Hostname: page-component-586b7cd67f-gb8f7 Total loading time: 0 Render date: 2024-11-25T21:37:36.799Z Has data issue: false hasContentIssue false
  • English
  • Français

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
Get access Rights & Permissions [Opens in a new window]

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 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Smart, D. R. and Gill, K. F. Attitude control of a flexible space vehicle by means of a linear state observer. The Aeronautical Journal , RAeS, Vol 79, pp 86–95, 1975.Google Scholar
2. Smith, E. H. and Gill, K. F. A digital state observer for the attitude control of a flexible space vehicle. The Aeronautical Journal, RAeS, Vol 79, No 779, pp 506–509, 1975.Google Scholar
3. Luenberger, D. G. Observing the state of a linear system. IEEE Trans Mil Elec, MIL-8, pp 74–80, 1974.Google Scholar
4. Hughes, W. G. Design for high precision in spacecraft jet attitude control systems. RAE Tech Rep 71089, April 1971.Google Scholar
5. Smith, E. H. and GILL, K. F. Flexible space vehicle control based on state observation and Lyapunov's method. Proc ESA Symposium on Flexible Space Vehicles. Frascati, Italy, May 1976.Google Scholar
6. Smart, D. R., Gill, K. F., Gething, J. M. and Holt, J. A. Dynamic analysis of flexible space vehicles having uncoupled control axes. The Aeronautical Journal, RAeS, Vol 78, No 768, pp 560–569, 1974.Google Scholar
7. Smith, E. H. and Gill, K. F. Controlling the attitude and two flexure-modes of a flexible space vehicle. The Aeronautical Journal, RAeS, Vol 81, No 793, pp 41-4, January 1977.Google Scholar