Development of flight prototype, fiber-optic sensing system components for measuring nine sensed parameters (three temperatures, two speeds, three positions, and one flame) on an F404-400 aircraft engine is described. Details of each sensor's design, functionality, and environmental testing, and the electro-optics architecture for sensor signal conditioning are presented. Eight different optical sensing techniques were utilized. Design, assembly, and environmental testing of an engine-mounted, electro-optics chassis unit (EOU), providing MIL-C-1553 data output, are related. Interconnection cables and connectors between the EOU and the sensors are identified. Results of sensor/cable/circuitry integrated testing, and installation and ground testing of the sensor system on an engine in October 1993 and April 1994 are given, including comparisons with the engine control system's electrical sensors. Lessons learned about the design, fabrication, testing, and integration of the sensor system components are included.
Fiber Optic (Flight Quality) Sensors for Advanced Aircraft Propulsion
1994
90 pages
Report
Keine Angabe
Englisch
Avionics , Aircraft , Jet & Gas Turbine Engines , Laboratory & Test Facility Design & Operation , Aircraft engines , Electro-optics , Engine monitoring instruments , F-18 aircraft , Fiber optics , Temperature measurement , Temperature sensors , Engine control , Flames , Performance tests , Position sensing , Prototypes , Signal processing
Architecture for fiber-optic sensors and actuators in aircraft propulsion systems
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