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Challenging space missions include those at very low altitudes, where theatmosphere is source of aerodynamic drag on the spacecraft. To extend suchmissions lifetime, an efficient propulsion system is required. One solution isAtmosphere-Breathing Electric Propulsion (ABEP). It collects atmosphericparticles to be used as propellant for an electric thruster. The system wouldminimize the requirement of limited propellant availability and can also beapplied to any planet with atmosphere, enabling new mission at low altituderanges for longer times. Challenging is also the presence of reactive chemicalspecies, such as atomic oxygen in Earth orbit. Such species cause erosion of(not only) propulsion system components, i.e. acceleration grids, electrodes,and discharge channels of conventional EP systems. IRS is developing within theDISCOVERER project, an intake and a thruster for an ABEP system. The paperdescribes the design and implementation of the RF helicon-based inductiveplasma thruster (IPT). This paper deals in particular with the design andimplementation of a novel antenna called the birdcage antenna, a device wellknown in magnetic resonance imaging (MRI), and also lately employed forhelicon-wave based plasma sources in fusion research. The IPT is based on RFelectrodeless operation aided by an externally applied static magnetic field.The IPT is composed by an antenna, a discharge channel, a movable injector, anda solenoid. By changing the operational parameters along with the novel antennadesign, the aim is to minimize losses in the RF circuit, and accelerate aquasi-neutral plasma plume. This is also to be aided by the formation ofhelicon waves within the plasma that are to improve the overall efficiency andachieve higher exhaust velocities. Finally, the designed IPT with a particularfocus on the birdcage antenna design procedure is presented

RF Helicon-based Inductive Plasma Thruster (IPT) Design for an Atmosphere-Breathing Electric Propulsion system (ABEP)