Kurz, Armin (2017)
In-Flight Application of Dielectric Barrier Discharge Plasma Actuators for Active Wave Control.
Technische Universität Darmstadt
Dissertation, Erstveröffentlichung
Kurzbeschreibung (Abstract)
In the presented study the active closed-loop control of boundary layer disturbances using dielectric barrier discharge plasma actuators is investigated. The main goal of the study was to increase the technological level of the technique and to demonstrate its applicability in flight under realistic atmospheric conditions. For this purpose an experimental setup has been developed, which can be utilized in the wind tunnel, as well as on a GROB G109b motorized glider. The wing glove provides storage space for the necessary data acquisition equipment and features exchangeable measurement inlays housing the actuators and sensors without interfering with the structural integrity of the aircraft’s wing. Additionally, the plasma actuator offers two variations in the mode of operation. On the one hand, the direct frequency mode has been investigated, which means the plasma actuator is operated directly at the frequency of the boundary layer disturbances to be controlled. On the other hand, the plasma actuator offers the possibility to combine boundary layer stabilization and active wave control in a single device. This hybrid mode of operation has been successfully investigated during this study for the first time. Boundary layer stabilization is applied by injection of momentum into the lower boundary layer, increasing its local stability. Using adaptive control and suitable flow sensors, the remaining boundary layer disturbances can be further reduced by the principle of negative linear superposition. The energy requirements of the plasma actuator are not significantly altered due to the periodic nature of the additional amplitude modulation as compared to pure boundary layer stabilization. Therefore, the control efficiency is increased. Significant transition delay results could be demonstrated in the wind tunnel, as well as in flight under atmospheric conditions.
| Typ des Eintrags: | Dissertation | ||||
|---|---|---|---|---|---|
| Erschienen: | 2017 | ||||
| Autor(en): | Kurz, Armin | ||||
| Art des Eintrags: | Erstveröffentlichung | ||||
| Titel: | In-Flight Application of Dielectric Barrier Discharge Plasma Actuators for Active Wave Control | ||||
| Sprache: | Englisch | ||||
| Referenten: | Tropea, Prof. Dr. Cameron ; King, Prof. Dr. Rudibert ; Grundmann, Prof. Dr. Sven | ||||
| Publikationsjahr: | 2017 | ||||
| Ort: | Darmstadt | ||||
| Datum der mündlichen Prüfung: | 26 Januar 2016 | ||||
| URL / URN: | http://tuprints.ulb.tu-darmstadt.de/5929 | ||||
| Kurzbeschreibung (Abstract): | In the presented study the active closed-loop control of boundary layer disturbances using dielectric barrier discharge plasma actuators is investigated. The main goal of the study was to increase the technological level of the technique and to demonstrate its applicability in flight under realistic atmospheric conditions. For this purpose an experimental setup has been developed, which can be utilized in the wind tunnel, as well as on a GROB G109b motorized glider. The wing glove provides storage space for the necessary data acquisition equipment and features exchangeable measurement inlays housing the actuators and sensors without interfering with the structural integrity of the aircraft’s wing. Additionally, the plasma actuator offers two variations in the mode of operation. On the one hand, the direct frequency mode has been investigated, which means the plasma actuator is operated directly at the frequency of the boundary layer disturbances to be controlled. On the other hand, the plasma actuator offers the possibility to combine boundary layer stabilization and active wave control in a single device. This hybrid mode of operation has been successfully investigated during this study for the first time. Boundary layer stabilization is applied by injection of momentum into the lower boundary layer, increasing its local stability. Using adaptive control and suitable flow sensors, the remaining boundary layer disturbances can be further reduced by the principle of negative linear superposition. The energy requirements of the plasma actuator are not significantly altered due to the periodic nature of the additional amplitude modulation as compared to pure boundary layer stabilization. Therefore, the control efficiency is increased. Significant transition delay results could be demonstrated in the wind tunnel, as well as in flight under atmospheric conditions. |
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| URN: | urn:nbn:de:tuda-tuprints-59294 | ||||
| Sachgruppe der Dewey Dezimalklassifikatin (DDC): | 600 Technik, Medizin, angewandte Wissenschaften > 620 Ingenieurwissenschaften und Maschinenbau | ||||
| Fachbereich(e)/-gebiet(e): | 16 Fachbereich Maschinenbau 16 Fachbereich Maschinenbau > Fachgebiet Strömungslehre und Aerodynamik (SLA) |
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| Hinterlegungsdatum: | 22 Jan 2017 20:55 | ||||
| Letzte Änderung: | 24 Apr 2018 16:14 | ||||
| PPN: | |||||
| Referenten: | Tropea, Prof. Dr. Cameron ; King, Prof. Dr. Rudibert ; Grundmann, Prof. Dr. Sven | ||||
| Datum der mündlichen Prüfung / Verteidigung / mdl. Prüfung: | 26 Januar 2016 | ||||
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| Suche nach Titel in: | TUfind oder in Google | ||||
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