Abstract
In this paper, an accurate and simple model of a satellite with two flexible solar panels for three-dimensional dynamic studies is proposed and compared with other models. In the proposed model, each solar panel is assumed to be rigid and attached to the satellite body via a simple hinge, a torsional spring, and a torsional damper. Kane’s method is utilized to derive the equations of motion. The model of flexible satellite with the assumption of Euler-Bernoulli beam for the solar panels, generally used in the literature, has been introduced for comparison. A comprehensive model of flexible satellite, considering solar panels as flexible and finite element panels, has been provided in ADAMS environment as a reference when comparing the two mentioned models. The Euler-Bernoulli model does not appropriately simulate the three-dimensional motion of satellite. Conversely, the hinged, rigid-panel model proposed in this paper provides suitable results in both two- and three-dimensional maneuvers.
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
References
Y. Zeng, A. D. Araujo and S. N. Singh, Output feedback variable structure adaptive control of flexible spacecraft, Acta Astronautica, 44(1) (1999) 11–22.
H. Bang, Y. Cho and H. Lee, Slewing maneuver control of flexible spacecraft by output feedback, Acta Astronautica, 55 (2004) 903–916.
Q. Hu and G. Ma, Variable structure control and active vibration suppression of flexible spacecraft during attitude maneuver, Aerospace Science and Technology, 9 (2005) 307–317.
Q. Hu and Y. Liu, A hybrid scheme of feed-forward/feed-back control for vibration suppression of flexible spacecraft with on-of actuators during attitude maneuver, International Journal of Information technology, 11(12) (2005) 95–107.
B. N. Agrawal, R. S. Mcclelland and G. Song,, Attitude control of flexible spacecraft using pulse-width pulse-frequency modulation thrusters, Space Technology, 17(1) (1997) 15–34.
G. Song and B. N. Agrawal, Vibration suppression of flexible spacecraft during attitude control, Acta Astronautica, 49(2) (2001) 73–83.
Y. Chida, H. Soga, Y. Yamaguchi, T. Kida, I. Yamaguchi and T. Sekiguchi, On-orbit attitude control experiment using ETSVI by H ∞ control and two-degree-of-freedom control, Control Engineering Practice, 6 (1998) 1109–1116.
D. Gorinevsky and G. Vukovich, Control of flexible spacecraft using nonlinear approximation of input shape dependence on reorientation maneuver parameters, Control Engineering Practice, 5(12) (1997) 1661–1671.
J. Zheng, S. P. Banks and H. Alleyne, Optimal attitude control of three-axis stabilized flexible spacecraft, Acta Astronautica, 56 (2005) 519–528.
H. Bang, C. Ha and J. H. Kim, Flexible Spacecraft attitude maneuver by application of sliding mode control, Acta Astronautica, 57 (2005) 841–850.
S. Parman and H. Koguchi, Controlling the attitude maneuvers of flexible spacecraft by using time-optimal/fuel-efficient shaped inputs, Journal of Sound and Vibration, 221(4) (1999) 545–565.
A. D. Meglio and A. Ercolifinzi, Minimum time control of flexible spacecraft by Hamilton’s principle, Meccanica, 32 (1997) 555–565.
T. R. Kane, P. W. Likins and D. A. Levinson, Spacecraft Dynamics, McGraw-Hill, (1981).
H. Baruh, Analytical dynamics, McGraw-Hill, Singapore, (1999).
K. A. Ford and C. D. Hall, Reorienations of spacecraft using momentum exchange devices, Ph.D. Dissertation, air force inst of tech. Wright-Patterson AFB (1997).
Author information
Authors and Affiliations
Corresponding author
Additional information
This paper was recommended for publication in revised form by Associate Editor Eung-Soo Shin
Shahram Shahriari received his B.S. and M.S. degrees in Mechanical Engineering from the Sharif University of Technology in Iran in 1993 and 1998, respectively. He is currently a Ph.D. candidate in Tarbiat Modares University, Iran. His main research interests are in the area of robust control, multi-body dynamics, vehicle engineering, and satellite attitude control and dynamics.
Shahram Azadi received his BS and MS in Mechanical Engineering from the Sharif University of Technology, Iran in 1989 and 1992, respectively. He then received his PhD from the Amir-Kabir University of Technology in 1999. Currently, he is an Assistant Professor at the School of Mechanical Engineering at K.N. Toosi University of Technology in Tehran, Iran. His research interests include dynamics, control, and automotive engineering.
Majid Moghaddam received his B.Sc. degree in Mechanical Engineering in 1988 from the Sharif University of Technology, Iran, his M.Eng. degree in Mechanical Engineering in 1993 from McGill University, Canada, and his Ph.D. degree in Mechanical Engineering in 1996 from the University of Toronto, Canada. He is Professor of mechanical engineering at Tarbiat Modares University, Tehran, Iran. His current research, which focuses on applied robotics and robust H∞ control, is concerned with haptic robotics, rehabilitation robotics, inspection robotics, and rough terrain mobile robot design. He is a member of the Administrative Committee of the Mechatronics Society of Iran. He has served as co-chair for many national/international conferences in Iran.
Rights and permissions
About this article
Cite this article
Shahriari, S., Azadi, S. & Moghaddam, M.M. An accurate and simple model for flexible satellites for three-dimensional studies. J Mech Sci Technol 24, 1319–1327 (2010). https://doi.org/10.1007/s12206-010-0329-0
Received:
Revised:
Accepted:
Published:
Issue Date:
DOI: https://doi.org/10.1007/s12206-010-0329-0