A multirotor aircraft that includes a chassis, at least three engines that are equipped with propellers, and one or more axial free wings that are connected to the chassis by axial connections. The leading edges of the one or more axial free wings are designed to face constantly same direction when the multirotor flying, and the attack angles of the one or more axial free wings are designed to be changed relatively to the chassis due to flow of air over the one or more axial free wings.

A multirotor aircraft that includes a chassis, at least three engines that are equipped with propellers, and one or more axial free wings that are connected to the chassis by axial connections. The leading edges of the one or more axial free wings are designed to face constantly same direction when the multirotor flying, and the attack angles of the one or more axial free wings are designed to be changed relatively to the chassis due to flow of air over the one or more axial free wings.

A vehicle includes a propulsion system using one or more impellers as opposed to propellers. The impellers impart circumferential and radial velocity components to the working fluid, which may be air or water. The air is deflected by counter-vortex chambers in a shroud to convert the circumferential and radial velocity to an axial velocity aligned with the axis of rotation of the impeller.

A vehicle includes a propulsion system using one or more impellers as opposed to propellers. The impellers impart circumferential and radial velocity components to the working fluid, which may be air or water. The air is deflected by counter-vortex chambers in a shroud to convert the circumferential and radial velocity to an axial velocity aligned with the axis of rotation of the impeller.

A rotor with an elongated nosecone structure to provide stability when boarding or deplaning and to prevent damage to rotor blades is disclosed. A rotor as disclosed herein may include a plurality of rotor blades affixed to the hub structure; and an elongated nose structure extending away from the hub in a direction substantially orthogonal to a deployed direction of said rotor blades, the elongated nose structure having a length greater than a diameter of the elongated nose structure.

A rotor with an elongated nosecone structure to provide stability when boarding or deplaning and to prevent damage to rotor blades is disclosed. A rotor as disclosed herein may include a plurality of rotor blades affixed to the hub structure; and an elongated nose structure extending away from the hub in a direction substantially orthogonal to a deployed direction of said rotor blades, the elongated nose structure having a length greater than a diameter of the elongated nose structure.

An autonomous thrust vectoring ring wing pod is disclosed. A plurality of distributed propulsion element (thruster) layout within a self-articulating ring wing pod allows the pod to selectively control its thrust vector by controlling each propulsion element in the pod. This arrangement allows autonomous and independent control of the tilting of the ring wing relative to the aircraft. The ring wing pod acts as both a nacelle to house the propulsion elements as well as a lifting surface when in wing-borne flight. The autonomous thrust vectoring ring wing pod also provides superior aircraft attitude control in wing-borne flight, thus negating the need for conventional surface controls.

A vertical take-off and landing (VTOL) airborne vehicle includes a fuselage, a front vertical thrust fan positioned forward of the fuselage and rotating in a first plane, and a rear vertical thrust fan positioned rearward of the fuselage and rotating in a second plane above the first plane. The relative positioning of the front and rear vertical thrust fans changes the distribution of aerodynamic forces on an upper profile of the fuselage to reduce drag.

A ducted-rotor aircraft includes a fuselage, one or more ducts, and a spindle that rotatably couples the one or more ducts to the fuselage. Each duct includes a hub that is configured to support a rotor, a plurality of stators that are coupled to the hub, a duct ring that is coupled to the plurality of stators, and a fitting that is coupled to a first stator of the plurality of stators. The fitting has a tubular collar that defines a first aperture that extends through the fitting. The collar is configured to receive a portion of the spindle. The first stator includes a rib that is spaced inward from the fitting and that defines a second aperture that is aligned with the first aperture and that is configured to receive an end of the spindle.

A ducted-rotor aircraft includes a fuselage, one or more ducts, and a spindle that rotatably couples the one or more ducts to the fuselage. Each duct includes a hub that is configured to support a rotor, a plurality of stators that are coupled to the hub, a duct ring that is coupled to the plurality of stators, and a fitting that is coupled to a first stator of the plurality of stators. The fitting has a tubular collar that defines a first aperture that extends through the fitting. The collar is configured to receive a portion of the spindle. The first stator includes a rib that is spaced inward from the fitting and that defines a second aperture that is aligned with the first aperture and that is configured to receive an end of the spindle.