Provided is a drone with a multiple DOF flight mode according to the present invention. The drone may include: a fuselage in which a battery is mounted and a forward direction is set in an x-axis; a plurality of rotors disposed around the fuselage in four or more, each rotational axis of which is aligned in a z-axis direction; an x-axis tilting mechanism unit formed to tilt the plurality of rotors about an axis parallel to the x-axis; a y-axis tilting mechanism unit formed to tilt the plurality of rotors about an axis parallel to the y-axis; a first drive motor unit driving the y-axis tilting mechanism unit; a second drive motor unit guiding the x-axis tilting mechanism unit; and a control unit configured to implement a plurality of flight modes by controlling the first rotor, the second rotor, the third rotor, the fourth rotor, the first drive motor unit, and the second drive motor unit.

An unmanned aerial vehicle (UAV), comprising a fuselage outer shell defining a lateral axis, a longitudinal axis and a plurality of shell sides; fuselage center assembly positioned within a cavity defined by the fuselage outer shell; and a rotor arm and joint assembly. The plurality of the shell sides are concave with respect to the lateral axis or the longitudinal axis. The fuselage center assembly includes a lattice center defining a superior surface and an inferior surface as well as a plurality of channels, each channel having a proximal end and a distal end, wherein each proximal end is coupled to the superior surface and the inferior surface. The rotor arm has a proximal end and a distal end. A motor and rotor system is coupled to the distal end of the rotor arm. The rotor arm joint is coupled to the proximal end of the rotor arm, and the rotor arm joint further comprises an outer shell; and a plurality of quick release latches coupled to the outer shell and configured to coule the rotor arm joint to a plurality of corresponding latch receivers positioned.

An unmanned aerial vehicle (UAV), comprising a fuselage outer shell defining a lateral axis, a longitudinal axis and a plurality of shell sides; fuselage center assembly positioned within a cavity defined by the fuselage outer shell; and a rotor arm and joint assembly. The plurality of the shell sides are concave with respect to the lateral axis or the longitudinal axis. The fuselage center assembly includes a lattice center defining a superior surface and an inferior surface as well as a plurality of channels, each channel having a proximal end and a distal end, wherein each proximal end is coupled to the superior surface and the inferior surface. The rotor arm has a proximal end and a distal end. A motor and rotor system is coupled to the distal end of the rotor arm. The rotor arm joint is coupled to the proximal end of the rotor arm, and the rotor arm joint further comprises an outer shell; and a plurality of quick release latches coupled to the outer shell and configured to coule the rotor arm joint to a plurality of corresponding latch receivers positioned.

An unmanned flying device including a body; a first blade and at least a second blade; a coupling assembly for coupling the first blade and the at least second blade to the body, wherein the coupling assembly urges the collapsing of the first blade and the at least second blade towards the body; and wherein both the first blade and the at least second blade are rotateable about the body, and wherein the first blade and the at least second blade are deployable away from the body via rotation of the first and the at least second blades about the body.

An unmanned flying device including a body; a first blade and at least a second blade; a coupling assembly for coupling the first blade and the at least second blade to the body, wherein the coupling assembly urges the collapsing of the first blade and the at least second blade towards the body; and wherein both the first blade and the at least second blade are rotatable about the body, and wherein the first blade and the at least second blade are deployable away from the body via rotation of the first and the at least second blades about the body.

In some embodiments, a rotor assembly for an aerial vehicle includes a main body; and four or more rotors having blades mounted relative to the main body for rotation about respective axes configured to provide thrust predominantly in a common direction. Respective blade trajectories of rotors of at least one pair of adjacent rotors of the four or more rotors rotate in different planes. The blade trajectories of the at least one pair of adjacent rotors partially overlap when viewed along a line containing the common direction.

An unmanned aerial system (UAS) adapted to measure one or more atmospheric conditions has a frame and a plurality of motorized rotors suspended on arms extending outward from the frame. The UAS further includes a flight control module that includes a computer programmable flight control board and a sensor package that has an air sampling scoop, a first sensor positioned inside the air sampling scoop, and a ducted fan inside the air sampling scoop. The ducted fan is configured to draw air through the air sampling scoop in contact with the first sensor. The ducted fan can be configured to operate only when the UAS is above a predetermined altitude. The UAS may also be configured to operate in a wind vane mode in which wind speed and direction is determined based on the pitch and heading of the UAS.

An unmanned aerial vehicle (UAV) includes a fuselage, a pair of wings attached to the fuselage, and a propulsion system mounted to the wings to provide propulsion to the UAV. The fuselage has an outer fuselage shell that is a first mechanical support structure for an airframe of the UAV. The pair of wings is attached to the fuselage and shaped to provide aerodynamic lift. The wings have outer wing shells that are second mechanical support structures for the airframe. The outer fuselage shell or the outer wing shells comprise one or more formed-metal sheets.

An unmanned aerial vehicle (UAV) includes a fuselage, a pair of wings attached to the fuselage, and a propulsion system mounted to the wings to provide propulsion to the UAV. The fuselage has an outer fuselage shell that is a first mechanical support structure for an airframe of the UAV. The pair of wings is attached to the fuselage and shaped to provide aerodynamic lift. The wings have outer wing shells that are second mechanical support structures for the airframe. The outer fuselage shell or the outer wing shells comprise one or more formed-metal sheets.

A line-replaceable thrust module includes a nacelle configured to be mechanically connected to an anchoring location of an unmanned aerial vehicle (UAV), an electric motor coupled to the nacelle, an electric speed controller configured to control the speed of the electric motor and configured to be electrically connected to a communication network of the UAV, and a fuel cell system configured to produce electrical energy from an electrochemical reaction between hydrogen and oxygen. The fuel cell system includes a fuel cell, a hydrogen tank, a pressure regulator coupled to the hydrogen tank, and a supply line coupled between the pressure regulator and the fuel cell.