A method of operating an aircraft is disclosing including, during a non-braking time period, taxiing the aircraft by using driving torque provided by a landing gear drive system, and not providing a braking torque from the landing gear brake system, and, during a braking time period, providing the brake command device at one or more command levels within a sub-range of a brake command range, and controlling the landing gear drive system, in response to the level of the brake command device, to reduce the driving torque provided.

A retainer assembly may comprise: a retainer main body having a first mounting flange, a second mounting flange, a body portion, a first rib and a second rib, the body portion extending from the first mounting flange to the second mounting flange, the first rib extending from the second mounting flange towards the first mounting flange, the second rib extending from the second mounting flange towards the first mounting flange, the first rib and the second rib extending orthogonal to the body portion; and a retainer sleeve having a first slot extending from the first axial end towards the second axial end and a second slot extending from the first axial end towards the second axial end, a portion of the first rib disposed in the first slot, and a portion of the second rib disposed in the second slot.

A braking system and method utilizing a simplified estimate of a distance between two locations on the earth based on spherical geometry. A braking system utilizing the aforementioned simplified estimate does not require computationally intensive calculations and is more efficient and better equipped to handle real-time generation of distance estimates for braking needs and variable conditions. In the present invention, geodesics evaluations are not used; rather, a modified Haversine formula that simplifies computations is used, including a one-time computation of the cosine of latitude coordinate.

Method for monitoring the braking of the wheels of an aircraft in which the braking of the wheels of the aircraft is controlled by a wheel braking controller actuating the wheel brakes of the aircraft based on both a deceleration regulation request and a thrust reverser deployment request.

A system for performing frequency response health monitoring of a servo valve prior to flight of an aircraft may comprise: the servo valve; and a brake controller in electrical communication with the servo valve, the brake controller configured to: determine the brake controller is powering up, supply a variable current to the servo valve to perform the frequency response health monitoring to the servo valve in response to determining the brake controller is powering up, and determine a health status of the servo valve based on the frequency response health monitoring.

A controller for a hydraulic braking system for an aircraft is disclosed. The hydraulic braking system includes a first accumulator and a second accumulator, the controller configured to: receive first signals including first pressure data from a first pressure transducer associated with the first accumulator, receive second signals including second pressure data from a second pressure transducer associated with the second accumulator, monitor the received first and second signals to determine whether a predetermined condition has been met, and issue a warning indicating a loss of integrity of the hydraulic braking system in response to a determination that one or more predetermined conditions has been met. A hydraulic braking system for an aircraft and method to determine the integrity of a hydraulic braking system are also disclosed.

A retainer for a segmented annular heat shield of a wheel includes a first end, a second end opposite the first end, and a body extending between the first end and the second end. Both the first end and the second end are configured to be coupled to at least one of the wheel and a torque bar. Further, the body includes opposing longitudinal sides configured to respectively engage and secure a respective heat shield segment of the segmented annular heat shield. Also, the retainer includes a cover coupled to and extending over at least the body, with an air gap being defined between the body and the cover.

A method of parking an aircraft is disclosed including flight crew pedal braking to cause a brake force to be applied to the aircraft wheel brakes to slow the aircraft to a stationary state in which it is ready to be parked. Flight crew then activate a parking brake device and then release the pedal braking. An electronic control device, forming part of the aircraft’s braking system for example, automatically intervenes, following the manual release of the pedal braking, to cause a brake force to continue to be applied to the wheels. This may be until sufficient brake force is applied, as a result of the activation of the parking brake device, to hold the aircraft in its parked state or may be for a predetermined period of time, say, ten seconds.

A braking system for an aircraft may comprise: a brake assembly; a hydraulic braking subsystem having a hydraulic brake actuator configured to operate the brake assembly; an electric braking subsystem having an electric brake actuator configured to operate the brake assembly and a load cell configured to measure a force supplied by the electric brake actuator; a hydraulic brake control unit configured to control the hydraulic braking subsystem; and an electric brake control unit configured to control the electric braking subsystem, the electric brake control unit in operable communication with the hydraulic brake control unit, the electric brake control unit configured to calibrate the load cell by a scale factor based on a measured force from the load cell, a measured hydraulic pressure used to exceed the measured force received from the hydraulic brake control unit, and a piston area of the hydraulic brake actuator.

A braking system for an aircraft is disclosed herein. The braking system may comprise: a brake assembly; a hydraulic braking subsystem having a hydraulic brake actuator configured to operate the brake assembly; an electric braking subsystem and a hydraulic braking subsystem. During a flight, one of the electric braking subsystem and the hydraulic braking subsystem may be selected as a primary braking system. The braking system may be configured to command braking of a brake assembly by the hydraulic braking subsystem and the electric braking subsystem during an RTO phase of the flight. The braking system may be configured to command braking of a brake assembly by a secondary braking system in response to a failure of a primary braking system during the RTO phase of the flight.