A system for an aircraft includes a heater comprising a resistive heating element and insulation surrounding the resistive heating element. A first current flows into the resistive heating element to provide heat and a second current flows out of the resistive heating element. The system further includes a leakage sensor configured to produce a leakage sensor signal representing a leakage current from the heater and a prediction processor configured to predict heater failure based on the leakage sensor signal.
REAL TIME OPERATIONAL LEAKAGE CURRENT MEASUREMENT FOR PROBE HEATER PHM AND PREDICTION OF REMAINING USEFUL LIFE
MESURE DE COURANT DE FUITE OPERATIONNELLE EN TEMPS REEL POUR RECHAUFFEUR DE SONDE PHM ET PREDICTION DE LA DUREE DE VIE UTILE RESTANTE
2020-06-14
Patent
Electronic Resource
English
IPC: | G01R Messen elektrischer Größen , MEASURING ELECTRIC VARIABLES / G01D MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE , Anzeigen oder Aufzeichnen in Verbindung mit Messen allgemein / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
European Patent Office | 2023
|