Abstract:
An amphibious vertical takeoff and landing unmanned device comprises a modular and expandable waterproof body (802), a chassis (804), an outer body shell (806), a propulsion system, a propeller protection system, a surface skidding material platform, a landing system, control surfaces, a ballast, an onboard air compressor, an onboard electrolysis system, a waterproof through-body wire or antenna feed-through, a single or multiple-axis tilt-motor device (1025), a tilt fuselage device, a tilt wing device (1015), a battery, a power distribution board, a Global Positioning System module, a lost model alert, a cooling device (1041), a detachable impact absorbing skin or shell, vision aiding and orientative lights, hatches, quick connect payloads, a lap counter for racing, a flat or inclined launch platform or footing, claws, an apparatus for externally attaching and internally housing a cargo, a charging station, a partial vacuum device, a manually or automatically deployable parachute (1130), and an onboard or ground station electricity generator. A video capture, realtime broadcast, and video downlink system for an amphibious VTOL unmanned device and a collision avoidance, flight stabilization, and multi-rotor control system for an amphibious VTOL unmanned device are also provided.
Abstract:
Die Erfindung betrifft ein Luftfahrzeug (1), umfassend eine Rumpfeinheit (2) und zumindest eine aufblasbare Tragflächeneinheit (3), welche im nicht aufgeblasenen Zustand in der Rumpfeinheit (2) angeordnet ist und durch Aufblasen aus der Rumpfeinheit (2) heraus in eine Tragflächenstellung positionierbar ist. Erfindungsgemäß ist die zumindest eine Tragflächeneinheit (3) im nicht aufgeblasenen Zustand in die Rumpfeinheit (2) eingerollt und durch Aufblasen aus der Rumpfeinheit (2) ausrollbar.
Abstract:
A disposable unmanned aerial glider (UAG) with pre-determined UAG flight capabilities. The UAG comprises a flight module comprising at least one aerodynamic arrangement; and a fuselage module comprising a container configured for storing therein a payload and having structural integrity. The container is pressurized so as to maintain structural integrity thereof at least during flight, so that the UAG flight capabilities are provided only when the container is pressurized.
Abstract:
An unmanned aerial vehicle (UAV) can be deployed from a small stowed package for flight and stowed back into the package after the flight is complete is disclosed. The UAV is retracted to a volume that is less than half of its fully deployed volume. This allows the UAV to be transported to any desired field position on a truck or other convenient transportation. The UAV may also be launched from a ship deck. In a further aspect, the flexible deployment of the UAV will allow a single UAV to be used in place of multiple types of UAVs.
Abstract:
[PROBLEMS] An aircraft that can be transported in a small space and has high performance. [MEANS FOR SOLVING PROBLEMS] An aircraft in which a kite wing (300) is attached to an aircraft body (100) via struts (210, 220) and a propeller (500) is rotatably supported by a shaft. A propeller guard section (120) for guarding the outer circumference of the propeller (500) is provided at the aircraft body (100). The struts (210, 220) can be fixed to the propeller guard section (120).
Abstract:
An air vehicle, as well as a method for folding an air vehicle for storage, may include a fuselage and a wing connected to the fuselage. The wing may include two ends positioned opposite from each other, and the wing may be substantially perpendicular to the fuselage. At least one of the ends may define a space therebetween the fuselage and the wing. The space may be sized to receive a potion of the wing when the wing is wrapped around the fuselage.
Abstract:
A morphing aircraft that is achieves multi- modality location and camouflage for payload emplacement The morphing aircraft includes a substantially cylindrical fuselage including a shape configured as a packaging container with a first end and a second end A set of wings is coupled to the fuselage The set of wings includes a first position where the set of wings is extended outwards from the fuselage and a second position where the set of wings is retracted inwards towards the fuselage A tail is coupled to the second end of the cylindrical fuselage The tail includes a first position where the tail is extended outward from the fuselage and a second position where the tail is retracted inward towards the fuselage A propeller is mounted to the first end of the fuselage An engine is mechanically coupled to the propeller The engine is enclosed within the fuselage and powers the propeller.
Abstract:
A morphing aircraft that is achieves multi- modality location and camouflage for payload emplacement The morphing aircraft includes a substantially cylindrical fuselage including a shape configured as a packaging container with a first end and a second end A set of wings is coupled to the fuselage The set of wings includes a first position where the set of wings is extended outwards from the fuselage and a second position where the set of wings is retracted inwards towards the fuselage A tail is coupled to the second end of the cylindrical fuselage The tail includes a first position where the tail is extended outward from the fuselage and a second position where the tail is retracted inward towards the fuselage A propeller is mounted to the first end of the fuselage An engine is mechanically coupled to the propeller The engine is enclosed within the fuselage and powers the propeller.
Abstract:
A UAV having an airframe supporting a tri-rotor triangular array, each tri-rotor comprising a pair of rotors (21,23) on the same axis, withan individual motor (20,22) for each rotor, the pairs of rotors being arrangedto contra-rotate.
Abstract:
Methods and apparatus for systems having deployable elements according to various aspects of the present invention comprise a system including a deployable surface and an adaptive actuator including a polymer foam. In one embodiment, the system comprises a vehicle including a deployable wing comprising an exterior surface. The exterior surface may be adjusted by adjusting the shape, size, position, and/or orientation of the adaptive actuator.