Abstract
Combining the conventional energy and attitude control system is a feasible solution for small satellites to improve the space missions. In this combined energy and attitude control system (CEACS) a double rotating flywheel in the pitch axis is used to replace the conventional battery for energy storage as well as to control the attitude of an earth oriented satellite. Each flywheel is to be controlled in the torque mode. The energy and attitude inputs for the flywheels' control architecture are also in the torque mode. All related mathematical representations along with the relevant transfer functions are developed. The required numerical calculations are performed using Matlab™ for studying the system performances. The goals of this work are to determine the CEACS attitude performance in the torque mode with respect to the ideal and non-ideal test cases for chosen reference missions.
| Original language | English |
|---|---|
| Pages (from-to) | 147 |
| Number of pages | 160 |
| Journal | Journal of Industrial Technology |
| Volume | 14 |
| Issue number | 2 |
| Publication status | Published - 2005 |