FIELD: testing technology; engine building.
SUBSTANCE: invention relates to devices for testing electric rocket engines, in particular to reactive thrust meters. Electric rocket engine reactive thrust measuring device comprises a lever element, on one of which ends there is a receiving graphite plate, a support element, a strain gauge and a set of means for calculating a reactive thrust, where the strain gauge by one end is rigidly connected to the support member, and by the other end is rigidly connected to the lever element with formation in the strain gauge sensor of the area free from rigid connection, capable of microscopic parallel shift relative to the rigidly connected ends of the strain gauge sensor.
EFFECT: invention provides performance measurement in continuously operating mode of any ERE, including magnetic-plasma engines, in stationary mode of operation and provides for long-term tests.
9 cl, 3 dwg
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