FIELD: engines and pumps.
SUBSTANCE: proposed method comprises control over jet engine thrust vector, fuel flow running out from combustion chamber along Laval nozzle, lengthwise duplex control electromagnets mounted at nozzle outer expanded section, current MHD-generator installed at the nozzle throat, current stabiliser and rectifier and aircraft control system that controls said electromagnets. Control over jet engine thrust vector is ensured by deflection of plasma flow running out from combustion chambers with respect to nozzle mirror axis by electromagnetic field induced by control electromagnets. Plasma flow is known to consist of positively charge ions and electrons. Note here that bulk of ions is several orders of magnitudes higher than that of electrons. This defines the thrust vector by the direction of positive ion flow.
EFFECT: simplified design of aircraft, decreased weight, higher reliability of engine and aircraft.
4 cl, 2 dwg
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