In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.

An aerial vehicle includes a fuselage, a wing, and a wing shift device. The wing shift device is configured to be coupled to the fuselage. The wing shift device comprises a plurality of apertures for coupling the wing to the aerial vehicle. The plurality of apertures are configured to permit the wing to be shifted in a forward or aft direction along the fuselage based on a center of gravity of the aerial vehicle.

An unmanned aerial vehicle includes a plurality of propellers and an airframe. The airframe includes a body having a hollow portion, and a plurality of through holes connected to the hollow portion and formed on an outer peripheral surface of the body. The airframe also includes a plurality of arms supporting the plurality of propellers, and each arm of the plurality of arms includes a base end portion disposed at a body side in a longitudinal direction of the respective arm. The base end portion is inserted in a corresponding through hole of the plurality of through holes and supported by the body. Each arm of the plurality of arms is configured to be stored in the hollow portion of the body by being retracted into the body via the through hole, and expanded out of the body by being pulled out of the body via the through hole.

An unmanned aerial vehicle includes a plurality of propellers and an airframe. The airframe includes a body having a hollow portion, and a plurality of through holes connected to the hollow portion and formed on an outer peripheral surface of the body. The airframe also includes a plurality of arms supporting the plurality of propellers, and each arm of the plurality of arms includes a base end portion disposed at a body side in a longitudinal direction of the respective arm. The base end portion is inserted in a corresponding through hole of the plurality of through holes and supported by the body. Each arm of the plurality of arms is configured to be stored in the hollow portion of the body by being retracted into the body via the through hole, and expanded out of the body by being pulled out of the body via the through hole.

To provide an unmanned aerial vehicle that is optimized for freight purposes and that efficiently performs loading and unloading of freight and efficiently performs airframe management. This object is solved by an unmanned aerial vehicle that includes a plurality of propellers. An airframe of the unmanned aerial vehicle includes: a body having a freight chamber that is a hollow portion and that is integral with the body; and a plurality of arms supporting each of the plurality of propellers. A combination of the one arm and the one propeller or plurality of propellers supported by the one arm constitute a retractable propeller. The retractable propeller is partially or entirely storable in the freight chamber.

To provide an unmanned aerial vehicle that is optimized for freight purposes and that efficiently performs loading and unloading of freight and efficiently performs airframe management. This object is solved by an unmanned aerial vehicle that includes a plurality of propellers. An airframe of the unmanned aerial vehicle includes: a body having a freight chamber that is a hollow portion and that is integral with the body; and a plurality of arms supporting each of the plurality of propellers. A combination of the one arm and the one propeller or plurality of propellers supported by the one arm constitute a retractable propeller. The retractable propeller is partially or entirely storable in the freight chamber.

An unmanned aerial vehicle includes a plurality of propellers and an airframe. The airframe includes a body having a hollow portion, and a plurality of through holes connected to the hollow portion and formed on an outer peripheral surface of the body. The airframe also includes a plurality of arms supporting the plurality of propellers, and each arm of the plurality of arms includes a base end portion disposed at a body side in a longitudinal direction of the respective arm. The base end portion is inserted in a corresponding through hole of the plurality of through holes and supported by the body. Each arm of the plurality of arms is configured to be stored in the hollow portion of the body by being retracted into the body via the through hole, and expanded out of the body by being pulled out of the body via the through hole.

An unmanned aerial vehicle includes a plurality of propellers and an airframe. The airframe includes a body having a hollow portion, and a plurality of through holes connected to the hollow portion and formed on an outer peripheral surface of the body. The airframe also includes a plurality of arms supporting the plurality of propellers, and each arm of the plurality of arms includes a base end portion disposed at a body side in a longitudinal direction of the respective arm. The base end portion is inserted in a corresponding through hole of the plurality of through holes and supported by the body. Each arm of the plurality of arms is configured to be stored in the hollow portion of the body by being retracted into the body via the through hole, and expanded out of the body by being pulled out of the body via the through hole.

This disclosure describes a multi-wing manned or unmanned compact personal vertical takeoff and landing aircraft, comprising the integration of: a plurality of parallel wings forming a boxed planform multi-wing assembly with no dynamic airfoil control surfaces, statically affixed to a co-planar adjacent counter-rotating quad-rotor air propulsion system; and a fuselage free to rotate under servo control about an axial shaft, permitting dynamic orientation manipulation. The vehicle described herein achieves: high maneuverability and attitude orientation control incumbent upon the ratio of power delivered to the quad-rotors; area constrained and enhanced wind gust insensitive VTOL capability; high fuel efficient non-hover aerodynamic flight capability; high external field-of-view optical visibility from the fuselage interior; convenient fuselage interior accessibility; and enhanced net pitching moment of inertia about the multi-wing assembly net aerodynamic center, permitting rapid transitioning to and from aerodynamic flight orientation.

This disclosure describes a multi-wing manned or unmanned compact personal vertical takeoff and landing aircraft, comprising the integration of: a plurality of parallel wings forming a boxed planform multi-wing assembly with no dynamic airfoil control surfaces, statically affixed to a co-planar adjacent counter-rotating quad-rotor air propulsion system; and a fuselage free to rotate under servo control about an axial shaft, permitting dynamic orientation manipulation. The vehicle described herein achieves: high maneuverability and attitude orientation control incumbent upon the ratio of power delivered to the quad-rotors; area constrained and enhanced wind gust insensitive VTOL capability; high fuel efficient non-hover aerodynamic flight capability; high external field-of-view optical visibility from the fuselage interior; convenient fuselage interior accessibility; and enhanced net pitching moment of inertia about the multi-wing assembly net aerodynamic center, permitting rapid transitioning to and from aerodynamic flight orientation.