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Research Papers

Discrete Time Transfer Matrix Method for Dynamic Modeling of Complex Spacecraft With Flexible Appendages

[+] Author and Article Information
Bao Rong

Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing 210094, P. R. Chinarongbao_nust@sina.com

Xiaoting Rui

Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing 210094, P. R. Chinaruixt@163.net

Hailong Yu

Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing 210094, P. R. Chinayhls02080888@mail.china.com

Guoping Wang

Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing 210094, P. R. Chinawgp1976@163.com

J. Comput. Nonlinear Dynam 6(1), 011013 (Oct 07, 2010) (10 pages) doi:10.1115/1.4002266 History: Received May 31, 2009; Revised July 27, 2010; Published October 07, 2010; Online October 07, 2010

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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Figures

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Figure 1

Dynamic model of a spacecraft with a flexible solar panel

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Figure 2

Position description of arbitrary point on solar panel

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Figure 3

Rigid body moving in space with n input points and m output points

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Figure 4

Transfer relationship of rigid swinging bracket

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Figure 5

Flexible solar panel moving in space

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Figure 6

Flow chart of algorithms for the proposed method

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Figure 7

Natural frequency (Hz) and mode shape of solar panel

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Figure 8

Time history of transverse deformation at point E on solar panel

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Figure 9

Normal stress and strain at center point on the top surface of solar panel

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