Abstract The growing amount of orbital debris is becoming a serious concern for space development activities. To remedy the situation, it is necessary to prevent new debris generation through highly probable post-mission disposal operations and remove existing large debris objects from crowded orbits. An electrodynamic tether (EDT) is a promising deorbit propulsion device for both purposes, as it is propellant-less in principle and thus simple and cost effective. An on-orbit EDT experiment called the Kounotori Integrated Tether Experiment (KITE) was conducted in early 2017 on the sixth H-II Transfer Vehicle (HTV-6) for demonstrating and raising the maturity of the core EDT technologies. In the KITE mission, EDT operation was planned using the combination of a bare tether (720 m long) and a field emission cathode (FEC). Although tether deployment was unsuccessful due to a mechanical malfunction of the holding & releasing mechanism of the end-mass, the FEC operated successfully throughout the mission period and demonstrated its capabilities in low Earth orbit (LEO). Another KITE device – an electrical potential monitor called LP-POM – also operated successfully from HTV launch to re-entry, obtaining engineering and scientific results. In addition to these experimental results, the lessons learned during the development process are meaningful for future EDT research and development.
Highlights An on-orbit experiment of an electrodynamic tether (called KITE) was conducted. KITE features the combination of a net-like bare tether and a field emission cathode. End-mass was not released by a mechanical trouble, so the tether was not deployed. The field emission cathode operated successfully and showed its capabilities in space.
Review of KITE – Electrodynamic tether experiment on the H-II Transfer Vehicle
Acta Astronautica ; 177 ; 750-758
2020-03-10
9 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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