A method and system for processing parameter values from a redundant sensor configured to sense a parameter used in the control of an aircraft engine is provided. The method includes: a) receiving a plurality of parameter values from a redundant sensor by sensing the same parameter at the same time; b) identifying mismatched parameter values; c) producing a predicted parameter value using an artificial intelligence (AI) model having a database of parameter values representative of the sensed parameter; d) providing the predicted parameter value to a control unit; and e) operating the control unit to select a first parameter value or a second parameter value using the predicted parameter for use in the control of the aircraft engine.

A method and system for processing parameter values from a redundant sensor configured to sense a parameter used in the control of an aircraft engine is provided. The method includes: a) receiving a plurality of parameter values from a redundant sensor by sensing the same parameter at the same time; b) identifying mismatched parameter values; c) producing a predicted parameter value using an artificial intelligence (AI) model having a database of parameter values representative of the sensed parameter; d) providing the predicted parameter value to a control unit; and e) operating the control unit to select a first parameter value or a second parameter value using the predicted parameter for use in the control of the aircraft engine.

An aircraft includes a fuselage, a wing attached thereto, a wing tip device attached to a wing end of the wing (2), a wing-like element having a wing root, a wing leading edge and a wing trailing edge, and a torque control device having a rotatable interface means. The torque control device is adapted for rotatably supporting the wing root of the wing-like element on the interface means about a rotational axis extending from the interface means into the wing-like element and to limit the degree of rotation depending on a torque introduced into the interface means by the wing-like element. The wing-like element is adapted to induce a rotation around the rotational axis in an air flow. The wing root is coupled with the wing tip device, the wing or the fuselage through the torque control device such that the leading edge extends into an airflow surrounding the aircraft.

An aircraft includes a fuselage, a wing attached thereto, a wing tip device attached to a wing end of the wing (2), a wing-like element having a wing root, a wing leading edge and a wing trailing edge, and a torque control device having a rotatable interface means. The torque control device is adapted for rotatably supporting the wing root of the wing-like element on the interface means about a rotational axis extending from the interface means into the wing-like element and to limit the degree of rotation depending on a torque introduced into the interface means by the wing-like element. The wing-like element is adapted to induce a rotation around the rotational axis in an air flow. The wing root is coupled with the wing tip device, the wing or the fuselage through the torque control device such that the leading edge extends into an airflow surrounding the aircraft.

An actuation system to manipulate an interface in an aircraft having an actuation controller, a vision system, a robotic arm, and a housing. Each of the vision system and the robotic arm assembly may be operatively coupled to the actuation controller. The vision system may be configured to optically image a display device of the preexisting interface, while the robotic arm assembly may be configured to engage a user-actuable device of the preexisting interface. The housing can be configured to affix to a surface adjacent the preexisting interface, where each of the vision system and the robotic arm assembly are coupled to the housing. In operation, the actuation controller may be configured to instruct the robotic arm assembly based at least in part on data from the vision system.

A method of operating a manipulation system of the type having a movable arm with a proximal end connected to a base and a distal end that is movable relative to the base and is coupled to an end-effector. The method comprises moving the distal end of the movable arm towards a target object and into contact with a stabilization object proximate to the target object, maintaining contact between the distal end of the movable arm and the stabilization object while operating the end-effector to perform a desired operation at the target object, and upon completing the desired operation at the target object, disengaging the distal end of the movable arm from contact with the stabilization object.

An electrical connector includes a first pass-through connector, a second pass-through connector, and a center portion coupled between the first pass-through connector and the second pass-through connector. The center portion includes a plurality of electrical connection points on an exterior surface of the center portion. The electrical connector also includes a plurality of pass-through wires extending from the first pass-through connector to the second pass-through connector through the center portion, wherein the plurality of electrical connection points are electronically coupled to the plurality of pass-through wires.

A remote optical control surface indication system comprising mechanisms configured to engage heads of respective fasteners that attach an alignment indexing plate to a vehicular structure having a control surface coupled thereto. The system further comprises: a camera having a field of view that encompasses a portion of an end face of the control surface when the mechanisms are engaged with the fasteners and when the control surface is in a neutral position; a source of light that is activatable to project light that illuminates the end face of the control surface; a display screen comprising an array of pixels; and a computing system configured to process image data captured by the camera to determine a current position of a centerline of the end face of the control surface relative to a baseline position and control the display screen to display symbology indicating the current position relative to the baseline position.

Pilot health monitoring systems, methods, and apparatuses are provided. A pilot health monitoring system is configured to collect information regarding the pilot's physiological and/or physical characteristics, and information regarding a state of the aircraft; analyze the information; determine a health condition of the pilot and/or a state of the aircraft; and/or provide warnings and/or commands as a function of the information.

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.