A command model connected to plurality of flight components of an electric aircraft and comprises a circuitry configured to detect a predicted state and a measured state datum, transmit predicted state datum to an actuator model, and transmit measured state datum to a plant model. An actuator model connected to the sensor configured to receive the predicted state datum and generate a performance datum. A plant model connected to the sensor configured to receive measured state datum and performance datum from the actuator model, transmit a feedback path to controller, and generate an inconsistency datum as a function of the measured state datum and the performance datum. A controller communicatively connected to the sensor, wherein the controller is configured to receive the inconsistency datum from the plant model and apply a torque to the aircraft as a function of the inconsistency datum.

A method of controlling an aircraft electrical taxiing system, the method comprising the steps of: defining a target value (Ld_nmax) for an electrical parameter; generating a nominal force command (Cmd_nom) for the electrical taxiing system; in parallel with generating the nominal force command (Cmd_nom), using a processing system (2) to produce a maximum command force (Force_max) for the electrical taxiing system so that a real value of the electrical parameter reaches the target value (Ld_nmax), the processing system (2) comprising a regulator loop (4); and generating an optimized force command (Cmd_opt) for the electrical taxiing system equal to the smaller of the nominal force command and the maximum command force.

A method for optimizing the take-off parameters of an aircraft. The aircraft comprises a system for automatically controlling the high lift devices at the moment when the wheels of the aircraft leave the ground. The method comprises a step of selecting a first configuration of the high lift devices at the start of the take-off phase and a selection of an acceleration speed of the aircraft. The method is advantageous in that, on reception of an actual aircraft take-off detection signal, a control unit is configured to transmit a control command making it possible to bring the high lift devices into a second configuration, in which they are retracted relative to the first position, and consecutively accelerate the speed of the aircraft automatically to an acceleration speed entered by the pilot.

An actuating mechanism is disclosed for a body in an air and/or space vehicle. having at least one control surface on the body for moving relative to the body and thereby enabling control of the air flow and enabling the air vehicle to maneuver. The actuating mechanism has at least two actuators produced from an electro-active polymer material between the body and the control surface for changing its form depending on electrical energy and thereby triggering the control surfaced.

A method for adjusting play in a high-lift system of an aircraft with several flaps, moved by a drive unit with the aid of driving stations connected to a driveshaft, includes disengaging the mechanical connections between the driveshaft and the driving stations in the first position, displacing the individual drive levers by mechanically driving a gear input of the associated rotary actuator such that the individual drive levers come into mechanical contact with a stop in a second position, spaced apart from the first position, and are pretensioned by a certain torque, rotationally fixing the gear inputs of the rotary actuators, adapting the length of connecting links between the respective drive levers and a support arm carrying the associated flap such that a position of the associated flap corresponding to the position of the stop is reached, and reconnecting the driving stations to the driveshaft pretensioned to have no play.

A method for adjusting play in a high-lift system of an aircraft with several flaps, moved by a drive unit with the aid of driving stations connected to a driveshaft, includes disengaging the mechanical connections between the driveshaft and the driving stations in the first position, displacing the individual drive levers by mechanically driving a gear input of the associated rotary actuator such that the individual drive levers come into mechanical contact with a stop in a second position, spaced apart from the first position, and are pretensioned by a certain torque, rotationally fixing the gear inputs of the rotary actuators, adapting the length of connecting links between the respective drive levers and a support arm carrying the associated flap such that a position of the associated flap corresponding to the position of the stop is reached, and reconnecting the driving stations to the driveshaft pretensioned to have no play.

An aircraft system interface has a center pedestal and a touchscreen display carried by the center pedestal. The interface has one or more programs including instructions for displaying a virtual input device, instructions for detecting movement of an object on or near the touchscreen display, and instructions for rotating the virtual input device displayed on the touchscreen display in response to detecting the movement.

An aircraft system interface has a center pedestal and a touchscreen display carried by the center pedestal. The interface has one or more programs including instructions for displaying a virtual input device, instructions for detecting movement of an object on or near the touchscreen display, and instructions for rotating the virtual input device displayed on the touchscreen display in response to detecting the movement.

A method and apparatus for calibrating a set of transducers. In one illustrative embodiment, an apparatus comprises a target device, an imaging device, and a calibrator. The imaging device generates a plurality of images of a target formed by the target device as the target device is rotated relative to the imaging device about a pivot axis formed at an interface between a first structure and a second structure in response to the first structure being rotated about the pivot axis relative to the second structure. The calibrator identifies a plurality of angles of the target about the pivot axis using the plurality of images. The calibrator further identifies calibration information using the plurality of angles.

A method and apparatus for calibrating a set of transducers. In one illustrative embodiment, an apparatus comprises a target device, an imaging device, and a calibrator. The imaging device generates a plurality of images of a target formed by the target device as the target device is rotated relative to the imaging device about a pivot axis formed at an interface between a first structure and a second structure in response to the first structure being rotated about the pivot axis relative to the second structure. The calibrator identifies a plurality of angles of the target about the pivot axis using the plurality of images. The calibrator further identifies calibration information using the plurality of angles.