NUTATIONAL DAMPING OF A SLOWLY SPINNING SATELLITE STABILIZED BY USE OF A ROTOR.

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Abstract:

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

Author(s):
Anand, D. K. ; Pardoe, P. P. ; Whisnant, J. M.
Author Organization(s):
JOHNS HOPKINS UNIV SILVER SPRING MD APPLIED PHYSICS LAB
Descriptive Note:
Technical memo.,
Pagination:
0043

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
APL-TG-997, IDEP-347.00.00.00-S6-06
Contract/Grant Number(s):
NOw-62-0604
Monitor Series:
347.00.00.00-S6-06
 Subject Terms
Modernization Areas:
Space
Communities of Interest:
Space
Descriptor(s):
*ARTIFICIAL SATELLITES, DAMPING, GYRO STABILIZERS, SPIN STABILIZATION, VECTOR ANALYSIS, MOMENT OF INERTIA, KINETIC ENERGY, PARTIAL DIFFERENTIAL EQUATIONS, EQUATIONS OF MOTION, MASS
Field(s)/Group(s):
Spacecraft Trajectories and Reentry
Report Date:
1968 Apr 01