A circular orbit and constant atmospheric density was assumed. A computer program which determines equilibrium attitudes and the associated eigenvalues of these attitudes is presented. Demonstration of the use of this program was made using the former Skylab satellite as an example.
Equilibrium and Stability of a Satellite Influenced by Gravitational and Aerodynamic Torques
1981
77 pages
Report
No indication
English
Unmanned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Aerodynamics , Computer programs , Gravitational effects , Orbital mechanics , Satellite control , Spacecraft stability , Torque , Attitude stability , Gravitational fields , Satellite configurations , Satellite orbits , Satellite perturbation