Along with technology advances in the field of optical and laser payload, spacecraft pointing accuracy requirements become more and more severe, especially for scientific and Earth observation satellites. Attitude and orbit control equipments and payload moving parts generate in-orbit microvibrations which are critical to instruments line of sight pointing performance. A number of activities aimed at characterizing the in-orbit microvibrations endured by spacecraft payloads such as SPOT 4, SILEX, and SOHO were undertaken. A ground test campaign performed on SPOT flight model 3 is focused on. Primary objectives were to measure the structural damping coefficient. The test led to the conclusion that damping coefficients of 0.5 can be anticipated in orbit. It also demonstrated a relatively good representativeness of finite element models used for performance predictions.
Influence of Microvibrations on Spacecraft Performances
1991
6 pages
Report
No indication
English
Unmanned Spacecraft , Manned Spacecraft , Pointing control systems , Spacecraft control , Structural vibration , Vibration damping , Dynamic structural analysis , Finite element method , Performance prediction , Spacecraft performance , Spacecraft structures , Coefficients , Payloads , Spot (French satellite) , Vibration tests , Foreign technology
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