H₂ and H ͚ satellite attitude controls for combined energy and attitude control systems
Combined Energy Storage and Attitude Control System (CEACS) is a new satellite system developed using flywheels to offer mass reduction, longer operation life and also cost reduction. To date, the demonstration of the CEACS attitude control performance has been limited only to the proportional de...
Saved in:
| 主要作者: | |
|---|---|
| 格式: | Thesis |
| 語言: | English |
| 出版: |
2015
|
| 主題: | |
| 在線閱讀: | http://psasir.upm.edu.my/id/eprint/71212/1/FK%202017%2076%20-%20IR.pdf |
| 標簽: |
添加標簽
沒有標簽, 成為第一個標記此記錄!
|
| 總結: | Combined Energy Storage and Attitude Control System (CEACS) is a new satellite
system developed using flywheels to offer mass reduction, longer operation life and
also cost reduction. To date, the demonstration of the CEACS attitude control
performance has been limited only to the proportional derivative control (PD) and
the active force control-proportional derivative (AFC-PD). Both controllers have
their limitations where the PD controller is known to be less sensitive to
uncertainties while the AFC-PD requires accurate in-situ measurement, which is not
readily available at the moment. This proposed study will focus on improving the
performance of small satellites with the CEACS system as the pitch attitude actuator
by applying advanced control methods, H2 control and H∞ control. Both controllers
were applied on three different classes of satellite, nanosatellite, microsatellite and
enhanced microsatellite and simulated via MATLAB™ and SIMULINK®
programming for the ideal and non-ideal scenarios. From the testing, it is found that
the CEACS pitch attitude performance for both the H2 control and H∞ control can
meet the required pitch attitude requirement of 0.2°. The comparison between both
controllers shows that the H2 control method has a slightly better pitch attitude
performance compared to the H∞ control for ideal and non-ideal scenarios. As for the
comparison with the conventional PD controller and the PD-AFC controller, the
results indicate that both the H2 and H∞ controllers outperform the conventional PD
controller while having a slight advantage over the PD-AFC controller in terms of
the attitude performance. However, as the feasibility of the AFC controller is highly
dependent on the in-situ measurement of systems where the development of these
systems requires time, thus the H2 and H∞ controls are the favourable control options
for an immediate deployment of the CEACS system while providing an accurate
pitch control in the face of orbit uncertainties. |
|---|