A wing ring flying saucer is disclosed, which is operative to be driven to fly fast without needing an extra engine, and can turn, brake and fly backwards. The method of flying the wing ring flying saucer is as follows: airfoils of the wing ring or flow generators are enabled to repeat the same inclining process while passing by a specific section in circular motions of two times or more than three times in succession, so that a force perpendicular to the axial direction is created from an original resultant force in line with the axial direction of the wing ring (that is, a resultant force created by lift produced by all the airfoils), thereby enabling the wing ring flying saucer to fly, turn and go backwards at a relatively high speed.

A vertical take-off and landing (VTOL) unmanned aerial vehicle having a foldable fixed wing and a twin-ducted fan power system (7) arranged at a tail portion of a fuselage in a transverse and tail propulsion arrangement provides lift for vertical take-off and landing and propulsion for horizontal flight. By means of deflection of a control servo plane arranged at a duct exit, a vectored thrust is provided to enable a fast attitude change. When the aerial vehicle takes off and lands vertically/flies at a low speed, the wing is folded to reduce the frontal area exposure to crosswind. When the aerial vehicle is flying horizontally, the wing is expanded to obtain larger lift. A Coanda effect is created at a trailing edge of the wing by suction of the duct to improve performance.

A vertical take-off and landing (VTOL) unmanned aerial vehicle having a foldable fixed wing and a twin-ducted fan power system (7) arranged at a tail portion of a fuselage in a transverse and tail propulsion arrangement provides lift for vertical take-off and landing and propulsion for horizontal flight. By means of deflection of a control servo plane arranged at a duct exit, a vectored thrust is provided to enable a fast attitude change. When the aerial vehicle takes off and lands vertically/flies at a low speed, the wing is folded to reduce the frontal area exposure to crosswind. When the aerial vehicle is flying horizontally, the wing is expanded to obtain larger lift. A Coanda effect is created at a trailing edge of the wing by suction of the duct to improve performance.

We describe an aircraft design, which is capable of vertical takeoff and landing and also high-speed cruise on a fixed wing. The aircraft comprises a fuselage with a probe-deployment mechanism, which deploys a sample-gathering probe, located at a front end of the fuselage. A main wing is coupled to a middle section of the fuselage, wherein a right motor and right propeller are coupled to a right side of the main wing, and a left motor and left propeller are coupled to a left side of the main wing. The right and left propellers are angled with respect to the fuselage enabling the aircraft to pitch up to a vertical-takeoff mode and pitch down a horizontal-cruising mode. A pitch motor and pitch propeller are located at the rear end of the fuselage, wherein the pitch propeller is angled to provide substantially vertical thrust to control a pitch of the fuselage.

An aircraft capable of Vertical Take-Off and Landing (VTOL) and traverse flight. The aircraft generally includes a fixed outer structure including at least a generally cylindrical wing having an internal body situated within the fixed outer structure. A space is defined between the internal body and the fixed outer structure. Within this space are one or more rotatable ring impellers that create(s) thrust sufficient to achieve lift for the aircraft.

An aircraft capable of Vertical Take-Off and Landing (VTOL) and traverse flight. The aircraft generally includes a fixed outer structure including at least a generally cylindrical wing having an internal body situated within the fixed outer structure. A space is defined between the internal body and the fixed outer structure. Within this space are one or more rotatable ring impellers that create(s) thrust sufficient to achieve lift for the aircraft.

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.

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.

An aircraft includes an airframe with a thrust array attached thereto. The thrust array includes a plurality of propulsion assemblies that are independently controlled by a flight control system. A landing gear assembly is coupled to the airframe and includes a plurality of landing feet. An altitude sensor array includes a plurality of altitude sensors each of which is disposed within one of the landing feet such that when the aircraft is in the VTOL orientation, the altitude sensor array is configured to obtain multifocal altitude data relative to a landing surface. The flight control system is configured to generate a three-dimensional terrain map of the surface based upon the multifocal altitude data.

The present specification relates generally to unmanned aerial vehicles, and specifically to a vertical take-off and lift unmanned aerial vehicle configured for high speed, long-distance flight, and vertical take-off and lift, while carrying a significant payload. The aerial vehicle includes a first propeller and a second propeller, each comprising at least two blades and each disposed on opposite lateral edges of the aerial vehicle; a tail segment forming a trailing edge of the aerial vehicle, wherein the tail segment comprises: an elevator; and a first wing and a second wing, each comprising an aileron. The aerial vehicle further includes four fins, wherein the four fins are affixed to lateral edges behind the first propeller or the second propeller and configured as endplates; a motor; and a power supply.