FIELD: engines and pumps.
SUBSTANCE: invention relates to testing low-thrust liquid-propellant rocket engines. Device for measuring mass of liquid fuel components during operation of low-thrust rocket engine in mode of single inclusions and in pulse modes, consisting of electropneumatic valve, graduated glass tubes of different diameters, wherein each tube is connected to common header by means of electropneumatic valves and shutoff electropneumatic valve, according to the invention between the cavity of the device supercharging and the outlet header there is a pressure difference sensor with the possibility of measuring pressure drop before and after the engine start when the sensor readings stabilization and transmission of the signal to the computer system for measuring, processing and displaying information, and tubes contain fuel components, their number, diameter and length ensure engine operation from minimum single engine switching to mode with maximum number and duration of pulses during engine operation in pulsed mode. Differential pressure sensor with analogue or digital signal is used.
EFFECT: invention provides higher accuracy of determination of main parameters of liquid components required for determination of weight of fuel passed through engine.
3 cl, 1 dwg
