The present invention achieves technical advantages as a pilot and passenger seating. An aircraft employs a pilot seat, comprising a contoured structure having ergonomically formed and padded surfaces, with left and right arm supports that include an articulated control knob, movable in three rectangular axes and rotatable about a vertical axis to provide one or more aircraft steering functions for an aircraft, and a touch-sensitive control surface for controlling one or more power system components. A passenger seat, having a contoured structure, having ergonomically formed and padded surfaces, a headrest, a seat, a left support member, and a right support member are adapted to cradle a portion of a passenger's body to support the passenger during travel.

The invention relates to a force application device for an aircraft control column, the control column comprising a control lever configured to rotate a first shaft and a second shaft, the force application device comprising a first force feedback member configured to exert a resistive force opposing the rotation of the first shaft, a second force feedback member configured to exert a resistive force opposing the rotation of the second shaft and a common braking device comprising a housing, a first braking member and a second braking member which are coaxial and mounted rotatably inside the housing and configured to engage with the first shaft and the second shaft, respectively, so as to brake them, preferably simultaneously.

A control system for assisting a pilot to control an aircraft operating under control of an active inceptor, the control system comprising: a receiver for receiving pilot-inputs on an active inceptor; an instruction generator to generate an instruction, the instruction based on an external signal associated with the geographical location of the aircraft; a tactile cue generator to generates a tactile cue which causes the active inceptor to move from a nominal position to a first offset position within a predetermined time period in response to the instruction.

A control system for assisting a pilot to control an aircraft operating under control of an active inceptor, the control system comprising: a receiver for receiving pilot-inputs on an active inceptor; an instruction generator to generate an instruction, the instruction based on an external signal associated with the geographical location of the aircraft; a tactile cue generator to generates a tactile cue which causes the active inceptor to move from a nominal position to a first offset position within a predetermined time period in response to the instruction.

A system may include a vehicle. The vehicle may include an array of haptic devices. The system may further include at least one processor configured to: determine a location of an object or occurrence relative to the user; based at least on the location of the object or occurrence relative to the user, select at least one haptic device of the array of haptic devices to be driven and function as a directional haptic alert to the user, wherein the directional haptic alert is indicative of a direction from the user toward the object or occurrence; and output at least one command to cause a driving of the selected at least one haptic device, wherein the driving of the selected at least one haptic device is perceivable by the user as the directional haptic alert.

An electronic control device of an avionics system for implementation of a critical avionics function, comprising: a module for receiving a voice instruction signal; a speech recognition module configured to transform the voice signal into a textual transcript; a processing module configured to associate the textual transcript with at least one action to be performed; a monitoring system comprising: a control module configured to check whether the textual transcript and/or the action to be performed is consistent if and only if: a) the textual transcript and/or the action to be performed is consistent with the expected syntax, b) the textual transcript and/or the action to be performed is consistent with the expected lexical field, and c) the textual transcript and/or the action to be performed is consistent with the current context, a module for generating an associated command only if no inconsistencies are detected.

An anti-spin system for an aircraft can include an anti-spin module configured to execute a computer implemented method. The method can include receiving flight data from one or more aircraft flight data systems, determining if the aircraft is near stall or in a stall using the flight data, and determining if the aircraft is in uncoordinated flight while near stall or in a stall to determine if the aircraft is near spin or in a spin using the flight data. If the aircraft is determined to be near spin, the method includes at least one of sending an alert to a warning indicator in a cockpit to warn the pilot of a spin or near spin condition, or sending a signal to an automated control system for inputting automatic control to the aircraft to avoid a spin by coordinating the aircraft or avoiding a stall while uncoordinated.

An anti-spin system for an aircraft can include an anti-spin module configured to execute a computer implemented method. The method can include receiving flight data from one or more aircraft flight data systems, determining if the aircraft is near stall or in a stall using the flight data, and determining if the aircraft is in uncoordinated flight while near stall or in a stall to determine if the aircraft is near spin or in a spin using the flight data. If the aircraft is determined to be near spin, the method includes at least one of sending an alert to a warning indicator in a cockpit to warn the pilot of a spin or near spin condition, or sending a signal to an automated control system for inputting automatic control to the aircraft to avoid a spin by coordinating the aircraft or avoiding a stall while uncoordinated.

A flight control computer (FCC) for a rotorcraft includes a processor and a non-transitory computer-readable storage medium storing a program to be executed by the processor, with the program including instructions for providing main rotor overspeed protection. The instructions for providing the main rotor overspeed protection include instructions for monitoring sensor signals indicating a main rotor RPM, determining a target operating parameter, determining one or more flight parameters in response to a relationship between the main rotor RPM and the target operating parameter indicating a main rotor overspeed condition. Determining the one or more flight parameters includes determining a setting for a flight control device of the rotorcraft that changes the main rotor RPM, controlling positioning of a pilot control according to the flight parameters, and controlling the flight control device of the rotorcraft according to positioning of the pilot control.

A flight control computer (FCC) for a rotorcraft includes a processor and a non-transitory computer-readable storage medium storing a program to be executed by the processor, with the program including instructions for providing main rotor overspeed protection. The instructions for providing the main rotor overspeed protection include instructions for monitoring sensor signals indicating a main rotor RPM, determining a target operating parameter, determining one or more flight parameters in response to a relationship between the main rotor RPM and the target operating parameter indicating a main rotor overspeed condition. Determining the one or more flight parameters includes determining a setting for a flight control device of the rotorcraft that changes the main rotor RPM, controlling positioning of a pilot control according to the flight parameters, and controlling the flight control device of the rotorcraft according to positioning of the pilot control.