An aerial vehicle is includes a wing, first and second rotors, and a movement sensor. The first and second multicopter rotors are rotatably coupled to the wing, the first multicopter rotor is rotatable relative to the wing about a first lateral axis, and the second multicopter rotor is rotatable relative to the wing about a second lateral axis. Each multicopter rotor is coupled to each other multicopter rotor, wherein the multicopter rotors are restricted to collective synchronous rotation relative to the wing between a multicopter configuration and a fixed-wing configuration. The movement sensor is coupled to the multicopter rotors, wherein the movement sensor is positioned to rotate relative to the wing when the multicopter rotors rotate relative to the wing between the multicopter and fixed-wing configurations.

To enhance the containment capability of a ducted fan device at the time of FBO without hindering the weight reduction thereof, in a ducted fan device including a fan shroud (52) having an annular shape in plan view and an electric fan disposed at a center of the fan shroud (52) and having a fan blade (58, 64), the fan shroud (52) has a multilayer structure including a fiber layer (74) and a resin layer (70, 72), and has an opposing section (A) including a part that opposes a tip of the fan blade (58, 64) and a non-opposing section (B) that does not oppose the tips of the fan blade (58, 64), the opposing section and the non-opposing section being arranged in an axial direction, wherein in the non-opposing section (B), the fiber layer (74) is impregnated with part of resin forming the resin layer (70, 72), and in the opposing section (A), the fiber layer (74) is not impregnated with the resin forming the resin layer (70, 72).

To enhance the containment capability of a ducted fan device at the time of FBO without hindering the weight reduction thereof, in a ducted fan device including a fan shroud (52) having an annular shape in plan view and an electric fan disposed at a center of the fan shroud (52) and having a fan blade (58, 64), the fan shroud (52) has a multilayer structure including a fiber layer (74) and a resin layer (70, 72), and has an opposing section (A) including a part that opposes a tip of the fan blade (58, 64) and a non-opposing section (B) that does not oppose the tips of the fan blade (58, 64), the opposing section and the non-opposing section being arranged in an axial direction, wherein in the non-opposing section (B), the fiber layer (74) is impregnated with part of resin forming the resin layer (70, 72), and in the opposing section (A), the fiber layer (74) is not impregnated with the resin forming the resin layer (70, 72).

A lift nacelle may comprise an airflow generator; a sidewall system coupled to the airflow generator and spanning in a first direction, wherein the sidewall system defines a nacelle interior space, wherein the airflow generator defines one of a forward boundary or an aft boundary of the nacelle interior space; and a lift body disposed in the nacelle interior space and spanning substantially perpendicular to the first direction and substantially perpendicular to an upward lift direction. The airflow generator may be configured to accelerate airflow in an aft direction into the nacelle interior space through the forward boundary of the nacelle interior space. The airflow may contact and/or interact with the lift body creating lift in response.

An unmanned aerial vehicle (UAV) includes a fuselage that supports breakaway components that are attached using magnets. One component is a battery pack which powers the vehicle. Another component is a rotor set including two identical pod pairs that each support a motor and a propeller. Each motor is attached to a hub assembly that includes a plurality of spokes captured in a motor hub and sandwiched by a rigid motor printed circuit board on top and a rigid hub plate. The hub assembly construction is rigid in plane and functions to keep the motor firmly stable during operation. The hub assembly is compliant and resilient when impacted parallel to the plane. Other features of the pod pairs encage the otherwise dangerous spinning propeller. This allows the vehicle to operate with a higher level of safety than conventional UAVs.

A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The VTOL may also include a decoupling mechanism having either a linear or non-linear beam coupled to a ring. The beam may optionally include sliders at ends thereof that provide an additional rotation freedom to the inner frame.

A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The VTOL may also include a decoupling mechanism having either a linear or non-linear beam coupled to a ring. The beam may optionally include sliders at ends thereof that provide an additional rotation freedom to the inner frame.

A vehicle capable of multiple varieties of locomotion having a main body; a plurality of motors and blades providing flying capability; each motor being associated with and powering a blade assembly; two legs extending from opposing sides of the main body creating a ground propulsion system. The ground propulsion system having two legs; each leg connected to a track body at the opposing leg end; each track body comprised of a plurality of drive gears; each track body connected to and retaining a track providing ground propulsion. The vehicle can either drive or fly based on its base structure, in additional to carrying a payload. The payload is carried below the main body of the vehicle and between the tracks or running gear. When the vehicle is in flight, the tracks are able to rotate up into a fly/flight mode to protect the blades during flight.

A vehicle capable of multiple varieties of locomotion having a main body; a plurality of motors and blades providing flying capability; each motor being associated with and powering a blade assembly; two legs extending from opposing sides of the main body creating a ground propulsion system. The ground propulsion system having two legs; each leg connected to a track body at the opposing leg end; each track body comprised of a plurality of drive gears; each track body connected to and retaining a track providing ground propulsion. The vehicle can either drive or fly based on its base structure, in additional to carrying a payload. The payload is carried below the main body of the vehicle and between the tracks or running gear. When the vehicle is in flight, the tracks are able to rotate up into a fly/flight mode to protect the blades during flight.

This disclosure describes a configuration of an unmanned aerial vehicle (“UAV”) in which the fuselage of the UAV is center mounted and at least some of the motors are configured to encompass at least a portion of the fuselage. In such a configuration, the stator and rotor of the motor extend around a perimeter of the fuselage, the propellers are coupled to an outer perimeter of the rotor, and the propellers extend radially outward away from the fuselage. Likewise, a closed wing may be coupled to the fuselage and positioned to encompass the radially extending propellers and at least a portion of the fuselage.