Performance improvement on MEMS micropropulsion system through a novel two-depth micronozzle design

K. H. Cheah, J. K. Chin

Research output: Contribution to journalArticle

23 Citations (Scopus)

Abstract

A novel micronozzle geometry with different depths at converging and diverging section was designed with the aim in mitigating viscous loss due to formation of subsonic viscous boundary layers at nozzle sidewalls. Feasible fabrication schemes based on available fabrication techniques, deep reactive ion etching (DRIE) and low temperature co-fired ceramic (LTCC) tapes, were proposed to prove practicality of the design. Numerical simulations were performed in evaluating the parameters of micronozzle performance, thrust, mass flow rate and specific impulse efficiency, for both 3D linear and two-depth micronozzles with 15° and 30° expander half-angles over a range of throat Reynolds numbers (Rethroat≈601068). Pressurized nitrogen gas was selected as propellant in this study. Comparison of numerical results shows two-depth micronozzles outperform linear micronozzles for the entire range of Re throat and all performance parameters. The new micronozzle design has successfully reduced viscous loss through shorter expander length and mitigation of subsonic layers merging at nozzle expander section. Although the asymmetric geometry was found inducing a Z-axis thrust component, it can be offset through proper arrangement of the micronozzles. In conclusion, the design demonstrates improved performance over conventional micropropulsion system utilizing linear micronozzles by approximately 5%.

LanguageEnglish
Pages59-70
Number of pages12
JournalActa Astronautica
Volume69
Issue number1-2
Early online date25 Mar 2011
DOIs
Publication statusPublished - 1 Jul 2011
Externally publishedYes

Fingerprint

MEMS
Nozzles
Fabrication
Geometry
Reactive ion etching
Propellants
Merging
Tapes
Boundary layers
Reynolds number
Flow rate
Nitrogen
Computer simulation
Gases
Temperature

Cite this

@article{5d184a6afcfa4974bd66e4601188a959,
title = "Performance improvement on MEMS micropropulsion system through a novel two-depth micronozzle design",
abstract = "A novel micronozzle geometry with different depths at converging and diverging section was designed with the aim in mitigating viscous loss due to formation of subsonic viscous boundary layers at nozzle sidewalls. Feasible fabrication schemes based on available fabrication techniques, deep reactive ion etching (DRIE) and low temperature co-fired ceramic (LTCC) tapes, were proposed to prove practicality of the design. Numerical simulations were performed in evaluating the parameters of micronozzle performance, thrust, mass flow rate and specific impulse efficiency, for both 3D linear and two-depth micronozzles with 15° and 30° expander half-angles over a range of throat Reynolds numbers (Rethroat≈601068). Pressurized nitrogen gas was selected as propellant in this study. Comparison of numerical results shows two-depth micronozzles outperform linear micronozzles for the entire range of Re throat and all performance parameters. The new micronozzle design has successfully reduced viscous loss through shorter expander length and mitigation of subsonic layers merging at nozzle expander section. Although the asymmetric geometry was found inducing a Z-axis thrust component, it can be offset through proper arrangement of the micronozzles. In conclusion, the design demonstrates improved performance over conventional micropropulsion system utilizing linear micronozzles by approximately 5{\%}.",
keywords = "CFD, MEMS, Micro- and nanosatellites, Micronozzle, Micropropulsion",
author = "Cheah, {K. H.} and Chin, {J. K.}",
year = "2011",
month = "7",
day = "1",
doi = "10.1016/j.actaastro.2011.02.018",
language = "English",
volume = "69",
pages = "59--70",
journal = "Acta Astronautica",
issn = "0094-5765",
publisher = "Elsevier Limited",
number = "1-2",

}

Performance improvement on MEMS micropropulsion system through a novel two-depth micronozzle design. / Cheah, K. H.; Chin, J. K.

In: Acta Astronautica, Vol. 69, No. 1-2, 01.07.2011, p. 59-70.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Performance improvement on MEMS micropropulsion system through a novel two-depth micronozzle design

AU - Cheah, K. H.

AU - Chin, J. K.

PY - 2011/7/1

Y1 - 2011/7/1

N2 - A novel micronozzle geometry with different depths at converging and diverging section was designed with the aim in mitigating viscous loss due to formation of subsonic viscous boundary layers at nozzle sidewalls. Feasible fabrication schemes based on available fabrication techniques, deep reactive ion etching (DRIE) and low temperature co-fired ceramic (LTCC) tapes, were proposed to prove practicality of the design. Numerical simulations were performed in evaluating the parameters of micronozzle performance, thrust, mass flow rate and specific impulse efficiency, for both 3D linear and two-depth micronozzles with 15° and 30° expander half-angles over a range of throat Reynolds numbers (Rethroat≈601068). Pressurized nitrogen gas was selected as propellant in this study. Comparison of numerical results shows two-depth micronozzles outperform linear micronozzles for the entire range of Re throat and all performance parameters. The new micronozzle design has successfully reduced viscous loss through shorter expander length and mitigation of subsonic layers merging at nozzle expander section. Although the asymmetric geometry was found inducing a Z-axis thrust component, it can be offset through proper arrangement of the micronozzles. In conclusion, the design demonstrates improved performance over conventional micropropulsion system utilizing linear micronozzles by approximately 5%.

AB - A novel micronozzle geometry with different depths at converging and diverging section was designed with the aim in mitigating viscous loss due to formation of subsonic viscous boundary layers at nozzle sidewalls. Feasible fabrication schemes based on available fabrication techniques, deep reactive ion etching (DRIE) and low temperature co-fired ceramic (LTCC) tapes, were proposed to prove practicality of the design. Numerical simulations were performed in evaluating the parameters of micronozzle performance, thrust, mass flow rate and specific impulse efficiency, for both 3D linear and two-depth micronozzles with 15° and 30° expander half-angles over a range of throat Reynolds numbers (Rethroat≈601068). Pressurized nitrogen gas was selected as propellant in this study. Comparison of numerical results shows two-depth micronozzles outperform linear micronozzles for the entire range of Re throat and all performance parameters. The new micronozzle design has successfully reduced viscous loss through shorter expander length and mitigation of subsonic layers merging at nozzle expander section. Although the asymmetric geometry was found inducing a Z-axis thrust component, it can be offset through proper arrangement of the micronozzles. In conclusion, the design demonstrates improved performance over conventional micropropulsion system utilizing linear micronozzles by approximately 5%.

KW - CFD

KW - MEMS

KW - Micro- and nanosatellites

KW - Micronozzle

KW - Micropropulsion

UR - http://www.scopus.com/inward/record.url?scp=79956096024&partnerID=8YFLogxK

U2 - 10.1016/j.actaastro.2011.02.018

DO - 10.1016/j.actaastro.2011.02.018

M3 - Article

VL - 69

SP - 59

EP - 70

JO - Acta Astronautica

T2 - Acta Astronautica

JF - Acta Astronautica

SN - 0094-5765

IS - 1-2

ER -