An aircraft which includes a float-wing having a leading edge, a trailing edge, and an airfoil shape to produce aerodynamic lift when the float-wing flows through air at a lift-producing angle of attack in a forward flight mode of operation. The float-wing further includes a submersible portion that includes at least the trailing edge and which is constructed of materials and in a shape selected to produce a buoyancy force sufficient to prevent at least a non-submersible portion of the aircraft from being submersed under conditions in which the aircraft is in a waterborne non-flight position in which at least the trailing edge of the float-wing is submersed but at least the non-submersible portion of the aircraft is not submersed.

An aircraft, such as an unmanned aerial vehicle or single-seat aircraft, including a main body and a pair of wing sections, each wing section including a front wing and a rear wing, wherein the front wing and the rear wing each include a first end that is connected to the main body, and a second end, wherein the second end of the front wing is connected to the second end of the rear wing. The main body is located between the pair of wing sections, and each wing section includes a propulsion unit located between the front wing and the rear wing of the wing section. Each propulsion unit may include a first rotor and a second rotor, which may be pivotable with respect to the rest of the aircraft.

A ducted fan unmanned aerial vehicle (UAV) docking station is provided. The docking station comprises: a guide sized to receive a ducted fan UAV; and a housing communicatively coupled to the guide. The housing comprises: a storage assembly comprising: at least one compartment sized to store the UAV; and at least one dampening system coupled to the at least one storage compartment for cushioning the UAV.

A single-shaft aerial vehicle comprises a propeller, an aerial vehicle body and a wing driver unit constituting a portion of the aerial vehicle body. The aerial vehicle body has a streamlined shape. A ring-shaped wing extending out of the wing driver unit is provided at a central position of the wing driver unit. The ring-shaped wing is movable horizontally under the drive of the wing drive unit. When drag areas of the ring-shaped wing extending out of an outer circumference of the wing drive unit are the same in all directions, the single-shaft aerial vehicle maintains its current flying posture. When the ring-shaped wing moves toward a certain direction to increase the drag area extending out of the wing drive unit in the certain direction, and contracts into the wing drive unit in its opposite direction to reduce the drag area in the opposite direction, the single-shaft aerial vehicle changes its current flying posture.

The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

An aircraft includes a wing where a first rotor and a second rotor are coupled to the wing at a fixed position relative to the wing. The aircraft also includes a fuselage and a bearing. The bearing mechanically couples the wing and the fuselage and permits the wing and the fuselage to rotate with respect to each other about an axis of rotation. The bearing permits the fuselage to rotate under the influence of gravity to be in a same orientation relative to ground when the wing is in a first orientation relative to the ground as well as a second orientation relative to the ground.

An airframe design may include a bonded frame or assembly, and one or more components that may be removably attached to the bonded frame. The bonded frame may include struts, central bulkheads, a tail section, a plurality of wing sections, and motor mounts that are adhered together using adhesive. The one or more attachable components may include a forward fuselage, motors, propellers, motor pod fairings, stabilizer fins, and landing gear that are attached using fasteners. The bonded frame may reduce the number of parts of the airframe design and may also reduce complexity, cost, and weight, while also increasing stiffness and strength. Further, the various attachable components may facilitate fabrication, assembly, and maintenance of an aerial vehicle having the airframe design.

A single-shaft aerial vehicle comprises a propeller, an aerial vehicle body and a wing driver unit constituting a portion of the aerial vehicle body. The aerial vehicle body has a streamlined shape. A ring-shaped wing extending out of the wing driver unit is provided at a central position of the wing driver unit. The ring-shaped wing is movable horizontally under the drive of the wing drive unit. When drag areas of the ring-shaped wing extending out of an outer circumference of the wing drive unit are the same in all directions, the single-shaft aerial vehicle maintains its current flying posture. When the ring-shaped wing moves toward a certain direction to increase the drag area extending out of the wing drive unit in the certain direction, and contracts into the wing drive unit in its opposite direction to reduce the drag area in the opposite direction, the single-shaft aerial vehicle changes its current flying posture.

The embodiments of the present invention provide a navigator, comprising a gyro flying device and a cover that seals and encloses the gyro flying device. The gyro flying device is connected to the cover by a retaining mechanism. The gyro flying device comprises: a gyrorotor having an axisymmetric structure and rotatable around a central axis thereof; and a driving mechanism coaxially mounted with the gyrorotor to drive the gyrorotor to rotate around the central axis thereof, thereby manipulating rise and fall of the navigator. The retaining mechanism is further disposed to adjust an inclination angle of the gyro flying device, so as to adjust a flying direction of the navigator. The navigator has the advantages of quiet, safe, frictionless, extensive uses, etc.