Pylon engine mount health monitoring system
A system comprises an engine mounted to an aircraft wing by a plurality of clevis pins, a respective strain sensor mounted in at least one of the clevis pins, and a monitoring system operatively connected to each respective strain sensor to monitor stress in each of the clevis pins having a respective strain sensor.
1. A system comprising:
an engine mounted to an aircraft wing by a plurality of clevis pins;
a respective strain sensor mounted in a hollow core of at least one of the clevis pins; and
a monitoring system operatively connected to each respective strain sensor to monitor stress in each of the clevis pins having a respective strain sensor.
2. The system as recited in claim 1 , wherein each respective strain sensor includes a respective fiber Bragg grating, and wherein the monitoring system is optically coupled to each respective fiber Bragg grating to illuminate each respective fiber Bragg grating and to monitor changes in wavelength reflected from each respective fiber Bragg grating to monitor stress in each of the clevis pins having a respective fiber Bragg grating.
3. The system as recited in claim 2 , wherein the monitoring system is configured to provide real-time stress monitoring based on reflections from each respective fiber Bragg grating.
4. The system as recited in claim 3 , wherein real-time stress monitoring includes monitoring both static and dynamic load spectra on each of the clevis pins having a respective fiber Bragg grating.
5. The system as recited in claim 2 , wherein each respective fiber Bragg grating includes multiple Bragg reflectors.
6. The system as recited in claim 1 , further comprising a pylon affixed to the wing, wherein the engine is mounted to the pylon at a plurality of engine mounts.
7. The system as recited in claim 6 , wherein the plurality of clevis pins includes at least seven clevis pins affixing the pylon to the wing, wherein an entirety of a load of the engine on the wing passes through the at least seven clevis pins.
8. The system as recited in claim 2 , wherein the monitoring system is configured to detect a shift in reflected wavelength corresponding to a stress leading to significant latent fatigue.
9. The system as recited in claim 8 , wherein the monitoring system is configured to raise a high priority damage flag if the stress leading to significant latent fatigue exceeds a predetermined threshold.
10. The system as recited in claim 1 , wherein the clevis pins are fuse pins.
11. A method comprising:
monitoring stress with a respective strain sensor in a hollow core in at least one clevis pin in a plurality of clevis pins in a load bearing path from an aircraft wing to an aircraft engine.
12. The method as recited in claim 11 , wherein monitoring stress is performed in real time.
13. The method as recited in claim 11 , wherein monitoring stress includes illuminating a respective fiber Bragg grating in each of the at least one clevis pins and monitoring changes in wavelength reflected from each respective fiber Bragg grating to monitor stress in each of the at least one clevis pins having a respective fiber Bragg grating.
14. The method as recited in claim 13 , wherein real-time stress monitoring includes monitoring both static and dynamic load spectra on each of the clevis pins having a respective fiber Bragg grating.
15. The method as recited in claim 13 , wherein real-time stress monitoring includes detecting a shift in reflected wavelength corresponding to a stress leading to significant latent fatigue, and raising a high priority damage flag if the stress leading to significant latent fatigue exceeds a predetermined threshold.