This addendum to an earlier paper1 considers the possibility of obtaining a more appropriate value of the damping time constant T from the knowledge of the characteristic roots. The method used is based on postulating an exponential time function to describe the decay of spacecraft nutation. It is indicated that the present values of T are in closer agreement with those determined approximately in the previous paper.
An Addendum to "The Use of a Spinning Dissipator for Attitude Stabilization of Earth-Orbiting Satellites"
IEEE Transactions on Aerospace and Electronic Systems ; AES-10 , 1 ; 167-168
1974-01-01
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Article (Journal)
Electronic Resource
English
The use of a spinning dissipator for attitude stabilization of earth-orbiting satellites
Tema Archive | 1973
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