A system for flight control for managing actuators for an electric aircraft is provided. The system includes a controller, wherein the controller is designed and configured to receive a sensor datum from at least a sensor, generate an actuator performance model as a function of the sensor datum, identify a defunct actuator of the electric aircraft as a function of the sensor datum and the actuator performance model, generate an actuator allocation command datum as a function of at least the actuator performance model and at least the identification of the defunct actuator, and perform a torque allocation as a function of the actuator allocation command datum.

A system for flight control for managing actuators for an electric aircraft is provided. The system includes a controller, wherein the controller is designed and configured to receive a sensor datum from at least a sensor, generate an actuator performance model as a function of the sensor datum, identify a defunct actuator of the electric aircraft as a function of the sensor datum and the actuator performance model, generate an actuator allocation command datum as a function of at least the actuator performance model and at least the identification of the defunct actuator, and perform a torque allocation as a function of the actuator allocation command datum.

A harmonic drive, having: a housing; an output shaft within the housing; an input shaft within the housing, the input shaft is configured for being in a first position in which rotation of the input shaft rotates the output shaft, and a second position that is axially offset from the first position, in which rotation of the input shaft does not rotate the output shaft; a solenoid coil within the housing that, when energized, moves the input shaft to the second position; and a spring within the housing that, when the solenoid coil is not energized, moves the input shaft to the first position.

A harmonic drive, having: a housing; an output shaft within the housing; an input shaft within the housing, the input shaft is configured for being in a first position in which rotation of the input shaft rotates the output shaft, and a second position that is axially offset from the first position, in which rotation of the input shaft does not rotate the output shaft; a solenoid coil within the housing that, when energized, moves the input shaft to the second position; and a spring within the housing that, when the solenoid coil is not energized, moves the input shaft to the first position.

A rotary geared actuator RGA includes an actuator body that has a gear or gears and means configured to rotate said gear or gears about a first central longitudinal axis X. The RGA also includes a drive transmission shaft extending along a second central longitudinal axis X, means for rotating said drive transmission shaft about said central longitudinal axis X, and means for translating said rotation of said drive transmission shaft to said gears so as to cause rotation of said gears about said first central longitudinal axis X. The second central longitudinal axis X of said drive transmission shaft is laterally offset from said first central longitudinal axis X.

A health monitoring method for checking a functionality of a flight control surface driving apparatus using a load sensor for sensing a load imposed on a control surface drive device by: comparing a load sensor output signal of the load sensor with a first while operating the control surface drive device to move the at least one control surface to a predetermined extended position; or, comparing a load sensor output signal of the load sensor with a second threshold while operating the control surface drive device to move the control surface from an extended position to a retracted position; or both. Also a flight control surface drive apparatus, a flight control system and an aircraft.

A health monitoring method for checking a functionality of a flight control surface driving apparatus using a load sensor for sensing a load imposed on a control surface drive device by: comparing a load sensor output signal of the load sensor with a first while operating the control surface drive device to move the at least one control surface to a predetermined extended position; or, comparing a load sensor output signal of the load sensor with a second threshold while operating the control surface drive device to move the control surface from an extended position to a retracted position; or both. Also a flight control surface drive apparatus, a flight control system and an aircraft.

An aerodynamic control surface assembly includes a structure (2) with an aerodynamic surface (8) and a curved aerodynamic control surface (20) configured to move between an extended (24) and a retracted position (22). The aerodynamic control surface is arranged to deploy through an aperture (18) in the aerodynamic surface and into an oncoming airflow (A). An actuation mechanism (52, 152, 252) coupled to the aerodynamic control surface (20) moves the aerodynamic control surface (20) between extended and retracted positions. The actuation mechanism (52, 152, 252) is configured such that the control surface (20) follows a curved kinematic path (40, 140, 240) as the control surface moves between the extended (24) and retracted positions (22). The actuation mechanism (52, 152, 252) remains fully behind the aerodynamic surface (8) throughout the movement of the aerodynamic control surface (20) between the extended (24) and retracted positions (22).

An aerodynamic control surface assembly includes a structure (2) with an aerodynamic surface (8) and a curved aerodynamic control surface (20) configured to move between an extended (24) and a retracted position (22). The aerodynamic control surface is arranged to deploy through an aperture (18) in the aerodynamic surface and into an oncoming airflow (A). An actuation mechanism (52, 152, 252) coupled to the aerodynamic control surface (20) moves the aerodynamic control surface (20) between extended and retracted positions. The actuation mechanism (52, 152, 252) is configured such that the control surface (20) follows a curved kinematic path (40, 140, 240) as the control surface moves between the extended (24) and retracted positions (22). The actuation mechanism (52, 152, 252) remains fully behind the aerodynamic surface (8) throughout the movement of the aerodynamic control surface (20) between the extended (24) and retracted positions (22).

The illustrative examples provide a slat movement system for use in an aircraft. An aircraft comprises a wing having a fixed edge and a wing front spar, and a moveable slat connected to the wing by a four bar linkage and a slat arm, the slat arm movable along a track comprising a slot terminating prior to the wing front spar.