Development of an indirect measurement Micro-to-Milli-Newton thrust balance
Development of an indirect measurement Micro-to-Milli-Newton thrust balance
The performance of an indirect pendulum thrust balance suitable for micro-Newton level thrusters is presented. A design based on a frictionless pendulum with a laser optical lever and detection system makes it possible for thrusters to be mounted independently of the thrust measurement system. This simplifies the process of calibration without having to compensate for electrical connections, flow lines and other equipment. Measurements are not limited by thruster mass and offer thrust measurements down to 80?N. The balance was demonstrated by measuring the performance of two micro propulsion devices; the T5 and T6 hollow cathode thrusters. The T5 generating thrusts from 0.1mN to 1.4mN and the T6 showed thrusts from 0.2mN to 1.9mN.
thrust balance, propulsion, space, hollow cathode
Grubisic, A.N.
a4cab763-bbc0-4130-af65-229ae674e8c8
Gabriel, S.B.
ac76976d-74fd-40a0-808d-c9f68a38f259
5 May 2008
Grubisic, A.N.
a4cab763-bbc0-4130-af65-229ae674e8c8
Gabriel, S.B.
ac76976d-74fd-40a0-808d-c9f68a38f259
Grubisic, A.N. and Gabriel, S.B.
(2008)
Development of an indirect measurement Micro-to-Milli-Newton thrust balance.
2nd International Symposium on Propulsion for Space Transportation, Crete, Greece.
05 - 08 May 2008.
11 pp
.
Record type:
Conference or Workshop Item
(Paper)
Abstract
The performance of an indirect pendulum thrust balance suitable for micro-Newton level thrusters is presented. A design based on a frictionless pendulum with a laser optical lever and detection system makes it possible for thrusters to be mounted independently of the thrust measurement system. This simplifies the process of calibration without having to compensate for electrical connections, flow lines and other equipment. Measurements are not limited by thruster mass and offer thrust measurements down to 80?N. The balance was demonstrated by measuring the performance of two micro propulsion devices; the T5 and T6 hollow cathode thrusters. The T5 generating thrusts from 0.1mN to 1.4mN and the T6 showed thrusts from 0.2mN to 1.9mN.
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e-pub ahead of print date: May 2008
Published date: 5 May 2008
Venue - Dates:
2nd International Symposium on Propulsion for Space Transportation, Crete, Greece, 2008-05-05 - 2008-05-08
Keywords:
thrust balance, propulsion, space, hollow cathode
Organisations:
Astronautics Group
Identifiers
Local EPrints ID: 72465
URI: http://eprints.soton.ac.uk/id/eprint/72465
PURE UUID: d2b0d6e8-6a20-4598-8644-4a365e03d601
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Date deposited: 15 Feb 2010
Last modified: 13 Mar 2024 21:30
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Author:
S.B. Gabriel
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