Dynamics of electro-dynamic tether de-orbiting system for LEO satellites

Author

Xianren, Kong ; Dafu, Xu ; Jun, Liao

Author_Institution

Res. Center of Satellite Technol., Harbin Inst. of Technol., Harbin, China

fYear

2010

fDate

8-10 June 2010

Firstpage

550

Lastpage

555

Abstract

This paper presents a flexible cable model considering that tether is easy to inflect can be used for analyzing the dynamic behavior of the electro-dynamic tether (EDT) de-orbiting system. The model can describe tether inflecting and bowing under action of electro-dynamic drag and gravity gradient induced force, and the influences on electro motive force and electro-dynamic drag. Two mathematical simulations are employed to show the differences between the flexible cable model and the rigid bar model. Vibration of the EDT system during de-orbiting course is discussed, at which the simulation result shows vertical response is the main vibration way of EDT.

Keywords

artificial satellites; electric potential; electrodynamics; LEO satellite; electro motive force; electrodynamic tether de orbiting system; flexible cable model; gravity gradient induced force; low earth orbit; Drag; Force; Lorentz covariance; Mathematical model; Satellites; Torque; Vibrations;

fLanguage

English

Publisher

ieee

Conference_Titel

Systems and Control in Aeronautics and Astronautics (ISSCAA), 2010 3rd International Symposium on

Conference_Location

Harbin

Print_ISBN

978-1-4244-6043-4

Electronic_ISBN

978-1-4244-7505-6

Type

conf

DOI

10.1109/ISSCAA.2010.5633582

Filename

5633582