elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Impressum | Datenschutz | Kontakt | English
Schriftgröße: [-] Text [+]

Planar Micro Nozzles - CFD Model Demands for Thrust Optimization

Banuti, Daniel und Grabe, Martin und Hannemann, Klaus (2014) Planar Micro Nozzles - CFD Model Demands for Thrust Optimization. Space Propulsion 2014, 2014-05-19 - 2014-05-22, Cologne, Germany.

Dieses Archiv kann nicht den Volltext zur Verfügung stellen.

Offizielle URL: http://www.propulsion2014.com

Kurzfassung

Regarding current trends in the miniaturization of satellites, an appropriate propulsion system is sought. Within the EU project PRECISE, a system analysis has shown that a MEMS (micro-electro-mechanical system) monopropellant hydrazine thruster has the potential to deliver thrust and Isp on a level that cannot be matched by other microsystems (e.g. cold gas). While manufacturers and researchers are experienced in catalyst and MEMS design, there is to date no standard or state-of-the-art in the analysis and design of high Reynolds number, micro scale, planar nozzles. Therefore, we undertook a systematic study of the modeling demands for such flows. A first part concerns the thermochemical fluid representation in CFD. We show that a constant property perfect gas representation will misevaluate thruster performance, as changes in the isentropic exponent have major impact on the theoretical exhaust velocity. The error grows with the complexity of the exhaust molecules and is more pronounced for molecules such as ammonia NH3 which is present in hydrazine decomposition. Hence, it is also important to model the gas composition as detailed as possible. Heat loss in the combustion chamber is assessed, which is very pronounced in micro scale systems. It is shown that a thus reduced chamber temperature strongly affects engine efficiency and hence also needs to be incorporated into any serious analysis. Finally, geometrical simplifications in CFD are regarded. We demonstrate that planar nozzle flows are inherently three dimensional in nature; CFD analysis of a 2D configuration will yield grossly wrong results as it cannot capture the boundary layers growing from the top and bottom wall. This effect is a lot more pronounced than the boundary layers growing from the contoured nozzle walls. All four boundary layers interact, choking the nozzle flow until it almost resembles a fully developed pipe flow.

elib-URL des Eintrags:https://elib.dlr.de/89116/
Dokumentart:Konferenzbeitrag (Vortrag)
Zusätzliche Informationen:Paper-Nr. SP2014-2967647, Session 4
Titel:Planar Micro Nozzles - CFD Model Demands for Thrust Optimization
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Banuti, Danieldaniel.banuti (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Grabe, Martinmartin.grabe (at) dlr.dehttps://orcid.org/0000-0003-0361-2734NICHT SPEZIFIZIERT
Hannemann, Klausklaus.hannemann (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:2014
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Seitenbereich:Seiten 1-9
Name der Reihe:Confereance Proceedings on CD-ROM
Status:veröffentlicht
Stichwörter:MEMS, CFD, micro, nozzle
Veranstaltungstitel:Space Propulsion 2014
Veranstaltungsort:Cologne, Germany
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:19 Mai 2014
Veranstaltungsende:22 Mai 2014
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Raumfahrt
HGF - Programmthema:Raumtransport
DLR - Schwerpunkt:Raumfahrt
DLR - Forschungsgebiet:R RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):R - Raumfahrzeugsysteme - Numerische Verfahren und Simulation (alt)
Standort: Göttingen
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Raumfahrzeuge
Hinterlegt von: Micknaus, Ilka
Hinterlegt am:28 Aug 2014 10:04
Letzte Änderung:24 Apr 2024 19:55

Nur für Mitarbeiter des Archivs: Kontrollseite des Eintrags

Blättern
Suchen
Hilfe & Kontakt
Informationen
electronic library verwendet EPrints 3.3.12
Gestaltung Webseite und Datenbank: Copyright © Deutsches Zentrum für Luft- und Raumfahrt (DLR). Alle Rechte vorbehalten.