A momentum flux measuring instrument (MFMI) has been used to take thrust measurements of the helicon double layer thruster (HDLT) prototype immersed in a vacuum chamber. The MFMI recorded a sharp increase in force when the plasma transitioned into a low-magnetic field, high-density mode. The HDLT uses a helicon antenna to generate an ion beam-containing plasma in a diverging magnetic field. The presence of a low-magnetic field mode in the HDLT prototype was demonstrated and its properties were explored at 0.3 mTorr argon at various applied rf powers, locations within the source tube and downstream vacuum chamber, and applied magnetic field strengths. The low-magnetic field mode occurs at solenoid currents that correspond to peak magnetic fi...
International audienceThe variation of electron density (ne), ion °ux and emission of argon lines we...
A xenon ion beam is spatially characterized by using a retarding-field energy analyzer positioned 7 ...
In order to enable comparison of Helicon ion thruster performance across different vacuum test facil...
A conical pyrex plasma source with a conical helicon antenna surrounded by two cylindrically wound s...
Transverse magnetic fields (along the x-axis, transverse to the z-axis) are applied to a helicon dou...
The performance of a helicon double layer thruster (HDLT) has been characterized using a pendulum ty...
A high density ‘blue ’ mode has been observed when operating the Helicon Double Layer Thruster (HDLT...
An experimental characterization of the ion beam formed during a low magnetic field (<3 mT) helicon ...
Direct thrust measurements of a permanent magnet helicon double layer thruster have been made using ...
This thesis describes an experimental investigation into the performance of a radio frequency plasma...
This thesis is concerned with characterising the plume expansion in the magnetic nozzle of a helicon...
A prototype of the helicon double-layer thruster (HDLT) has been tested and characterized when immer...
Ion energy distribution functions are measured using a retarding field energy analyser located 7.5 c...
Optimization of radiofrequency (RF) plasma sources for the development of space thrusters differs fr...
International audienceThe self-consistently generated current-free electric double layer (DL) is sho...
International audienceThe variation of electron density (ne), ion °ux and emission of argon lines we...
A xenon ion beam is spatially characterized by using a retarding-field energy analyzer positioned 7 ...
In order to enable comparison of Helicon ion thruster performance across different vacuum test facil...
A conical pyrex plasma source with a conical helicon antenna surrounded by two cylindrically wound s...
Transverse magnetic fields (along the x-axis, transverse to the z-axis) are applied to a helicon dou...
The performance of a helicon double layer thruster (HDLT) has been characterized using a pendulum ty...
A high density ‘blue ’ mode has been observed when operating the Helicon Double Layer Thruster (HDLT...
An experimental characterization of the ion beam formed during a low magnetic field (<3 mT) helicon ...
Direct thrust measurements of a permanent magnet helicon double layer thruster have been made using ...
This thesis describes an experimental investigation into the performance of a radio frequency plasma...
This thesis is concerned with characterising the plume expansion in the magnetic nozzle of a helicon...
A prototype of the helicon double-layer thruster (HDLT) has been tested and characterized when immer...
Ion energy distribution functions are measured using a retarding field energy analyser located 7.5 c...
Optimization of radiofrequency (RF) plasma sources for the development of space thrusters differs fr...
International audienceThe self-consistently generated current-free electric double layer (DL) is sho...
International audienceThe variation of electron density (ne), ion °ux and emission of argon lines we...
A xenon ion beam is spatially characterized by using a retarding-field energy analyzer positioned 7 ...
In order to enable comparison of Helicon ion thruster performance across different vacuum test facil...