A multi-disk brake system comprises an electrical generator disposed therein. The electrical generator is configured to convert mechanical energy to electrical energy. The mechanical energy may be generated during a braking event of the multi-disk brake system. The electric generator may power various electrical components on the aircraft or store the electrical energy in a capacitor bank. The electric generator may also act as a motor and/or power a landing gear in a motor configuration.

A multi-disk brake system comprises an electrical generator disposed therein. The electrical generator is configured to convert mechanical energy to electrical energy. The mechanical energy may be generated during a braking event of the multi-disk brake system. The electric generator may power various electrical components on the aircraft or store the electrical energy in a capacitor bank. The electric generator may also act as a motor and/or power a landing gear in a motor configuration.

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.

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.

A braking system architecture for aircraft, the architecture comprising: a brake (20) comprising a plurality of electromechanical actuators (26), each electromechanical actuator including a digital communication module; at least one power supply unit (21, 22); two control units (23, 24), each control unit being connected to a distinct group of one or more electromechanical actuators and comprising an upstream digital communication module (27), a control module (28) arranged to generate digital control signals (Sn1, Sn2), and a downstream digital communication module (29) connected to the digital communication modules of the electromechanical actuators of said group in order to transmit the digital control signals to the power modules of said electromechanical actuators; and a digital communication network (25) to which the upstream digital communication modules (27) of both control units are connected.

A braking system architecture for aircraft, the architecture comprising: a brake (20) comprising a plurality of electromechanical actuators (26), each electromechanical actuator including a digital communication module; at least one power supply unit (21, 22); two control units (23, 24), each control unit being connected to a distinct group of one or more electromechanical actuators and comprising an upstream digital communication module (27), a control module (28) arranged to generate digital control signals (Sn1, Sn2), and a downstream digital communication module (29) connected to the digital communication modules of the electromechanical actuators of said group in order to transmit the digital control signals to the power modules of said electromechanical actuators; and a digital communication network (25) to which the upstream digital communication modules (27) of both control units are connected.

The present application relates to a piston assembly for engaging two selectively engageable parts. The piston assembly has a housing defining a piston cylinder and a piston. The assembly also has a piston stroke limiter. The piston stroke limiter is configured to limit the length of a return stroke of the piston from an extended stroke position and a retracted stroke position. A crushable body acts between the piston and the piston stroke limiter and is arranged to reduce in axial length when a length of an extended stroke exceeds a length of a retraction stroke to maintain the length of the return stroke.

The present application relates to a piston assembly for engaging two selectively engageable parts. The piston assembly has a housing defining a piston cylinder and a piston. The assembly also has a piston stroke limiter. The piston stroke limiter is configured to limit the length of a return stroke of the piston from an extended stroke position and a retracted stroke position. A crushable body acts between the piston and the piston stroke limiter and is arranged to reduce in axial length when a length of an extended stroke exceeds a length of a retraction stroke to maintain the length of the return stroke.

A braking system is disclosed. In various embodiments, the braking system includes a brake stack; an actuator configured to apply a compressive load to the brake stack; a servo valve coupled to a power source and to the actuator; and a brake control unit configured to operate the servo valve at a current ramp rate in response to a pedal deflection signal, wherein the current ramp rate is determined via a relationship between the current ramp rate and a brake pressure command signal.

A braking system is disclosed. In various embodiments, the braking system includes a brake stack; an actuator configured to apply a compressive load to the brake stack; a servo valve coupled to a power source and to the actuator; and a brake control unit configured to operate the servo valve at a current ramp rate in response to a pedal deflection signal, wherein the current ramp rate is determined via a relationship between the current ramp rate and a brake pressure command signal.