DEVICE FOR MEASUREMENT OF PROPELLANT BURNING RATE IN SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2001 - IPC

FIELD: monitoring of parameters of solid-propellant rocket engine. SUBSTANCE: the device has a combustion chamber of the solid-propellant rocket engine accommodating an end-burning solid-propellant charge and a rod with a number of orifices, whose geometric axes are positioned at known distances from one another and perpendicular to the geometric axis of the rod installed inside the charge in parallel with the combustion chamber axis and shortening at a rate equal to the rate of movement of charge burning front, radiation sensor, photoamplifier and a recording instrument with a time marker. Besides, each orifice of the rod accommodates a microdose of chemical compound of the alkaline group addition element. Installed before the radiation sensor is a monochromatic filter with a filtration wavelength equal to the wavelength of the central part of the spectral line of the alkaline group addition element. The sighting line of the radiation sensor with the monochromatic filter passes through the shear plane of the solid-propellant rocket engine nozzle. EFFECT: removal of modulated radiation from the combustion chamber of the solid- propellant rocket engine, as a result, enhanced number of the results of measurement of burning rate per experiment. 1 cl, 2 dwg