An unmanned aerial system includes an elongated fuselage having first and second rotational degrees of freedom. A forward propulsion assembly is disposed at the forward end of the fuselage. The forward propulsion assembly includes a forward rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a first gimballing axis to provide a first moment on the fuselage in the first rotational degree of freedom. An aft propulsion assembly is disposed at the aft end of the fuselage. The aft propulsion assembly includes an aft rotor hub assembly rotatably coupled to the fuselage and reversibly tiltable about a second gimballing axis to provide a second moment on the fuselage in the second rotational degree of freedom. The first gimballing axis is out of phase with the second gimballing axis to control the orientation of the fuselage.

A portable multithruster unmanned aircraft for search and rescue missions, including avalanche beacon position/detection, as well as military field operations such as forward observer deployment is disclosed. In one aspect, the aircraft includes four rotor assemblies, housed in cowlings, deployably stowed in a cylindrical airframe to present a smooth surface for portability in tight quarters, such as a backpack, duffle bag or the like. The rotor assemblies, upon activation, are deployed by mechanical or electromechanical means to operating, flight ready position, exterior the airframe through slots in the skin of the airframe or by unfolding the hinged cowlings nested within the airframe. In one aspect, four deployed rotor assemblies are quadrantally positioned about the airframe, preferably in a horizontal plane perpendicular to the vertical axis of the airframe. A payload, including a power source, is contained within the cylindrical airframe for operation, including navigation. In another aspect, three deployed rotor assemblies are equilaterally positioned about the airframe, preferably in a horizontal plane perpendicular to the vertical axis of the airframe.

Disclosed herein are aspects of an unmanned aerial vehicle (UAV). In one embodiment, the UAV includes a container body having a cargo bay configured to hold cargo, and a plurality of rotor assemblies coupled to the container body. Each rotor assembly is configured to provide the container body with propulsion. A control system may be held by the container body and operatively connected to the rotor assemblies. The control system may be configured to fly the container body to a destination. The rotor assemblies may be moveable between a flight configuration and a shipping configuration. In the flight configuration, the rotor assemblies may extend outward from the container body such that the rotor assemblies are positioned to propel the container body through the air. In the shipping configuration, the rotor assemblies may be folded to the container body such that the container body is configured to be shipped to a destination.

Provided is a method for controlling flight of a drone and an apparatus supporting the same. More specifically, the drone according to the present invention determines whether or not a specific condition is satisfied to deploy a parachute during the flight, and in a case where the specific condition is satisfied, the drone may stop an operation of one or more propellers to deploy the parachute. Next, the drone deploys the parachute, the parachute is deployed toward an area beside the drone, and the flight of the drone may be controlled by adjusting a rotation speed of each of the one or more propellers.

A method of analyzing a propeller status of a wireless aerial robot can include measuring status information related to the propeller status by a sensor of a propeller; determining whether an operation of the propeller is abnormal based on the status information; transmitting the status information and operation information regarding whether an operation of the propeller is abnormal to a control unit using short range wireless communication; and analyzing, by the control unit, a flight status of the wireless aerial robot based on the status information and the operation information regarding whether the operation of the propeller is abnormal.

Flight control method and apparatus for multi-rotor aircraft that is programmed for varied control commands and conditions in the control of the aircraft in flight.

Provided is an airbag device for a flying object sufficiently having a performance of protecting a battery.

An airbag device 1 is an airbag device for a flying object including an upper cover member 19 and a lower cover member 20 as a housing, and a battery 24 provided inside the housing and includes an expandable member 2 which is provided inside the housing of the flying object 10 and is expandable inside the housing, a gas generator 3 which is connected to the expandable member 2 and receives a predetermined amount of current to make gas flow into the expandable member 2, and a current supply section which supplies current to the gas generator 3 according to collision of the flying object 10.

PROBLEM: To provide a chemical spraying drone (unmanned air vehicle) in which minimizes chemical drift outside the field by a simple structure without additional equipment and complicated control.

SOLUTION: To provide a chemical spraying drone that actively uses the air flow made by rotors for spraying, comprising chemical spray nozzles and rotors (preferably two-stage rotors), wherein the chemical spray nozzles are positioned under the rotors and under a circular area with its center at a point offset by a predetermined distance rearward with respect to the flying direction from the rotor's rotation axis, its radius 90 percent of the radius of the rotor blade, on a straight line with a depression angle of about 60 degrees rearward from the horizontal line passing through the rotor's rotation axis. The position of the chemical spray nozzles may be dynamically adjusted.

A motor assembly including a housing, a first rotor (R1, R1) and a second rotor (R2, R2) provided in the housing. The first rotor (R1, R1) is configured to drive a first output shaft, and the second rotor is configured to drive a second output shaft.

A VTOL aircraft comprising a plurality of motor assemblies, each configured to generate thrust by movement of air past the motor assembly along a respective axis of thrust of the motor assembly, and a wing, wherein 1) the orientations of the axes of thrust are each fixed, during operation of the aircraft, at a constant respective pitch angle oblique to a pitch orientation of the wing; 2) the plurality of motor assemblies is operable together to both fully support the aircraft in a hovering mode, and to propel the aircraft forward in a forward flight mode; 3) the wing does not intersect with any right cylinder centered on any motor assembly and having a central longitudinal axis aligned with the axis of thrust of the motor assembly, and having a radius equal to a radius of a propeller of the motor assembly.