A rudder control unit includes a single-piece main module mobile on a curved support frame. The rudder control unit includes a curved support and guide frame to be mounted in a floor of the aircraft, and a unique main module including the pedals and a set of functionalities, the main module configured such that it is movable and positioned on the support and guide frame using a movement unit, thus making it possible to obtain an extremely simplified architecture with a reduced number of pieces.

An aircraft rudder pedal frame includes a base, a support framework and connection interfaces. Each connection interface is able to connect another part of the rudder pedal to the frame. The support framework connects each connection interface to the base. The support framework includes framework elements arranged in a lattice, at least one of the framework elements extending from each connection interface.

An aircraft rudder pedal frame includes a base, a support framework and connection interfaces. Each connection interface is able to connect another part of the rudder pedal to the frame. The support framework connects each connection interface to the base. The support framework includes framework elements arranged in a lattice, at least one of the framework elements extending from each connection interface.

An aircraft rudder pedal includes a frame, a pair of pedals, an output shaft and a mechanical kinematic chain for transmitting to the output shaft a displacement of at least one of the pedals relative to the frame. The mechanical kinematic chain comprises a central transmission part able to be rotated relative to the frame by a displacement of one of the pedals relative to the frame. The mechanical kinematic chain also includes a transmission mechanism joining the central transmission part to the output shaft. The transmission mechanism includes a homokinetic association of two universal joints between said central transmission part and the output shaft.

An aircraft rudder pedal comprising a frame and at least one pedal side system. The or each pedal side system includes 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 presents a first pivotal articulation connection to the frame and a second pivotal articulation connection with the support link. The lever presents a first pivotal articulation connection with the frame and a second pivotal articulation connection with the support link.

A control system (400) for an active inceptor (103) for a fly by wire aircraft permits a zero force null point to settle to a non-zero displacement trim position. An internal position state of a second order mass spring damper model is moved in conjunction with force-displacement characteristic coordinates. This results in no second order dynamics being superimposed on the feel of the inceptor (103) when dynamically adjusting the trim position, thereby eliminating the possibility of any unpleasant buzzing been felt by the operator of the inceptor during a trimming operation.

A control system (400) for an active inceptor (103) for a fly by wire aircraft permits a zero force null point to settle to a non-zero displacement trim position. An internal position state of a second order mass spring damper model is moved in conjunction with force-displacement characteristic coordinates. This results in no second order dynamics being superimposed on the feel of the inceptor (103) when dynamically adjusting the trim position, thereby eliminating the possibility of any unpleasant buzzing been felt by the operator of the inceptor during a trimming operation.

A yaw control system for a rotorcraft featuring a floor mounted pair of pedals configured to measure an up and down motion of a pair of pedals and utilize that up and down motion as a yaw moment control input. The pair of pedals can rock laterally, fore and aft, or vertically. The pair of pedals can be mechanically interconnected to other pairs of pedals or electrically interconnected to duplicate motion across pairs of pedals.

A configuration system (80) arranged to configure an aircraft in a single-pilot mode and a two-pilot mode, comprising: acquisition means (84) and authentication means (83) arranged to acquire and authenticate a configuration order that defines the selected mode and controls the configuration system (80) to configure the aircraft in the selected mode; first activation means (85) arranged to activate equipment dedicated to piloting by a single-pilot on board when the aircraft is configured in single-pilot mode, and to deactivate dedicated equipment when the aircraft is configured in two-pilot mode; verification means (87) arranged to, when the aircraft is configured in the single-pilot mode, verify that single-pilot flight conditions are met and inform the sole pilot on board and a ground station of the results of these checks.

A configuration system (80) arranged to configure an aircraft in a single-pilot mode and a two-pilot mode, comprising: acquisition means (84) and authentication means (83) arranged to acquire and authenticate a configuration order that defines the selected mode and controls the configuration system (80) to configure the aircraft in the selected mode; first activation means (85) arranged to activate equipment dedicated to piloting by a single-pilot on board when the aircraft is configured in single-pilot mode, and to deactivate dedicated equipment when the aircraft is configured in two-pilot mode; verification means (87) arranged to, when the aircraft is configured in the single-pilot mode, verify that single-pilot flight conditions are met and inform the sole pilot on board and a ground station of the results of these checks.