Document Type : Research Paper
Authors
Department of Aerospace University Camplex, Maleke Ashtar University of Technology.Tehran.IRAN
Abstract
In this paper, the three-axis magnetic attitude control using PD and LQR control laws have been studied in a lab environment. Evaluation of the magnetic attitude control with this control laws is done by a "three degrees of freedom air-bearing simulator". Developed dynamic and kinematic equations to be used in actual simulator are evaluated by open loop test. Then control laws evaluated by comparing close loop simulation and laboratory test. Due to the inherent simulator limitations, magnetic attitude control only possible in the yaw axis. Laboratory test results indicate the improved and accurate performance of LQR control law for most satellite missions. Therefore by generalized LQR controller, three-axis simulation was performed for a satellite.
Keywords
[1] Ovchinnikom, Yu., Penkovv, I., Ilyina, A. and Selivanovs, A., “Magnetic Attitude Control Systems of The Nanosatellite Tns-Series,” Selected Proceedings of the 5th International Symposium of the International Academy of Astronautics, Berlin, 2005, pp. 337-344
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[12] Kulick, W.J., “Development of A Control Moment Gyroscope Controlled, Three Axis Satellite Simulator, With Active Balancing for The Bifocal Relay Mirror Initiative,” (M Sc Thesis), Naval Postgraduate School Monterey, CA 93943-5000, Dec. 2004.
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[14] Makovec, K.L., A Nonlinear Magnetic Controller for Three-Axis Stability of Nanosatellites, (M Sc Thesis), of Science in Aerospace Engineering, Virginia Polytechnic Institute and State University, 2001.
[15] Gießelmann, J. “Development of an Active Magnetic Attitude Determination and Control System for Picosatelliteson highly inclined circular Low Earth Orbits, (M Sc. Thesis), School of Aerospace, Engineering and Technology Portfolio RMIT University, 2006.
[16] Guerrant, D.V., Design and Analysis of Fully Magnetic Control For Picosatellite Stabilization, (M Sc Thesis) Aerospace Engineering, California Polytechnic State University, San Luis Obispo, 2005.
[17] Lorentzen, T. “Attitude Control and Determination Systemfor DTUsat1,” Cube Sat project Department of Automation, Ørsted•DTU Technical University of Denmark, Feb. 2002.
[18] Tavakoli, A.H., Kalhor, A. and Dehghan, S. M.M., “Implementation of Three Axis Attitude Controllers for Evaluation of a Micro-gravity Satellite Simulator,”JSST, Vol 5, No. 2, 2012, pp. 59-68 (In Persian).
[19] Zipfel, P.H., Modeling and Simulation of Aerospace Vehicle Dynamics, University of Florida, Gainesville, Florida, 2007.
[20] Kim, B.M., Velenis, E., Kriengsiri, P., and Tsiotras, P.,“Designing a Low Cost Spacecraft Simulator,” IEEE Control Systems Magazine, 2003
[21] Regan, F.J. and Anandakrishnan, S.M., Dynamics of Atmospheric Re-Entry, American Institute of Aeronautics and Astronautics, 1992.
[22] Sidi, M.J., Spacecraft Dynamics and Control Camberidge University press, 1997.
[23] Silani, E. and Lovera, M., “Magnetic Spacecraft Attitude Control: A Survey and Some New Results,” Control Engineering Practice (Elsevier), Vol. 13, 2005,pp. 357–371.
[24] Makovec, K.l., “A Nonlinear Magnetic Controller for Three-Axis Stability of Nanosatellites,” (M Sc Thesis) Aerospace Engineering, Blacksburg, Virginia, 2001.
[2] Bolandi, H., Ghorbani, V.B. and Ataei, M. “Attitude Control System of a Spinning Satellite using Only Magnetic Coils,” Presented at the 4th International and 8th AnnualConference of Iranian Mechanical Engineerin g(ISME2000), Sharif University, Tehran, Iran, 2000.
[3] Bolandi, H. and Vaghei, B.G., “Stable Supervisory- AdaptiveController for Spinning Satelliteusing Only Magnetorquers,” IEEE Transactions on Aerospace and Electronic Systems, Vol. 45, No. 1, Jan. 2009.
[4] White, J.S., Shigemoto, F.H. and Bourquin, K. “Satellite Attitude Control Utilizing the Earth’s Magneticfield,” National Aeronautics and Space Administration, Technical Report NASA TN-D1068, 1961.
