A system for an aircraft that includes a plurality of zones including: a first fiber optic cable routed through a zone of the plurality of zones. The first fiber optic cable is attached to a landing gear of the aircraft in the zone of the plurality of zones; and a first controller configured to provide a first optical signal to the first fiber optic cable and obtain a first optical response signal from the first fiber optic cable. The first controller is further configured to determine at least one temperature within the zone of the plurality of zones based on the first optical response signal, the first optical signal, and coherent optical frequency domain reflectometry (COFDR).
INTEGRATED LANDING GEAR FIRE DETECTION & FATIGUE MONITORING SYSTEM
2021-01-28
Patent
Electronic Resource
English
Integrated landing gear fire detection and fatigue monitoring system
European Patent Office | 2022
|INTEGRATED LANDING GEAR FIRE DETECTION AND FATIGUE MONITORING SYSTEM
European Patent Office | 2023
|Detection of fatigue crack growth in aircraft landing gear
Tema Archive | 2004
|Fatigue Analysis of Light Aircraft Landing Gear
Tema Archive | 2012
|Landing Gear Structural Health Monitoring
SAE Technical Papers | 2019