A parametric study of the behavior of the angular momentum vector during spin rate changes of rigidbody spacecraft
Abstract
During a spinup or spindown maneuver of a spinning spacecraft, it is usual to have not only a constant bodyfixed torque about the desired spin axis, but also small undesired constant torques about the transverse axes. This causes the orientation of the angular momentum vector to change in inertial space. Since an analytic solution is available for the angular momentum vector as a function of time, this behavior can be studied for large variations of the dynamic parameters, such as the initial spin rate, the inertial properties and the torques. As an example, the spinup and spindown maneuvers of the Galileo spacecraft was studied and as a result, very simple heuristic solutions were discovered which provide very good approximations to the parametric behavior of the angular momentum vector orientation.
 Publication:

Journal of Guidance Control Dynamics
 Pub Date:
 June 1984
 DOI:
 10.2514/3.19858
 Bibcode:
 1984JGCD....7..295L
 Keywords:

 Angular Momentum;
 Galileo Spacecraft;
 Rigid Structures;
 Spacecraft Maneuvers;
 Spin Stabilization;
 Computer Techniques;
 Euler Equations Of Motion;
 Heuristic Methods;
 Numerical Integration;
 Parameterization;
 Spin Dynamics;
 Astrodynamics