Accession Number:

AD0743258

Title:

Attitude Stability and Performance of a Dual-Spin Satellite with Large Flexible Appendages,

Descriptive Note:

Corporate Author:

TORONTO UNIV (ONTARIO) INST FOR AEROSPACE STUDIES

Personal Author(s):

Report Date:

1971-10-01

Pagination or Media Count:

123.0

Abstract:

The attitude stability criteria and nutation decay times of a dual-spin satellite with a large flexible solar array are found in terms of significant satellite parameters. The equations of motion are developed from Hamiltons principle and then linearized, with solar array natural modes utilized as array degrees of freedom. It is shown that with proper mass balancing, the equations for spin variables can be decoupled from those for transverse variables. The linearized equations are numerically studied through the system eigenvalues thus yielding direct statements of stability and nutation damping time. These eigenvalue studies are done first assuming the array to be rigid and then with array flexibility included. A complementary analysis for the solar array develops practical information regarding array natural mode frequencies and shapes and boom buckling considerations. Author

Subject Categories:

  • Unmanned Spacecraft
  • Spacecraft Trajectories and Reentry

Distribution Statement:

APPROVED FOR PUBLIC RELEASE