Wear estimation for wear liner bearings

1. A method for estimating wear in aircraft rotor systems, comprising:

collecting, by a flight control computer of a flight control system of a fly-by-wire aircraft, from a linear electric, hydraulic, or electrohydraulic swashplate actuator, loads and motions of the swashplate actuator to drive a swashplate, and wherein at least one control link is coupled to the swashplate;

estimating, by the flight control computer, using the loads and the motions of the swashplate actuator to drive the swashplate, loads and motions of the at least one control link;

collecting, by the flight control computer, data associated with overall motions or maneuvers performed by the aircraft during flight;

estimating, by the flight control computer, the loads and motions of the at least one control link based upon the overall motions or maneuvers;

merging, by the flight control computer, estimates of control link loads and motions based upon the loads and motions of the swashplate actuator and estimates of control link loads and motions based upon the overall motions or maneuvers to create a wear model;

using the wear model, by the flight control computer, estimating current wear of control link components due to the loads and motions of the at least one control link; and

displaying, by the flight control computer, a resulting current wear estimate of control link components in a cockpit and/or avionics bay of the aircraft.

2. The method of claim 1 , wherein the at least one control link comprises a pitch link.

3. The method of claim 1 , wherein the control link components comprise bearing wear liners on the at least one control link.

4. The method of claim 1 , wherein the swashplate actuator is coupled to a non-rotating section of the swashplate and wherein the at least one control link is coupled to a rotating section of the swashplate.

5. The method of claim 1 , further comprising:

measuring loads on the at least one control link; and

estimating the loads and motions of the at least one control link based upon the measured loads.

6. The method of claim 1 , wherein the overall motions or maneuvers comprise at least one of a banking motion, a turning motion, a pulling up motion, a pushing over motion, or a level flight motion.

7. The method of claim 1 , further comprising:

monitoring aircraft data;

estimating environmental conditions based upon the aircraft data; and

estimating current wear of control link components due to the loads and motions of the at least one control link, by the wear model, based on resulting estimated environmental conditions.

8. The method of claim 7 , wherein the aircraft data is associated with one or more of an aircraft location, aircraft sensors, and an aircraft configuration.

9. The method of claim 7 , wherein the aircraft comprises a bypass for an engine inlet filter, and wherein the aircraft data comprises information regarding whether or not the bypass is selected.

10. The method of claim 1 , further comprising:

storing data associated with a wear history of the control link components; and

updating the wear history with the estimate of current wear of the control link components.

11. An aircraft, comprising:

a rotor system comprising a swashplate, a linear electric, hydraulic, or electrohydraulic swashplate actuator coupled to a non-rotating section of the swashplate, and at least one control link coupled to a rotating section of the swashplate; and

a flight control computer configured to estimate wear in rotor system components, the flight control computer comprising one or more processors and a memory, wherein the memory stores instructions for executing a wear estimation application, the instructions causing the flight control computer to perform the steps of:

collecting, from the swashplate actuator, loads and motions of the swashplate actuator to drive the swashplate;

estimating, using the loads and motions of the swashplate actuator to drive the swashplate, loads and motions of the at least one control link;

collecting data associated with overall motions or maneuvers performed by the aircraft during flight;

estimating the loads and motions of the at least one control link based upon the overall motions or maneuvers;

merging estimates of control link loads and motions based upon the loads and motions of the swashplate actuator and estimates of control link loads and motions based upon the overall motions or maneuvers to create a wear model; and

using the wear model, estimating current wear of control link components due to the loads and motions of the at least one control link.

12. The aircraft of claim 11 , wherein the control link components comprise bearing wear liners on the at least one control link.

13. The aircraft of claim 11 , wherein the instructions further causing the flight control computer to perform the steps of:

measuring loads on the at least one control link; and

estimating the loads and motions of the at least one control link based upon the measured loads.

14. The aircraft of claim 11 , wherein the overall motions or maneuvers comprise at least one of a banking motion, a turning motion, a pulling up motion, a pushing over motion, or a level flight motion.

15. The aircraft of claim 11 , further comprising:

one or more sensors for monitoring aircraft data; and

wherein the instructions further causing the flight control computer to perform the steps of:

estimating environmental conditions based upon the aircraft data; and

compensating estimating current wear of control link components due to the loads and motions of the at least one control link, by the wear model, based on resulting estimated environmental conditions.

16. The aircraft of claim 15 , wherein the aircraft data is associated with one or more of an aircraft location, aircraft sensors, and an aircraft configuration.

17. The aircraft of claim 15 , wherein the aircraft comprises a bypass for an engine inlet filter, and wherein the aircraft data comprises information regarding whether or not the bypass is selected.

18. The aircraft of claim 11 , wherein the instructions further causing the flight control computer to perform the steps of:

storing, in the memory, data associated with a wear history of the control link components; and

updating the wear history with the estimate of current wear of the control link components.

19. A non-transitory medium having machine readable instructions executable by a flight control computer stored thereupon, the machine readable instructions, upon execution by the flight control computer, cause the flight control computer to:

estimate wear in rotor system components, by:

collecting, from a linear electric, hydraulic, or electrohydraulic swashplate actuator, loads and motions of the swashplate actuator to drive a swashplate;

estimating, using the loads and motions of the swashplate actuator to drive the swashplate, loads and motions of the at least one control link;

collecting data associated with overall motions or maneuvers performed by the aircraft during flight;

estimating the loads and motions of the at least one control link based upon the overall motions or maneuvers;

merging estimates of control link loads and motions based upon the loads and motions of the swashplate actuator and estimates of control link loads and motions based upon the overall motions or maneuvers to create a wear model; and

using the wear model, estimating current wear of control link components due to the loads and motions of the at least one control link.

20. The non-transitory medium of claim 19 , wherein, upon execution by the flight control computer, the machine readable instructions cause the flight control computer to observe loads and motions of the swashplate actuator, collecting the loads and motions of the swashplate actuator to drive the swashplate.