Abstract: The present invention relates to a body (2) on an air vehicle; at least one engine (3) that provides a required power for the flight of the body (2); at least one rotor (4) connected to the engine (3) and enabling blades of the air vehicle to rotate; at least one shaft (5) that transmits the movement of the engine (3) to the rotor (4); at least a first transfer element (6) located on the shaft (5); at least a first spindle (7) transmitting the engine (3) drive to the propulsion system (P) and/or anti-torque system (T) that provide movement of the air vehicle; a first spindle element (8) located on the first spindle (7) and allowing the movement of the first spindle (7); an intermediate transfer element (9) that transmits the engine (3) drive from the first transfer element (6) to the first spindle element (8) and rotor (4).

Abstract: The present invention relates to a body (2) on the air vehicle; at least one motor (3) which provides required power for the flight of the body (2); at least one rotor (4) extending outward from the body (2), connected to the motor (3), and rotating around itself; a plurality of blades (5) located on the rotor (4); a helicopter mode (H) in which the body (2) performs tasks such as vertical landing and take-off, autorotation and hovering; an anti-torque system (6) on the body (2), which creates anti-torque when the body (2) is in helicopter mode (H); an airplane mode (A) in which the rotor (4) is stopped and the blades (5) are used as fixed wings; at least one propulsion system (7) that provides thrust for the movement of the body (2) when the body (2) is in airplane mode (A); a transition mode (T) in which the rotor (4) is stopped and the propulsion system (7) is activated while the body (2) is switched from helicopter mode (H) to airplane mode (A); at least one canard (8) located in the nose area of the body

Abstract: The present invention relates to a body (2) on an air vehicle; at least one engine (3) that provides a required power for the flight of the body (2); at least one rotor (4) connected to the engine (3) and enabling blades of the air vehicle to rotate; at least one shaft (5) that transmits the movement of the engine (3) to the rotor (4); at least a first transfer element (6) located on the shaft (5); at least a first spindle (7) transmitting the engine (3) drive to the propulsion system (P) and/or anti-torque system (T) that provide movement of the air vehicle; a first spindle element (8) located on the first spindle (7) and allowing the movement of the first spindle (7); an intermediate transfer element (9) that transmits the engine (3) drive from the first transfer element (6) to the first spindle element (8) and rotor (4).

Abstract: 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)

Abstract: An air vehicle has a body, more than one wing located on the body creating a lifting force, at least one control surface located on the wing and movable along the direction in which the wing extends, an open position in which the control surface moves out of the wing in the direction in which the wing extends and increases the lifting force acting on the body, a closed position in which the control surface is moved from the open position and brought to the wing, a main actuator moving the control surface between the open and closed positions, at least one shaft enabling the control surface to be moved with the triggering of the main actuator and having one end connected to the control surface, and at least one additional actuator enabling the attack angle of the wings to be changed by rotating the wings on the body.

Abstract: A rotary wing air vehicle has a body; at least one engine located on the body; a rotor that extends outwards from the body and rotates around its own axis in connection with the engine; at least one shaft extending outward from the rotor and triggered by the engine to rotate around an axis that the shaft extends from the rotor; at least two blades connected with the shaft and triggered by the shaft to move; at least one flap on the blade which provides drag force to the rotor by its movement to a closed position or an open position; at least one brake system which is located on the body in connection with the rotor to enable the flap to move to the closed position and/or open position so that a rotational speed of the rotor is adjusted by a user.

Abstract: An air vehicle has a body, more than one wing located on the body creating a lifting force, at least one control surface located on the wing and movable along the direction in which the wing extends, an open position in which the control surface moves out of the wing in the direction in which the wing extends and increases the lifting force acting on the body, a closed position in which the control surface is moved from the open position and brought to the wing, a main actuator moving the control surface between the open and closed positions, at least one shaft enabling the control surface to be moved with the triggering of the main actuator and having one end connected to the control surface, and at least one additional actuator enabling the attack angle of the wings to be changed by rotating the wings on the body.

Abstract: A rotary wing air vehicle has a body; at least one engine located on the body; a rotor that extends outwards from the body and rotates around its own axis in connection with the engine; at least one shaft extending outward from the rotor and triggered by the engine to rotate around an axis that the shaft extends from the rotor; at least two blades connected with the shaft and triggered by the shaft to move; at least one flap on the blade which provides drag force to the rotor by its movement to a closed position or an open position; at least one brake system which is located on the body in connection with the rotor to enable the flap to move to the closed position and/or open position so that a rotational speed of the rotor is adjusted by a user.