A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

The invention relates to a vector control for an aerial vehicle drive wherein a rotor shaft (16) which is suspended from a frame (19) via a. pivot bearing (18). A rotor (14) is mounted rotatably relative to the rotor shalt (16). A motor (20) is configured to set the rotor (14) in rotation. An actuator (21, 22) which extends between the frame (19) and the rotor shaft (.16) is configured to change the orientation of the rotor shaft (16). The invention also concerns a method for controlling a helicopter drive.

The invention relates to a vector control for an aerial vehicle drive wherein a rotor shaft (16) which is suspended from a frame (19) via a. pivot bearing (18). A rotor (14) is mounted rotatably relative to the rotor shalt (16). A motor (20) is configured to set the rotor (14) in rotation. An actuator (21, 22) which extends between the frame (19) and the rotor shaft (.16) is configured to change the orientation of the rotor shaft (16). The invention also concerns a method for controlling a helicopter drive.

According to one embodiment, linear motor translator assembly for use in an electromagnetic actuator is provided. The linear motor translator assembly comprises: a cylindrical housing having a first end, a second end opposite the first end, a flanged portion at the second end, and a blind hole initiating at the second end and extending into the cylindrical housing to a blind hole base; a tubular body located within the blind hole, the tubular body including a plurality of permanent magnets; and an end cap securely fastened to the flanged portion.

A rocket or ballistic launch rotary wing air vehicle may include a rocket or ballistic launch propulsion system for launching the vehicle, a rotary wing flight system for providing powered flight comprising dual counter rotating coaxial rotors, and a control system programmed to adjust the pitch of a rotor to anyh determined degree of pitch independently of a flap angle of the flap hinge during a transition of the dual counter rotating coaxial rotors from a stowed position to a deployed position.

A rocket or ballistic launch rotary wing air vehicle may include a rocket or ballistic launch propulsion system for launching the vehicle, a rotary wing flight system for providing powered flight comprising dual counter rotating coaxial rotors, and a control system programmed to adjust the pitch of a rotor to anyh determined degree of pitch independently of a flap angle of the flap hinge during a transition of the dual counter rotating coaxial rotors from a stowed position to a deployed position.

An unmanned aerial vehicle includes a propulsion system having at least one propulsion module comprised of at least one propeller and at least two motors/engines, one or more of the motors/engines providing mechanical energy to drive the propeller, wherein the difference between the angular velocities of the motors/engines provides energy input to a mechanical or magneto-mechanical linkage system to change the blade pitch angle of the propeller, in cyclic and/or collective manner.

An unmanned aerial vehicle includes a propulsion system having at least one propulsion module comprised of at least one propeller and at least two motors/engines, one or more of the motors/engines providing mechanical energy to drive the propeller, wherein the difference between the angular velocities of the motors/engines provides energy input to a mechanical or magneto-mechanical linkage system to change the blade pitch angle of the propeller, in cyclic and/or collective manner.

A component of a laminated bearing assembly is for movably coupling an inner member and an outer member, the inner member having a central axis and the outer member having a bore. The component includes a laminated body disposeable within the outer member bore and having an inner radial end connectable with the inner member and an outer radial end connectable with the outer member. The body is formed of a plurality of alternating, generally arcuate elastomeric and metallic laminae nested generally about the central axis, each one of the elastomeric and metallic laminae having opposing first and second arcuate ends and inner and outer circumferential surfaces extending circumferentially between the first and second arcuate ends. Each metallic lamina has a radial thickness varying circumferentially between a first value at the first, radially-widest arcuate end and a second, lesser value at the second, radially-narrowest arcuate end.

An anti-torque rotor of a helicopter, having: a supporting body; a drive shaft which rotates about a first axis with respect to the supporting body; a hub connected operatively to drive shaft and angularly fixed with respect to first axis; at least one blade which is connected operatively to hub, is angularly fixed with respect to first axis, and is angularly movable with respect to a second axis to adjust the pitch angle of blade; and an actuator which can be operated to rotate blade about second axis to adjust the pitch angle of blade; actuator has an electric motor which generates torque along the first axis; and a mechanical stage interposed between the electric motor and blade, and designed to convert the torque into rotation of blade about the respective second axes; electric motor is fixed to supporting body.