[5] Musser, K.L. and Ebert, W.L., “Autonomous Spacecraft Attitude Control Using Magnetic Torquing Only,”Flight Mechanics/Estimation Theory Symposium, NASA Conference Publication, 1989, pp. 23–38.
[6] Wisniewski, R., Satellite Attitude Control Using Only Electromagnetic Actuation, (Ph.D. Thesis), Department of Control Engineering Aalborg University Fredrik Bajers Vej 7, DK-9220 Aalborg Ø, Denmark, Dec. 1996.
[7] Wisniewski, R. and Markley, L.M., “Optimal magnetic attitude control,” Proceeding of The 14th IFAC World Congress, Beijing, China, 1999.
[8] Psiaki, M.L., “Magnetic Torquer Attitude Control Via Asymptotic Periodic Linear Quadratic Regulation,”AIAA 2000, p.13.
[9] Raschke, C., Roemer, S. and Grossekatthoefer, K., “Test Bed for Verification of Attitude Control System,” ample of Paper for Journal of the Japan Society for Test Bed, 2012, pp. 1-4.
[10] Min, H., Guoqiang, Z. and Yudong G., “Thruster Control for Micro-Satellite Attitude and Hardware-inthe-loop Demonstration”, American Journal of Engineering and Technology Research, Vol. 11, No. 12,2012, pp. 588-591.
[11] Prado, J., Bisiacchi, G., Reyes, L., Vicente E., Contreras F., Mesinas M. and Juárez, A., “Three-Axis Air-Bearing Based Platform for Small Satellite Attitude Determination and Control Simulation,” Journal of Applied Research and Technology, December, año/vol. 3, Número 003 Universidad Nacional Autónoma de México Distrito Federal, México, 2005, pp. 222-237.
[12] Kulick, W.J., “Development of A Control Moment Gyroscope Controlled, Three Axis Satellite Simulator, With Active Balancing for The Bifocal Relay Mirror Initiative,” (M Sc Thesis), Naval Postgraduate School Monterey, CA 93943-5000, Dec. 2004.
[13] Larson, W.J. and Wertz, J.R. Space Mission Analysis and Design, Microcosm, Inc., 1992
[14] Makovec, K.L., A Nonlinear Magnetic Controller for Three-Axis Stability of Nanosatellites, (M Sc Thesis), of Science in Aerospace Engineering, Virginia Polytechnic Institute and State University, 2001.
[15] Gießelmann, J. “Development of an Active Magnetic Attitude Determination and Control System for Picosatelliteson highly inclined circular Low Earth Orbits, (M Sc. Thesis), School of Aerospace, Engineering and Technology Portfolio RMIT University, 2006.
[16] Guerrant, D.V., Design and Analysis of Fully Magnetic Control For Picosatellite Stabilization, (M Sc Thesis) Aerospace Engineering, California Polytechnic State University, San Luis Obispo, 2005.
[17] Lorentzen, T. “Attitude Control and Determination Systemfor DTUsat1,” Cube Sat project Department of Automation, Ørsted•DTU Technical University of Denmark, Feb. 2002.
[18] Tavakoli, A.H., Kalhor, A. and Dehghan, S. M.M., “Implementation of Three Axis Attitude Controllers for Evaluation of a Micro-gravity Satellite Simulator,”JSST, Vol 5, No. 2, 2012, pp. 59-68 (In Persian).
[19] Zipfel, P.H., Modeling and Simulation of Aerospace Vehicle Dynamics, University of Florida, Gainesville, Florida, 2007.
[20] Kim, B.M., Velenis, E., Kriengsiri, P., and Tsiotras, P.,“Designing a Low Cost Spacecraft Simulator,” IEEE Control Systems Magazine, 2003
[21] Regan, F.J. and Anandakrishnan, S.M., Dynamics of Atmospheric Re-Entry, American Institute of Aeronautics and Astronautics, 1992.
[22] Sidi, M.J., Spacecraft Dynamics and Control Camberidge University press, 1997.
[23] Silani, E. and Lovera, M., “Magnetic Spacecraft Attitude Control: A Survey and Some New Results,” Control Engineering Practice (Elsevier), Vol. 13, 2005,pp. 357–371.
[24] Makovec, K.l., “A Nonlinear Magnetic Controller for Three-Axis Stability of Nanosatellites,” (M Sc Thesis) Aerospace Engineering, Blacksburg, Virginia, 2001.
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