An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.

A helicopter includes a gimbal assembly, a first rotor assembly, a second rotor assembly, a fuselage, and a controller. The first rotor assembly, the second rotor assembly, and the fuselage are mechanically coupled to the gimbal assembly. The first rotor assembly includes a first rotor and the second rotor assembly includes a second rotor, the first rotor including a plurality of first fixed-pitch blades and the second rotor including a plurality of second fixed-pitch blades. Each of the plurality of first and the second fixed-pitch blades are coupled to a hub of its respective rotor via a hinge mechanism that is configured to allow each of the fixed-pitch blades to pivot from a first position to a second position, the first position being substantially parallel to the fuselage and the second position being substantially perpendicular to the fuselage.

A helicopter includes a gimbal assembly, a first rotor assembly, a second rotor assembly, a fuselage, and a controller. The first rotor assembly, the second rotor assembly, and the fuselage are mechanically coupled to the gimbal assembly. The first rotor assembly includes a first rotor and the second rotor assembly includes a second rotor, the first rotor including a plurality of first fixed-pitch blades and the second rotor including a plurality of second fixed-pitch blades. Each of the plurality of first and the second fixed-pitch blades are coupled to a hub of its respective rotor via a hinge mechanism that is configured to allow each of the fixed-pitch blades to pivot from a first position to a second position, the first position being substantially parallel to the fuselage and the second position being substantially perpendicular to the fuselage.

One embodiment of a vertical take-off and landing aircraft held aloft by way of one or more powered assemblies of wing type elements capable of generating aerodynamic lift by means of rotation. A main body having an integrated means for directing air impelled from an inlet, by way of one or more powered impellers, through a cavity, acting as a duct, to an outlet. At least one movable surface located in sufficient proximity to the outlet to direct expelled air in a vectored manner providing a means of affecting the motion of the aircraft.

A rotor system for a rotary wing aircraft includes a rotor hub including a first beam attachment member and a second beam attachment member. A hub arm including a U-shaped beam member is connected to the rotor hub. The U-shaped beam member includes a first end portion, a second end portion and an intermediate section connecting the first and second end portions. The first end portion is connected at the first beam attachment member. The second end portion is connected at the second beam attachment member. A pitch change bearing is mounted between the first and second beam attachment member through the first end portion and the second end portion.

The present invention discloses an unfolding propeller unit type unmanned aerial vehicle including a body unit, a plurality of propeller units in which propellers are installed, a locking unit configured to lock the propeller units so that a state in which the propeller units are overlapping on the body unit is maintained, and propeller unit unfolders, each configured to connect each of the propeller units to the body unit, and unfold the propeller unit from the body unit so the propeller units are positioned around the body unit when locking of the locking unit is released.

The present invention discloses an unfolding propeller unit type unmanned aerial vehicle including a body unit, a plurality of propeller units in which propellers are installed, a locking unit configured to lock the propeller units so that a state in which the propeller units are overlapping on the body unit is maintained, and propeller unit unfolders, each configured to connect each of the propeller units to the body unit, and unfold the propeller unit from the body unit so the propeller units are positioned around the body unit when locking of the locking unit is released.

An unmanned aerial vehicle includes a fuselage body, a foldable wing assembly and a gear assembly. The foldable wing assembly, including a pair of opposing wing members, is coupled to the fuselage body and positionable in a stowed position and a deployed position. The gear assembly positions the wing members in a stowed position and a deployed position and include a support bracket assembly and a pair of opposing hinge members. The support bracket assembly is coupled to the fuselage body and including first and second support brackets forming a cavity therebetween and a pair of opposing hinge members. The pair of opposing hinge members are pivotably coupled to the support bracket assembly and positioned within the cavity. Each hinge member is coupled to a corresponding wing member and includes a set of gear teeth extending outwardly from an arcuate radially outer surface and coupled in a meshed arrangement.

Described are apparatus and processes for reconfiguring aerial vehicles, such as unmanned aerial vehicles (UAV) during navigation of the aerial vehicle between a maneuverability configuration and an efficiency configuration. When an aerial vehicle needs to be able to quickly maneuver in any direction (vertical, horizontal, pitch, roll, yaw) it is operating in a maneuverability configuration. When configured to operate in the maneuverability configuration, the primary function of the aerial vehicle configuration is to increase maneuverability of the aerial vehicle. When the aerial vehicle is navigating in a direction that is substantially horizontal, for example when navigating between locations, it may be configured to operate in an efficiency configuration. When configured to operate in the efficiency configuration, the primary function of the aerial vehicle configuration is to increase efficiency of the aerial vehicle and reduce power consumption.

A collapsible flying device is provided having a housing including first and second housing sections forming an enclosure, and a motorized assembly that includes a drive motor and a drive shaft driven by the drive motor. The drive shaft matingly receives the first housing section and is coupled to the second housing section, wherein operation of the drive motor drives the drive shaft to move the first housing section from a closed position adjacent the second housing section to an open position spaced from the second housing section. A rotor hub is rotatingly driven by the drive motor. At least two rotor blades are coupled thereto and positioned within the enclosure in a collapsed position when the first housing section is in the closed position, and extend beyond the enclosure in an expanded position when the first housing section is in the open position.