RF helicon-based inductive plasma thruster (IPT) design for an atmosphere-breathing electric propulsion system (ABEP)
Challenging space missions include those at very low altitudes, where the atmosphere is
source of aerodynamic drag on the spacecraft. To extend such missions lifetime, an efficient …
source of aerodynamic drag on the spacecraft. To extend such missions lifetime, an efficient …
System design study of a VLEO satellite platform using the IRS RF helicon-based plasma thruster
G Herdrich, K Papavramidis, P Maier, J Skalden, F Hild… - Acta Astronautica, 2024 - Elsevier
To achieve a feasible lifetime of several years, most satellites are deployed in orbits higher
than 400 km. Drag of residual atmosphere causes a slow orbit decay, resulting in the deorbit …
than 400 km. Drag of residual atmosphere causes a slow orbit decay, resulting in the deorbit …
Experimental study of the plasma flow created by a low-power helicon source and approaches to increase the average energy of its ion component
II Zadiriev, EA Kralkina, GV Shvydkiy, AM Nikonov… - Vacuum, 2024 - Elsevier
The article presents the results of an experimental study of the characteristics of a low-power
helicon ion source. Particular attention is paid to the parameters of the particle flow …
helicon ion source. Particular attention is paid to the parameters of the particle flow …
[PDF][PDF] System design study of a VLEO satellite platform using the IRS RF Helicon-based Plasma Thruster G. Herdricha*, K. Papavramidisa, P. Maiera, J. Skaldena, F …
PCE Borrasd, NH Crispe - cris.unibo.it
To achieve a feasible lifetime of several years, most satellites are deployed in orbits higher
than 400 km. Drag of residual atmosphere causes a slow orbit decay, resulting in the deorbit …
than 400 km. Drag of residual atmosphere causes a slow orbit decay, resulting in the deorbit …