DEVICE FOR MEASURING THE TEMPERATURE OF A LIQUID PROPELLANT ROCKET ENGINE NOZZLE Russian patent published in 2021 - IPC F02K9/64 

FIELD: rocketry.

SUBSTANCE: invention relates to methods for functional monitoring and diagnostics of the state of complex pneumohydraulic objects, for example, liquid propellant rocket engines (LRE). A device for measuring the temperature of the walls of a rocket engine nozzle is proposed, which contains a nozzle made of electrically conductive and heat-resistant materials, on the inner surface of which a layer of material with a low work function of electrons is applied, while the emission layer on the surface of the nozzle forms a cathode, at the exit from the nozzle there is an anode, wherein, the anode is electrically connected in series with the cathode through the power source, the anode is in mechanical contact with the nozzle through the electrical insulation layer, the emission layer is made in the form of a ring with a thickness of 5 to 10 mm, in the critical section, in the electrical circuit between the anode and the voltage source is a measuring complex.

EFFECT: invention improves the accuracy of temperature measurement in the area of ​​the critical section of the liquid propellant rocket engine nozzle.

1 cl, 1 dwg