On the Design of a Propulsion System for the Lunar Meteoroid Impact Observer (LUMIO)

Master thesis (2021)

Authors

F.A. Nett Aerospace Engineering

Contributors

A. Cervone Space Systems Egineering (mentor)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2021 Fabian Nett
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Published Date

13-10-2021

Language

English

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Faculty

Aerospace Engineering

Abstract

LUMIO is a 12U CubeSat destined for a halo orbit around the Earth-Moon L2 point, requiring 203 m/s of delta V for orbital transfer, station-keeping and disposal manoeuvres, to be delivered by its Main Propulsion System (MPS). A total impulse of 170 N-s is required to be delivered by its Reaction Control System (RCS) for de-tumbling and reaction wheel de-saturation. A custom propulsion system was designed including commercial-off-the-shelf thrusters, valves, filters, sensors and a micro-gear pump to fulfil these functions. The pump-fed MPS uses 'green' mono-propellant LMP-103s and the RCS uses water propellant, with a resulting wet mass of 5.563 kg for the MPS and 0.822 kg for the RCS.