Micro Coriolis mass flow sensor for chemical micropropulsion systems

Remco J. Wiegerink; Theodorus S.J. Lammerink; Jarno Groenesteijn; Pieter J. Dijkstra; Joost Conrad Lötters

Micro Coriolis mass flow sensor for chemical micropropulsion systems

Remco J. Wiegerink, Theodorus S.J. Lammerink, Jarno Groenesteijn, Pieter J. Dijkstra, Joost Conrad Lötters

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Abstract

We have designed a micromachined micro Coriolis flow sensor for the measurement of hydrazine (N2H4, High Purity Grade) propellant flow in micro chemical propulsion systems. The sensor measures mass flow up to 10 mg/s for a single thruster or up to 40 mg/s for four thrusters. The sensor will first be used for measurement and characterization of the micro thruster system in a simulated space vacuum environment. Integration of the sensor chip within the micro thruster flight hardware will be considered at a later stage. The new chip has an increased flow range because of an integrated on-chip bypass channel.

Original language	Undefined
Number of pages	1
Publication status	Published - 15 Oct 2012
Event	8th ESA Micro & Nano Technologies Round Table for Space Applications Statistics 2012 - Noordwijk, Netherlands Duration: 15 Oct 2012 → 18 Oct 2012 Conference number: 8

Conference

Conference	8th ESA Micro & Nano Technologies Round Table for Space Applications Statistics 2012
Country/Territory	Netherlands
City	Noordwijk
Period	15/10/12 → 18/10/12

Keywords

EWI-24367
IR-89182

Access to Document

ESAMNT_Wiegerink

http://eprints.eemcs.utwente.nl/secure2/24367/01/ESAMNT_Wiegerink.pdf

Cite this

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title = "Micro Coriolis mass flow sensor for chemical micropropulsion systems",

abstract = "We have designed a micromachined micro Coriolis flow sensor for the measurement of hydrazine (N2H4, High Purity Grade) propellant flow in micro chemical propulsion systems. The sensor measures mass flow up to 10 mg/s for a single thruster or up to 40 mg/s for four thrusters. The sensor will first be used for measurement and characterization of the micro thruster system in a simulated space vacuum environment. Integration of the sensor chip within the micro thruster flight hardware will be considered at a later stage. The new chip has an increased flow range because of an integrated on-chip bypass channel.",

keywords = "EWI-24367, IR-89182",

author = "Wiegerink, {Remco J.} and Lammerink, {Theodorus S.J.} and Jarno Groenesteijn and Dijkstra, {Pieter J.} and L{\"o}tters, {Joost Conrad}",

note = "http://www.congrexprojects.com/2012-events/12c11/introduction; 8th ESA Micro & Nano Technologies Round Table for Space Applications Statistics 2012 ; Conference date: 15-10-2012 Through 18-10-2012",

year = "2012",

month = oct,

day = "15",

language = "Undefined",

}

Wiegerink, RJ, Lammerink, TSJ, Groenesteijn, J, Dijkstra, PJ & Lötters, JC 2012, 'Micro Coriolis mass flow sensor for chemical micropropulsion systems', Paper presented at 8th ESA Micro & Nano Technologies Round Table for Space Applications Statistics 2012, Noordwijk, Netherlands, 15/10/12 - 18/10/12. <http://eprints.eemcs.utwente.nl/secure2/24367/01/ESAMNT_Wiegerink.pdf>

TY - CONF

T1 - Micro Coriolis mass flow sensor for chemical micropropulsion systems

AU - Wiegerink, Remco J.

AU - Lammerink, Theodorus S.J.

AU - Groenesteijn, Jarno

AU - Dijkstra, Pieter J.

AU - Lötters, Joost Conrad

N1 - Conference code: 8

PY - 2012/10/15

Y1 - 2012/10/15

N2 - We have designed a micromachined micro Coriolis flow sensor for the measurement of hydrazine (N2H4, High Purity Grade) propellant flow in micro chemical propulsion systems. The sensor measures mass flow up to 10 mg/s for a single thruster or up to 40 mg/s for four thrusters. The sensor will first be used for measurement and characterization of the micro thruster system in a simulated space vacuum environment. Integration of the sensor chip within the micro thruster flight hardware will be considered at a later stage. The new chip has an increased flow range because of an integrated on-chip bypass channel.

AB - We have designed a micromachined micro Coriolis flow sensor for the measurement of hydrazine (N2H4, High Purity Grade) propellant flow in micro chemical propulsion systems. The sensor measures mass flow up to 10 mg/s for a single thruster or up to 40 mg/s for four thrusters. The sensor will first be used for measurement and characterization of the micro thruster system in a simulated space vacuum environment. Integration of the sensor chip within the micro thruster flight hardware will be considered at a later stage. The new chip has an increased flow range because of an integrated on-chip bypass channel.

KW - EWI-24367

KW - IR-89182

M3 - Paper

T2 - 8th ESA Micro & Nano Technologies Round Table for Space Applications Statistics 2012

Y2 - 15 October 2012 through 18 October 2012

ER -