FIELD: transportation.
SUBSTANCE: proposed method includes the formation of plasma flux by the plasma formation source along the magnetic diffuser axis and the flux influence upon the accelerated spacecraft magnetic reflecting system. The plasma flux in the case under consideration, is captured by a closed super-conducting circuit moved along with the accelerated spacecraft from the diffuser. This makes the diffuser magnetic field to get pressed, together with the plasma efflux, to the diffuser axis. One end of the said flux acts on the spacecraft magnetic reflecting system. The other one affecting the magnetic plug area formed inside the magnetic diffuser. To ensure a more complete compression of the diffuser magnetic field and plasma flux, a closed-circuit can be used incorporating a super-conducting locking ring system. With the spacecraft accelerated, these rings are consecutively disconnected from the circuit and arranged along the diffuser compressed magnetic field length.
EFFECT: longer acceleration distance and enhanced spacecraft acceleration characteristics.
10 cl, 2 dwg
