An aircraft includes a first landing gear assembly, a second landing gear assembly, a braking circuit, a brake control circuit, and a braking capability circuit. The landing gear assemblies each include a first braking wheel and a second braking wheel. The braking circuit may apply brakes independently to each of the braking wheels. The brake control circuit actuates braking of the first braking wheels in response to initial receipt of a braking command in a first braking phase and restrict braking at the second braking wheels during the first braking phase until the first braking wheels reach an anti-skid limit at an end of the first braking phase. The braking capability circuit determines a braking capability of the aircraft based on an amount of braking applied to reach the anti-skid limit at the first braking wheels.

An aircraft system for an aircraft is disclosed having a controller that is configured to receive at least one signal during a landing procedure of the aircraft and to determine that the aircraft is at a predetermined stage in the landing procedure, on the basis of the at least one signal. The predetermined stage in the landing procedure is before a command to extend at least one landing gear of the aircraft is issued during the landing procedure. The controller is configured to cause initiation of at least a part of a procedure to interrogate an aircraft braking system, on the basis of the determination.

An aircraft system for an aircraft is disclosed having a controller that is configured to receive at least one signal during a landing procedure of the aircraft and to determine that the aircraft is at a predetermined stage in the landing procedure, on the basis of the at least one signal. The predetermined stage in the landing procedure is before a command to extend at least one landing gear of the aircraft is issued during the landing procedure. The controller is configured to cause initiation of at least a part of a procedure to interrogate an aircraft braking system, on the basis of the determination.

This system (36) for controlling an aircraft thrust reversal means comprises a reverse idle control means (38), a first detection means (31) configured to detect, when the reverse idle control is active, a condition for activation of the thrust reversal means, and an actuation means (52) configured to activate the thrust reversal means when the first detection means (31) detects a condition for activation of the thrust reversal means.

It further comprises a second detection means (42, 44, 46, 48, 49) configured to detect a condition for activation of the reverse idle control, the control means (38) being configured to activate the reverse idle control when the second detection means (42, 44, 46, 48, 49) detects a condition for activating the reverse idle control.

An emergency braking method for aircraft, comprising using a progressing parking brake controlled by a lever (10) that can be actuated by the pilot between a “0%” position in which the brakes are connected to the return pressure of the aircraft, and a “100%” position in which the brakes are connected to the feed pressure of the aircraft, the lever being blockable in the 100% position in order to provide parking braking when the aircraft is stationary. According to the invention, the emergency braking method being characterized in that it comprises: using a valve having an outlet port connected to the brakes, a return port, and a feed port, the valve presenting a state connecting the outlet port to the return port and a state connecting the outlet port to the feed port; and controlling the valve to occupy one or other of those states by pulse width modulation (PWM) having a duty ratio (R) that is a function of the position of the lever in order to deliver the brakes with pressure lying in the range return pressure to feed pressure, depending on the position of the lever.

An aircraft includes a processor, an airframe, a pitch attitude flight control surface coupled with the airframe, a nose wheel coupled with the airframe, main wheels coupled with the airframe, and a brake system coupled with the main wheels. The processor is programmed to determine that the aircraft has entered a braking segment of a landing phase of a flight of the aircraft while the aircraft is on a ground surface and to command the pitch attitude flight control surface with a nose up command during the braking segment in response to determining that the aircraft has entered the braking segment. The nose up command causes the pitch attitude flight control surface to generate a downforce that increases traction between the main wheels and the ground surface due to a weight shift from the nose wheel to the main wheels and directly due to the downforce on the main wheels.

An aircraft includes a processor, an airframe, a pitch attitude flight control surface coupled with the airframe, a nose wheel coupled with the airframe, main wheels coupled with the airframe, and a brake system coupled with the main wheels. The processor is programmed to determine that the aircraft has entered a braking segment of a landing phase of a flight of the aircraft while the aircraft is on a ground surface and to command the pitch attitude flight control surface with a nose up command during the braking segment in response to determining that the aircraft has entered the braking segment. The nose up command causes the pitch attitude flight control surface to generate a downforce that increases traction between the main wheels and the ground surface due to a weight shift from the nose wheel to the main wheels and directly due to the downforce on the main wheels.

A system, and associated method, for reducing oxidation of a friction disk may include a braking assembly comprising the friction disk and a conduit coupled to the braking assembly, with the conduit being in selectable fluid providing communication with the braking assembly. That is, the conduit may be configured to deliver inert fluid to the braking assembly, thus reducing the concentration of oxygen in the vicinity of the friction disks and thus reducing/mitigating oxidation of the friction disks.

A system, and associated method, for reducing oxidation of a friction disk may include a braking assembly comprising the friction disk and a conduit coupled to the braking assembly, with the conduit being in selectable fluid providing communication with the braking assembly. That is, the conduit may be configured to deliver inert fluid to the braking assembly, thus reducing the concentration of oxygen in the vicinity of the friction disks and thus reducing/mitigating oxidation of the friction disks.

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.