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Non-active nutation damping for single-spin spacecraft of all mass distributions

Published online by Cambridge University Press:  04 July 2016

S. W. Tonkin
S. W. Tonkin*
Affiliation:
Space Systems and Sounding Rockets, British Aircraft Corporation
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Extract

The purpose of this paper is to describe a new component for spacecraft. The subject is not quite new in that the author presented a paper (Ref. 1) on the subject this year.

The original idea for the device came from thoughts about an extension beyond the terms of reference of a study contract. After a proposal had been made it became apparent that Cloutier of Hughes Aircraft had made a remotely similar proposal, but apart from its mention in some letters, no publication has been seen by the author.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 80 , Issue 789 , September 1976 , pp. 394 - 401
Copyright
Copyright © Royal Aeronautical Society 1976 

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References

1. Tonkin, S. W. A semi-active nutation damper for spinning prolate or oblate satellites. Proceedings of the VIIth IFAC Symposium on Automatic Control in Space. 17th—21st May 1976.Google Scholar
2. Landon, V. D. The rotational stability of a body containing a rotor. Internal RCA report. About 1962.Google Scholar
3. Landon, V. D. and Stewart, B. Nutational stability of an axisymmetric body containing a rotor. Journal of Spacecraft and Rockets, Vol 1. November-December 1964.Google Scholar
4. Iorillo, A. J. Nutation damping dynamics of rotor stabilised satellites. ASME Winter Meeting, 1965.Google Scholar
5. Iorillo, A. J. Improvements in and relating to spacecraft. British Patent No 1,167,997. Original US filing date 25th July 1966.Google Scholar
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9. Craig, R. J. G. Theory of operation of an elastically supported tuned gyroscope. IEEE Trans on Aerospace & Electronic Systems, Vol AES-8, No 3. May 1972.Google Scholar