A coupling is disclosed for connecting a propeller to a motor in an aircraft such as a rotary wing aircraft and the like. The coupling comprises a propeller hub having an inner propeller hub bore defining an axial keyway. A rotatable shaft has an internal shaft bore connected for rotation with the motor. A radial key is slidably located in a radial aperture extending through the rotatable shaft. An actuator is slidably mounted within the internal shaft bore of the rotatable shaft. The radial key is received with the axial keyway for securing the propeller hub to the rotatable shaft. A depression of the actuator retracting the radial key relative to an outer surface of the rotatable shaft for permitting the propeller hub bore to be introduced onto the rotatable shaft.

A coupling is disclosed for connecting a propeller to a motor in an aircraft such as a rotary wing aircraft and the like. The coupling comprises a propeller hub having an inner propeller hub bore defining an axial keyway. A rotatable shaft has an internal shaft bore connected for rotation with the motor. A radial key is slidably located in a radial aperture extending through the rotatable shaft. An actuator is slidably mounted within the internal shaft bore of the rotatable shaft. The radial key is received with the axial keyway for securing the propeller hub to the rotatable shaft. A depression of the actuator retracting the radial key relative to an outer surface of the rotatable shaft for permitting the propeller hub bore to be introduced onto the rotatable shaft.

A gas turbine engine for an aircraft, includes: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan assembly located upstream of the engine core; and a gearbox receiving an input from the core shaft and outputs drive to the fan assembly so as to drive the fan assembly at a lower rotational speed than the core shaft, wherein the fan assembly has fan blades mounted around a hub, the fan blades having blade tips defining an outer diameter of the fan assembly of from around 220 cm to around 400 cm, the hub having slots located around a rim of the hub, each slot receiving a root of a corresponding fan blade, wherein a ratio of a mass of the hub to a total mass of the fan blades is within the range of around 0.45 to around 0.7.

A gas turbine engine for an aircraft, includes: an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan assembly located upstream of the engine core; and a gearbox receiving an input from the core shaft and outputs drive to the fan assembly so as to drive the fan assembly at a lower rotational speed than the core shaft, wherein the fan assembly has fan blades mounted around a hub, the fan blades having blade tips defining an outer diameter of the fan assembly of from around 220 cm to around 400 cm, the hub having slots located around a rim of the hub, each slot receiving a root of a corresponding fan blade, wherein a ratio of a mass of the hub to a total mass of the fan blades is within the range of around 0.45 to around 0.7.

An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight. An aerial vehicle able to quickly alter its thrust. A quick reaction propeller system which alters the pitch of the propeller blades in response to changes in coning angle of the propeller.

An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight. An aerial vehicle able to quickly alter its thrust. A quick reaction propeller system which alters the pitch of the propeller blades in response to changes in coning angle of the propeller.

A detachable propeller holder device includes a propeller holder module, a fixed seat and a motor module. Paddles are located the propeller holder module, a buckling component is located on the propeller holder module, the buckling component includes two elastic arms and two hooks, the two elastic arms are symmetrically located at two sides of the propeller holder module, the hooks are respectively located at an end of the two elastic arms and are respectively buckled with two limit portions which are symmetrically located at the fixed seat, so as to fix the propeller holder module to the fixed seat. In the detachable propeller holder device, only the buckling component at the side of the propeller holder module is pinched by fingers to deform inwardly till the hooks are detached from the limit portions of the fixed seat, and then the propeller holder module is pulled upwardly to be removed.

A detachable propeller holder device includes a propeller holder module, a fixed seat and a motor module. Paddles are located the propeller holder module, a buckling component is located on the propeller holder module, the buckling component includes two elastic arms and two hooks, the two elastic arms are symmetrically located at two sides of the propeller holder module, the hooks are respectively located at an end of the two elastic arms and are respectively buckled with two limit portions which are symmetrically located at the fixed seat, so as to fix the propeller holder module to the fixed seat. In the detachable propeller holder device, only the buckling component at the side of the propeller holder module is pinched by fingers to deform inwardly till the hooks are detached from the limit portions of the fixed seat, and then the propeller holder module is pulled upwardly to be removed.

Disclosed is a propeller having at least first and second blade assemblies located one above the other. Each of the blade assemblies has a plurality of blades that extend radially outward from a shaft. The shaft can be coupled to a suitable land, sea or air vehicle (e.g., a ship). The blades of the first blade assembly lie above and alternate out of phase with the blades of the second blade assembly. Each of the blades of the first and second blade assemblies slopes downwardly relative to the shaft such that the leading sides thereof are located lower along the shaft than the opposite trailing sides. The blades of the first blade assembly are aligned with respective ones of the blades of the second blade assembly to establish substantially continuous and long downwardly sloping surface areas capable of maximizing the propulsion force generated by the propeller.

Disclosed is a propeller having at least first and second blade assemblies located one above the other. Each of the blade assemblies has a plurality of blades that extend radially outward from a shaft. The shaft can be coupled to a suitable land, sea or air vehicle (e.g., a ship). The blades of the first blade assembly lie above and alternate out of phase with the blades of the second blade assembly. Each of the blades of the first and second blade assemblies slopes downwardly relative to the shaft such that the leading sides thereof are located lower along the shaft than the opposite trailing sides. The blades of the first blade assembly are aligned with respective ones of the blades of the second blade assembly to establish substantially continuous and long downwardly sloping surface areas capable of maximizing the propulsion force generated by the propeller.