SYSTEM AND METHOD REDUCING AIRCRAFT BRAKE WEAR

Abstract

A system and method are provided for continuous monitoring and controlling of aircraft braking that can reduce brake wear and aircraft operating costs through the retention of carbon brake powder from the brakes or addition of carbon powder in a device mounted with respect to the brake disk stack. The use of carbon powder reduces brake wear by providing small particles between the brake disks, acting as a buffer between the brake disks when the brake stack is clamped together. Moreover, when carbon powder or small particles are used at application, such use reduces the roughness of the carbon surface and reduces the number of large particles from braking off the carbon surface, thereby reducing brake wear. Adaptive or selective braking may be used in conjunction with carbon powder to further reduce carbon brake wear.

Claims

1. A method of adaptive braking of an aircraft to reduce brake wear and wear brakes evenly, the aircraft including a plurality of brake disks that cooperate to brake the aircraft in response to a brake command, the method comprising the steps of: collecting data on aircraft speed, aircraft deceleration, aircraft weight, brake temperature, and brake pressure; monitoring for a brake command; actuating one or more of a plurality of wheel brakes in response to the brake command based on the collected data; and adjusting a surface condition of the brake disk surfaces based on the collected data.

2. The method of claim 1, wherein the adjusting the surface condition of the brake disk surfaces includes applying a carbon particulate to the brake disk surfaces to reduce brake temperature to a desired value.

3. The method of claim 2, further comprising: collecting pieces of the brake disks released during the actuating one or more wheel brakes into the powder dispenser; pulverizing the pieces with a grinder to form recycled carbon particulate; and returning the recycled carbon particulate to one or more surfaces of the plurality of brake disks.

4. The method of claim 3, further comprising spraying an adhesive from the powder dispenser onto the one or more surfaces of the plurality of brake disks to promote retention of the recycled carbon particulate on the brake disks.

5. A system for monitoring and controlling braking for an aircraft to reduce brake wear, the aircraft including a plurality of wheel brakes each having a plurality of brake disks that engage to decelerate the aircraft in response to a brake command, the system comprising: a brake actuation controller configured to monitor for a brake command and to actuate one or more of the plurality of wheel brakes in response to the brake command; and a carbon powder recycling dispenser mounted adjacent the plurality of wheel brakes and configured to collect pieces of carbon removed from the disk brakes during a braking operation, the carbon powder recycling dispenser including a grinder for pulverizing said pieces of carbon into carbon particulate, and an ejector delivering the carbon particulate onto surfaces of the plurality of brake disks.

6. The system of claim 5, wherein the carbon powder recycling dispenser further comprises a vacuum for collecting the pieces of carbon.

7. The system of claim 6, further comprising a sprayer for applying a liquid to the surfaces of the plurality of brake disks.

8. The system of claim 5, wherein the brake actuation controller is configured to monitor for one or more aircraft braking conditions and is further configured to disable one or more of the wheel brakes in response to the one or more aircraft braking conditions.

9. The system of claim 8, wherein the one or more aircraft braking conditions are selected from the group consisting of aircraft speed, aircraft deceleration, aircraft weight, brake temperature, brake command, airport taxiway patterns, taxi speeds, tire pressure, tire wear, brake wear, and wear rate.

10. The system of claim 9, wherein the brake actuation controller is configured to communicate with a database storing manufacturer braking characteristics for each of the plurality of wheel brakes, and wherein the brake actuation controller is configured to disable one or more of the wheel brakes based on the manufacturer braking characteristics.

11. The system of claim 10, wherein the manufacturer braking characteristics include an optimal brake temperature operating range for each of the plurality of wheel brakes, wherein the one or more aircraft braking conditions is the brake temperature, and wherein the brake actuation controller is configured to adjust brake pressure to one or more of the wheel brakes if the brake temperature falls outside the optimal brake temperature operating range.

