Abstract
Adjustment of the orbit of a spacecraft using the forces
created by an electro-dynamic space-tether has been
shown as a theoretic possibility in recent literature.
Practical implementation is being pursued for larger
scale missions where a hot filament device controls
electron emission and the current flowing in the
electrodynamic space tether. Applications to small
spacecraft, or space debris in the 1–10 kg range, possess
difficulties with electron emission technology, as low
power emitting devices are needed. This paper addresses
the system concepts of a small spacecraft electrodynamic
tether system with focus on electron emitter
design and manufacture using micro-electro-mechanical-
system (MEMS) technology. The paper addresses
the system concepts of a small size electrodynamic
tether mission and shows a novel electron emitter for
the 1-2 mA range where altitude can be effectively
affected and other orbit parameters can be controlled for
small sized missions, without on-board propulsion.
Original language | English |
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Title of host publication | Proceedings of the ESA Symposium on Small Spacecraft Systems |
Place of Publication | La Rochelle |
Publisher | European Space Agency |
Publication date | 2004 |
Pages | 227-232 |
Publication status | Published - 2004 |
Event | ESA Symposium on Small Spacecraft Systems - La Rochelle, France, Sept. 20-24 Duration: 1 Jan 2004 → … |
Conference
Conference | ESA Symposium on Small Spacecraft Systems |
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City | La Rochelle, France, Sept. 20-24 |
Period | 01/01/2004 → … |