As essential components of an electrical propulsion system, traditional hollow cathodes,
such as BaO-W and LaB 6, have stringent requirements on the ignition procedure and …

A deorbiting strategy for small satellites is proposed that exploits the effect of solar radiation
pressure to increase the spacecraft orbit eccentricity so that the perigee falls below an …

This paper presents an analytical model and a geometric numerical integrator for a tethered
spacecraft model that is composed of two rigid bodies connected by an elastic tether. This …

RECENTLY, the increase of space debris on Earth orbits is becoming a threat to future
space activities [1]. First, malfunctioning or end-of-life satellites and upper stages of spent …

This paper aims to assess the efficiency of a de-orbiting system based upon conductive
tethers under realistic assumptions for its interaction with the ionospheric environment. We …

The paper addresses the problem of attitude stabilization of electrodynamic space tether
system (EDTS) in the local vertical position. The EDTS includes a negatively charged …

IN RECENT years, electrodynamic tethers (EDTs) have been proposed for a number of
space applications. An EDT is a long, thin, conductive tether in orbit around a body with a …

Over 9000 satellites and other trackable objects are currently in orbit around the Earth, along
with many smaller particles. As the low Earth orbit is not a limitless resource, some sort of …

ATETHERED satellite system (TSS) is a system of two or more satellites connected with
cables. TSSs have been proposed in connection with numerous different tasks and for …

The survivability analysis carried out to support the design of a new tether system, being
studied in Italy for spacecraft and upper stages end-of-life de-orbiting, is presented. In …