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Attitude Dynamics and Stability Conditions of a Non-Rigid Spinning Satellite

Published online by Cambridge University Press:  07 June 2016

L. C. Rossi ,
R. C. Michelini Di San Martino  and
R. Ghigliazza
L. C. Rossi
Affiliation:
Institute of Applied Mechanics, University of Genoa
R. C. Michelini Di San Martino
Affiliation:
Institute of Applied Mechanics, University of Genoa
R. Ghigliazza
Affiliation:
Institute of Applied Mechanics, University of Genoa
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Summary

The attitude dynamics of a spinning satellite containing an elastically-restrained, viscously-damped mass, is investigated. This non-rigidity approximately represents the interesting practical case of equipment supported by relatively soft anti-shock mountings and the case of a particular viscous nutation damper. The linearised differential equations and the transfer functions relating the dynamic behaviour of the oscillating mass to the spinning-body components of the angular speed and the external torque are determined. On these grounds, the possibility of unstable configurations is singled out and discussed, and the stability condition is established, within the small perturbation approximations. Furthermore, the attitude dynamics for the satellite, both for large manoeuvres and fine corrections, is obtained by applying a train of pulsed torques by means of a suitable control logic and mass-ejection jets. The results are compared with those obtained from rigid-body theory. It is demonstrated that comparatively wide nutations may be produced, and the influence of the relevant parameters is determined.

Type
Research Article
Information
Aeronautical Quarterly , Volume 20 , Issue 3 , August 1969 , pp. 223 - 236
Copyright
Copyright © Royal Aeronautical Society. 1969

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