In-orbit Refuelling with Hydrogen Peroxide: An Architecture and Transfer Mechanism

Master thesis (2022)

Authors

E.D. Gilleran Aerospace Engineering

Contributors

B.V.S. Jyoti Space Systems Egineering (mentor)
R. Noomen Astrodynamics & Space Missions - Aerospace Engineering (graduation committee member)
E.K.A. Gill Space Systems Egineering (graduation committee member)
Dinesh Mengu (graduation committee member)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2022 Eoghan Gilleran
More Info
expand_more

Published Date

30-09-2022

Language

English

Reuse Rights

Other than for strictly personal use, it is not permitted to download, forward or distribute the text or part of it, without the consent of the author(s) and/or copyright holder(s), unless the work is under an open content license such as Creative Commons.

Faculty

Aerospace Engineering

Abstract

The current state of in-orbit refuelling involves launching propellant from the Earth’s surface in a single use refuelling craft, often to transfer hydrazine to the customer. This method is a logical first step however this architecture is not reusable, and it centres around a toxic and carcinogenic propellant. An architecture is proposed where hydrogen peroxide, a green oxidiser useful in both propulsion and power systems, is created from water ice in the solar system and refuelled with a reusable refuelling craft. First order sizing of the craft is conducted showing the viability of refuelling routes from Deimos, Phobos and the Moon. Prototype testing of a propellant transfer mechanism has shown the promise of using a piston-based transfer system, and the results of testing are used to better estimate the mass of a potential reusable refuelling craft.

Files

Thesis_E_Gilleran_In_Orbit_Ref... (pdf)
- Embargo expired in 29-09-2024
Unknown license