Method to reduce carbon brake wear through residual brake force
The method for reducing aircraft carbon brake wear involves monitoring the commanded initiation of braking, and setting a residual brake clamping force to a predetermined minimum residual brake clamping force, which is maintained following the commanded initiation of braking to prevent release of braking during taxiing of the aircraft. The minimum residual brake clamping force is applied despite a commanded release of braking until at least one predetermined control logic condition occurs.
1. A method for controlling carbon brakes of an aircraft having a plurality of wheels and a corresponding plurality of wheel brakes for the plurality of wheels to reduce brake wear when the aircraft is taxiing, comprising the steps of:
monitoring commanded initiation of braking of any of the plurality of wheel brakes of the aircraft;
setting a residual brake clamping force to a predetermined minimum residual brake clamping force for the plurality of wheel brakes in response to said commanded initiation of braking of any of the plurality of wheel brakes; and
applying said predetermined minimum residual brake clamping force to the plurality of wheel brakes despite a commanded release of braking of any of the plurality of wheel brakes.
2. The method of claim 1 , further comprising the step of discontinuing applying said predetermined minimum residual brake clamping force in response to at least one control logic condition.
3. The method of claim 2 , further comprising the steps of determining an average wheel speed and comparing said average wheel speed with a predetermined wheel speed threshold, and wherein said at least one control logic condition comprises when said average wheel speed is below said predetermined wheel speed threshold.
4. The method of claim 3 , wherein said predetermined wheel speed threshold is in the range of about 2 knots to about 15 knots.
5. The method of claim 3 , wherein said predetermined wheel speed threshold is in the range of about 2 knots to about 10 knots.
6. The method of claim 3 , wherein said aircraft has left and right landing gear, and said step of determining an average wheel speed comprises determining an average wheel speed of the left landing gear and an average wheel speed of the right landing independently, comparing said average wheel speeds of the left and right landing gear, and comparing the lesser of the average wheel speeds of the left and right landing gear with said predetermined wheel speed threshold.
7. The method of claim 2 , wherein said aircraft includes at least one engine thrust lever, further comprising the step of monitoring engine thrust lever position, and wherein said at least one control logic condition comprises when said at least one engine thrust lever is in an advanced position.
8. The method of claim 2 , further comprising the step of detecting wheel speed acceleration, and comparing said wheel speed acceleration with a predetermined acceleration threshold, and wherein said at least one control logic condition comprises when said wheel speed acceleration exceeds said acceleration threshold.
9. The method of claim 2 , further comprising monitoring temperature of said plurality of wheel brakes, and comparing said temperature of said plurality of wheel brakes with a temperature threshold, and wherein said at least one control logic condition comprises when said temperature of said plurality of wheel brakes exceeds said temperature threshold.
10. The method of claim 2 , further comprising determining distance rolled with said predetermined minimum residual brake clamping force applied, comparing said distance rolled with a predetermined distance threshold, and wherein said at least one control logic condition comprises when said distance rolled exceeds said predetermined distance threshold.
11. The method of claim 1 , wherein said predetermined minimum residual brake clamping force comprises about 1-10% of a maximum brake clamping force of said plurality of wheel brakes.
12. The method of claim 1 , wherein said predetermined minimum residual brake clamping force comprises about 2-5% of a maximum brake clamping force of said plurality of wheel brakes.
13. A method for controlling carbon brakes of an aircraft having a plurality of wheels and a corresponding plurality of wheel brakes for the plurality of wheels to reduce brake wear when the aircraft is taxiing, comprising the steps of:
monitoring commanded initiation of braking of any of the plurality of wheel brakes of the aircraft;
setting a residual brake clamping force to a predetermined minimum residual brake clamping force for the plurality of wheel brakes in response to said commanded initiation of braking of any of the plurality of wheel brakes;
monitoring commanded release of braking of any of the plurality of wheel brakes of the aircraft;
applying said predetermined minimum residual brake clamping force to the plurality of wheel brakes following said commanded release of braking of any of the plurality of wheel brakes until at least one predetermined control logic condition occurs; and
setting said residual brake clamping force to zero in response to said at least one control logic condition.
14. The method of claim 13 , further comprising the steps of determining an average wheel speed and comparing said average wheel speed with a predetermined wheel speed threshold, and wherein said at least one control logic condition comprises when said average wheel speed is below said predetermined wheel speed threshold.
15. The method of claim 14 , wherein said predetermined wheel speed threshold is in the range of about 2 knots to about 15 knots.
16. The method of claim 14 , wherein said predetermined wheel speed threshold is in the range of about 2 knots to about 10 knots.
17. The method of claim 14 , wherein said aircraft has left and right landing gear, and said step of determining an average wheel speed comprises determining an average wheel speed of the left landing gear and an average wheel speed of the right landing independently, comparing said average wheel speeds of the left and right landing gear, and comparing the lesser of the average wheel speeds of the left and right landing gear with said predetermined wheel speed threshold.
18. The method of claim 13 , wherein said aircraft includes at least one engine thrust lever, further comprising the step of monitoring engine thrust lever position, and wherein said at least one control logic condition comprises when said at least one engine thrust lever is in an advanced position.
19. The method of claim 13 , further comprising the step of detecting wheel speed acceleration, and comparing said wheel speed acceleration with a predetermined acceleration threshold, and wherein said at least one control logic condition comprises when said wheel speed acceleration exceeds said acceleration threshold.
20. The method of claim 13 , further comprising monitoring temperature of said plurality of wheel brakes, and comparing said temperature of said plurality of wheel brakes with a temperature threshold, and wherein said at least one control logic condition comprises when said temperature of said plurality of wheel brakes exceeds said temperature threshold.
21. The method of claim 13 , further comprising determining distance rolled with said predetermined minimum residual brake clamping force applied, comparing said distance rolled with a predetermined distance threshold, and wherein said at least one control logic condition comprises when said distance rolled exceeds said predetermined distance threshold.
22. The method of claim 13 , wherein said predetermined minimum residual brake clamping force comprises about 1-10% of a maximum brake clamping force of said plurality of wheel brakes.
23. The method of claim 13 , wherein said predetermined minimum residual brake clamping force comprises about 2-5% of a maximum brake clamping force of said plurality of wheel brakes.
24. A system for controlling carbon brakes of an aircraft having a plurality of wheels and a corresponding plurality of wheel brakes for the plurality of wheels to reduce brake wear when the aircraft is taxiing, the system comprising:
means for monitoring commanded initiation of braking of any of the plurality of wheel brakes of the aircraft;
means for setting a residual brake clamping force to a predetermined minimum residual brake clamping force for the plurality of wheel brakes in response to the commanded initiation of braking of any of the plurality of wheel brakes; and
means for applying the predetermined minimum residual brake clamping force to the plurality of wheel brakes despite a commanded release of braking of any of the plurality of wheel brakes.
25. The system of claim 24 , further comprising means for discontinuing applying said predetermined minimum residual brake clamping force in response to at least one control logic condition.