Hostname: page-component-586b7cd67f-t8hqh Total loading time: 0 Render date: 2024-11-22T05:10:51.207Z Has data issue: false hasContentIssue false
  • English
  • Français

Attitude estimation and control of a flexible spacecraft using inertial and optical measurements

Published online by Cambridge University Press:  04 July 2016

D. Horton ,
J. Fenton  and
K. F. Gill
D. Horton
Affiliation:
Department of Mechanical Engineering, The University of Leeds
J. Fenton
Affiliation:
Department of Mechanical Engineering, The University of Leeds
K. F. Gill
Affiliation:
Department of Mechanical Engineering, The University of Leeds
Get access Rights & Permissions [Opens in a new window]

Extract

It is envisaged that future earth resources satellites will be required to perform frequent attitude manoeuvres and also to maintain a given orientation to within a few seconds of arc. These requirements place a severe demand on the attitude measurement and control systems used, and this, demand is increased when the satellite needs to carry large flexible solar arrays.

By combining inertial and optical measurements using an optimal filter, an attitude estimate can be obtained for which the error components are minimised over a wide frequency band. Jude, used intermittent star sensor readings to update the attitude and gyroscope drift estimates from an optimal filter and he noted that it would be useful to study the effect of mismatch between actual sensor models and those assumed in the computation of the optimal filter. Jude's recommendation is investigated in this paper.

Type
Research Article
Information
The Aeronautical Journal , Volume 85 , Issue 845 , June 1981 , pp. 240 - 243
Copyright
Copyright © Royal Aeronautical Society 1981 

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. Bryson, A. E. and Kortum, W. Estimation of the local attitude of orbiting spacecraft, Automatica, Vol 7, pp 163–180, Pergamon Press, 1971.Google Scholar
2. Jordan, J. F., Madrid, B. A. and Pease, G. E. Effects of major error sources on planetary spacecraft navigation accuracies, Journal of Spacecraft & Rockets, Vol 9, No 3, pp 196–204, March 1972.Google Scholar
3. Jude, R. J. System study of an inertial attitude measurement system for earth pointing satellites. Proceedings of the Attitude and Orbit Control Systems Conference, ESASP-128,pp 131–144, November 1977.Google Scholar
4. Hewer, G. A. An iterative technique for the computation of the steady state gains for the discrete optimal regulator, IEEE Trans. Automatic Control, Vol AC-16, pp 382–383, August 1971.Google Scholar