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Flexible spacecraft attitude control using a simple P + D algorithm

Published online by Cambridge University Press:  04 July 2016

J. Fenton  and
K. F. Gill
J. Fenton
Affiliation:
Department of Mechanical Engineering, University of Leeds
K. F. Gill
Affiliation:
Department of Mechanical Engineering, University of Leeds
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Extract

Two philosophies for the attitude control of space vehicles with flexible appendages have appeared in the literature, these are:

  1. (i) control of the rigid centre body to lie within some bounded region while the flexural vibrations are allowed to behave in an uncontrolled manner;

  2. (ii) control of all plant states to some finite value as time tends to infinity.

The former method does not require flexural information and therefore avoids the on-board computational burden associated with state estimation, or the cost of additional instrumentation. However, attitude degradation has been observed and reported indicating a clear need to compensate for structural vibrations.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 85 , Issue 844 , May 1981 , pp. 185 - 189
Copyright
Copyright © Royal Aeronautical Society 1981 

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References

1. Beysens, A. Design of a control loop with flexibility and in-flight identification of the flexible modes. Dynamics and Control of Non-rigid Spacecraft, ESA SP-117, pp 273–283, July 1976.Google Scholar
2. Harris, R. S., and Todman, D. C. Three axis control of spacecraft with large flexible appendages. Dynamics and Control of Non-rigid Spacecraft, ESA SP-117, pp 285–296, July 1976.Google Scholar
3. Gething, J. M. and Gill, K. F. An attitude control system for a flexible satellite providing active damping of flexural motion. The Aeronautical Journal of the Royal Aeronautical Society, Vol 80, No 783, pp 134–139, March 1976.Google Scholar
4. Larson, V., Likins, P., and Marsh, E. Optimal estimation and attitude control of a solar electric propulsion spacecraft. Transactions IEEE, Vol AES-13, No 1, pp 35–46, January 1977.Google Scholar
5. Noll, R. B., Deyst, J. J., and Spenny, C. H. A survey of structural flexibility effects on spacecraft control systems. AIAA Paper No 69-116, presented at the AIAA 7th Aerospace Science Meeting, New York, 20th-22nd January, 1969.Google Scholar
6. Likins, P. W. Interactive problems between the dynamics and control system for non-rigid spacecraft. Dynamics and Control of Non-rigid Spacecraft, ESA SP-117, pp 265–271, July 1976.Google Scholar
7. Paraskevopoulos, P. N. On pole assignment by proportional plus derivative output feedback. Electronics Letters, Vol 14, No 2, pp 34–35, January 1976.Google Scholar
8. Anderson, B.D.O., and Moore, J. B. Linear Optimal Control. 1st Edition, Prentice-Hall, 1971.Google Scholar
9. Klienman, D. L. An easy way to stabilise a linear constant system. IEEE Transactions of Automatic Control, Vol AC 15, pp 692, December 1970.Google Scholar