INERTING SYSTEM FOR A FUEL RESERVOIR IN AN AIRCRAFT, DESIGNED TO CALCULATE THE QUANTITY OF OXYGEN PRESENT IN AN INERTING GAS INJECTED INTO THE SAID RESERVOIR

摘要

The present invention relates to a system for inerting (1) a fuel tank of an aircraft. Said system comprises a sensor (6) comprising a phosphorescent material (7), arranged in distribution means (4) of a inert gas and in contact with said inerting gas; a light source (10) illuminating the phosphorescent material (7); means (11) for measuring the phosphorescence of the phosphorescent material (7); and calculating means (12) for the amount of oxygen present in the inerting gas as a function of the attenuation of the measured phosphorescence which is directly related to the amount of oxygen in the inerting gas. The inerting system according to the invention is simpler to implement because it does not necessarily require a specific chamber to measure, and does not create a hot spot in the system. The measuring device of the inerting system works cold and in real time.