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Characterization of the T-series hollow cathode thrusters for all-electric spacecraft

Characterization of the T-series hollow cathode thrusters for all-electric spacecraft
Characterization of the T-series hollow cathode thrusters for all-electric spacecraft
This paper presents the Phase A study of the Solar Electric Propulsion subsystem
selected for the ESA European Student Moon Orbiter enhanced microsatellite, performed at
QinetiQ under ESA funding. To minimise mass, a so-called "all electric" approach is
adopted based around the re-use of the GOCE T5 gridded ion engine and the introduction of
Hollow Cathode Thrusters (HCTs) for attitude control functions. Three different subsystem
architectures are considered and analyzed 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.
Grubisic, Angelo
a4cab763-bbc0-4130-af65-229ae674e8c8
Gabriel, Stephen
ac76976d-74fd-40a0-808d-c9f68a38f259
Grubisic, Angelo
a4cab763-bbc0-4130-af65-229ae674e8c8
Gabriel, Stephen
ac76976d-74fd-40a0-808d-c9f68a38f259

Grubisic, Angelo and Gabriel, Stephen (2007) Characterization of the T-series hollow cathode thrusters for all-electric spacecraft. 30th International Electric Propulsion Conference. 17 - 20 Sep 2007.

Record type: Conference or Workshop Item (Paper)

Abstract

This paper presents the Phase A study of the Solar Electric Propulsion subsystem
selected for the ESA European Student Moon Orbiter enhanced microsatellite, performed at
QinetiQ under ESA funding. To minimise mass, a so-called "all electric" approach is
adopted based around the re-use of the GOCE T5 gridded ion engine and the introduction of
Hollow Cathode Thrusters (HCTs) for attitude control functions. Three different subsystem
architectures are considered and analyzed 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: 2007
Venue - Dates: 30th International Electric Propulsion Conference, 2007-09-17 - 2007-09-20
Organisations: Aerodynamics & Flight Mechanics Group, Astronautics Group

Identifiers

Local EPrints ID: 402478
URI: http://eprints.soton.ac.uk/id/eprint/402478
PURE UUID: f883d38b-4e8e-4f94-89ed-58d33f03634f

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Date deposited: 10 Nov 2016 12:21
Last modified: 15 Mar 2024 03:19

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Contributors

Author: Angelo Grubisic
Author: Stephen Gabriel

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