ABLATION PULSE PLASMA ENGINE Russian patent published in 2019 - IPC F03H1/00 H05H1/54 

FIELD: astronautics.

SUBSTANCE: invention relates to electric rocket engines used in spacecraft propulsion systems. Ablation pulse plasma engine comprises two discharge electrodes installed opposite each other: cathode (1) and anode (2). Electrodes form an expanding discharge channel. End insulator (3) is installed between electrodes. Electrodes are connected through current leads (5 and 6) to capacitive energy storage. Two dielectric blocks (4) made of ablating material are arranged on the side of end insulator between discharge electrodes. Device (7) for initiation of electric discharge includes electrodes installed through hole made in cathode in discharge channel between end surfaces of dielectric blocks. Discharge electrodes are installed so that tangents to opposite located generatrixes of their surfaces in longitudinal plane of section of discharge channel, at least, within channel section between end surfaces of dielectric blocks are located at acute angle relative to each other. Cross-section of dielectric blocks according to shape and dimensions corresponds to longitudinal section of discharge channel section limited by surface of end insulator and side surface of blocks facing open part of discharge channel. Discharge electrodes are made with a flat or curved surface.

EFFECT: use of invention increases efficiency of working substance use, increases specific thrust pulse and increases traction efficiency of plasma engine.

7 cl, 3 dwg