Aircraft component longevity
In an embodiment, proprotor pitch ranges used during nominal cruise flight may be varied. By selecting ideal combinations of proprotor pitch angle and proprotor rpm, instead of the proprotor blade pitch bearing spending most of its time in a first range, multiple ranges may be alternated between. Additionally, in an aircraft with multiple proprotors, the portion of total thrust produced by each individual proprotor may be varied over time in order to allow for proprotor blade pitch angle to be varied without varying proprotor rpm. By properly cycling between different blade pitch ranges, bearing life can be significantly increased.
1. A VTOL aircraft comprising:
a wing;
a proprotor carried by the wing, and comprising a first proprotor blade;
a first proprotor blade pitch actuator; and
an electronic flight control system configured to compute, using pitch axis bearing history data, a first pitch of the first proprotor blade, and wherein the electronic flight control system is configured to command the first proprotor blade pitch actuator to move the proprotor blade to the computed first pitch.
2. The aircraft of claim 1 wherein the bearing history data comprises a measurement of time the proprotor blade has been within a first pitch angle range.
3. The aircraft of claim 1 wherein the electronic flight control system is configured to command an equal amount of thrust when the first proprotor blade is at a first pitch and when the first proprotor blade is at a second pitch.
4. The aircraft of claim 1 wherein the electronic flight control system is configured to command a change in rotations per minute (rpm) of the proprotor contemporaneous to commanding a pitch change of the first proprotor blade.
5. The aircraft of claim 4 wherein the electronic flight control system is configured to compute a combination of pitch of the first proprotor blade and rpm of the proprotor using propeller efficiency data.
6. The aircraft of claim 5 wherein the efficiency data comprises propeller efficiency versus rpm and advance ratio data.
7. The aircraft of claim 1 wherein the aircraft is an electric vertical takeoff and landing aircraft.
8. The aircraft of claim 1 wherein the proprotor is a rigid proprotor.
9. The aircraft of claim 1 wherein the aircraft is a tiltrotor aircraft.
10. The aircraft of claim 9 , wherein the tiltrotor aircraft is a quad-tiltrotor aircraft.
11. The aircraft of claim 1 wherein the electronic flight control system is configured to compute the first pitch of the first proprotor blade using proprotor pitch bearing history data when the aircraft is in wingborne cruise flight.
12. A method for controlling a VTOL aircraft comprising a wing-mounted proprotor having a proprotor blade, the method comprising the steps of:
during nominal cruise flight, commanding a proprotor blade pitch actuator to move a proprotor blade to a first pitch angle;
computing, using proprotor blade pitch bearing history data, a second pitch angle of a proprotor blade; and
commanding the proprotor blade pitch actuator to move the proprotor blade to the computed second pitch angle.
13. The method of claim 12 wherein the bearing history data is a measurement of time the proprotor blade has been within a first pitch angle range.
14. The method of claim 12 further comprising the step of commanding an equal amount of thrust when the first proprotor blade is at a first pitch and when the first proprotor blade is at a second pitch.
15. The method of claim 14 wherein the commanding an equal amount of thrust comprises commanding a change in rotations per minute of the wing-mounted proprotor.
16. The method of claim 12 further comprising the step of commanding a change in rotations per minute of the proprotor contemporaneous to commanding a pitch change of the first proprotor blade.
17. The method of claim 16 further comprising computing a combination of pitch of the first proprotor blade and proprotor rpm using propeller efficiency data.
18. The method of claim 17 wherein the efficiency data comprises propeller efficiency versus rpm and advance ratio data.
19. The method of claim 12 wherein the wing-mounted proprotor is a rigid proprotor.
20. The method of claim 12 wherein the step of computing the second pitch angle of the wing-mounted proprotor occurs while the aircraft is in wingborne cruise flight.
21. A method of preventing proprotor pitch axis bearing degradation in a VTOL aircraft, the method comprising the steps of generating a first amount of thrust with a set of proprotors, changing the pitch angle of at least two of the proprotors of the set such that a total thrust of the set is the same but a portion of total thrust generated by each proprotor of the set is different than before the change of the pitch angle of the at least two of the proprotors of the set.
22. A VTOL aircraft comprising:
a wing-borne proprotor comprising a first proprotor blade;
a first proprotor blade pitch actuator;
an electronic flight control system configured to compute, using aircraft life data, a first pitch of the first proprotor blade, and wherein the electronic flight control system is configured to command the first proprotor blade pitch actuator to move the proprotor blade to the computed pitch.