A propeller blade arrangement comprising a propeller blade attached to and rotatable with a hub, via a retention bearing, the blade being rotatable about a center line of the blade, the retention bearing configured to tilt the blade such that its center line is tilted with respect to the hub.

Disclosed is a personal flying machine using compressed air as power source, and an operation method thereof, the flying machine including a stationary rotor lift device in a cyclone duct, a seat frame and a compressed air supply device; wherein the stationary rotor lift device in a cyclone duct includes a cyclone duct, in-duct stationary rotors and in-duct compressed air artificial wind blowing ports; wherein the in-duct stationary rotor includes a stationary propeller hub and a plurality of stationary blades fixed connected around the stationary propeller hub and arranged radially; wherein the stationary blade is shaped as an airplane's wing having an airfoil, an angle of attack, a leading edge and a trailing edge; wherein the compressed-air supply device supplies compressed air to the in-duct compressed-air artificial wind blowing ports to eject airflows towards the leading edges of the stationary blades and form a cyclone to generate lift. The present application solves the problems of efficiency limitation, high cost, heavy structure and energy-environment issues related to the traditional personal flying machines of burning fossil fuels to do work, and overcomes their shortcomings and problems with the wingless or wing-movement to generate lift in relatively static air.

Disclosed is a personal flying machine using compressed air as power source, and an operation method thereof, the flying machine including a stationary rotor lift device in a cyclone duct, a seat frame and a compressed air supply device; wherein the stationary rotor lift device in a cyclone duct includes a cyclone duct, in-duct stationary rotors and in-duct compressed air artificial wind blowing ports; wherein the in-duct stationary rotor includes a stationary propeller hub and a plurality of stationary blades fixed connected around the stationary propeller hub and arranged radially; wherein the stationary blade is shaped as an airplane's wing having an airfoil, an angle of attack, a leading edge and a trailing edge; wherein the compressed-air supply device supplies compressed air to the in-duct compressed-air artificial wind blowing ports to eject airflows towards the leading edges of the stationary blades and form a cyclone to generate lift. The present application solves the problems of efficiency limitation, high cost, heavy structure and energy-environment issues related to the traditional personal flying machines of burning fossil fuels to do work, and overcomes their shortcomings and problems with the wingless or wing-movement to generate lift in relatively static air.

This invention is an aircraft of the type known as a “Convertiplane” which can conduct vertical flight operations in the manner of a rotor-wing aircraft and conduct cruise flight operations in the manner of a fixed-wing aircraft. This aircraft has rotor blades mounted on each wingtip and tilting propulsors mounted at the tips of the horizontal stabilizers on the aircraft tail. The wingtip mounted rotor blades and vertically oriented tail propulsors provide thrust for vertical takeoff. To transition to cruise flight, at sufficient airspeed, the wingtip rotors are stopped and moved from the rotor-wing position to a “V” configuration extending out from the wingtips to function as ailerons, while the tail mounted propulsors are tilted forward from a vertical to a horizontal orientation to provide thrust for forward flight

This invention is an aircraft of the type known as a “Convertiplane” which can conduct vertical flight operations in the manner of a rotor-wing aircraft and conduct cruise flight operations in the manner of a fixed-wing aircraft. This aircraft has rotor blades mounted on each wingtip and tilting propulsors mounted at the tips of the horizontal stabilizers on the aircraft tail. The wingtip mounted rotor blades and vertically oriented tail propulsors provide thrust for vertical takeoff. To transition to cruise flight, at sufficient airspeed, the wingtip rotors are stopped and moved from the rotor-wing position to a “V” configuration extending out from the wingtips to function as ailerons, while the tail mounted propulsors are tilted forward from a vertical to a horizontal orientation to provide thrust for forward flight

A composite yoke includes a plurality of packs of unidirectional plies and at least one pack of chopped fibers disposed between two adjacent packs of unidirectional plies. A method of manufacturing a composite yoke includes arranging a plurality of plies of unidirectional fibers to form a first pack of unidirectional plies, arranging a layer of chopped fibers on the first pack of unidirectional plies, arranging a plurality of plies of unidirectional fibers on to form a second pack of unidirectional plies on the layer of chopped fibers, curing the composite yoke to form a cured composite yoke, and cutting excess material from the first pack of unidirectional plies, the layer of chopped fibers, and the second pack of unidirectional plies to form a plurality of arms.

An improved efficiency propeller for aircraft includes a blade structure mounted onto a propeller hub, a servo unit, and a cantilevered base. A distinctive feature of the invention is that the blade structure includes a main mast, which is mounted onto a propeller hub and forms the spine of the leading edge of the blade structure, and at least one secondary mast aligned with the main mast, and turning spacers with struts fitted with a strut are mounted onto the main mast, and the struts are covered by lateral pieces of a skin module, and the overlapping and flexible lateral piece of the skin module form a skin.

A rotor-wing assembly includes a motor, a propeller, and a connection assembly connecting the propeller to the motor. The motor includes a rotating portion. The connection assembly includes a locking member and a reinforcing member arranged between the propeller and the motor. The locking member locks the propeller to the rotating portion. A first end of the reinforcing member is mounted at the rotating portion. A second end of the reinforcing member opposite to the first end is engaged with the locking member, to reinforce the locking member to lock the propeller to the rotating portion.

A rotor-wing assembly includes a motor, a propeller, and a connection assembly connecting the propeller to the motor. The motor includes a rotating portion. The connection assembly includes a locking member and a reinforcing member arranged between the propeller and the motor. The locking member locks the propeller to the rotating portion. A first end of the reinforcing member is mounted at the rotating portion. A second end of the reinforcing member opposite to the first end is engaged with the locking member, to reinforce the locking member to lock the propeller to the rotating portion.

The invention relates to a test stand comprising a support (19, 25) which is moveably connected to a wall (18, 18′, 18″), a base, a frame (26) of the test stand or another part of the test stand and can be moved on a predetermined path; an actuator (22) which is connected to the support and by means of which the support (19, 25) that can be moved on the predetermined path, two clamping devices (13) respectively comprising a ball joint, wherein one of the two clamping devices (13) is seemed to the support (19, 25) and the other of the two clamping devices (13) is arranged in an axis (10) with the first of the two clamping devices (13), such that a test body (1) is clamped between the two clamping devices (13) on outer surfaces of the test body and can be maintained by the clamping devices (13), and a test force exerted by a test body by moving the support (19, 25) through the first of the two clamping devices (13) acts essentially along the axis (10). The test body is fixed by means of an elastic element (23) in order to limit a rotation of the test body about the axis (10).