Aircraft rudder with articulated support structure of pedal

An aircraft rudder pedal comprising:

• a frame;
• and
• at least one pedal side system, the or each pedal side system comprising a pedal and an articulated support structure of the pedal connecting the pedal to the frame;
• the articulated support structure of said pedal comprises a crank, a lever and a support link,
• the crank presenting a first pivotal articulation connection to the frame and a second pivotal articulation connection to the support link, the lever presenting a first pivotal articulation connection to the frame and a second pivotal articulation connection to the support link,
• wherein the crank and the lever form a kinematic trapezoid, a line passing through the first pivotal articulation connection of the crank with the frame and through the second pivotal articulation connection of the crank with the support link being substantially parallel to a line passing through the first pivotal articulation connection of the lever with the frame and through the second pivotal articulation connection of the lever with the support link;
• wherein, during any displacement of the pedal relative to the frame, a distance between an axis of rotation of the crank relative to the frame and an axis of rotation of the crank relative to the support link is greater than a distance between an axis of rotation of the lever relative to the frame and an axis of rotation of the lever relative to the support link.

An aircraft rudder pedal comprising:

• a frame;
• and
• at least one pedal side system, the or each pedal side system comprising a pedal and an articulated support structure of the pedal connecting the pedal to the frame;
• the articulated support structure of said pedal comprises a crank, a lever and a support link,
• the crank presenting a first pivotal articulation connection to the frame and a second pivotal articulation connection to the support link, the lever presenting a first pivotal articulation connection to the frame and a second pivotal articulation connection to the support link,
• wherein the at least one pedal side system comprises a braking system configured to control braking of the aircraft, the braking system comprising the pedal of the pedal side system, said pedal being connected to the crank by a braking pivotal link;
• wherein the braking system comprises a braking acquisition system configured to generate an electrical signal representative of a displacement of said pedal relative to the crank about the braking pivotal link, the braking acquisition system being supported by at least one of the crank, the lever and the support link;
• wherein the braking acquisition system comprises at least two redundant acquisition sensors, the at least two redundant acquisition sensors being supported by the same articulated support structure,
• wherein each acquisition sensor comprises a fixed element and a movable element, the movable element being configured to be displaced relative to the fixed element, each acquisition sensor being configured to generate an electrical measurement signal as a function of a position of the movable element relative to the fixed element;
• the braking acquisition system also comprising a joint drive device for the acquisition sensors, the joint drive device being configured to displace, for each acquisition sensor, the movable element relative to the fixed element of the acquisition sensor.