FIELD: engine building.
SUBSTANCE: invention relates to the field of tests of spacecraft engines. The proposed device operates according to a principle of tachometric flow meter. It contains a turbine in the form of a screw or a rod with a screw groove made of refractory metal and placed inside a rack, which is a cylindrical pipe with gas-intake slots. The rack is fixed in an active zone of a plasma engine, where the turbine is driven into rotation with a gas flow of a flowing working medium. A speed of rotation is measured with a magnetic current interrupter, by readings of which engine thrust is determined.
EFFECT: increase in the reliability of determination of engine thrust by direct measurement of parameters of a gas flow creating thrust (its flow rate).
1 cl, 1 dwg
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