A rotary-wing aircraft and system for flying a rotary-wing aircraft. The aircraft includes a servo system for actuating a rotor of the aircraft. A hydraulic system provides hydraulic power to the servo system, and a sensor measures a parameter of the hydraulic system. A processor determines a condition of the hydraulic system from the parameter and enforces an effective flight envelop based on the condition of the hydraulic system in order to fly the aircraft within the effective flight envelope.

A rotary-wing aircraft and system for flying a rotary-wing aircraft. The aircraft includes a servo system for actuating a rotor of the aircraft. A hydraulic system provides hydraulic power to the servo system, and a sensor measures a parameter of the hydraulic system. A processor determines a condition of the hydraulic system from the parameter and enforces an effective flight envelop based on the condition of the hydraulic system in order to fly the aircraft within the effective flight envelope.

The Curtis Protocol, an aircraft control interface, is provided. The Curtis Protocol standardizes the division and selection of aircraft flight regimes and flight modes within the selected flight regime.

The Curtis Protocol, an aircraft control interface, is provided. The Curtis Protocol standardizes the division and selection of aircraft flight regimes and flight modes within the selected flight regime.

The invention relates to a force application device for an aircraft control stick comprising: —a casing (24), —an electromagnet (22) mounted on the casing (24), —an actuator (30) mounted on the shaft (13), the actuator (30) being mobile in translation in relation to the shaft (13) along the axis (A), the actuator (30) comprising a magnetic material, and —a coupling device comprising an input gear (40) that is mounted so as to be stationary in relation to the casing (24) and an output gear (50) connected to the actuator (30) by means of an attachment part (60), the attachment part (60) being configured so as to allow a limited angular displacement between the output gear (50) and the shaft (13) around the axis (A) and to allow the actuator (30) of the output gear (50) to translate along the axis (A).

The invention relates to a force application device for an aircraft control stick comprising: —a casing (24), —an electromagnet (22) mounted on the casing (24), —an actuator (30) mounted on the shaft (13), the actuator (30) being mobile in translation in relation to the shaft (13) along the axis (A), the actuator (30) comprising a magnetic material, and —a coupling device comprising an input gear (40) that is mounted so as to be stationary in relation to the casing (24) and an output gear (50) connected to the actuator (30) by means of an attachment part (60), the attachment part (60) being configured so as to allow a limited angular displacement between the output gear (50) and the shaft (13) around the axis (A) and to allow the actuator (30) of the output gear (50) to translate along the axis (A).

A flight stick cockpit simulator ground station system is provided. The system includes a base. The system also includes a yoke control module connected to the base. Further, the system includes a yaw control module connected to the base. Additionally, the system includes a throttle control module connected to the base. The system also includes a manipulator module for an aerial TUC transmitter for remote controlled aircraft connected to the base and configured to receive inputs from the yoke control module, the yaw control module, and the throttle control module and structured to mechanically control the aerial R/C transmitter without the need for electrical or computerized mechanisms.

A yaw control system for a rotorcraft featuring a floor mounted pair of pedals configured to measure an up and down motion of a pair of pedals and utilize that up and down motion as a yaw moment control input. The pair of pedals can rock laterally, fore and aft, or vertically. The pair of pedals can be mechanically interconnected to other pairs of pedals or electrically interconnected to duplicate motion across pairs of pedals.

A yaw control system for a rotorcraft featuring a floor mounted pair of pedals configured to measure an up and down motion of a pair of pedals and utilize that up and down motion as a yaw moment control input. The pair of pedals can rock laterally, fore and aft, or vertically. The pair of pedals can be mechanically interconnected to other pairs of pedals or electrically interconnected to duplicate motion across pairs of pedals.

An exemplary method for controlling low speed flight of an aircraft having a controller receiving pilot input includes transitioning from a translational rate command (TRC) to a linear acceleration command (LAC) when the controller is displaced above a control transition displacement (CTD), and while in LAC holding speed when the controller is relaxed to CTD.