A fitting for securing a rotor blade in pivotable engagement with a yoke that is coupled to a mast of an aircraft for rotation therewith about a mast axis has a body that extends from an inboard end to an outboard end. The body of the fitting has an opening that extends into the body from the outboard end and that is adapted to receive a root end of the blade. The body further has a first bearing race that is defined along an outer surface of the body and is located between the inboard and outboard ends. The body further has an array of apertures that is located between the inboard end and the first bearing race, each aperture adapted to receive a respective fastener for retaining the blade within the opening.

An aerial vehicle and a method of taking a measurement using a sensor mounted on an aerial vehicle. The aerial vehicle has one or more propellers and one car more motors which are selectively operable to drive the one or more propellers to rotate to cause the vehicle to fly. A sensor is mounted on the aerial vehicle. The method includes operating the one or more motors to drive the one or more propellers to cause the vehicle to fly. At a first time instant, the one or more motors are slowed down or turned off. When the one or more motors are slowed down or turned off, a measurement is taken using the sensor; at a second time instant, which is after the measurement has been taken using sensor, operating the one or more motors again to drive the one or more propellers to cause the vehicle to fly.

An aerial vehicle and a method of taking a measurement using a sensor mounted on an aerial vehicle. The aerial vehicle has one or more propellers and one car more motors which are selectively operable to drive the one or more propellers to rotate to cause the vehicle to fly. A sensor is mounted on the aerial vehicle. The method includes operating the one or more motors to drive the one or more propellers to cause the vehicle to fly. At a first time instant, the one or more motors are slowed down or turned off. When the one or more motors are slowed down or turned off, a measurement is taken using the sensor; at a second time instant, which is after the measurement has been taken using sensor, operating the one or more motors again to drive the one or more propellers to cause the vehicle to fly.

A flying apparatus includes a main structure and a rotative wing surface, the rotation of the wing surface allowing stabilizing the apparatus (100). A fuselage hangs from the wing surface around a hanging point, allowing the wing surface and the fuselage be moveable independently with respect to each other and the wing surface is configured as a disc to manoeuvre the apparatus and including one or more elements acting as security and secondary command and control surfaces, orienting the apparatus in desired directions. The main structure and wing surface can overwrap at least partially the the fuselage in order to improve the aerodynamic performance. The airframe or fuselage and the wing surface are rotatable around any of three rotational axes independently.

Systems, methods, lift fans, and aircraft involving active flow control of a ducted fan or fan-in-wing configuration are described.

An electric vacuum jet engine is a more ecofriendly alternative to gas-fueled jet engines that generates the same or higher thrust than traditional gas-fueled jet engines. The jet engine includes a tubular housing, at least one first propeller assembly, and at least one second propeller assembly. The tubular housing accommodates an alternating of series of propeller assemblies formed by the at least one first propeller assembly and the at least one second propeller assembly. Together, the at least one first propeller assembly and the at least one second propeller assembly generate several vacuums along the tubular housing that increase the velocity of air flow through the tubular housing to generate the thrust necessary to propel the desired aircraft. The tubular housing also includes a housing inlet and a housing outlet corresponding to the open ends of the tubular housing through which air flow enters and exits the tubular housing, respectively.

A propulsive assembly, in particular for an aircraft, comprising a mast and a propulsion device comprising an engine and a nacelle, the engine comprising a propeller, the propulsive assembly comprising: A standby protection device comprising a first connecting member fixedly mounted to the mast and a second connecting member fixedly mounted to the propulsion device, the second connecting member being rotatably hinged with respect to the first connecting member in at least one degree of freedom, and at least one retaining member keeping the second connecting member fixed with respect to the first connecting member, and configured, in the presence of a predetermined unbalance force on the propeller, to release the standby protection device in order to protect the mast.

A propulsive assembly, in particular for an aircraft, comprising a mast and a propulsion device comprising an engine and a nacelle, the engine comprising a propeller, the propulsive assembly comprising: A standby protection device comprising a first connecting member fixedly mounted to the mast and a second connecting member fixedly mounted to the propulsion device, the second connecting member being rotatably hinged with respect to the first connecting member in at least one degree of freedom, and at least one retaining member keeping the second connecting member fixed with respect to the first connecting member, and configured, in the presence of a predetermined unbalance force on the propeller, to release the standby protection device in order to protect the mast.

A propulsor fan array having reduced noise emission is disclosed. The propulsor fan array includes a plurality of propulsor fans that collectively generate thrust. Each of the propulsor fans include a blade fan having a plurality of blades. The plurality of blades are tensioned at tips of the plurality of blade fans such that a pitch of the blades during thrust generation is substantially the same as a pitch of the blades at rest. By tensioning the tips of the blades, an angle of the blades is maintained during operation of the propulsor fan thereby reducing noise that may result from changes in the angle of the blades.

A hybrid air mobility system is capable of flying a long distance through effective operation of an engine and batteries. The hybrid air mobility system includes a fuselage configured to supply power to a propeller and electric equipment, the fuselage being provided with a duct including an inlet and an outlet so as to circulate air to the engine and the electric equipment; a deflector rotatably installed at the outlet of the duct so as to convert a discharge direction of exhaust gas generated by the engine and cooling air after cooling the electric equipment; and a controller configured to determine whether or not the engine is driven and to control a rotated position of the deflector depending on an amount of driving of the engine so as to selectively adjust movement of the exhaust gas and the cooling air towards the propeller.