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 aircraft comprising an airframe; a rotor system mounted to the airframe, the rotor system including a plurality of rotor blades, each of the plurality of rotor blades including a root portion extending to a tip portion through an airfoil portion, the airfoil portion having a leading edge and a trailing edge; at least one control surface mounted within the airfoil portion of at least one of the plurality of rotor blades; at least one actuator configured to actuate the at least one control surface; and at least one actuator configured to pitch at least one of the plurality of rotor blades about a blade pitch axis.

An aircraft comprising an airframe; a rotor system mounted to the airframe, the rotor system including a plurality of rotor blades, each of the plurality of rotor blades including a root portion extending to a tip portion through an airfoil portion, the airfoil portion having a leading edge and a trailing edge; at least one control surface mounted within the airfoil portion of at least one of the plurality of rotor blades; at least one actuator configured to actuate the at least one control surface; and at least one actuator configured to pitch at least one of the plurality of rotor blades about a blade pitch axis.

An improved actuator arrangement for operating a driven element with different actuators. The actuator arrangement comprises a first actuator that drives a driven element in a first direction via a first output member and a second actuator that drives the driven element in a second direction opposite to the first direction via a second output member. The first and second actuators are configured to work in a counter-acting manner to move the driven element in the first and second directions. An additional connecting and supporting device is connected between the first and second output members to support the output members to bear transversal forces transversal to the moving direction and/or to bear pre-load force for pre-loading the actuators.

An improved actuator arrangement for operating a driven element with different actuators. The actuator arrangement comprises a first actuator that drives a driven element in a first direction via a first output member and a second actuator that drives the driven element in a second direction opposite to the first direction via a second output member. The first and second actuators are configured to work in a counter-acting manner to move the driven element in the first and second directions. An additional connecting and supporting device is connected between the first and second output members to support the output members to bear transversal forces transversal to the moving direction and/or to bear pre-load force for pre-loading the actuators.

The present invention relates to a body (2); at least one engine (3) on the body (2), which generates the necessary force for the flight of the air vehicle (1); at least one rotor (4) capable of rotating around itself, connected with the engine (3), and extending outward from the body (2); at least one shaft (5) in the rotor (4), which is triggered by the engine (3) and rotates around an axis along which it extends; a plurality of blades (6) connected with the shaft (5), which are triggered by the shaft (5) to move; at least one flap (7) located on the blade (6) and applying a drag force to the rotor due to its position on the blade; a closed position (C) in which the flap (7) almost completely corresponds to the aerodynamic surface of the blade (6); an open position (O) to which the flap (7) moves from the closed position (C) and in which the flap (7) extends outward from the blade (6) and increases the drag force acting on the rotor (4); a plurality of fasteners (8) in the blade (6) that allow the flaps (7) to be attached to the blade (6) movably.

The present invention relates to a body (2); at least one engine (3) on the body (2), which generates the necessary force for the flight of the air vehicle (1); at least one rotor (4) capable of rotating around itself, connected with the engine (3), and extending outward from the body (2); at least one shaft (5) in the rotor (4), which is triggered by the engine (3) and rotates around an axis along which it extends; a plurality of blades (6) connected with the shaft (5), which are triggered by the shaft (5) to move; at least one flap (7) located on the blade (6) and applying a drag force to the rotor due to its position on the blade; a closed position (C) in which the flap (7) almost completely corresponds to the aerodynamic surface of the blade (6); an open position (O) to which the flap (7) moves from the closed position (C) and in which the flap (7) extends outward from the blade (6) and increases the drag force acting on the rotor (4); a plurality of fasteners (8) in the blade (6) that allow the flaps (7) to be attached to the blade (6) movably.