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.

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.

Abstract: The present invention is a system and method for evaluating runway conditions that combines known brake control systems with a new runway condition monitoring unit working in conjunction with an anti-skid/brake control unit to improve runway condition evaluation. The runway condition monitoring unit is installed on an airplane and receives data from the brake control unit, and processes that data through hardware and software to formulate a runway condition report of the airplane while landing on a runway. The invention may include additional sensors or interfaces that supplement the data received from the BCU. The runway condition monitoring unit contains a processor and interfaces that calculates and creates a runway condition report.

Abstract: The present invention combines known brake control systems with a new runway condition monitoring unit that works in conjunction with an anti-skid/brake control unit to improve runway condition evaluation. The runway condition monitoring unit is installed on an airplane and receives data from the brake control unit, and processes that data through hardware and software to formulate a runway condition report of the airplane while landing on a runway. The invention may include additional sensors or interfaces that supplement the data received from the BCU. The runway condition monitoring unit contains a processor and interfaces that calculates and creates a runway condition report. The runway condition monitoring unit communicates the report by way of the avionics communication network on the airplane to devices that then send the runway condition report to consumers of the data; such as the flight deck, air traffic controllers, airport operators and airline operations.

Abstract: A wheel speed measuring device for an aircraft braking system uses dual technology packaged in a single transducer that incorporates the robust and reliable variable reluctance technology along with a secondary package for measuring position and velocity bi-directionally for low speed and taxi operations. The transducer of the present invention is preferably incorporated into the envelope of the axle to allow both retrofit on existing aircraft and to maintain existing axle design and configuration.

Abstract: A brake monitoring system is described for use on aircraft having carbon brakes. The system displays the number of times the brakes have been applied in a preselected counting interval such as during each takeoff and landing cycle. By raising the pilot's awareness of the number of times the brakes have been applied, a more efficient brake use is encouraged in view of the knowledge that carbon brake wear is substantially a function of the number of applications rather than the total energy that is converted thereby. Additionally, the monitoring system provides an indication of the temperature of the brakes which encourages the pilot to maintain a minimum temperature therein beyond which wear is reduced.

Abstract: A wheel speed transducer including a magnetic device associated with a wheel and a sensor device associated with the axle of the wheel provides data indicative of the velocity of the wheel. A processor located at the axle receives the wheel speed data and processes it to perform antiskid control functions. The velocity data is stored in a data concentrator also associated with the axle. A tire pressure sensor, a brake temperature sensor and a brake torque sensor, each associated with the wheel, send data to the processor at the axle, for storage in the data concentrator. A transmitting antenna associated with the axle and in communication with the data concentrator transmits stored data to a receiving antenna associated with the wheel. A data port at the wheel and in communication with the receiving antenna provides an interface to an external device for receiving the data.

Abstract: 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.

Abstract: An anti-skid brake control system for a multi-wheeled vehicle includes both a paired function and an individual function. The paired function controls the wheels of the vehicle in unison. The individual function controls the wheels of the vehicle individually. A paired/individual logic circuit alternatively activates and deactivates the paired function and the individual function. A method for controlling the skid of a vehicle utilizing a paired function and a individual function is also provided.

Abstract: The shock and vibration isolation system for hard mounting of a manifold of a brake control valve protects the brake control valve manifold from shock and vibration by incorporation of shock and vibration isolators in mounting feet of the manifold. The shock and vibration isolators have a pre-selected natural frequency chosen to protect components of the brake control valve damaging shock and vibration. The shock and vibration isolators each include a silicone rubber insert portion, a first outer sheath secured about a first end of the silicone rubber insert portion, a second outer sheath member secured about a second end of the silicone rubber insert portion, with a gap between the first and second outer sheaths.

Abstract: 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.

Abstract: 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.

Abstract: A wheel speed transducer including a magnetic device associated with a wheel and a sensor device associated with the axle of the wheel provides data indicative of the velocity of the wheel. A processor located at the axle receives the wheel speed data and processes it to perform antiskid control functions. The velocity data is stored in a data concentrator also associated with the axle. A tire pressure sensor, a brake temperature sensor and a brake torque sensor, each associated with the wheel, send data to the processor at the axle, for storage in the data concentrator. A transmitting antenna associated with the axle and in communication with the data concentrator transmits stored data to a receiving antenna associated with the wheel. A data port at the wheel and in communication with the receiving antenna provides an interface to an external device for receiving the data.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: An anti-skid brake control system for a multi-wheeled vehicle includes both a paired function and an individual function. The paired function controls the wheels of the vehicle in unison. The individual function controls the wheels of the vehicle individually. A paired/individual logic circuit alternatively activates and deactivates the paired function and the individual function. A method for controlling the skid of a vehicle utilizing a paired function and a individual function is also provided.

Abstract: The shock and vibration isolation system for hard mounting of a manifold of a brake control valve protects the brake control valve manifold from shock and vibration by incorporation of shock and vibration isolators in mounting feet of the manifold. The shock and vibration isolators have a pre-selected natural frequency chosen to protect components of the brake control valve damaging shock and vibration. The shock and vibration isolators each include a silicone rubber insert portion, a first outer sheath secured about a first end of the silicone rubber insert portion, a second outer sheath member secured about a second end of the silicone rubber insert portion, with a gap between the first and second outer sheaths.

Abstract: The shock and vibration isolation system for hard mounting of a manifold of a brake control valve includes shock and vibration isolators that can be assembled in the mounting feet of the manifold of the brake control valve. The shock and vibration isolators have a pre-selected, predetermined natural frequency operative to protect components of the brake control valve from shock and vibration. Each of the shock and vibration isolators includes a radially inner generally spool shaped rigid insert portion and a radially outer generally spool shaped vibration insulating sheath portion.

Abstract: 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.