Abstract
This paper presents a global mode modeling of space structures and a control scheme from the practical point of view. Since the size of the satellite has become bigger and the accuracy of attitude control more strictly required, it is necessary to consider the structural flexibility of the spacecraft. Although it is well known that the finite element (FE) model can accurately model the flexibility of the satellite, there are associated problems: FE model has the system matrix with high order and does not provide any physical insights, and is available only after all structural features have been decided. Therefore, it is almost impossible to design attitude and orbit controller using FE model unless the structural features are in place. In order to deal with this problem, the control design scheme with the global mode (GM) model is suggested. This paper describes a flexible structure modeling and three-axis controller design process and demonstrates the adequate performance of the design with respect to the maneuverability by applying it to a large flexible spacecraft model.
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
References
Balas, M. J., 1982, “Trends in Large Space Structures Control Theory: Fondest Hopes, Wildest Dreams.”IEEE Transaction on Automatic Control, Vol. 27, No. 3, pp. 552–535.
Bang, H. and Lho, Y., 2001, “Sliding Mode Control for Spacecraft Containing Rotating Wheels,” AIAA
Guidance, Navigation, and Control Conference & Exhibt(2001-4213).
Howley, B.. 1996. “Genetic Programming of Spacecraft Attitude Maneuvers Under Reaction Wheel Control,” AIAA Guidance, Navigation, and Control Conference (96-3849).
Hughes, PC, 1987, “Spacecraft Attitude Dynamics,” John Wiley & Sons.
Marcel, J., 1997, Spacecraft Dynamics and Control, Cambridge University Press.
Hughes, P. C., 1972“Attitude Dynamics of a Three-Axis Stabilized Satellite with a Large Flexible Solar Array.”Journal of the Astronautical Sciences, Vol. 20, No. 3.
Iwens, R. P., 1982,Basic Spacecraft Attitude Control Tools.
Junkins J. L. and Kim, Y., 1993,Introduction to Dynamics and Control of Flexible Structure, AIAA Education Series, Published by American Institute Of Aeronautics and Astronautics, Washington, D.C.
Li, X., Throckmorton, A. J. and Boka, J. B, 1996. “Stability Analysis on Earth Observing System AM-1 Spacecraft Earth Acquistion,” AIAA Guidance, Navigation, and Control Conference (96-3827).
Likins, P. W., 1979, “The New Generation of Dynamics Interaction Problems,”Journal of Astroautical Sciences, Vol. XXVII, No. 2.
Meirovitch, L., 1990, Dynamics and Control of Structures, Wiley, New York.
Meirovitch, L., 1967, Analytical Methods in Vibrations, Macmillan, New York.
Ryan, R. R., 1990, “Simulation of Actively Controlled Spacecraft with Flexible Appendages,”Journal of Guidance and Control. Vol. 13, No. 4, pp. 691–702.
Wie, B. and Liu Q., 1993. “Classical and Robust Control Redesign for the Hubble Space Telescope,”Journal of Guidance Control and Dynamics, Vol. 6, No. 6, pp. 1069–1077.
Wie, B. and Plescia, C. T., 1984. “Attitude Stablization of Flexible Spacecraft During Station Keeping Maneuvers.”J, of Guidance and Control, Vol. 7. No. 4, pp. 62–68.
Wie, B., Gonzales, M., 1992, “Control Synthesis for Flexible Space Structure Excited by Persitent Disturbance,”Journal of Guidance and Control, Dynamics, Vol. 15, No. 1, pp. 73–80.
Author information
Authors and Affiliations
Corresponding author
Rights and permissions
About this article
Cite this article
Chae, JS., Park, TW. Dynamic modeling and control of flexible space structures. KSME International Journal 17, 1912–1921 (2003). https://doi.org/10.1007/BF02982430
Received:
Revised:
Published:
Issue Date:
DOI: https://doi.org/10.1007/BF02982430