An electrically actuated braking system for an aircraft, comprising: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a motor controller for generating a drive signal for the EMAbrake; and a braking control unit for generating a braking force command signal for the EMAC, wherein the braking control unit and the EMAC are disposed together with the EMAbrake in a common line replaceable unit (LRU).

An electrically actuated braking system for an aircraft, comprising: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a motor controller for generating a drive signal for the EMAbrake; and a braking control unit for generating a braking force command signal for the EMAC, wherein the braking control unit and the EMAC are disposed together with the EMAbrake in a common line replaceable unit (LRU).

An electrically controlled park and emergency brake system is disclosed. The brake system may comprise a brake control module having a shut-off valve in fluid communication with an outboard servo-valve and an inboard servo-valve. An emergency/park power source may supply fluid to the shut-off valve. The brake system may also comprise a vehicle management system in electronic communication with the brake control module. The brake system may also comprise mechanical inputs, including a wheel well brake handle and a cockpit brake handle. The brake system may also comprise redundant emergency/park power sources.

An electrically controlled park and emergency brake system is disclosed. The brake system may comprise a brake control module having a shut-off valve in fluid communication with an outboard servo-valve and an inboard servo-valve. An emergency/park power source may supply fluid to the shut-off valve. The brake system may also comprise a vehicle management system in electronic communication with the brake control module. The brake system may also comprise mechanical inputs, including a wheel well brake handle and a cockpit brake handle. The brake system may also comprise redundant emergency/park power sources.

A system is provided having a normal operational mode and a modulated operational mode. The system includes an input device configured to generate a command signal. The system further includes a brake controller configured to generate a brake actuation signal in response to the command signal. The system further includes a fluid source configured to provide fluid in response to the brake actuation signal. The fluid has a first portion and a second portion. The system further includes a return valve in fluid communication with the fluid source, and configured to return the first portion of the fluid to the fluid source when the system is in the modulated operational mode. The system further includes a wheel brake in fluid communication with the fluid source and configured to engage a wheel of the aircraft in response to at least the second portion of the fluid.

A system is provided having a normal operational mode and a modulated operational mode. The system includes an input device configured to generate a command signal. The system further includes a brake controller configured to generate a brake actuation signal in response to the command signal. The system further includes a fluid source configured to provide fluid in response to the brake actuation signal. The fluid has a first portion and a second portion. The system further includes a return valve in fluid communication with the fluid source, and configured to return the first portion of the fluid to the fluid source when the system is in the modulated operational mode. The system further includes a wheel brake in fluid communication with the fluid source and configured to engage a wheel of the aircraft in response to at least the second portion of the fluid.

An anti-lock braking system for an aircraft, including a braking actuator configured to apply a braking pressure to a brake stator, and a piezoelectric actuator connected in series with the braking actuator. The piezoelectric actuator is operable to modify the braking pressure applied to the brake stator to provide anti-skid protection.

An anti-lock braking system for an aircraft, including a braking actuator configured to apply a braking pressure to a brake stator, and a piezoelectric actuator connected in series with the braking actuator. The piezoelectric actuator is operable to modify the braking pressure applied to the brake stator to provide anti-skid protection.

The invention relates to a device for braking a wheel, the device comprising: a brake including at least a first actuator and a second actuator arranged to apply a braking torque to the wheel; a control system arranged to control the first and second actuators individually as a function of a required braking value; and at least a first breaking torque sensor arranged to supply the control unit with a first measurement of the braking torque applied to the wheel by the brake. According to the invention, the control system is arranged to interrupt control of the first actuator or control of the second actuator in the event of the braking torque measured by the first sensor exceeding a predetermined braking torque limit.

The invention relates to a device for braking a wheel, the device comprising: a brake including at least a first actuator and a second actuator arranged to apply a braking torque to the wheel; a control system arranged to control the first and second actuators individually as a function of a required braking value; and at least a first breaking torque sensor arranged to supply the control unit with a first measurement of the braking torque applied to the wheel by the brake. According to the invention, the control system is arranged to interrupt control of the first actuator or control of the second actuator in the event of the braking torque measured by the first sensor exceeding a predetermined braking torque limit.