Development of an indirect counterbalanced pendulum optical-lever thrust balance for micro- to millinewton thrust measurement
Development of an indirect counterbalanced pendulum optical-lever thrust balance for micro- to millinewton thrust measurement
This paper describes the design and testing of an indirect hanging pendulum thrust balance using a laser-optical-lever principle to provide micro- to millinewton thrust measurement for the development of electric propulsion systems. The design philosophy allows the selection of the total thrust range in order to maximize resolution through a counterbalanced pendulum principle, as well as passive magnetic damping in order to allow relatively rapid transient thrust measurement. The balance was designed for the purpose of hollow cathode microthruster characterization, but could be applied to other electric propulsion devices in the thrust range of micro- to millinewtons. An initial thrust characterization of the T5 hollow cathode is presented
105101
Grubišić, A.N.
a4cab763-bbc0-4130-af65-229ae674e8c8
Gabriel, S.B
ac76976d-74fd-40a0-808d-c9f68a38f259
3 August 2010
Grubišić, A.N.
a4cab763-bbc0-4130-af65-229ae674e8c8
Gabriel, S.B
ac76976d-74fd-40a0-808d-c9f68a38f259
Grubišić, A.N. and Gabriel, S.B
(2010)
Development of an indirect counterbalanced pendulum optical-lever thrust balance for micro- to millinewton thrust measurement.
Measurement Science and Technology, 21 (10), .
(doi:10.1088/0957-0233/21/10/105101).
Abstract
This paper describes the design and testing of an indirect hanging pendulum thrust balance using a laser-optical-lever principle to provide micro- to millinewton thrust measurement for the development of electric propulsion systems. The design philosophy allows the selection of the total thrust range in order to maximize resolution through a counterbalanced pendulum principle, as well as passive magnetic damping in order to allow relatively rapid transient thrust measurement. The balance was designed for the purpose of hollow cathode microthruster characterization, but could be applied to other electric propulsion devices in the thrust range of micro- to millinewtons. An initial thrust characterization of the T5 hollow cathode is presented
Text
0957-0233_21_10_105101.pdf
- Version of Record
Restricted to Repository staff only
Request a copy
More information
Published date: 3 August 2010
Organisations:
Astronautics Group
Identifiers
Local EPrints ID: 356588
URI: http://eprints.soton.ac.uk/id/eprint/356588
ISSN: 1361-6501
PURE UUID: 1fd8c10b-eebf-4287-94e3-8f1b98d903be
Catalogue record
Date deposited: 16 Sep 2013 12:33
Last modified: 14 Mar 2024 14:50
Export record
Altmetrics
Contributors
Author:
S.B Gabriel
Download statistics
Downloads from ePrints over the past year. Other digital versions may also be available to download e.g. from the publisher's website.
View more statistics