The authors describe a technique in which measurements from only two sensors are used in estimating the structural bending modes as well as the forced harmonics of a large space structure. A step-by-step approach is used to identify structural flexing via the filter error method of the maximum-likelihood formulation with a minimum number of sensors. The methodology was applied to actual spacecraft flight data and satisfactory results were obtained.
Parameter estimation of spacecraft structural dynamics from flight test data
Parameterschaetzung der Raumfahrzeugdynamik aus Flugtestdaten
1988
2 Seiten, 6 Quellen
Aufsatz (Konferenz)
Englisch
Estimation of in-flight structural dynamics models of a spacecraft launcher
British Library Conference Proceedings | 1998
|NTIS | 1991
|NTIS | 1981
|Structural Mode Identification of Galileo Spacecraft from Flight Data
British Library Conference Proceedings | 1994
|