12. The system of claim 5, wherein the plurality of brake disks include multiple pairs of rotors and stators, and the carbon powder recycling dispenser includes a plurality of outlets each for individually dispensing carbon particulate to each pair of rotors and stators.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0020] FIG. 1 is a perspective view of a prior art wheel and carbon brake assembly for an aircraft;

[0021] FIG. 2 is a cross sectional view of the carbon brake assembly of the present invention;

[0022] FIG. 3 is a cross sectional schematic view of the wheel and carbon brake assembly of the present invention;

[0023] FIG. 4 is a schematic diagram of a powder injector/dispenser control system; and

[0024] FIG. 5 is a flow diagram of a logic for applying brake commands based on optimal wear conditions.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0025] A prior art aircraft wheel and brake assembly 100 is shown in FIG. 1, where a wheel 109 encompass a plurality of disks of the brake assembly mounted along a centerline 117, that cooperate to arrest the velocity of the aircraft under the influence of an actuator 114. Carbon brakes generally comprise a piston housing 202 including pistons, a torque tube, and a carbon brake stack. The carbon brake stack is made up of several disks (stators) that are keyed to the stationary torque tube, and interleaved disks (rotors) that are keyed to the inside rim of the wheel and rotate with the wheel. The stack is bounded by the piston housing 202 and a pressure plate 205 on one side, and a backing plate 204 on the other side that compress the stators and rotors. During the interaction of the disks, particles 51 that can prematurely wear the disks are dislodged around the inner and outer diameter of the disks. Most of the particles 51 eventually get expelled from the brake assembly 100 and are jettisoned from the wheel housing 109 into the atmosphere.

[0026] Referring to FIG. 2, a cross sectional view of the braking assembly of the present invention is shown. The aircraft brake assembly 102 includes a piston housing 202 having a plurality of actuators 114, a brake stack 144 and torque tube 124.

[0027] Referring to FIG. 3, a cross sectional view of the wheel and carbon brake assembly of the present invention is shown. The aircraft brake assembly 102 is coupled to the axle flange 128 via, for example, brake bolts 132. The actuators 114 in the piston housing 202 are configured to engage and disengage the brake stack 144, which includes the alternating rotor disks 136 and stator disks 138. The rotor disks 136 are engaged by wheel 122 via, for example, rotor drive keys 140, and the stator disks 138 are engaged by the torque tube keys 203.

[0028] A preferred embodiment of the present invention allows for the use of carbon powder as a lubricant between the wheel brake disks to further reduce brake wear. In one exemplary embodiment, each wheel brake includes one or more powder dispensers 60 mounted proximal to the wheel brake. The powder dispenser 60 is preferably mounted on or adjacent to a carrier assembly (not shown) of the wheel brake with access to the surfaces between the rotor disks 136 and stator disks 138, but may alternatively be mounted adjacent to the wheel brake such as on the axle 118. The powder dispenser 60 may include an injector 62 and a receptacle 70 containing carbon powder, at least one outlet 64 for dispensing of carbon powder to the surfaces between one or more brake disks, an inlet 66 for receiving carbon particles broken off from the surfaces during braking of the aircraft, and a grinder 68 for grinding the larger carbon particles into a powder for placement into the receptacle 70. The powder dispenser 60 may be electrically connected to the brake actuation controller 26 (FIG. 3) to activate in response to a brake command 38 or other aircraft braking condition 28.

[0029] In one method of use, a braking actuator controller 26 receives a brake command from the pilot or autobrake system, and actuates one or more of the wheel brakes 10A, 10B. This in turn causes a piston to compress the brake stack 144. When braking is released and the rotors and stators' surfaces move apart, any carbon particles that are created are removed through the inlet 66 (via vacuum or other methods) and transferred to the powder receptacle 70. This particulate may be further pulverized in the grinder 68 before transference to the receptacle 70. Consequently, when braking is reengaged the abrasive condition of the brake disk stack is reduced due to the removal of the large carbon particles, resulting in less brake wear while the receptacle 70 and grinder 68 are shown as a source for the powder to be applied at the surface of the brakes from injector 62.

[0030] The aforementioned description of the mechanism and placement of the powder dispenser 60 indicates one presently preferred embodiment, and is not intended to be limited to any specific mechanism or placement. For example, mechanisms other than a vacuum for receiving carbon powder, or a pump for spraying carbon powder, may be used for the powder dispenser 60 while keeping the spirit and scope of the invention. Additionally, placement of the powder dispenser 60 with respect to the brake stack 144 may occur other than on the carrier assembly or axle. Moreover, while the above-described embodiment describes use of a single powder dispenser for a brake stack, multiple powder dispensers may be used for a single wheel brake. For example, each powder dispenser 60 may be placed such that its outlet 64 corresponds to a single pair of rotors 136 and stators 138. Alternatively, a single powder dispenser with multiple outlets 64, each corresponding to a single pair of rotors and stators, may be used.

