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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.

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

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