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European Student Moon Orbiter solar electric propulsion subsystem architecture: an all-electric spacecraft

Coletti, M., Grubisic, A, Collingwood, C., Wallace, N., Wells, N. and Gabriel, S.B. (2009) European Student Moon Orbiter solar electric propulsion subsystem architecture: an all-electric spacecraft Acta Astronautica, 65, (3-4), pp. 354-364. (doi:10.1016/j.actaastro.2009.03.001).

Record type: Article


This paper presents the results of the Phase A study for the solar electric propulsion subsystem selected for the ESA European
Student Moon Orbiter spacecraft, performed at QinetiQ under ESA funding. To minimise mass, a so-called “all electric” approach is adopted based around the re-use of a flight-spare GOCE T5 gridded ion engine and the introduction of hollow cathode thrusters (HCTs) for attitude control functions. Three different subsystem architectures are considered and analysed with reference to the mass, cost, risk and level of integration between the HCTs and the T5. The favoured system architecture that best meets the various requirements adopts a shared tank and gas flow controller between the HCTs and the T5, with power being supplied from two dedicated power processing units. The possibility of reducing the propellant requirement by using an engine gimbal mechanism is also presented. The study also demonstrates how an increase in the T5 specific impulse to higher values than used on GOCE does not offer substantial system-level mass savings in this particular case.

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Published date: August 2009
Organisations: Aeronautics, Astronautics & Comp. Eng


Local EPrints ID: 156383
ISSN: 0094-5765
PURE UUID: 9f838ae6-b70c-4487-891a-f3f8b300b0b6

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Date deposited: 02 Jun 2010 08:59
Last modified: 18 Jul 2017 12:43

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Author: M. Coletti
Author: A Grubisic
Author: C. Collingwood
Author: N. Wallace
Author: N. Wells
Author: S.B. Gabriel

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