TU Darmstadt / ULB / TUbiblio

Unmanned Aerial Vehicle for Flow Control Experiments with Dielectric Barrier Discharge Plasma Actuators

Friedrichs, Wilm (2014):
Unmanned Aerial Vehicle for Flow Control Experiments with Dielectric Barrier Discharge Plasma Actuators.
Darmstadt, TU Darmstadt, [Online-Edition: http://tuprints.ulb.tu-darmstadt.de/3776],
[Ph.D. Thesis]

Abstract

Dielectric Barrier Discharge (DBD) plasma actuators are a relatively novel type of actuators for active flow control. They offer several benefits, such as fast reaction times due to the absence of mechanical parts. On the other hand there are several difficulties which must be overcome before they reach a stage of maturity suitable for application on aircraft.

In the present study the design, construction and commissioning of an Unmanned Aerial Vehicle (UAV) for flow control experiments with plasma actuators under realistic flight conditions is presented. The UAV has a wingspan of 2.38 m and a flight mass of approximately 10 kg. It is equipped with a flight control system to autonomously conduct the experiments and record measurement data. The fault-free operation of all systems, despite electromagnetic emissions from the high-voltage system of the actuators, and the suitability of the UAV as a flight-test platform have been demonstrated.

Two sections of the modular wing are used for flow control, different airfoil and actuator configurations can thus be interchanged. The attainable Reynolds numbers are in the range of 300, 000 to 600, 000. Validation of the entire system with several configurations has been performed in the wind tunnel prior to free-flight experiments.

Item Type: Ph.D. Thesis
Erschienen: 2014
Creators: Friedrichs, Wilm
Title: Unmanned Aerial Vehicle for Flow Control Experiments with Dielectric Barrier Discharge Plasma Actuators
Language: English
Abstract:

Dielectric Barrier Discharge (DBD) plasma actuators are a relatively novel type of actuators for active flow control. They offer several benefits, such as fast reaction times due to the absence of mechanical parts. On the other hand there are several difficulties which must be overcome before they reach a stage of maturity suitable for application on aircraft.

In the present study the design, construction and commissioning of an Unmanned Aerial Vehicle (UAV) for flow control experiments with plasma actuators under realistic flight conditions is presented. The UAV has a wingspan of 2.38 m and a flight mass of approximately 10 kg. It is equipped with a flight control system to autonomously conduct the experiments and record measurement data. The fault-free operation of all systems, despite electromagnetic emissions from the high-voltage system of the actuators, and the suitability of the UAV as a flight-test platform have been demonstrated.

Two sections of the modular wing are used for flow control, different airfoil and actuator configurations can thus be interchanged. The attainable Reynolds numbers are in the range of 300, 000 to 600, 000. Validation of the entire system with several configurations has been performed in the wind tunnel prior to free-flight experiments.

Place of Publication: Darmstadt
Uncontrolled Keywords: Unmanned Aerial Vehicle, UAV, Flow Control, DBD, Plasma Actuator
Divisions: 16 Department of Mechanical Engineering > Fluid Mechanics and Aerodynamics (SLA)
16 Department of Mechanical Engineering
Date Deposited: 02 Mar 2014 20:55
Official URL: http://tuprints.ulb.tu-darmstadt.de/3776
URN: urn:nbn:de:tuda-tuprints-37765
Referees: Tropea, Prof. Cameron and Klingauf, Prof. Uwe
Refereed / Verteidigung / mdl. Prüfung: 14 January 2014
Alternative keywords:
Alternative keywordsLanguage
Unbemanntes Luftfahrzeug, Strömungskontrolle, Plasma-AktuatorGerman
Alternative Abstract:
Alternative abstract Language
Dielectric Barrier Discharge (DBD) Plasma-Aktuatoren sind eine relativ neue Art von Aktuatoren zur aktiven Strömungskontrolle. Sie bieten eine Reihe von Vorteilen, wie ihre schnelle Reaktionszeit aufgrund des Fehlens von mechanischen Teilen. Andererseits gibt es einige Problematiken, die überwunden werden müssen, bevor sie einen für die Verwendung auf Flugzeugen erforderlichen Reifegrad erreichen. In der vorliegenden Arbeit wird daher die Entwicklung, Konstruktion und Inbetriebnahme eines Unmanned Aerial Vehicle (UAV) zur Durchführung von Experimenten zur Strömungskontrolle mit Plasma-Aktuatoren unter realen Flugbedingungen beschrieben. Das UAV hat eine Spannweite von 2, 38 m und eine Flugmasse von circa 10 kg. Zur automatischen Durchführung der Experimente und Messdatenerfassung ist es mit einem Flugkontrollsystem ausgerüstet. Die störungsfreie Funktion aller Systeme, trotz elektromagnetischer Einstreuung durch das Hochspannungssystem der Aktuatoren, und die Eignung des UAV als Messplattform wurden gezeigt. Zwei Segmente des modular aufgebauten Flügels werden zur Strömungskontrolle genutzt, verschiedene Flügelprofile und Aktuatorkonfigurationen können so verwendet und gegeneinander ausgetauscht werden. Die hierbei erreichten Reynoldszahlen liegen im Bereich von 300.000 bis 600.000. Vor Experimenten im Freiflug wurde eine Validierung des Gesamtsystems mit verschiedenen Konfigurationen im Windkanal durchgeführt.German
Export:
Suche nach Titel in: TUfind oder in Google

Optionen (nur für Redakteure)

View Item View Item