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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
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
1361-6501
105101
Grubišić, A.N.
a4cab763-bbc0-4130-af65-229ae674e8c8
Gabriel, S.B
ac76976d-74fd-40a0-808d-c9f68a38f259
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), 105101. (doi:10.1088/0957-0233/21/10/105101).

Record type: Article

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

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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

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Date deposited: 16 Sep 2013 12:33
Last modified: 14 Mar 2024 14:50

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Contributors

Author: A.N. Grubišić
Author: S.B Gabriel

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