FIELD: monitoring of parameters of solid-propellant rocket engine. SUBSTANCE: the device has a combustion chamber accommodating a restricted solid-propellant charge, radiation sensor, photoelectric amplifier and a multi-channel recorder with a time marker. The charge has holes, whose geometric axes are arranged at known distances from one another and are perpendicular to the charge geometric axis. Placed in the holes at different radii from the charge geometric axis are microdoses of chemical compounds of different replenishing elements of the alkali group within 0.001 cu.cm to 0.01 cu. cm. In different holes the microdose of the chemical compound of one and the same replenishing element is positioned on one radius from the charge geometric axis, and the free space between the microdoses is filled with an armoring compound. The sighting line of the radiation sensor is matched with the shear plane of the nozzle of the solid-propellant rocket engine, and a monochromatic filter is installed before the radiation sensor with a filtration wave- length equal to the wave-length of the saturated central part of the spectral line of one of the n-used replenishing elements of the alkali group, n-1 beam-splintering plates and an objective lens. Installed in each beam reflected from the beam-splintering plates is an additional monochromatic filter, having a filtration wave-length equal to the wave- length of the saturated central part of the spectral line of one of the n-used replenishing elements of the alkali group. EFFECT: measurement of the rate and uniformity of solid propellant burning. 2 dwg
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