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On the design of optimal discrete observers with particular reference to a flexible communications satellite

Published online by Cambridge University Press:  04 July 2016

E. H. Smith DR.  and
K. F. Gill DR.
E. H. Smith DR.
Affiliation:
Formerly University of Leeds, now with Department of Mechanical and Production Engineering, Preston Polytechnic
K. F. Gill DR.
Affiliation:
Department of Mechanical Engineering, Leeds University
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Extract

The electrical power consumed by an Earth-orbiting satellite is usually generated by panels of solar cells. On a vehicle such as the ESA Orbital Test Satellite the panels are attached, in cantilever fashion, to a relatively rigid centre body upon which are positioned the communication systems, attitude sensors and control equipment. The pay-load limitations of the launch vehicle imply that the relatively large solar panels must be of a lightweight construction and they are very flexible structures as a consequence. Currently-operating satellites do not appear to be troubled by the flexure of their solar panels. However, it is likely that attitude control problems will arise in the next generation of vehicles which will be equipped with considerably larger panels of solar cells.

Type
Research Article
Information
The Aeronautical Journal , Volume 82 , Issue 808 , April 1978 , pp. 174 - 177
Copyright
Copyright © Royal Aeronautical Society 1978 

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References

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