NUTATIONAL DAMPING OF A SLOWLY SPINNING SATELLITE STABILIZED BY USE OF A ROTOR.
JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB
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The nutational damping of a slowly spinning satellite, stabilized with a small rotor, is analyzed. The characteristic equation for the case of damper motion in a plane passing through the spin axis is seen to be similar to that of damper motion in a plane perpendicular to the spin axis. A parametric study of the characteristic equation is made for the case of one and two dampers. The damping characteristics of the one damper, with counterweight, appears to be preferable. Author
- Spacecraft Trajectories and Reentry