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 includes a fuselage, and a wing extending from the fuselage along a spanwise axis. A section of the wing is rotatable about the spanwise axis. A ducted fan is mounted to the section of the wing. The ducted fan has a hub configured to be drivingly engaged by an engine. The hub is rotatable about a fan axis. Blades protrude from the hub between roots mounted to the hub and tips radially spaced from the hub. A duct circumferentially extends about the fan axis and is mounted to the tips of the blades to rotate with the blades about the fan axis. The section of the wing and the ducted fan are rotatable about the spanwise axis between a hover mode in which the fan axis is substantially perpendicular to a ground, and an aircraft mode in which the fan axis is substantially parallel to the ground.

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 includes a fuselage, and a wing extending from the fuselage along a spanwise axis. A section of the wing is rotatable about the spanwise axis. A ducted fan is mounted to the section of the wing. The ducted fan has a hub configured to be drivingly engaged by an engine. The hub is rotatable about a fan axis. Blades protrude from the hub between roots mounted to the hub and tips radially spaced from the hub. A duct circumferentially extends about the fan axis and is mounted to the tips of the blades to rotate with the blades about the fan axis. The section of the wing and the ducted fan are rotatable about the spanwise axis between a hover mode in which the fan axis is substantially perpendicular to a ground, and an aircraft mode in which the fan axis is substantially parallel to the ground.