Abstract
One key of deorbit of satellite by means of electrodynamic tether system is the mutual effect between electrodynamic tether system and plasma, hence it is necessary to study the effect of contact impedances between electrodynamic tether system and plasma on deorbiting characteristics of electrodynamic tether. The paper took the lead in analyzing the sorts of resistances in the loop according to one kind of electrodynamic tether system. Then established the formula of the contact impedance between orbicular collecting container of electrodynamic tether system and plasma. Besides, the paper used the orbital six element method to analyze the effect of the contact impedance on the deorbit time, height and semi-axis of orbit of satellite under the 13th accurate geomagnetism field model and the International Reference Ionosphere 1990 model. The analytical and simulation results show the effect of the contact impedance on deorbiting characteristics of electrodynamic tether is very great for the electrodynamic tether system and parameters in the paper.
| Original language | English |
|---|---|
| Pages (from-to) | 366-369 |
| Number of pages | 4 |
| Journal | Yuhang Xuebao/Journal of Astronautics |
| Volume | 29 |
| Issue number | 1 |
| State | Published - Jan 2008 |
Keywords
- 13th accurate geomagnetism field model
- Contact impedance
- Deorbit
- Electrodynamic tether
- International Reference Ionosphere 1990
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