A convertible multi-mode vehicle capable of motorized travel in the air, on land, on water, and under water. The multi-mode vehicle is capable of controlled aerial flight, movement on the ground in terrestrial environments, on an aquatic surface, as well as underwater by changing between the different modes. Pivoting propulsion motors enable a convertible configuration from one vehicle locomotion mode to another.

A convertible multi-mode vehicle capable of motorized travel in the air, on land, on water, and under water. The multi-mode vehicle is capable of controlled aerial flight, movement on the ground in terrestrial environments, on an aquatic surface, as well as underwater by changing between the different modes. Pivoting propulsion motors enable a convertible configuration from one vehicle locomotion mode to another.

An aircraft operable between a deployed position and a stowed position is disclosed. The aircraft includes a fuselage, a pair of wing segments, and a translation and rotation mechanism for attaching the wing segments to the fuselage. The mechanism includes an upper assembly having an outer shaft and an inner shaft. A first wing segment is attached to the outer shaft and a second wing segment is attached to the inner shaft. The outer shaft translates downward with respect to the inner shaft. Thereafter, the outer and inner shafts rotate in opposite directions in order to rotate the wing segments on top of one another, parallel to a long axis of the fuselage, and into the stowed position. The operation of the outer and inner shafts is reversed in order to return the wing segments to the deployed position.

Disclosed is a multipurpose air vehicle including a frame (1) on which a propeller (11) and a mechanical unit (10) equipped with an engine are mounted, and a cabin (2) is coupled inside the frame (1). The frame (1) is constructed by upper and lower circular plates (101, 102) and curved posts (111, 112, 113, 114) that interconnect the upper and lower circular plates (101, 102), and is provided with two or more arms (12) that can protrude and retract, and a propeller (11) is provided on the tip end of each arm (12). The cabin (2) includes a circular plate member (3) and further includes at least four connectors (21) provided on the front, the rear, the left, and the right ends thereof, and each connector (21) has a tip end installed on a rail (13) of the frame (1) so as to guide pivoting of the cabin (2). The multipurpose air vehicle may freely perform upward and downward movement and forward and rearward movement, and thus may be used anywhere in the air, ground, or water. Moreover, the multipurpose air vehicle may allow the cabin (2) to maintain horizontal balance and to provide a lift force as needed, regardless of the flying angle during the upward or downward movement of the air vehicle.

Method and apparatus for a flight vehicle including a wing having a high aspect ratio and first and second rotors having a high aspect ratio, with a ratio of the rotor diameter to wing length ratio is equal to or greater than about 0.25. In embodiments, the flight vehicle can include a first and second motor, each less than about one thousand HP, to drive a respective rotor and a second motor. The flight vehicle can include a cruise mode and a VTOL mode.

An unmanned aerial vehicle (UAV) is provided including an envelope structure configured to have a spherically curved outer surface, and a plurality of propulsion units arranged on the outer surface of the envelope structure; wherein each of the propulsion units is configured to generate an air stream along on the outer surface of the envelope structure; and wherein each of the propulsion units comprises an impeller coupled to a motor, wherein the impeller is configured to generate the air stream.

An unmanned aerial vehicle (UAV) is provided including an envelope structure configured to have a spherically curved outer surface, and a plurality of propulsion units arranged on the outer surface of the envelope structure; wherein each of the propulsion units is configured to generate an air stream along on the outer surface of the envelope structure; and wherein each of the propulsion units comprises an impeller coupled to a motor, wherein the impeller is configured to generate the air stream.

An unmanned aerial vehicle includes multiple rotor arms; a rotor disposed at an end of each of the multiple rotor arms; and an adjustment component configured to enable a first rotor arm to move relative to a second rotor arm.

Disclosed is a multipurpose air vehicle including a frame (1) on which a propeller (11) and a mechanical unit (10) equipped with an engine are mounted, and a cabin (2) is coupled inside the frame (1). The frame (1) is constructed by upper and lower circular plates (101, 102) and curved posts (111, 112, 113, 114) that interconnect the upper and lower circular plates (101, 102), and is provided with two or more arms (12) that can protrude and retract, and a propeller (11) is provided on the tip end of each arm (12). The cabin (2) includes a circular plate member (3) and further includes at least four connectors (21) provided on the front, the rear, the left, and the right ends thereof, and each connector (21) has a tip end installed on a rail (13) of the frame (1) so as to guide pivoting of the cabin (2). The multipurpose air vehicle may freely perform upward and downward movement and forward and rearward movement, and thus may be used anywhere in the air, ground, or water. Moreover, the multipurpose air vehicle may allow the cabin (2) to maintain horizontal balance and to provide a lift force as needed, regardless of the flying angle during the upward or downward movement of the air vehicle.

An aircraft, a method of controlling the aircraft, and a control system for the aircraft has a fuselage and tilt-wing movable relative to the fuselage. A plurality of main propulsors coupled to main propellers that is coupled to the tilt-wing, which are configured to provide a first maximum amount of thrust. A plurality of auxiliary propulsors coupled to auxiliary propellers that are spaced apart from the tilt-wing, which are configured to provide a variable amount of thrust. A controller signals the main propulsors to operate at the first maximum amount of thrust when the tilt-wing moves from the cruise position to the transition position, and signals the auxiliary propulsors to operate at the variable amount of thrust when the tilt-wing is in the transition position in which the first maximum amount of thrust and the variable amount of thrust together provide an overall thrust to descend and land the aircraft.