There is provided a hydraulic system for a vehicle. The hydraulic system has a hydraulic rotary actuator assembly rotationally coupled to a road wheel of the vehicle. The hydraulic rotary actuator assembly has a first operating mode, wherein a rotation of the road wheel causes the hydraulic rotary actuator assembly to pump a fluid from a fluid supply system. The hydraulic system further has a variable restrictor assembly coupled to the hydraulic rotary actuator assembly in the vehicle. The variable restrictor assembly controls a flow of the fluid flowing from the hydraulic rotary actuator assembly, to brake the rotation of the road wheel on a ground surface. The hydraulic system further has a variable restrictor controller coupled to the variable restrictor assembly. The variable restrictor controller controls the variable restrictor assembly, so as to enable a variation of a rate of braking of the road wheel on the ground surface.

A system for detecting aircraft brake failure using retract braking may comprise a landing gear including a wheel, a brake coupled to the wheel, and a wheel sensor coupled to the wheel. A brake controller may be coupled to the brake and the wheel sensor. The brake controller may be configured to receive a begin retract braking signal, command the brake to apply a braking force to the wheel, calculate a wheel speed characteristic using data from the wheel sensor, and determine whether the wheel speed characteristic indicates a failure of the brake.

A brake system for a vehicle is disclosed and includes an energy storage device configured to store and discharge energy, a plurality of wheels, one or more processors operatively coupled to the energy storage device, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the brake system to determine the brake system is operating in a backup mode of operation. In response to determining the brake system is operating in the backup mode of operation, the brake system calculates a dynamic slip of the plurality of wheels. The brake system is caused to determine a slip error by comparing the dynamic slip with a target slip value of the plurality of wheels. The brake system is also caused to calculate an antiskid command based on the slip error.

A brake system is disclosed. The brake system includes a brake stack having a stack closure pressure, a force member positioned within a cylinder, a valve configured to control the fluid pressure of the brake system, and one or more pressure transducers that generate a proportional electrical signal representative of fluid pressure within the cylinder. The brake system also includes one or more processors in electronic communication with the valve, the one or more pressure transducers, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the brake system to determine the stack closure pressure of the brake stack.

A control method of an electrical braking system for aircraft includes a plurality of electromechanical actuators capable of applying a braking force on friction members. Each electromechanical actuator includes an electric motor equipped with one or more windings. The braking system further includes at least one power module configured to send to each electric motor winding a phase current and at least one control module configured to control, in response to a braking setpoint, the sending by the power module of a setpoint phase current determined depending on the braking force to be applied. The method further includes the variation of the phase current transmitted to each winding of the electric motor so as to cause the phase current to oscillate around the setpoint phase current.

An aircraft automatic braking system, comprising: a first functional module arranged in order to implement a state machine that includes a first branch comprising first states corresponding to a landing of the aircraft, a second branch comprising second states corresponding to a rejected take-off of the aircraft, and transitions, the first states, the second states and the transitions being defined independently of deceleration rates; a second functional module arranged in order to define a target deceleration of the aircraft at least on the basis of the deceleration rates and a current state of the state machine; and a third functional module arranged in order to define, at least on the basis of the current state and the target deceleration, an automatic braking command in order to control actuators of wheel brakes of the aircraft.

An autobrake selection interface for an aircraft includes a cockpit mounted user selectable display. The display includes autobrake selection options and braking information. The autobrake selection options include at least one of an autobrake off option, a rejected takeoff (RTO) option, a constant deceleration option, and a runway exit selection option. The braking information includes at least one of an estimated brake temperature, an estimated brake cooling time, and an estimated landing distance. The autobrake selection interface also includes a braking parameters determiner configured to determine at least one of the estimated brake temperature and the estimated landing distance according to user selection of the autobrake selection options.

Method of controlling a braking device (100), the method comprising the following steps: receiving a braking torque instruction (If); on the basis of the received braking torque instruction (If), setting a first braking torque set point (Cf1) for a first brake (1) and a second braking torque set point (Cf2) for a second brake (2); measuring a first value of a first parameter (I8) representative of the first braking torque (C1) and modifying the first braking torque set point (Cf1) as a function of the first value with the aid of a first servocontrol loop (93); measuring a second value of a second parameter (19) representative of the second braking torque (C2) and modifying the second braking torque set point (Cf2) as a function of the second value (19) with the aid of a second servocontrol loop (94).

Braking device (100)

Aircraft comprising this kind of braking device (100)

An electric braking system (1) for braking an aircraft, the system comprising: a brake (3) comprising an electromechanical actuator (5) designed so that when it applies a force to the friction members (4) that is less than or equal to a first maximum threshold, no degradation of the actuator occurs, and when it applies a force to the friction members (4) that is greater than the first maximum threshold, degradation is likely to occur; control means (7) configurable to occupy a first mode in which the controlled braking force cannot exceed the first maximum threshold, and to occupy a second mode in which the controlled braking force can reach the second maximum threshold; and configuration means (10) arranged to configure the control means (7) to occupy the second mode when in a situation preceding a potential interruption of takeoff (RTO) of the aircraft, and otherwise to occupy the first mode.

Systems and methods for shutoff valve control are provided. The system may receive a first hardware logic input, a second hardware logic input, and a weight-on-wheels (WOW) status wherein each of the first hardware logic input, the second hardware logic input, and the WOW status report a binary true or a false. The system may open the shutoff valve when each of the first hardware logic input, the second hardware logic input, and the WOW status report true. The system may close the shutoff valve when any of the first hardware logic input, the second hardware logic input, and the WOW status report false.