Abstract: 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.

Abstract: A method of pitching rotor blades by interrupting torque applied to the hub.

Abstract: A kiosk for use an unmanned aerial system (UAS) delivery system is disclosed. In one embodiment, the kiosk includes an enclosure comprising at least one vertical wall having a secured entrance therethrough to prevent unauthorized persons from entering the enclosure, wherein an external appearance of the enclosure corresponds to a location of the kiosk; a landing zone for an unmanned aerial vehicle (UAV) of the UAS located within the enclosure, the landing zone comprising infrastructure from which the UAV can take off and on which the UAV can land; sensors for detecting an environment of at least one of the kiosk and the enclosure; and a guidance system for providing signals to the UAV to guide the UAV into the enclosure and onto the landing zone.

Abstract: An autonomous cargo delivery aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes a fuselage having an aerodynamic shape with a leading edge, a trailing edge and first and second sides. First and second wings are coupled to the fuselage proximate the first and second sides, respectively. A distributed thrust array includes a first pair of propulsion assemblies coupled to the first wing and a second pair of propulsion assemblies coupled to the second wing. A flight control system is operably associated with the distributed thrust array and configured to independently control each of the propulsion assemblies. The first side of the fuselage includes a door configured to provide access to a cargo bay disposed within the fuselage from an exterior of the aircraft with a predetermined clearance relative to the first pair of propulsion assemblies.

Abstract: An aircraft that is convertible between a helicopter mode and an airplane mode. The aircraft includes a fuselage with a longitudinal axis and a vertical axis and distributed propulsion array that surrounds the vertical axis when the aircraft is operating the helicopter mode and surrounds the longitudinal axis when the aircraft is operating in the airplane mode.

Abstract: A damping landing gear assembly for a vertical takeoff and landing aircraft includes a spring housing forming a spring chamber, a spring disposed in the spring chamber and a plunger slidably coupled to the spring housing and movable between a compressed position and an extended position. The spring biases the plunger into the extended position during flight. The vertical takeoff and landing aircraft experiences a landing force during landing. The landing force compresses the plunger into the compressed position against the bias of the spring, thereby absorbing at least a portion of the landing force.

Abstract: 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.

Abstract: A damping landing gear assembly for a vertical takeoff and landing aircraft includes a spring housing forming a spring chamber, a spring disposed in the spring chamber and a plunger slidably coupled to the spring housing and movable between a compressed position and an extended position. The spring biases the plunger into the extended position during flight. The vertical takeoff and landing aircraft experiences a landing force during landing. The landing force compresses the plunger into the compressed position against the bias of the spring, thereby absorbing at least a portion of the landing force.

Abstract: 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.

Abstract: An engine cooling system for a rotorcraft includes an engine having an engine cooling circuit, a hydraulic pump powered by the engine to pump hydraulic fluid, and a hydraulic circuit in fluid communication with the hydraulic pump and the engine cooling circuit, the hydraulic circuit including at least one hydraulic-powered component. The hydraulic pump is adapted to pump the hydraulic fluid through both the hydraulic circuit and the engine cooling circuit, thereby cooling the engine.

Abstract: An autonomous cargo delivery aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes a fuselage having an aerodynamic shape with a leading edge, a trailing edge and first and second sides. First and second wings are coupled to the fuselage proximate the first and second sides, respectively. A distributed thrust array includes a first pair of propulsion assemblies coupled to the first wing and a second pair of propulsion assemblies coupled to the second wing. A flight control system is operably associated with the distributed thrust array and configured to independently control each of the propulsion assemblies. The first side of the fuselage includes a door configured to provide access to a cargo bay disposed within the fuselage from an exterior of the aircraft with a predetermined clearance relative to the first pair of propulsion assemblies.

Abstract: An aircraft that is convertible between a helicopter mode and an airplane mode. The aircraft includes a fuselage with a longitudinal axis and a vertical axis and distributed propulsion array that surrounds the vertical axis when the aircraft is operating the helicopter mode and surrounds the longitudinal axis when the aircraft is operating in the airplane mode.

Abstract: A method of pitching rotor blades by interrupting torque applied to the hub.

Abstract: 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.

Abstract: An engine cooling system for a rotorcraft includes an engine having an engine cooling circuit, a hydraulic pump powered by the engine to pump hydraulic fluid, and a hydraulic circuit in fluid communication with the hydraulic pump and the engine cooling circuit, the hydraulic circuit including at least one hydraulic-powered component. The hydraulic pump is adapted to pump the hydraulic fluid through both the hydraulic circuit and the engine cooling circuit, thereby cooling the engine.