Usage based propeller life monitoring
A system for monitoring propeller health includes a processing unit having a processor which is programmed to apply a plurality of algorithms to inputted aircraft parameter data. The system also includes a plurality of data inputs for inputting aircraft parameter data into the algorithms, wherein the processor is configured to apply the physics based algorithms to the aircraft parameter data to determine at least the fatigue life consumption of one or more critical components of a propeller. In addition, the system includes an output device which is able to output an indication of the determined fatigue life consumption to an observer.
1. A system for monitoring propeller health comprising:
a processing unit having a processor which is programmed to apply a plurality of algorithms to inputted aircraft parameter data;
a plurality of data inputs for inputting aircraft parameter data into the algorithms, wherein the processor is configured to apply the algorithms to the aircraft parameter data to determine at least the fatigue life consumption of one or more critical components of a propeller; and
an output device which is able to output an indication of the determined fatigue life consumption to an observer;
wherein the fatigue life consumption is determined based on actual aircraft usage;
and wherein the aircraft data comprises one or more of: air speed, altitude; flap setting; aircraft altitude; pitch rate; roll rate; and yaw rate.
2. The system according to claim 1 , wherein the algorithms are physics based algorithms and/or empirically derived algorithms.
3. The system according to claim 1 , wherein the system comprises a propeller.
4. The system according to claim 1 , wherein the output device comprises a visual display in a cockpit of an aircraft.
5. The system according to claim 4 , wherein the fatigue life consumption is displayed as a percentage of an approved fatigue life figure.
6. The system according to claim 1 , wherein an alert for maintenance is triggered if:
the fatigue life consumption reaches a pre-determined threshold;
propeller loading exceeds a predetermined value; or
a flight exhibits high life consumption.
7. The system according to claim 6 , wherein:
the predetermined threshold is in the range of 80% to 99% of an approved fatigue life figure;
the propeller loading is a value that is in the range of 80% to 99% of a maximum propeller loading figure, or is a value at or exceeds 100% of a maximum propeller loading figure; and/or
the flight's life consumption is a value in the range of 80% to 99% of a maximum life consumption figure, or is a value at or exceeds 100% of a maximum life consumption figure.
8. The system according to claim 1 , wherein the processing unit is within a Full Authority Digital Engine Control (FADEC), or wherein the aircraft parameter data is supplied by the FADEC.
9. The system according to claim 1 , wherein the system comprises an aircraft having a plurality of sensors to detect different types of aircraft parameter data and communication circuits to feed the aircraft parameter data to a FADEC.
10. The system according to claim 1 , wherein the aircraft data further comprises engine data including one or more of: rotational speed, throttle setting, thrust, engine temperature shaft horsepower, torque and engine pressure ratio.
11. The system according to claim 1 , wherein the algorithms are condition-determining algorithms.
12. A method of monitoring propeller health comprising:
inputting aircraft parameter data into a plurality of algorithms;
determining, by a processor of a processing unit, at least the fatigue life consumption of one or more critical components of a propeller using the plurality of algorithms based on the aircraft parameter data; and
outputting an indication of the determined fatigue life consumption to an observer;
wherein the fatigue life consumption is determined based on actual aircraft usage; and
wherein the aircraft data comprises one or more of: air speed, altitude; flap setting; aircraft altitude; pitch rate; roll rate; and yaw rate.
13. The method according to claim 12 , wherein the method further comprises the step of outputting the indication of the determined fatigue life consumption to an observer as a percentage of an approved fatigue life figure optionally an aviation authority approved fatigue life figure.
14. The method according to claim 13 , wherein the approve fatigue life figure is an aviation authority approved fatigue life figure.
15. The method according to claim 12 , wherein the method further comprises the step of comparing the fatigue life consumption to a predetermined threshold.
16. The method according to claim 15 , wherein the method further comprises the step of triggering an alert for maintenance if the fatigue life consumption reaches a pre-determined threshold.