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An attitude control system for a flexible satellite providing active damping of flexural motion

Published online by Cambridge University Press:  04 July 2016

J. M. Gething  and
K. F. Gill
J. M. Gething
Affiliation:
Formerly University of Leeds, now CEGB, Portishead
K. F. Gill
Affiliation:
Department of Mechanical Engineering, University of Leeds
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Extract

A great deal of interest has been shown in recent years in the problem of flexibility in spacecraft structures. Much published work has been devoted to analysing the dynamic interaction between deformation of flexible appendages and attitude control systems. A limited number of publications have sought to find ways of providing some form of active control of flexible motion. Where this has been attempted idealised systems consisting of flexible coupled pendulums or rotors have been considered.

The problem of flexibility may be tackled in three ways. Where the flexure can be shown to be secondary in nature, careful design of the attitude control system can ensure that interaction is kept to a minimum. To this end surveys of structural flexibility effect in spacecraft are invaluable to the design engineers. Where the flexural motion has a more dominant effect, as will follow from the inevitable increase in power requirements for communications, then a more direct approach will become necessary.

Type
Technical notes
Information
The Aeronautical Journal , Volume 80 , Issue 783 , March 1976 , pp. 134 - 139
Copyright
Copyright © Royal Aeronautical Society 1976 

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References

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