Feasibility analysis and preliminary design of an Helicon-based ABEP in VLMO

This project focuses on a feasibility study of an Helicon-based air breathing electric propulsion system in a Very Low Mars Orbit (VLMO) associated to a preliminary design of the spacecraft itself. First, it’s presented a model of the martian atmosphere, this will then be used to obtain a drag model necessary to simulate a spacecraft with set preliminary characteristics such as dimensions and drag coefficient. Then, a concept of operations will be carried out, composed by a first transfer orbit study since the spacecraft will likely be deployed in a larger orbit than the operational one, followed by a choice of the payload brought in the satellite and a preliminary sizing. A Global Model (GM) will then be presented, the numerical suite will allow to evaluate the propulsive performances of the engine and the Plasma Composition Characteristics (PCC) inside the ionization chamber thanks to the consideration of the reactions happening inside the propeller. The GM will be validated through simulations and comparisons with already existing results. Last, the simulation will be computed using set characteristics to evaluate the range of altitudes and powers in which such a mission is feasible.