  Challenging space missions include those at very low altitudes, where the
atmosphere is source of aerodynamic drag on the spacecraft that finally defines
the missions lifetime unless way to compensate for it is provided. This
environment is named Very Low Earth Orbit (VLEO) and is defined for $h<450~km$.
In addition to the satellite's aerodynamic design, to extend the lifetime of
such missions an efficient propulsion system is required.
  One solution is Atmosphere-Breathing Electric Propulsion (ABEP) that collects
atmospheric particles to be used as propellant for an electric thruster. The
system would minimize the requirement of limited propellant availability and
can also be applied to any planetary body with atmosphere, enabling new
missions at low altitude ranges for longer times. One of the objectives of the
H2020 DISCOVERER project, is the development of an intake and an electrode-less
plasma thruster for an ABEP system.
  The article describes the characteristics of intake design and the respective
final deigns providing collection efficiencies up to $94\%$. On the other side,
the radio frequency (RF) Helicon-based plasma thruster (IPT) developed at IRS,
is hereby presented as well, while its performances are being evaluated, the
thruster has been operated with single atmospheric species as propellant, and
has highlighted very low input power requirement for operation at comparable
mass flow rates $P\sim 60~W$.
