De-risk assessment: De-risking a novel electrodeless propulsion system

• The IRS IPT lab model with SSI PPU and FCU shall be able to ignite the plasma at a mass flow rate of 0.1-1.0 mg/s ±5% using Argon as a propellant • The SSI throttleable valve shall provide a mass flow rate of 0.1-1.0 mg/s ±5% necessary for ignition and operation of the thruster. • The SSI PPU shall provide a variable 50-100W ±5% RF power at 40.68 ± 1 MHz necessary for ignition and operation of the thruster

Achievements: • Successful plasma ignition was demonstrated with SSI-developed subsystems and the IRS IPT lab model. The ignition test campaign was conducted from 11th -14th April 2023 at IRS, Stuttgart. • Two PPU amplifiers were designed, simulated, built, and tested; the Class E amplifier successfully ignited the thruster. • Four throttleable valves (identified as critical components of FCU) concepts were designed, simulated, manufactured, and tested. Concept no.3 was coupled with IRS TH. It displayed successful plasma ignition as well as continued operation in the range of 0.08 – 1 mg/s. • Demonstrated the competence of SSI, as an SME, to develop and successfully demonstrate two mission-critical subsystems in a limited timeframe.   Benefits: • BC-EP propulsion system, is an electrodeless thruster that exhausts a quasi-neutral plasma and is, therefore, able to operate in VLEO and above while miAgaAng performance degradaAon. • The thruster possesses mulA-propellant capability, including propellants of aggressive corrosive nature, variable density, and composiAon. This can impact missions' cost and sustainability due to non-reliance on expensive/rare propellants. • Due to its simplicity and no-neutralizer design, it has lower component count thus imparAng high reliability, reduced lead Ame, and low cost beneficial for commercial missions. • It is also compaAble with future plaKorm needs such as on-orbit refueling, Atmosphere Breathing Electric Propulsion