The disclosed non-limiting embodiment provides important improvements in aircraft performance in short rejected takeoff systems by automatically detecting whether the speed of the aircraft does not exceed Vshort, where Vshort>V1; automatically detecting whether one of said plural engines has failed during takeoff while the aircraft is still in contact with the ground; and if the aircraft speed does not exceed vshort and an engine has failed, automatically performing an autonomous abort takeoff sequence to allow an improved takeoff weight in case of a single engine failure autonomously rejected takeoff. The aircraft's take off weight increase leads to increased payload or fuel quantity. The Payload increase allows for increased passenger and/or cargo capability. The fuel quantity increased allows the aircraft to achieve greater ranges. An aircraft provided with the proposed system, which reduces accelerate-stop distance, may then operate in shorter runways as compared to the prior art.

An aircraft includes an engine, a thrust reverser, landing gear, a brake system, a pilot input device, and a control system. The engine is configured to generate thrust directed to move the aircraft in a forward direction. The landing gear includes wheels. The brake system is configured to generate a braking force on the wheels. The pilot input device is positioned for use by a pilot of the aircraft. The control system is programmed to: determine whether the taxi operations are allowed; receive a request to achieve and hold a taxi speed at a desired taxi speed from the pilot input device; and command the engine, the thrust reverser, and the brake system to achieve and maintain the desired taxi speed in response to receiving the request to hold taxi speed only when the taxi operations are allowed.

A brake control system of the present disclosure calibrates a servo valve and calculates a calibrated transfer function associated with the servo valve for precise braking in open-loop mode. The calibration steps may include determining i) whether an aircraft is on a ground surface, ii) whether the aircraft is not moving relative to the ground surface, and iii) whether braking is applied to a brake system of the aircraft. The brake control unit may calibrate the servo valve in response to the brake control unit determining that i) the aircraft is on the ground surface, ii) the aircraft is not moving relative to the ground surface, and iii) the braking is not applied to the brake system of the aircraft. The calibration process includes sending two or more test currents to the servo valve, and determining braking pressures associated with those test currents to calculate the transfer function.

A system and method for braking an aircraft. A processor unit identifies an operating condition of the aircraft. The processor unit displays available modes indications on a display device on the aircraft. The available modes indications indicate modes of operating an automatic braking system on the aircraft that are available for selection by an operator based on the operating condition of the aircraft. The processor unit receives a mode selection from an operator interface. The mode selection indicates a selected mode of operating the automatic braking system that is selected by the operator from the available modes. The processor unit displays on the display device a selected mode indication indicating the selected mode.

A brake control system 200 and method 300 for controlling a park brake of an aircraft including a controller 201 configured to cause an increase in a brake torque of the park brake based of an indication to the controller. The indication is generated in response to touchdown of the aircraft.

An apparatus including a controller configured to generate a first indication for a vehicle braking system depending upon an oxidation state of a wheel brake of the vehicle is disclosed. Also disclosed is a braking system including a controller configured to receive a first indication, the first indication having been generated depending upon an oxidation state of a wheel brake of a vehicle and control the operation of the brake based on the first indication. Also disclosed is a method of controlling at least one brake of an aircraft, and an aircraft including the apparatus, the braking system and a temperature sensor configured to measure a temperature of a wheel brake of the aircraft and to transmit the temperature measurement to the apparatus.

The present disclosure provides a brake system including (a) a brake stack, (b) a force member moveable between a retracted position and an extended position in response to a brake command, wherein the force member contacts the brake stack in the extended position, and wherein the brake system includes a running clearance defined by a distance between the brake stack and the force member in the retracted position, (c) a sensor in communication with the brake stack to measure a force between the force member and the brake stack in response to the brake command, and (d) a brake control unit configured to determine a running clearance brake command defined as a percentage of a maximum braking force that causes the force member to contact the brake stack, wherein the running clearance brake command is determined based on the force measured by the sensor for a plurality of brake commands.

A system may include a processor installed in an aircraft. The processor may be configured to: obtain runway friction coefficient data and runway surface condition data for a runway; obtain braking coefficient data and braking action index data; obtain equivalent runway condition data and runway length data for the runway; obtain aircraft speed data of the aircraft and aircraft configuration data; based at least on the runway friction coefficient data, the runway surface condition data, the braking coefficient data, the braking action index data, the equivalent runway condition data, the aircraft speed data, and the aircraft configuration data, determine a rejected takeoff (RTO) initiating point (RIP) and a start automated RTO sequence point; and cause an automated RTO sequence to be performed if the start automated RTO sequence point is reached without the automated RTO sequence being manually overridden.

Methods for reducing brake wear during aircraft taxiing are disclosed. As one example, a method comprises determining a sequence to apply brakes of a given set of landing gear during a brake event, wherein the determining includes selecting a warmer brake of the brakes to initially apply at a start of the brake event, and selecting a cooler brake of the brakes to subsequently apply when the warmer brake is released during the brake event. The method further comprises applying the warmer brake and the cooler brake in the determined sequence during the brake event. In another example, an aircraft brake system comprises brakes and a controller that is programmed to, during taxiing, apply a warmer subset of the brakes before applying a cooler subset of the brakes during a brake event.

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.