Dynamic Modeling and Analysis of Spacecraft with Multiple Large Flexible Structures
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Published:2023-07-13
Issue:7
Volume:12
Page:286
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ISSN:2076-0825
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Container-title:Actuators
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language:en
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Short-container-title:Actuators
Author:
Wei Jin12, Liu Wei2, Liu Jia2, Yu Tao2
Affiliation:
1. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China 2. School of Electromechanical and Automotive Engineering, Yantai University, Yantai 264005, China
Abstract
An analytical dynamic model is presented for a spacecraft with multiple large flexible structures. Based on the partial differential equations (PDEs) of the motion of the solar panel and deployable arm, the governing equations of the main-body and deployable antenna and the boundary conditions at each end point are used to obtain the frequency and mode shapes of the system. Then, the ordinary differential equations (ODEs) of the system can be obtained from the orthogonality relations and mode shape. The influence of the deployable antenna on the frequencies and mode shapes of the spacecraft is investigated. The frequency veering and mode interchanged phenomenon are observed with the variation of the diameter of the deployable antenna. Using the ODEs, the dynamic responses of the spacecraft are calculated to study the influence of the control torque on the attitude and position of the antenna in the attitude maneuver.
Funder
China Postdoctoral Science Foundation National Natural Science Foundation of China Shandong Provincial Natural Science Foundation, China
Subject
Control and Optimization,Control and Systems Engineering
Reference31 articles.
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