Aircraft brake cooling systems and methods
Systems and methods for aircraft brake cooling are described. A system may include an air hose configured to intake pressurized air at a first end of the air hose from an aircraft propulsor. A nozzle at a second end of the air hose may be configured to exit the pressurized air through the air hose to a braking system. An actuator may be configured to allow the pressurized air to flow through the air hose or prevent the pressurized air from flowing through the air hose.
1. A system comprising:
an air hose configured to intake pressurized air at a first end of the air hose from an aircraft propulsor;
a nozzle at a second end of the air hose and configured to exit the pressurized air through the air hose to a braking system; and
an actuator configured to allow the pressurized air to flow through the air hose or prevent the pressurized air from flowing through the air hose;
wherein the actuator is configured to be actuated by a controller to allow the pressurized air to flow upon determining by the controller that each of one or more first conditions is satisfied, the one or more first conditions comprising a condition that a first predetermined amount of time has elapsed after an event which is at least one of: aircraft wheels touching down, and/or aircraft brakes being applied, wherein the first predetermined amount of time is sufficient to allow the brakes to warm up before the pressurized air is allowed to flow.
2. The system of claim 1 , wherein the braking system comprises a brake rotor and a brake pad, and the nozzle is positioned to apply the pressurized air to the brake rotor and/or the brake pad.
3. The system of claim 1 , wherein the aircraft propulsor is a turbofan engine.
4. The system of claim 1 , wherein the pressurized air is obtained from a bypass line of the aircraft propulsor.
5. The system of claim 1 , further comprising an aircraft landing gear, the landing gear comprising the braking system and the actuator.
6. The system of claim 1 , wherein the event is the brakes being applied, and the first predetermined amount of time is sufficient to allow the brakes to reach a predetermined optimal operating temperature.
7. The system of claim 6 , wherein the brakes are carbon-to-carbon brakes, and the predetermined optimal operating temperature is 400° C.
8. The system of claim 1 , wherein the controller is configured to operate the actuator to prevent the pressurized air from flowing upon determining by the controller that each of one or more second conditions is satisfied, the one or more second conditions comprising a condition that a second predetermined amount of time has elapsed after the actuator allowing the pressurized air to flow.
9. The system of claim 1 , wherein the event is the aircraft wheels touching down.
10. The system of claim 1 , wherein the event is the aircraft brakes being applied.
11. The system of claim 1 , wherein the one or more first conditions comprise a condition that a temperature of the braking system exceeds a set temperature.
12. An aircraft comprising the system of claim 1 , the aircraft comprising a landing gear assembly, the landing gear assembly comprising:
the braking system; and
a wheel assembly.
13. The system of claim 1 , wherein the actuator is a solenoid actuator.
14. A method comprising:
capturing pressurized air from an aircraft propulsor;
flowing the pressurized air to a braking system; and
applying the pressurized air to the braking system, thus removing heat generated from brake application with the applied pressurized air;
wherein the pressurized air is allowed to flow by a controller upon determining that each of one or more first conditions is satisfied, the one or more first conditions comprising a condition that a first predetermined amount of time has elapsed after an event which is at least one of: aircraft wheels touching down, and/or aircraft brakes being applied, wherein the first predetermined amount of time allows the brakes to warm up before the pressurized air is allowed to flow.
15. The method of claim 14 , wherein the event is the aircraft wheels touching down.
16. The method of claim 14 , wherein the event is the aircraft brakes being applied.
17. The method of claim 14 , wherein the one or more first conditions comprise a condition that a temperature of the braking system exceed a set temperature.
18. The method of claim 14 , wherein the brakes are carbon-to-carbon brakes, and the brakes warm up to at least 400° C. during the first predetermined amount of time.
19. The method of claim 14 , wherein the braking system comprises a brake rotor and a brake pad, wherein the pressurized air is applied to the brake rotor and the brake pad.
20. The method of claim 14 , further comprising stopping the pressurized air flow upon determining by the controller that each of one or more second conditions is satisfied, the one or more second conditions comprising a condition that a second predetermined amount of time has elapsed after allowing the pressurized air to flow.