Self-neutralization electric propulsion device based on ultrasonic electric fuel injection technology

Abstract

The invention discloses a self-neutralization electric propulsion device based on an ultrasonic electric fuel injection technology. The self-neutralization electric propulsion device comprises a plurality of ultrasonic nozzles formed in parallel and annular attraction poles arranged at the output ends of the nozzles separately, wherein the emission surfaces of the ultrasonic nozzles generate liquid-state micro standing wave arrays through mechanism vibration, pulsed high voltages with opposite polarities are applied onto each two adjacent annular attraction poles separately, and the annular attraction poles apply pulsed electric fields onto the micro standing wave arrays on the emission surfaces of the ultrasonic nozzles, so that a working solution at the wave crests of micro standing waves generate charge concentration and is stressed by an electric field force; and Taylor cones occur at the tops of the standing waves, and micro charged droplets are injected under the action of the electric field force, surface tension and an inertia force.

Description

technical field [0001] The invention relates to an electric propulsion (Electric Propulsion) charged droplet neutralization technology in the field of aerospace, in particular to a self-neutralization electric propulsion device using ultrasonic electrospray as an emission source and a neutralization source. Background technique [0002] At present, most electrostatic thrusters generate thrust by launching charged liquid droplets or charged particles. However, when the thrust is formed, a large amount of excess electric charge will be generated and attached to the surface of the spacecraft and equipment. If these harmful charges are not dealt with, it will cause the plume to continue to charge the spacecraft to a higher electric potential. This will cause harmful interference to the payload and system equipment, and in extreme cases will cause the failure of spacecraft equipment. In addition, for the electrostatic thruster, when the charged particles pass through the suctio...

AI Technical Summary

Problems solved by technology

At present, the main neutralizer used in the electric propulsion thruster is the hollow cathode. The hollow cathode needs a sufficiently stable propellant to work. The complex propellant storage and supply system reduces the payload of the aircraft, which is not conducive to the miniaturization of the electric propulsion system. Miniaturization

The small colloidal ion thruster newly developed in the United States uses a carbon nanotube field emission cathode as a neutralizer. This cathode has a complex manufacturing process and a high emission field strength.

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