SYSTEM FOR LIFESPAN MONITORING OF MISSILES

The system has an accessory sample (11) produced from a fuel-lot in addition to a rocket. The sample includes an engine combustion chamber, which is filled with a solid-propellant from the fuel-lot and corresponds to an engine combustion chamber of the rocket that is filled with the propellant. The propellants of the sample and the rocket adhere at a combustion chamber wall. The propellant of the sample is provided with dual stress and temperature sensors (12-15) at a surface, which adheres at the wall. The sensors are coupled with a data detecting device (16) of the sample.