A modular Unmanned Aerial System (UAS) has first and second flight configurations, and includes an Unmanned Aerial Vehicle (UAV) parent module and a plurality of UAV child modules. The parent module may have a fuselage, forward and aft wings connected to the fuselage, and a first plurality of flight propulsion devices. The child modules have a corresponding second plurality of flight propulsion devices. Each child module docks wingtip-to-wingtip with the parent module or an adjacent edge of a child module using the docking mechanisms. The child modules undock and separate from the forward wing and each other, and achieve controlled flight independently of the parent module while in the second flight configuration. A method for controlling the modular UAS is also disclosed.

A modular Unmanned Aerial System (UAS) includes an Unmanned Aerial Vehicle (UAV) parent module and UAV child modules. A main wing extends from a respective fuselage of the modules. The UAS includes docking mechanisms coupled to wingtips of the main wings. The child modules dock with the wingtips of the parent or an adjacent child module. Docking forms a linked-flight configuration, with undocking and separation from the parent or adjacent child module achieving an independent-flight configuration. The modules have booms arranged transverse to the main wings and parallel to the longitudinal axis, as well as front and rear rotors/propellers. The front and rear propellers have axes of rotation that are normal to a plane of the longitudinal axis in a vertical takeoff and landing (VTOL) configuration, with the axis of rotation of the rear propellers parallel to the longitudinal axis in a forward-flight configuration.

An unmanned aerial vehicle includes multiple rotor arms; a rotor disposed at an end of each of the multiple rotor arms; and an adjustment component configured to enable a first rotor arm to move relative to a second rotor arm.

A self-righting aeronautical vehicle comprising a hollowed frame and a lift mechanism. The exterior of the frame and center of gravity are adapted to self-right the vehicle. The frame can include sealed, hollowed sections for use in bodies of water. The frame can be spherical in shape enabling inspection of internal surface of partially or fully enclosed structures. Inspection equipment can be integrated into the vehicle and acquired data can be stored or wirelessly communicated to a server. A controlled or other mass can be pivotally assembled to a pivot axle spanning across the interior of the frame. The pivot axis can rotate about a vertical axis (an axis perpendicular to the elongated axis). The propulsion mechanisms can be adapted for use as a terrestrial vehicle when enclosed in a sealed spherical shell.

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.

An aircraft includes a fuselage having a longitudinal axis, a wing assembly, and a fuselage positioning mechanism operatively connecting the fuselage to the wing assembly. The fuselage positioning mechanism is operable to move the fuselage relative to the wing assembly in a longitudinal direction parallel to the longitudinal axis between a fuselage maximum forward position and a fuselage maximum aft position. When the aircraft for flight, a position of a center of gravity of the aircraft relative to a center of lift is determined. The fuselage can be moved relative to the wing assembly to bring the center of gravity within an allowable range of distances from the center of lift to balance the aircraft for flight. The fuselage positioning mechanism can be automated to allow adjustment of the fuselage position during the flight of the aircraft.

A drone can be used to carry a payload. The drone can include at least two wings extending from a fuselage and propellers that allow the drone to fly in a horizontal orientation. The drone can takeoff and land from a vertical orientation via landing rods at the rear of the fuselage. The drone also includes an adjustable center of gravity and/or an adjustable center of lift. The center of gravity can be adjusted by changing the weight of payload located fore and aft of the center of gravity or moving at least a portion of the payload fore or aft along the fuselage. The center of lift can be adjusted by swinging the wings away from or towards the fuselage or sliding the wings fore or aft along the fuselage such that the center of lift is adjacent to the center of gravity.

A drone can be used to carry a payload. The drone can include at least two wings extending from a fuselage and propellers that allow the drone to fly in a horizontal orientation. The drone can takeoff and land from a vertical orientation via landing rods at the rear of the fuselage. The drone also includes an adjustable center of gravity and/or an adjustable center of lift. The center of gravity can be adjusted by changing the weight of payload located fore and aft of the center of gravity or moving at least a portion of the payload fore or aft along the fuselage. The center of lift can be adjusted by swinging the wings away from or towards the fuselage or sliding the wings fore or aft along the fuselage such that the center of lift is adjacent to the center of gravity.

An unmanned aerial vehicle includes multiple rotor arms; a rotor disposed at an end of each of the multiple rotor arms; and an adjustment component configured to enable a first rotor arm to move relative to a second rotor arm.

A vertical takeoff and landing (VTOL) unmanned aircraft system (UAS) may be uniquely capable of VTOL via a folded wing design while also configured for powered flight as the wings are extended. In a powered flight regime with wings extended, the VTOL UAS may maintain controlled powered flight as a twin pusher canard design. In a zero airspeed (or near zero airspeed) nose up attitude in a VTOL flight regime with the wings folded, the unmanned aircraft system may maintain controlled flight using main engine thrust as well as vectored thrust as a vertical takeoff and landing aircraft. An airborne transition from VTOL flight regime to powered flight and vice versa may allow the VTOL UAS continuous controlled flight in each regime.