In some examples, a drive insert comprises a clip and a retainer. The clip is configured to be slidable over a surface adjacent to a drive slot of a brake disc in a tangential direction of the brake disc. The retainer is configured to be slidable over the clip when the clip is positioned over the surface to secure the clip to the brake disc. In some examples, the clip may comprise a body section and first and second arms extending from the body section. The retainer may comprise first and second legs configured to contact the first arm and the second arm of the clip when the retainer is positioned over the clip. The first and second legs may be resiliently biased to provide an inward clamping force on the clip when the retainer is positioned over the clip.

An emergency park brake system of an aircraft may include an electrical power interface, an electromechanical actuator, and a hydraulic brake valve. The electrical power interface may be configured to receive electrical power from a power source. The electromechanical actuator may be in selective power receiving communication with the electrical power interface and the electromechanical actuator may be mechanically coupled to and configured to selectively actuate the hydraulic brake valve. The electrical connection between the electromechanical actuator and the electrical power interface may be based on an emergency braking input.

An emergency park brake system of an aircraft may include an electrical power interface, an electromechanical actuator, and a hydraulic brake valve. The electrical power interface may be configured to receive electrical power from a power source. The electromechanical actuator may be in selective power receiving communication with the electrical power interface and the electromechanical actuator may be mechanically coupled to and configured to selectively actuate the hydraulic brake valve. The electrical connection between the electromechanical actuator and the electrical power interface may be based on an emergency braking input.

The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback maneuver, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.

A rotor drive bar for use in a brake system, according to various embodiments, includes a drive bar portion configured to be coupled to at least one rotor of the brake system. The rotor drive bar also includes an attachment boss configured to be coupled to an attachment platform of a wheel. The attachment boss has a boss face that faces the attachment platform and at least partially defines a pocket for reducing thermal transfer from the rotor drive bar to the wheel.

A rotor drive bar for use in a brake system, according to various embodiments, includes a drive bar portion configured to be coupled to at least one rotor of the brake system. The rotor drive bar also includes an attachment boss configured to be coupled to an attachment platform of a wheel. The attachment boss has a boss face that faces the attachment platform and at least partially defines a pocket for reducing thermal transfer from the rotor drive bar to the wheel.

The present disclosure includes the use of a smart load cell in a system for controlling an electromechanical actuator. A load cell may be positioned along the outer surface of the electromechanical actuator. Further, the load cell may utilize strain gages and a microcontroller. The load cell may be configured to transmit data to an electric brake actuator controller which includes calibration for operating temperature of the electromechanical actuator.

The present disclosure includes the use of a smart load cell in a system for controlling an electromechanical actuator. A load cell may be positioned along the outer surface of the electromechanical actuator. Further, the load cell may utilize strain gages and a microcontroller. The load cell may be configured to transmit data to an electric brake actuator controller which includes calibration for operating temperature of the electromechanical actuator.

The invention relates to a braking device (1) of an aircraft wheel, comprising a ring (15) which has a plurality of cavities (17) in which actuators (18) are fitted in order to apply a braking force to a stack of discs (11) which extend opposite the ring. The ring is provided with a heat shield (25) which extends opposite a face of the ring directed towards the stack of discs in order to protect the ring from thermal radiation which is generated by the stack of discs.

According to the disclosure, the heat shield is provided with holes (26) through which the actuators extend and which have a sectional profile which is formed to reflect the thermal radiation away from the device.

The invention relates to a braking device (1) of an aircraft wheel, comprising a ring (15) which has a plurality of cavities (17) in which actuators (18) are fitted in order to apply a braking force to a stack of discs (11) which extend opposite the ring. The ring is provided with a heat shield (25) which extends opposite a face of the ring directed towards the stack of discs in order to protect the ring from thermal radiation which is generated by the stack of discs.

According to the disclosure, the heat shield is provided with holes (26) through which the actuators extend and which have a sectional profile which is formed to reflect the thermal radiation away from the device.