Rate damping control for small satellite using thruster
- 作者：Weidong ; Huang ; Yulin ; Zhang
- 刊名：Acta Astronautica
- 出版年：2004
- 期刊代码：1_00945765
- 类别：et
- 出版时间：July, 2004
- 卷：55
- 期：1
- 页码：9-13
- 文件大小：111 K
摘要
There are various control laws for attitude stabilization and maneuvering such as magnetic torque control, solar torque control, momentum exchange control. Such controllers work in a linear continuous mode. But the torque that they can produce is in the range of 0.02–1Nm for momentum exchange control, 10−2–10−3Nm for magnetic torque control, and 10−5–10−6Nm for solar torque control. Therefore, the speed of attitude maneuvering is limited by the low-level maximal torques that can be delivered to the attitude control system. Thruster control used in attitude control is no linear continuous reaction thrust control. However, they can provide almost any torque level. Their range between 0.01Nm and 30Nm, which is very common in most satellite. It is practical and convenient to use thruster for the rate damping control of small satellite during initial separation from launch vehicle. The paper deals with the analysis and design of thruster attitude control of a small satellite OptimSat. Simulation results shows that rate damping control for small satellite using thruster is effective.