Dynamics of spin stabilized spacecraft during deployment of telescoping appendages
Abstract
The dynamics of a spin stabilized spacecraft with telescoping appendages are treated both analytically and numerically. Two types of telescoping appendages are considered: (a) where an end mass is mounted at the end of an (assumed) massless boom; and (b) where the appendage is assumed to consist of a uniformly distributed homogeneous mass throughout its length. For the telescoping system Eulerian equations of motion are developed. During all deployment sequences it is assumed that the transverse component of angular momentum is much smaller than the component along the major spin axis. Closed form analytical solutions for the time response of the transverse components of angular velocities are obtained when the spacecraft hub has a nearly spherical mass distribution. For the more general case, a series solution is obtained and this solution is limited by its radius of convergence. The comparison of the different approximate analytical methods with numerical integration results are studied and it is observed that the oscillatory nature of the responses of the transverse angular velocity components reduces rapidly with faster extension rates.
 Publication:

AIAA, Aerospace Sciences Meeting
 Pub Date:
 January 1976
 Bibcode:
 1976aiaa.meetW....S
 Keywords:

 Space Erectable Structures;
 Spacecraft Motion;
 Spacecraft Stability;
 Spin Dynamics;
 Spin Stabilization;
 Angular Momentum;
 Asymmetry;
 Deployment;
 Graphs (Charts);
 Mass Distribution;
 Series (Mathematics);
 Systems Stability;
 Time Response;
 Astrodynamics