The presently disclosed embodiments relate to vertical takeoff and landing (VTOL) aircraft that have the capability of hovering in both a “nose forward” and a “nose up” orientation, and any orientation between those two. The disclosed aircraft can also transition into wing born (non-hovering) flight from any of the hovering orientations. In addition, certain of the disclosed embodiments can, if desired, use only vectored thrust control to maintain stable flight in both hover and forward flight. No control surfaces (e.g. ailerons, elevators, rudders, flaps) are required to maintain a stable vehicle attitude. However, the disclosure contemplates aircraft both with and without such control surfaces.

The presently disclosed embodiments relate to vertical takeoff and landing (VTOL) aircraft that have the capability of hovering in both a “nose forward” and a “nose up” orientation, and any orientation between those two. The disclosed aircraft can also transition into wing born (non-hovering) flight from any of the hovering orientations. In addition, certain of the disclosed embodiments can, if desired, use only vectored thrust control to maintain stable flight in both hover and forward flight. No control surfaces (e.g. ailerons, elevators, rudders, flaps) are required to maintain a stable vehicle attitude. However, the disclosure contemplates aircraft both with and without such control surfaces.

A flying apparatus includes a main structure and a rotative wing surface, the rotation of the wing surface allowing stabilizing the apparatus (100). A fuselage hangs from the wing surface around a hanging point, allowing the wing surface and the fuselage be moveable independently with respect to each other and the wing surface is configured as a disc to manoeuvre the apparatus and including one or more elements acting as security and secondary command and control surfaces, orienting the apparatus in desired directions. The main structure and wing surface can overwrap at least partially the the fuselage in order to improve the aerodynamic performance. The airframe or fuselage and the wing surface are rotatable around any of three rotational axes independently.

An unmanned aerial vehicle capable of vertical takeoff and landing carries a remote sensing platform to a high altitude cruising altitude and flies over a target area, collecting remote sensing imagery before returning to earth. Instead of being piloted remotely, the vehicle employs an autonomous flight control system.

An unmanned aerial vehicle capable of vertical takeoff and landing carries a remote sensing platform to a high altitude cruising altitude and flies over a target area, collecting remote sensing imagery before returning to earth. Instead of being piloted remotely, the vehicle employs an autonomous flight control system.

An aircraft capable of carrying at least 400 pounds of payload, has four rotors systems, each of the rotor systems being independently driven by an electric motor or other torque-producing source. Each of the rotor systems provide sufficient thrust such that the aircraft is capable of controlled vertical takeoff and landing, even if one of the variable pitch rotor is inoperable. An electronic control system is configured to control the rotational speed and pitch of at least one of the rotor systems in each of the first and second rotor pairs. The rotors may be arranged in coaxial stacks or maybe otherwise configured.

An aircraft capable of carrying at least 400 pounds of payload, has four rotors systems, each of the rotor systems being independently driven by an electric motor or other torque-producing source. Each of the rotor systems provide sufficient thrust such that the aircraft is capable of controlled vertical takeoff and landing, even if one of the variable pitch rotor is inoperable. An electronic control system is configured to control the rotational speed and pitch of at least one of the rotor systems in each of the first and second rotor pairs. The rotors may be arranged in coaxial stacks or maybe otherwise configured.

A package delivery system uses unmanned aircraft operable to transition between thrust-borne lift in a VTOL configuration and wing-borne lift in a forward flight configuration. Each of the aircraft includes an airframe having at least one wing with a distributed thrust array coupled to the airframe. The distributed thrust array includes a plurality of propulsion assemblies configured to provide vertical thrust in the VTOL configuration and a plurality of propulsion assemblies configured to provide forward thrust in the forward flight configuration. A package delivery module is coupled to the airframe. A control system is operably associated with the distributed thrust array and the package delivery module. The control system is configured to individually control each of the propulsion assemblies and control package release operations of the package delivery module. The system includes a ground station configured to remotely communicate with the control systems of the aircraft during package delivery missions.

A package delivery system uses unmanned aircraft operable to transition between thrust-borne lift in a VTOL configuration and wing-borne lift in a forward flight configuration. Each of the aircraft includes an airframe having at least one wing with a distributed thrust array coupled to the airframe. The distributed thrust array includes a plurality of propulsion assemblies configured to provide vertical thrust in the VTOL configuration and a plurality of propulsion assemblies configured to provide forward thrust in the forward flight configuration. A package delivery module is coupled to the airframe. A control system is operably associated with the distributed thrust array and the package delivery module. The control system is configured to individually control each of the propulsion assemblies and control package release operations of the package delivery module. The system includes a ground station configured to remotely communicate with the control systems of the aircraft during package delivery missions.

An aerial vehicle may include a first wing structure. The aerial vehicle may further include a first propeller and a second propeller disposed along the first wing structure. The aerial vehicle may further include a second wing structure disposed to intersect the first wing structure to form a cross configuration. The aerial vehicle may further include a third propeller and a fourth propeller disposed along the second wing structure. In a hovering orientation of the aerial vehicle, respective propeller rotational axes of the first and second propellers may be angled off-vertical in respective planes which may be perpendicular to a transverse axis of the first wing structure, and respective propeller rotational axes of the third and fourth propellers may be angled off-vertical in respective planes which may be perpendicular to a transverse axis of the second wing structure.