PRESSURE SENSOR SYSTEM INCLUDED WITHIN THE STRUCTURE OF ROCKET ENGINE NOZZLE

The invention relates to a pressure sensor system included within the structure of rocket engine nozzle and to an innovative method for detecting the pressure inside the rocket engine chamber. The claimed sensor system comprises a disk (3) on which piezoelectric or piezoresistive pressure sensors (4) are arranged, where said disk is inserted inside the rocket engine nozzle (6) and can measure the force acting on the drive chamber walls by means of a mobile insert (2), the force acting thereupon being the same force which acts upon the drive chamber walls, the system, on which the piezoelectric or piezoresistive pressure sensors (4) are arranged being made of a material which keeps its elastic properties at high temperatures such as ferritic stainless steels or duplex steels, and has some premoulded semispheres which amplify the piezoelectric effect of the material of which the sensor is made. The claimed method for measuring the pressure in the combustion chamber of rocket engines with solid or hybrid fuel consists in that the sensors (4) are arranged on a disk (3) included in the rocket engine nozzle (6) upon which the insert (2) acts with a force (p1) proportional with the force (p) which is exerted upon the inner walls of a combustion chamber (1).