Hall engine electric jet propulsion system intended for use by spacecraft for inter-orbital transfer, orbit correction, and stabilization. The design featured high reliability due to duplication of the main units and assemblies. The stationary plasma engine with an anode layer could produce an exhaust velocity of 16000 m/s, had an energy efficiency of 16500 W/N, and provided a total impulse of 1.2 million N-s. Maximum continuous power consumption was 800 W, and service life 16 years, of which 300 hours could be continuous operation. Probability of failure-free operation was 0.98 and the engine exhaust was found to not affect the service life of solar arrays or interfere with radio transmissions from the spacecraft to ground.