An aircraft capable of carrying at least 400 pounds of payload, has four rotors systems, each of the rotor systems being independently driven by an electric motor or other torque-producing source. Each of the rotor systems provide sufficient thrust such that the aircraft is capable of controlled vertical takeoff and landing, even if one of the variable pitch rotor is inoperable. An electronic control system is configured to control the rotational speed and pitch of at least one of the rotor systems in each of the first and second rotor pairs. The rotors may be arranged in coaxial stacks or maybe otherwise configured.

A double-ring rotary wing spherical cabin aircraft includes a spherical cabin; an upper protective cover; a lower protective cover; a rotary wing fixing ring connected between inner circles of the upper and lower protective covers, and mounted with a gyroscope and a rotatable attitude-adjusting ring; an upper rotary wing rotor and a lower rotary wing rotor rotationally mounted on the rotary wing fixing ring; and a control system. The spherical cabin is rotationally mounted in the attitude-adjusting ring. Two attitude-adjusting articulated shafts opposite to each other are connected between the attitude-adjusting ring and the rotary wing fixing ring. Two cabin articulated shafts opposite to each other are connected between the spherical cabin and the attitude-adjusting ring. The attitude-adjusting articulated shaft and the cabin articulated shaft are in transmission connection with an attitude-adjusting motor. The attitude-adjusting motor and the gyroscope are electrically connected to the control system.

A double-ring rotary wing spherical cabin aircraft includes a spherical cabin; an upper protective cover; a lower protective cover; a rotary wing fixing ring connected between inner circles of the upper and lower protective covers, and mounted with a gyroscope and a rotatable attitude-adjusting ring; an upper rotary wing rotor and a lower rotary wing rotor rotationally mounted on the rotary wing fixing ring; and a control system. The spherical cabin is rotationally mounted in the attitude-adjusting ring. Two attitude-adjusting articulated shafts opposite to each other are connected between the attitude-adjusting ring and the rotary wing fixing ring. Two cabin articulated shafts opposite to each other are connected between the spherical cabin and the attitude-adjusting ring. The attitude-adjusting articulated shaft and the cabin articulated shaft are in transmission connection with an attitude-adjusting motor. The attitude-adjusting motor and the gyroscope are electrically connected to the control system.

In an aspect of the present disclosure is an electric aircraft lift motor with air cooling, the motor including a stator connected to the electric aircraft, the stator including: an inner cylindrical surface and an outer cylindrical surface, wherein each of the inner cylindrical surface and the outer cylindrical surface is coaxial about an axis of rotation; and a rotor coaxial within the stator, the rotor including a rotor cylindrical surface, wherein the rotor cylindrical surface and the inner cylindrical surface combine to form an air gap between the rotor cylindrical surface and the inner cylindrical surface; and a first fan connected to an axial end of the rotor and configured to rotate with the rotor, the first fan comprising at least a blade configured to direct air toward the air gap.

In an aspect of the present disclosure is an electric aircraft lift motor with air cooling, the motor including a stator connected to the electric aircraft, the stator including: an inner cylindrical surface and an outer cylindrical surface, wherein each of the inner cylindrical surface and the outer cylindrical surface is coaxial about an axis of rotation; and a rotor coaxial within the stator, the rotor including a rotor cylindrical surface, wherein the rotor cylindrical surface and the inner cylindrical surface combine to form an air gap between the rotor cylindrical surface and the inner cylindrical surface; and a first fan connected to an axial end of the rotor and configured to rotate with the rotor, the first fan comprising at least a blade configured to direct air toward the air gap.

The invention relates to a nubomachine with a longitudinal axis, comprising two, respectively upstream (122) and downstream, coaxial outer propellers (122), characterised in that at least some of the blades (148) of the upstream propeller (122) comprise at least one internal air circulation chimney (150) that communicates with air-bleeding openings (152) in tire boundary layers of the blades (148), and communicates with air outflow openings (158) on the radially outer end thereof, the air-bleeding openings (152) leading to opening inlets (152a) on tire passive surfaces (156) of the blades (148), the inlets (152a) of the air-bleeding openings being radially arranged in an area (H1) contained between 10% and 45% of the radial dimension (H2) of the blades (148), measured above turd from the radial height of the blades for which the tangent of the leading edge (138) of the blades is orthogonal to the longitudinal axis, and the inlets (152a) of the air bleeding openings being arranged in an area contained between 0% and 30% of the local chord of the blades (148), measured at the level of said inlets (152a) and from the leading edges (138) of tire blades (148).

An unmanned rotorcraft includes an airframe, rotor blades that are coupled to the airframe for rotation therewith, a propulsion unit having a propeller, and an actuator that is coupled to the airframe and adapted to temporarily reorient the propulsion unit such that an axis of the propeller moves out of alignment with an axis of the rotor blades. Rotation of the propeller causes counter-rotation of the airframe and rotor blades. The rotor blades and blades of the propeller are adapted to deploy from collapsed positions when flight of the rotorcraft is initiated. A method of operation by the rotorcraft includes, when it is determined that a current heading does not correspond to a determined flight path, causing the actuator to temporarily reorient the propulsion unit in accordance with an angular orientation of the actuator relative to the current heading.

A VTOL (vertical take-off and landing) box-wing aerial vehicle with multirotor to provide VTOL flight includes a detachable cabin, centered fuselage, a pair of first wings extending outward from the upper portion of the fuselage and a pair of second wings extending outwardly and from the lower portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joints the first wing and second wing at the tip to form the box-wing. The pylon includes heading control rudder. Secured to the wing or pylon or both wing and pylon, an overhead boom extending longitudinally to support a plurality of lift rotors or tiltable rotors for VTOL flight. Finally, the fuselage mounted push rotor or the overhead boom mounted tiltable rotors propel the vehicle forward to generate lift from the wings. Furthermore, the wings are equipped with elevators and ailerons for flight control.

A VTOL (vertical take-off and landing) box-wing aerial vehicle with multirotor to provide VTOL flight includes a detachable cabin, centered fuselage, a pair of first wings extending outward from the upper portion of the fuselage and a pair of second wings extending outwardly and from the lower portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joints the first wing and second wing at the tip to form the box-wing. The pylon includes heading control rudder. Secured to the wing or pylon or both wing and pylon, an overhead boom extending longitudinally to support a plurality of lift rotors or tiltable rotors for VTOL flight. Finally, the fuselage mounted push rotor or the overhead boom mounted tiltable rotors propel the vehicle forward to generate lift from the wings. Furthermore, the wings are equipped with elevators and ailerons for flight control.

An intentional fluid manipulation apparatus (IFMA) assembly with a first thrust apparatus that imparts a first induced velocity to a local free stream flow during a nominal operation requirement. The first thrust apparatus creates a streamtube. A second thrust apparatus is located in a downstream portion of the streamtube. The second thrust apparatus imparts a second induced velocity to the local free stream flow. The second induced velocity at the location of the second thrust apparatus has a component in a direction opposite to the direction of the first induced velocity at the location of the second thrust apparatus.