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PPT development for Nanosatellites applications: experimental results

PPT development for Nanosatellites applications: experimental results
PPT development for Nanosatellites applications: experimental results
In this paper, the design and performances of a
pulsed plasma thruster (PPT) for nanosatellite applications will
be presented. The breadboard model PPT presented in this paper
will be a part of six PPTs propulsion system designed to provide
attitude and translational control for a 20-kg nanosatellite for
a total delta-V of 40 m/s. The thruster performances have been
characterized in terms of electrical parameters, mass bit, impulse
bit, and specific impulse. The thruster was found to be compliant
with the mission requirement. Moreover, preliminary electromagnetic
noise interference measurements have been performed.
The spark plug discharge was found to be the main source of
noise as already found by previous authors. From the collected
data, it can be inferred that the noise is mostly radiated.
0093-3813
218-225
Coletti, Michele
2b74d4a0-0afd-4d17-aff6-70b27b531151
Ciarall, Simone
dd15fc8e-4a50-43f6-9cbf-0a87d025b5f6
Gabriel, Stephen
ac76976d-74fd-40a0-808d-c9f68a38f259
Coletti, Michele
2b74d4a0-0afd-4d17-aff6-70b27b531151
Ciarall, Simone
dd15fc8e-4a50-43f6-9cbf-0a87d025b5f6
Gabriel, Stephen
ac76976d-74fd-40a0-808d-c9f68a38f259

Coletti, Michele, Ciarall, Simone and Gabriel, Stephen (2014) PPT development for Nanosatellites applications: experimental results. IEEE Transactions on Plasma Science, 218-225. (doi:10.1109/TPS.2014.2368054). (In Press)

Record type: Article

Abstract

In this paper, the design and performances of a
pulsed plasma thruster (PPT) for nanosatellite applications will
be presented. The breadboard model PPT presented in this paper
will be a part of six PPTs propulsion system designed to provide
attitude and translational control for a 20-kg nanosatellite for
a total delta-V of 40 m/s. The thruster performances have been
characterized in terms of electrical parameters, mass bit, impulse
bit, and specific impulse. The thruster was found to be compliant
with the mission requirement. Moreover, preliminary electromagnetic
noise interference measurements have been performed.
The spark plug discharge was found to be the main source of
noise as already found by previous authors. From the collected
data, it can be inferred that the noise is mostly radiated.

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Accepted/In Press date: 3 November 2014
Organisations: EEE

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Local EPrints ID: 384415
URI: http://eprints.soton.ac.uk/id/eprint/384415
ISSN: 0093-3813
PURE UUID: 08adc494-01cc-4fa7-9509-4e9ba14d6a77

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Date deposited: 16 Dec 2015 16:38
Last modified: 16 Dec 2019 20:11

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