Optimum sizing of bare-tape tethers for de-orbiting satellites at end of mission

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Optimum sizing of bare-tape tethers for de-orbiting satellites at end of mission

Sanmartín, J.R. / Sánchez-Torres, A. / Khan, S.B. / Sánchez-Arriaga, G. / Charro, M.

Highlight • Conductive bare-tape tethers are optimally sized for end-of mission satellite de-orbiting. • Performance criteria are (1) very light tether, (2) high probability of survival to small debris, and low probability of big debris impact on (3) the satellite or (4) its tape.

Abstract De-orbiting satellites at end of mission would prevent generation of new space debris. A proposed de-orbit technology involves a bare conductive tape-tether, which uses neither propellant nor power supply while generating power for on-board use during de-orbiting. The present work shows how to select tape dimensions for a generic mission so as to satisfy requirements of very small tether-to-satellite mass ratio mt/MS and probability Nf of tether cut by small debris, while keeping de-orbit time tf short and product tf $\times$ tether length low to reduce maneuvers in avoiding collisions with large debris. Design is here discussed for particular missions (initial orbit of 720km altitude and 63° and 92° inclinations, and 3 disparate MS values, 37.5, 375, and 3750kg), proving it scalable. At mid-inclination and a mass-ratio of a few percent, de-orbit time takes about 2weeks and Nf is a small fraction of 1%, with tape dimensions ranging from 1 to 6cm, 10 to 54 $μ$ m, and 2.8 to 8.6km. Performance drop from middle to high inclination proved moderate: if allowing for twice as large mt/MS, increases are reduced to a factor of 4 in tf and a slight one in Nf, except for multi-ton satellites, somewhat more requiring because efficient orbital-motion-limited electron collection restricts tape-width values, resulting in tape length (slightly) increasing too.