Synchronous polyphase alternating current electrostatic ion thruster (SPACE-IT) for propulsion of spacecraft, such as for example satellites, mini-rockets, etc

An ion propulsion device, the device comprising:

• a plurality of emission modules arranged in an emission plane of the device, each said emission module comprising an insulating support, an emission electrode arranged on the insulating support, and a tank of conductive liquid with a microfluidic channel arranged to deposit conductive liquid on the emission electrode;
• an extraction electrode common to the plurality of emission modules and arranged opposite the plurality of emission modules;
• and
• at least one control unit;
• wherein:
• each said emission module is configured to emit an ion beam when an electric field is applied to the conductive liquid;
• the at least one control unit is configured to control an emission current of the ions emitted by the application of a potential difference between at least one emission electrode of the plurality of emission electrodes and the extraction electrode;
• the emission electrodes of the plurality of emission modules are spaced apart from one another by a linear distance I greater than a breakdown distance between two adjacent emission electrodes separated by an empty space, the linear distance | being less than the propagation distance of an electric leakage current by hopping conduction along the insulating support between the emission electrodes;
• and
• a length L of an insulating support between the emission electrodes is greater than a propagation distance of an electric leakage current by hopping conduction along the insulating support between the emission electrodes, the linear distance I and the length L of the insulating support being chosen so as to | maximize the number of the plurality of emission modules in the emission plane.