Influence of Structural Flexibility on Nonlinear Vibrations Induced by Orbital Maneuver for a Tethered Spacecraft
Publication: Journal of Aerospace Engineering
Volume 36, Issue 1
Abstract
An analytical nonlinear model for elastic planar motion of a tethered spacecraft (TS) is presented and used to investigate the mode characteristics and analyze the nonlinear vibrations induced by the orbital maneuver. Dynamic characteristics such as frequency densification caused by variation of solar panel length, mode localization, and mode interchanging phenomenon caused by acceleration variation are investigated. Two prerequisites and the mechanisms for the occurrence of the complete mode interchanging phenomenon are discussed in detail. Nonlinear phenomena were observed such as hardening, jumping, and third-order superharmonic resonance. Dynamic responses of TS with and without considering the geometrical nonlinearity of the tether were obtained and used to show the influence of the tether’s nonlinearity on the whole system. The influence of the tether’s nonlinearity was strengthened with the increase of the excitation amplitude. Numerical results showed that the geometrical nonlinearity of tether has a significant influence on the dynamical responses and residual vibrations of the whole tethered spacecraft.
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Data Availability Statement
All data, models, and code generated or used during the study appear in the published article.
Acknowledgments
This work is supported by the National Natural Science Foundation of China under Grant No. 11732005 and the Advanced Research Project on Civil Space Technology in China under Grant No. D020201.
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Journal of Aerospace Engineering
Volume 36 • Issue 1 • January 2023
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© 2022 American Society of Civil Engineers.
History
Received: Apr 9, 2022
Accepted: Sep 15, 2022
Published online: Nov 15, 2022
Published in print: Jan 1, 2023
Discussion open until: Apr 15, 2023
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