Electrical rocket engine space of the world for duration flights

摘要

Electrical rocket engine of the magnet plasma type in which the working medium in the gaseous state in the working chamber 2 with an outlet nozzle between two flat electrodes 3 is supplied, and outside of the working chamber 2 the magnet system 1 which is composed of individual superconducting coils, which are placed in the cryostat and generate a magnetic field, which is oriented at right angles with respect to the current direction is aligned between the electrodes 3, characterized in that for the purpose of the extension of the service life of the electrical rocket engine according to the length of the invention, the working chamber 2 is increased, within the working chamber 2 a second pair of electrodes 4 is installed, and after the wear during the engine operation of the first pair of electrodes 3, the working chamber along the longitudinal axis of the engine is displaced with respect to the stationary magnet system 1 and a new position, wherein the second pair of electrodes 4 is used.