This paper presents the results of a preliminary Control/Structure Interaction study of the Space Station Freedom. Assembly Work Platform and the Space Transportation System orbiter dynamics coupled with the orbiter and station control systems. The first three station assembly flight configurations and their finite element representations are shown. Performance between each of these configurations is compared in terms of control authority achieved in each axis, and the propellant usage. During deployment of the station truss, the inertias of the coupled spacecraft have shown to vary significantly. The control systems design parameters during assembly operations have been computed and the result of encountering low roll attitude control authority due to a significant change in the inertia properties is presented. Even though the rigid body response is acceptable with the orbiter Primary Reaction Control System, the flexible body response showed that the structural deflections and loads are quite large. It was found, as a special case, that if the stiffness of the Assembly Work Platform is assumed equivalent to that of the station truss, severe Control/Structure Interaction is observed. The robustness of the orbiter Vernier Reaction Control System to small changes in inertia properties is demonstrated by rotating a portion of the truss which alters the modal characteristics.
Preliminary control/structure interaction study of coupled space station freedom/assembly work platform/orbiter
Vorlaeufige Untersuchung der Wechselwirkung zwischen Regelung und Aufbau bei Montagearbeiten an einer Raumstation mit umlaufender Plattform
AIAA-Papers ; Jan ; 1-14
1988
14 Seiten, 18 Bilder, 5 Tabellen, 14 Quellen
Aufsatz (Konferenz)
Englisch
Space Station Freedom Attitude Control During Orbiter Berthing
British Library Conference Proceedings | 1993
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