Dielectric barrier discharge plasma actuators generate a net response force that exhibits potential for thrust applications such as propulsive systems. In this work, an angled actuator in which the exposed and encased electrodes are not parallel has been investigated using direct force measurements and particle image velocimetry. It was shown that the induced force was nonlinearly increased by increasing the angle between the electrodes. In addition, the direction of the upstream component of the ionic wind was changed by varying the electrode angle. Modifying the angle between the electrodes changes the electric field strength in the vicinity of the plasma actuator, thereby changing the response force produced. Analytical calculations were used to compare expected results with results obtained experimentally. Then, using the results obtained experimentally, a plasma thruster was designed as proof of concept for dielectric barrier discharge plasma actuators as propulsive devices.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Atmospheric Plasma Thruster: Theory and Concept


    Contributors:
    Greig, A. (author) / Birzer, C. H. (author) / Arjomandi, M. (author)

    Published in:

    AIAA Journal ; 51 , 2 ; 362-371


    Publication date :

    2013-02-01




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    The Microwave Thermal Thruster Concept

    Parkin, K. L. G. / DiDomenico, L. D. / Culick, F. E. C. et al. | British Library Conference Proceedings | 2004



    Experimental Evaluation of a Micro Liquid Pulsed Plasma Thruster Concept

    Simon, D. / Land, B. / Emhoff, J. et al. | British Library Conference Proceedings | 2006


    The Microwave Thermal Thruster Concept

    Parkin, Kevin L. G. / DiDomenico, Leo D. / Culick, Fred E. C. | American Institute of Physics | 2004