Survey on Electrical Propulsion Technologies for Potential Infusion in Dual-Mode Propulsion System with Green Chemical Propellant LMP-103S

The work carried out during the master’s thesis project at ECAPS AB aimed to investigate a potential electric thruster to be integrated into a dual-mode propulsion system. LMP-103S, a “green” propellant, represents one of the most important achievements of ECAPS AB, which focuses on green propellants for space applications and on the development of advanced rocket engines. The dual-mode propulsion system is one of the main research objectives and one of the most widely studied challenges by universities and companies worldwide. The interest lies in the possibility of using a single tank capable of feeding two distinct thrusters: one chemical and one electric. One of the company’s objectives is to develop a dual-mode propulsion system powered by its proprietary propellant. However, this propellant was originally conceived for chemical propulsion applications. The main challenge therefore lies in the composition of the propellant, which should not only be compatible with two different types of thrusters, but also ensure the required performance. Achieving this objective would bring several advantages, related both to chemical and to electric propulsion. During a mission, it would in fact be possible to exploit the high thrust and immediate response typical of a chemical thruster, together with the high specific impulse and the capability to sustain long-duration missions, which are characteristic of electric thrusters. The use of a single propellant would furthermore enable a significant reduction in onboard mass, a simplification from both a logistical and economic standpoint, as well as increased operational flexibility, redundancy, and reliability. To support this perspective, it was considered essential to present the electric propulsion technologies currently available on the market, the most commonly employed propellants, and their related advantages, including those in terms of nvironmental sustainability. A study is conducted on an electric thruster utilizing the combustion gases generated by the LMP-103S propellant. The objective is to utilize a Hall-effect thruster, specifically the Busek BHT-200 model already tested in previous campaigns, operating with the gases produced by a gas generator connected in series with the thruster. In addition, a transfer maneuver was performed to estimate the maximum altitude achievable. Finally, by fixing the propellant mass, a comparison with different propellants was carried out and their performance was discussed.