Rotor assembly apparatus are disclosed. An example rotor assembly includes a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the rotor assembly. A first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts. Each of the second shafts to provide torque to a respective blade coupled to the rotor assembly.

Rotor assembly apparatus are disclosed. An example rotor assembly includes a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the rotor assembly; and a first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts, each of the second shafts to provide torque to a respective blade coupled to the rotor assembly.

An edge morphing arrangement for an airfoil having upper and lower control surfaces is provided with an elongated edge portion that overlies the edge of the airfoil, the edge portion having a surface element having first and second edges that communicate with, and form extensions of, respective ones of the upper and lower control surfaces of the elongated airfoil. The surface elements are formed of deformable compliant material that extends cross-sectionally from the first surface element edge to an apex of the edge portion, and to the second surface element edge. There is additionally provided a driving link having first and second driving link ends, the first driving link end being coupled to the interior of one of the first and second rib portions. The second end is arranged to receive a morphing force, and the rib element is deformed in response to the morphing force.

A rotor blade system having a plurality of rotor blades, wherein at least one of the rotor blades includes an outer surface having generally opposing first and second surfaces, the rotor blade including a fluid flow altering surface positioned relative to one of the first or second surfaces which is moveable between first and second positions, wherein movement of the fluid flow altering surface is effected by an expandable member.

An edge morphing arrangement for an airfoil having upper and lower control surfaces is provided with an elongated edge portion that overlies the edge of the airfoil, the edge portion having a surface element having first and second edges that communicate with, and form extensions of, respective ones of the upper and lower control surfaces of the elongated airfoil. The surface elements are formed of deformable compliant material that extends cross-sectionally from the first surface element edge to an apex of the edge portion, and to the second surface element edge. There is additionally provided a driving link having first and second driving link ends, the first driving link end being coupled to the interior of one of the first and second rib portions. The second end is arranged to receive a morphing force, and the rib element is deformed in response to the morphing force.

An aerofoil has a main portion of aerofoil cross section and a trailing edge portion (12) movable with respect to the main portion by an actuating device (14), the trailing edge portion (12) is movable at or about an area/point of flexion A, the area/point of flexion A is located at or adjacent a pressure or suction surface of the aerofoil, the trailing edge portion (12) is connected to the main portion by first and second connection members (18, 20), the first connection member (18) extends inwardly away from the area/point of flexion A and has an end which is directly or indirectly connected to the main portion, the first and second connection members (18, 20) are flexible.

A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a hub and a rotor blade connected to the hub to extend radially away therefrom. The rotor blade may include biasing fibers, oriented to increase the twist of the rotor blade in response to an increase in the speed of rotation of the rotor corresponding to a mission, task, or maneuver.

The invention relates to a device comprising an asymmetrical wing profile (2) and an adjusting device (15), which asymmetrical wing profile (2) has a profile thickness (q) and a profile chord (p) extending between a wing leading edge (n) and a wing trailing edge (e), which asymmetrical wing profile (2) has, in at least one longitudinal portion (L1-Ln), a three-part variable wing profile (21) in which a front and a rear wing segment (211, 213) are joined to a central wing segment (212) in an articulated manner by means of two hinges (214) having axes of rotation (z) and are designed to permit a rotational movement about the associated axis of rotation (z) with respect to the central wing segment (212).