Authors
Abstract
Recently, many space missions have been using small satellites, because small satellites are easier and faster to develop and thereby, provide increased launch opportunities. Some of these missions include tasks that required agile maneuvers. In this paper, attitude stability testing of an agile three-degree-freedom micro-satellite simulator – which is equipped with a pyramid arrangement of single-gimbal control-moment gyros (SGCMGs) – is presented. In the attitude stability testing, the local quadratic regulator (LQR) control strategy is used, which has superiority to other approaches due to its independence of using steering law. This simulator allow to test different control laws by using SGCMGs. In this work, after introducing the actuator and satellite simulator and using the control strategy in the simulator, the attitude stability testing is performed and then, the experimental results are presented and discussed. The results show the attitude stability of the simulator which is exposed to the disturbing toques.
Keywords
- [1] Berner, R., Control Moment Gyro Actuator for Small Satellite Application, (M. Sc. Thesis), University of Stellenbosch, 2005.
- [2] Tayebi, J., Attitude Control of High Agility Nano Satellite with Control Moment Gyros, (M. Sc. Thesis), K. N. Toosi University, 1390 (In Persian).
- [3] Jacot, A. and Liska, D. J., “Control Moment Gyros in Attitude Control,” Journal of Spacecrafts and Rockets, Vol. 3, No. 9, 1966, pp. 1313-1320.
- [4] Margulies, and Aubrun, J. N., “Geometrical Theory of Single Gimbal Control Moment Gyro System,” The Journal of the Astronautical Sciences, Vol. XXVI, No.2, 1978, pp.159-191.
- [5] Bedrossian, N. , Paradiso, J., Bergman, E. and Rowell, D., “Redundant Single Gimbal Control Moment Gyroscope Singularity Analysis,” Journal of Guidance, Control, and Dynamics, Vol.13, No.6, 1990, pp.1096-1101.
- [6] Bedrossian, N. , Paradiso, J. and Bergman, E. “Steering Law Design For Redundant Single Gimbal Control Moment Gyroscopes,” Journal of Guidance, Control, and Dynamics, Vol. 13, No.6, 1990, pp. 1083-1089.
- [7] Vadali, S. , Oh, H. S. and Walker, S., “Preferred Gimbal Angles for Single Gimbal Control Moment Gyroscopes,” Journal of Guidance, Control and Dynamics, Vol.13, No.6, 1990, pp. 1090-1095.
- [8] Oh, H. and Vadali, S. R,. “Feedback Control and Steering Laws for Spacecraft Using Single Gimbal Control Moment Gyros,” The Journal of the Astronautical Sciences, Vol. 39, No. 2, 1991, pp. 183-203.
- [9] Meffe, G., and Stocking, M., “Momentum Envelope Topology of Single Gimbal CMG Arrays for Space Vehicle Control,” Proceedings of AAS Guidance and Control Conference, Keystone, CO, 1987.
- Kurokawa, H., “Constrained Steering Law of Pyramid-Type Control Moment Gyros and Ground Tests”, Journal of Guidance, Control, and Dynamics, 20, No.3, 1997, pp.445-449.
- B., Bailey, D. and Heiberg, C., “Singularity Robust Steering Logic for Redundant Single-Gimbal Control Moment Gyros,” Journal of Guidance, Control and Dynamics, Vol. 24, No. 5, 2001, pp. 865-871.
- Lappas, V. J. Steyn, W. H. and Underwood, C. I. “Attitude Control for Small Satellites using Control Moment Gyros”, 52nd IAF, 2001.
- Tekinalp, O. and Yavuzoglu, E., “A New Steering Law for Redundant Control Moment Gyroscope Cluster,” Aerospace Science and Technology, Vol. 9, No. 7, 2005, pp. 626-634.
- Won Kown, S., Tani, Y., Okubo, H. and Shimomura, T., “Fixed-Star Tracking Attitude Control of Spacecraft using Single-Gimbal Control Moment Gyros,” American Jounrnal of Engineering and Applied Sciences, Vol. 3, Issue 1, 2010, pp. 49-55.
- Harland, and MLorenz, R. D., Space Systems Failures, Editor J. Mason, Springer-Praxis, 2005.
- KrishnaKumar, K., “Adaptive Neuro-Control for Spacecraft Attitude Control”, Procceding of the IEEE Confrence on Control Applications, Aug. 1994.
- Unnikrishnan, , Balakrishnan, S. N., and Padhi, R. “Dynamicre-optimization of a Spacecraft Attitude Controller in the Presence of Uncertainties”, Procceding of IEEE Int’l Symposium on Intelligent Control, Munich, Germany, Oct. 2006.
- Makunis, W., “Adaptive Satellite Attitude Control In The Presense of Inertia And Cmg Gimbal Friction Uncertainties”, Journal of the Astronautical Sciences, Vol. 56, No. 1, 2008, pp. 121–134,.
- Aghalari, A., Kalhor, A., Dehghan, S. M. M. and Abedian, A., “Designing, Testing and Evaluation of A Single Gimbal Control Moment Gyro for Microsatellite”, Journal of Space Science and Technology, Aerospace research Institute, Vol. 2, No. 3, 1388, pp. 13-24, (In Persian).
- Aghalari, A., Study on Satellite Simulators, Designing and Fabrication of a Single Gimbal Control Moment Gyro for Simulator, Technical Report, Aerospace University Complex, 1389, (In Persian).
- Kalhor, A. and Cheheltani, S. H., Designing and Integration of Electronics and Computer Parts of Satellite Simulator With Single Gimbal Control Moment Gyros, Technical Report, Aerospace University Complex, 1390, (In Persian).
- Aghalari, A. and Abedian, A., Designing and Integration of a Satellite Simulator with Single Gimbal Control Moment Gyros, Technical Report, Aerospace University Complex, 1389, (In Persian).
- Available, [on line]: http://www.Microstrain.com
)