A trimmable horizontal stabiliser actuator (THSA) control system includes least one main THSA motor for driving the THSA in response to inputs from a flight control computer (FCC), a pilot trim control system for manual control of the THSA by a pilot overriding the FCC. The pilot trim control system comprises a trim control for receiving an input from the pilot, the trim control including a trim control sensor for detecting the input from the pilot and providing a pilot trim control signal; a THSA trim control motor for driving the THSA in response to the pilot trim control signal; and an electronic override system for giving inputs from the pilot priority over inputs from the FCC.

A trimmable horizontal stabiliser actuator (THSA) control system includes least one main THSA motor for driving the THSA in response to inputs from a flight control computer (FCC), a pilot trim control system for manual control of the THSA by a pilot overriding the FCC. The pilot trim control system comprises a trim control for receiving an input from the pilot, the trim control including a trim control sensor for detecting the input from the pilot and providing a pilot trim control signal; a THSA trim control motor for driving the THSA in response to the pilot trim control signal; and an electronic override system for giving inputs from the pilot priority over inputs from the FCC.

An aircraft has a substantially cylindrical body having a longitudinal axis, a cockpit, counter-rotating propellers of an overall diameter substantially greater than a maximum diameter of the body, DC motors powering the propeller sets, a battery compartment at a lower extremity of the cylindrical body, enclosing a DC battery, fixes wings extending a substantial distance away from the cylindrical body in a first direction, a rudder in a plane parallel to the axis of the cylindrical body, landing struts extending from a lower and outer extremity of each wing and of the providing a support structure for the aircraft; and controls operable to move the rudder and the wing flaps, and to manage power and rpm of the counter rotating propellers. The aircraft may lift vertically in hovering flight, transition to level flight, and return to hovering flight to land again.

An aircraft has a substantially cylindrical body having a longitudinal axis, a cockpit, counter-rotating propellers of an overall diameter substantially greater than a maximum diameter of the body, DC motors powering the propeller sets, a battery compartment at a lower extremity of the cylindrical body, enclosing a DC battery, fixes wings extending a substantial distance away from the cylindrical body in a first direction, a rudder in a plane parallel to the axis of the cylindrical body, landing struts extending from a lower and outer extremity of each wing and of the providing a support structure for the aircraft; and controls operable to move the rudder and the wing flaps, and to manage power and rpm of the counter rotating propellers. The aircraft may lift vertically in hovering flight, transition to level flight, and return to hovering flight to land again.

A device for releasably mounting an autopilot control circuit to a flight control component of an aircraft, includes a frame that holds a component of an autopilot control circuit; a first coupler releasably fastened to the frame and operable to releasably mount the frame to the airframe of an aircraft; and a second coupler releasably fastened to the frame and operable to releasably mount the frame to a flight control component of the aircraft. When the device is releasably mounted in an aircraft's cabin and the autopilot control circuit is engaged, the autopilot control circuit controls an aspect of the aircraft's flight by moving the second coupler relative to the first coupler. With the device one can releasably mount an autopilot control circuit to an aircraft that does not have one and use the autopilot control circuit and device to control one or more aspects of the aircraft's flight.

A device for releasably mounting an autopilot control circuit to a flight control component of an aircraft, includes a frame that holds a component of an autopilot control circuit; a first coupler releasably fastened to the frame and operable to releasably mount the frame to the airframe of an aircraft; and a second coupler releasably fastened to the frame and operable to releasably mount the frame to a flight control component of the aircraft. When the device is releasably mounted in an aircraft's cabin and the autopilot control circuit is engaged, the autopilot control circuit controls an aspect of the aircraft's flight by moving the second coupler relative to the first coupler. With the device one can releasably mount an autopilot control circuit to an aircraft that does not have one and use the autopilot control circuit and device to control one or more aspects of the aircraft's flight.

A method of controlling an artificial force feel generating device for generation of an artificial feeling of force on an inceptor that is adapted for controlling a servo-assisted control unit of a vehicle control system, wherein the artificial force feel generating device comprises at least one force generating device that is mechanically connected to the inceptor for generating a tactile cue force acting in operation on the inceptor, and wherein a safety device is provided for limiting authority of the at least one force generating device, the method comprising at least the steps of: monitoring usage of the safety device during operation of the artificial force feel generating device, determining a current accumulated fatigue of the safety device on the basis of the monitored usage, and re-configuring the at least one force generating device on the basis of the current accumulated fatigue.

An artificial force feel generating device for generation of an artificial feeling of force on an inceptor of a vehicle control system, the inceptor being adapted for controlling a servo-assisted control unit of the vehicle control system via a mechanical linkage, wherein at least one first force generating device and at least one second force generating device are mechanically connected to the inceptor, the first force generating device being provided for generating a nominal force acting in operation on the inceptor and the second force generating device being provided for generating a tactile cue force acting in operation on the inceptor, the first and second force generating devices being arranged in parallel. The invention relates further to an aircraft comprising such an artificial force feel generating device.

An artificial force feel generating device for generation of an artificial feeling of force on an inceptor of a vehicle control system, the inceptor being adapted for controlling a servo-assisted control unit of the vehicle control system via a mechanical linkage, wherein at least one first force generating device and at least one second force generating device are mechanically connected to the inceptor, the first force generating device being provided for generating a nominal force acting in operation on the inceptor and the second force generating device being provided for generating a tactile cue force acting in operation on the inceptor, the first and second force generating devices being arranged in parallel. The invention relates further to an aircraft comprising such an artificial force feel generating device.

An aircrew automation system relates to the field of flight control systems, methods, and apparatuses; even more particularly, to a system, method, and apparatus for providing aircraft state monitoring and/or an automated aircrew employing a robotic arm with integrated imaging and force sensing modalities.