LEO is characterised by atmospheric drag. Owing to the growing space debris theres a great demand for deorbitting the defunct satellites. Usage of an electro dynamic tether (EDT) is known to accelerate the process. however there are certain challenges as to the determination of the length of the tether, strength and succeptibility of tether to temperature gradients & vibrations etc.,
through this discussion i would like to gain insights into how to go about EDT for a nano satellite in LEO beginning from its material of construction, length etc., to the deorbitting time required.
hope to see some thought provoking positive and active discussion
thanks and regards
Sudeep
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