Efficient, precise dynamic analysis for a complex spacecraft has become a research focus in the field of spacecraft dynamics. In this paper, by combining discrete time transfer matrix method of multibody system and finite element method, the transfer equations and transfer matrices of typical elements of spacecrafts are developed, and a high-efficient dynamic modeling method is developed for high-speed computation of spacecraft dynamics. Compared with ordinary dynamic methods, the proposed method does not need the global dynamic equations of system and has the low order of system matrix, high computational efficiency. This method has more advantages for dynamic modeling and real-time control of complex spacecrafts. Formulations of the proposed method as well as a numerical example of a spacecraft with a flexible solar panel are given to validate the method.
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e-mail: rongbao_nust@sina.com
e-mail: ruixt@163.net
e-mail: yhls02080888@mail.china.com
e-mail: wgp1976@163.com
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January 2011
Research Papers
Discrete Time Transfer Matrix Method for Dynamic Modeling of Complex Spacecraft With Flexible Appendages
Bao Rong,
Bao Rong
Institute of Launch Dynamics,
e-mail: rongbao_nust@sina.com
Nanjing University of Science and Technology
, Nanjing 210094, P. R. China
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Xiaoting Rui,
Xiaoting Rui
Institute of Launch Dynamics,
e-mail: ruixt@163.net
Nanjing University of Science and Technology
, Nanjing 210094, P. R. China
Search for other works by this author on:
Hailong Yu,
Hailong Yu
Institute of Launch Dynamics,
e-mail: yhls02080888@mail.china.com
Nanjing University of Science and Technology
, Nanjing 210094, P. R. China
Search for other works by this author on:
Guoping Wang
Guoping Wang
Institute of Launch Dynamics,
e-mail: wgp1976@163.com
Nanjing University of Science and Technology
, Nanjing 210094, P. R. China
Search for other works by this author on:
Bao Rong
Institute of Launch Dynamics,
Nanjing University of Science and Technology
, Nanjing 210094, P. R. Chinae-mail: rongbao_nust@sina.com
Xiaoting Rui
Institute of Launch Dynamics,
Nanjing University of Science and Technology
, Nanjing 210094, P. R. Chinae-mail: ruixt@163.net
Hailong Yu
Institute of Launch Dynamics,
Nanjing University of Science and Technology
, Nanjing 210094, P. R. Chinae-mail: yhls02080888@mail.china.com
Guoping Wang
Institute of Launch Dynamics,
Nanjing University of Science and Technology
, Nanjing 210094, P. R. Chinae-mail: wgp1976@163.com
J. Comput. Nonlinear Dynam. Jan 2011, 6(1): 011013 (10 pages)
Published Online: October 7, 2010
Article history
Received:
May 31, 2009
Revised:
July 27, 2010
Online:
October 7, 2010
Published:
October 7, 2010
Citation
Rong, B., Rui, X., Yu, H., and Wang, G. (October 7, 2010). "Discrete Time Transfer Matrix Method for Dynamic Modeling of Complex Spacecraft With Flexible Appendages." ASME. J. Comput. Nonlinear Dynam. January 2011; 6(1): 011013. https://doi.org/10.1115/1.4002266
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