An Addendum to "The Use of a Spinning Dissipator for Attitude Stabilization of Earth-Orbiting Satellites"

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.