allow focus on the localized vibrational jitter.
EOS instrument jitter assessment and mitigation
AIAA, AHS, and ASEE, Aerospace Design Conference ; 1993 ; Irvine, CA, United States
1993-02-01
Conference paper
No indication
English
Solar Dynamics Observatory On-orbit Jitter Testing, Analysis, and Mitigation Plans
British Library Conference Proceedings | 2011
|Electro-Optic Time-to-Space Converter for Optical Detector Jitter Mitigation
Online Contents | 2013