[0031] The powder dispenser 60 preferably applies a carbon powder to the surfaces of the brake disks before the brake stack is compressed by the pistons. For example, after a brake command is received into the brake actuator controller, but before the brake stack is compressed, the braking actuator controller 26 activates the powder dispenser 60. The rotors 136 and stators 138 surfaces are disengaged and apart at this time. Carbon powder in the receptacle 70 is injected through the outlet 64 and injected to the inner surface of one or more of the brake disks. For example, the powder dispenser 60 may inject the powder onto the friction surface of each rotor while it turns to fully coat its surface. The powder dispenser 60 may also spray a weak adhesive from a separate reservoir (not shown) before, during, or after dispensing the carbon powder to facilitate retention of the powder on the brake disks. Consequently, when the braking actuator controller 26 subsequently actuates the wheel brakes, the abrasive condition of the brake disk stack is reduced due to the addition of the small carbon particles or carbon powder, further resulting in less brake wear.

[0032] In FIG. 4, the brake disks engage in response to a brake command 38, which is monitored by the brake actuation controller 26. The brake command 38 may be initiated for example, by actuation of a brake pedal by a pilot or an autobrake system. Once the brake command is received, the brake actuation controller 26 monitors for one or more aircraft braking conditions 28, in response to which the brake actuation controller actuates the plurality of wheel brakes 10A, 10B at wheels 22. These conditions 28 may include, but are not limited to, aircraft speed 30, aircraft deceleration 32, aircraft weight 34, brake temperature 36, airport taxiway patterns 40, taxi speeds 42, tire pressure 44, brake wear 46, wear rate 48, tire wear 39, and braking pressure 47. Monitoring the aforementioned conditions is accomplished based upon the knowledge of one of ordinary skill in the art; for example, a wheel speed transducer (not shown) may be provided near the wheel brake to receive wheel speed data which is transmitted to the brake actuation controller, and the brake actuation controller processes this data to derive the aircraft speed 30. Using this data, the brake actuation controller 26 disables one or more of the wheel brakes 10A, 10B in response to the one or more aircraft braking conditions also according to the knowledge of one of ordinary skill in the art. For example, the brake actuation controller may instruct one of the wheel brakes not to apply braking dependent upon the aircraft speed in combination with other conditions 28.

[0033] In a preferred embodiment of the present invention, one of the aircraft braking conditions includes manufacturer braking characteristics 50. Here, each wheel brake 10A, 10B on an aircraft may be of a different manufacturer, and the brake actuation controller 26 disables one or more of the wheel brakes 10A, 10B in response to the manufacturer braking characteristics. An example of a manufacturer braking characteristics 50 is an optimal brake temperature operating range 52 for that wheel brake. In one exemplary embodiment, the braking actuation controller 26 communicates with a database 54 of manufacturer brake characteristics including the optimal brake temperature operating range 52 for each wheel brake of each aircraft, and selectively disables the wheel brakes 10A, 10B depending upon the brake temperature 36 sensed.

[0034] For example, when the brake actuation controller monitors and receives the brake temperature 36 of each wheel brake, it compares the brake temperature against the database 54 to determine whether a wheel brake falls outside its optimal brake temperature operating range, and if so, disables that brake 10A or 10B accordingly. This characteristic, as well as other manufacturer braking characteristics 50 stored in the database 54, may be used in combination with the sensed aircraft braking conditions by the brake actuation controller to perform adaptive braking according to the knowledge of one of ordinary skill in the art, while further allowing for the use of wheel brakes by different manufacturers for an aircraft which was generally not present in conventional adaptive braking techniques, in order to balance and reduce brake wear.

[0035] FIG. 5 illustrates an exemplary flow diagram for conducting a braking operation using the present invention. The brake characteristic/wear rates for each brake manufacturer is input in order to determine an optimal brake wear characteristic for each wheel. This optimal brake wear is then input into a controller that uses the input to issue an adaptive brake wear command for each wheel. If the aircraft is in taxi mode the brake command is issued and the brakes are applied accordingly. If the aircraft is in a landing phase, the brake temperature data is determined and stored in a brake temperature memory. This temperature is then recalled along with the current brake temperature when the aircraft is in taxiing mode in order to determine the correct brake command for each manufacturer's brake.

[0036] It will be apparent from the foregoing that, while particular forms of the invention have been illustrated and described, various modifications can be made without departing from the spirit and scope of the invention. Accordingly, it is not intended that the invention be limited, except as by the appended claims.