Energy Optimal Path Planning of Satellite Attitude Manuever Using Control Moment Gyros
- Paper number
IAC-08.C1.8.12
- Author
Mr. Yohichiroh Kusuda, Keio University, Japan
- Coauthor
Dr. Masaki Takahashi, Keio University, Japan
- Coauthor
Prof. Kazuo Yoshida, Keio University, Japan
- Year
2008
- Abstract
Background
Recently, missions of a spacecraft such as an earth observing satellite have required more rapid multitarget acquisition and higher accurate pointing control performance. Control Moment Gyros (CMGs) has been expected to be applied to the attitude control actuator of an agile satellite because it can generate high torques. However, it is pointed out that CMGs has a singularity problem, and there are many researches about singularity avoidance steering logic of CMGs. Additionally, it is important to reduce energy consumption in space environment. So far, there are few efficient researches taking consideration with energy reduction.
Purpose
From the previous background, a purpose of this paper is to find the optimal path of CMGs under the control requirement of the satellite attitude maneuver. And by using the optimal path as a feedforward control input of CMGs, this paper shows that the feedforward control can avoid the singularity problem and control CMGs more effectively than a feedback control using an existing steering logic in points of energy consumption.
Methodology
In this method, Fourier Basis Algorithm is used to find the optimal path. This algorithm approximates the control input of CMGs by Fourier series. In the optimized calculation, both energy consumption and satellite attitude errors at the end of the maneuver are evaluated. Thereby the method can find an optimal path of CMGs to reduce energy consumption and to satisfy the control requirement of the satellite attitude maneuver simultaneously. Furthermore, design parameters of the method are less than other optimization method, so it is effective for on-board computer resources of the satellite system.
Results and Conclusions
In this study, in order to verify the availability of the proposed feedforward control, the numerical simulations about some large-angle maneuver missions are carried out. From the simulation results of gimbal motions, it is shown that the proposed method can control CMGs without meeting the singularity problem to satisfy the control requirement. Additionally, energy consumption of CMGs can be reduced by approximately 48% by comparison with the feedback control using GSR Inverse method that is one of representative steering logic. The proposed method can control CMGs without rapid changes of input commands to CMGs.
In conclusion, this paper finds the energy optimal path of CMGs under the control requirement of the satellite attitude maneuver using CMGs and shows the availability of the proposed control method for CMGs in points of the singularity problem and energy consumption.
- Abstract document
- Manuscript document
IAC-08.C1.8.12.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.