| Abstrakt: |
In this research, the dielectric barrier discharge plasma driven channel flow with the applied magnetic field has been proposed for use as a thruster in propulsion applications and studied experimentally. Measurements of the thrust and consumed power of thruster for different values of the barrier thickness have been performed and the data have been compared with the corresponding ones without magnetic field. It is found that consumed power and thrust of the thruster in the presence of magnetic field are respectively little reduced and increased than that without the magnetic field. The measurements show that the effectiveness increases to a maximum and then drops as the operating voltage monotonically increases over a range from 12 to 26 kV. A power law analysis for revealing the relationships among the effectiveness, thrust, consumed power, and operating voltage has been presented for the thruster with and without the magnetic field. It is seen that the applied magnetic field and thicker dielectric barrier can lead to a higher effectiveness at the point of transition from the glow regime to the filamentary regime . The effects of micro-discharge channels on the effectiveness in the both regimes have been discussed. The observations indicate that in the presence of magnetic field, the additional micro-discharge channels are generated and develop along the magnetic field lines and the diffuse background emission of the discharge is stronger in plasma. The underlying physical mechanisms of mentioned phenomena have been explained and mainly ascribed to the enhanced ionization by applying the magnetic field. [ABSTRACT FROM AUTHOR] |
