An aircraft includes actuators coupled to a lift device. The aircraft also includes a lift device control interface disposed on a flight deck of the aircraft. The lift device control interface is configured to receive a pilot input. The aircraft further includes a flight control system configured to generate a command corresponding to a target lift device position. The flight control system is also configured to send the command to the lift device control interface to cause the lift device control interface to indicate the target lift device position. The flight control system is further configured to send a control signal to the actuators to set the lift device to the target lift device position.

A vehicle, such as an airplane sets a limit for a control variable used to deflect a control surface. The limit is set as a function of an unfavorable flight condition/target angle of attack and a rate of change of angle of attack so that a pilot control variable command is prevented from exceeding the limit to prevent the vehicle from reaching an unfavorable flight condition and/or exceeding a desired angle of attack limit.

A flight control system for an aircraft includes at least one flight control computer that carries out a ground lift dump function that selectively extends a spoiler located on a wing of the aircraft into an airflow passing over the wing. The at least one flight control computer includes arming logic that is responsive to an input signal indicative of an aircraft parameter to automatically arm the ground lift dump function during certain phases of operation of the aircraft. The at least one flight control computer includes spoiler deployment logic that is responsive to an arming signal from the aiming logic which indicates that the ground lift function is armed to deploy the spoiler into its extended position within the airflow passing over the wing of the aircraft to assist in stopping the aircraft while the aircraft is on the ground.

Systems and methods for locking a control lever are provided. One system includes a locking device having a body configured to couple to a control lever within an aircraft to prevent the control lever from moving. The locking device also includes at least one hole defined through the body. The one hole is configured to receive one of a lock or a tag therein.

A system for controlling a high-lift device of an aircraft may include an interface for placement in a flight deck of an aircraft. The interface may include an edge control device for controlling a position of the high-lift device. The interface may be operable to select any of a plurality of control device positions. Each one of the plurality of control device positions may correspond to a different flight phase of the aircraft. The edge control device may be operable to engage, in response to a selection of a first control device position, a command mode for actuating the high-lift device in an automated manner based on the flight phase associated with the first control device position.

An angular position sensing device (1) comprising Hall Effect sensors (4a, 4b) is disclosed. The sensors (4a, 4b) are mounted in front of at least one rotatable magnet (3). The output voltage of the sensors (4a, 4b) varies with changing rotational position of the magnet (3). The magnet (3) is suitably mounted and the magnetic surface has a varying surface profile such that in the event of rotation of the magnet (3), a uniformly varying air gap is formed between the sensors (4a, 4b) and the magnetic surface, thus creating a uniformly varying magnetic field. The voltage output of the sensors is linear and reflective of the angular position of magnet (3).

A vehicle, such as an airplane sets a limit for a control variable used to deflect a control surface. The limit is set as a function of an unfavorable flight condition/target angle of attack and a rate of change of angle of attack so that a pilot control variable command is prevented from exceeding the limit to prevent the vehicle from reaching an unfavorable flight condition and/or exceeding a desired angle of attack limit.

A control system performs a method of controlling a wing of an airplane. The control system includes an optical fiber, a bending device and a processor. The optical fiber is configured to receive light having an input optical phase. The bending device applies an external force on the optical fiber. The external force causes the light exiting the optical fiber to have an output optical phase. a processor determines a phase shift between the input optical phase and the output optical phase and controls the wing based on the phase shift.

A wing for an aircraft. The wing includes a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing. The trailing edge high lift assembly includes a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position, wherein the connection assembly is configured such that the flap is movable relative to the main wing in a linear and/or rotational manner. The connection assembly is configured such that the flap is movable relative to the main wing in a decoupled linear and rotational manner.

A system of an electric aircraft with pitch control using an elevator is presented. In some embodiments, the electric aircraft may include an elevator configured to deflect. In some embodiments, the electric aircraft may further include a lift lever configured to generate a lift command upon activation by a pilot. In some embodiments, the electric aircraft may further include a flight controller communicatively connected with the lift lever and the elevator, wherein the flight controller is configured to receive the lift command from the lift lever and adjust the elevator as a function of the lift command.