The present disclosure provides an unmanned aerial vehicle (UAV) having a housing containing electronic components required of the UAV and a heat transfer device for cooling heat generated by said electronic components; at least one boom for connecting said housing to at least one propeller. The boom includes one or more inlet located on a first surface of the boom and within an airflow of said at least one propeller; at least one outlet on a second surface of the boom; a hallow channel extending in interior of the boom from said at least one inlet to said at least one outlet, wherein said airflow generated by said at least one propeller passes into said at least one inlet through the hollow channel to said at least one outlet providing cooling for said heat transfer device.

An unmanned aerial vehicle according to various embodiments includes: a housing; a communication circuit, wherein the communication circuit establishes wireless communication with an external controller; and a plurality of propulsion systems connected to the housing, wherein the propulsion systems include: a motor; a rotation shaft having an axis extending in a first direction, wherein a first end is connected to the motor, and wherein the rotation shaft is rotates in a first direction by the motor; a cap structure fixed to the second end of the rotation shaft, a propeller including: a hub including a through-hole formed in the first direction, such that the rotation shaft rotatably passes through the through-hole, wherein the propeller is detachably connected to the cap structure, such that, when an external force is exerted on the blade, the propeller is released from the cap structure to be freely movable along the axis toward the motor.

An aerial vehicle, preferably including: a rotary wing and a protection housing enclosing the rotary wing. An aerial vehicle, preferably including: a first rotary wing module including a first rotary wing and a second rotary wing module including a second rotary wing, wherein the first rotary wing module and the second rotary wing module are preferably operable between a folded configuration and an unfolded configuration. A method of aerial vehicle operation.

Techniques and architecture are disclosed for a multirotor vehicle having a rotor assembly with a plurality of rotors to provide upward thrust. Attached to the rotor assembly is a frame that includes a frame extension having a first end pivotally attached to the rotor assembly. The extension also includes a second end pivotally attached to a frame body. The vehicle further includes first and second actuators. The first actuator pivots the rotor assembly to position it within a horizontal plane to allow thrust generated by the rotor assembly to lift the vehicle. The second actuator pivots the rotor assembly within the horizontal plane so that thrust generated by the rotor assembly lifts the vehicle. The vehicle also includes a harness connected to the frame and configured to secure an operator's torso to the multirotor vehicle.

A repeatably reconfigurable robot, comprising at least two printed circuit board (PCB) rigid sections, at least one PCB flexible section coupled to the at least two PCB rigid sections, at least one wheel, hybrid wheel propeller, wheel and propeller, or hybrid wheel screw propeller rotatably coupled to at least one of the at least two PCB rigid sections and at least one actuator coupled to the at least two PCB rigid sections, wherein the at least one actuator folds and unfolds the repeatably reconfigurable robot.

There is provided an electric apparatus including a battery (6); a first pair of motors (3a, 3d) coupled with a first pair of wings and a second pair of motors (3b, 3e) coupled with a second pair of wings; and a first motor control circuitry (12ad) configured to control, the first pair of motors and a second motor control circuitry (12be) configured to control the second pair of motors. The battery (6) is configured to supply power to the first motor control circuitry (12ad) via a first power line, and the battery (6) is configured to supply power to the second motor control circuitry (12be) via a second power line.

A flight vehicle control device includes: an identification information storage unit in which identification information for identifying a flight vehicle or a user of the flight vehicle is stored; a wireless communication unit that receives, through a wireless base station, airspace information about an airspace in which the flight vehicle flies, based on the stored identification information; an own vehicle position measuring unit that measures a position of the flight vehicle; and a flight state control unit that controls a flight vehicle based on the received airspace information and the measured position of the flight vehicle.

A remote controlled aircraft includes an aircraft that may be flown. A plurality of light emitters is coupled to the aircraft. A plurality of fans is coupled to the aircraft. Each of the fans may move air thereby facilitating each of the fans to urge the aircraft to fly. A control unit is coupled to the aircraft and the control unit is electrically coupled to each of the fans. The control unit includes a global positioning system. Thus, the control unit may identify a position of the aircraft with respect to Earth. A remote control is provided and the remote control may be manipulated. The remote control is in electrical communication with the control unit such that the remote control controls directional flight of the aircraft.

An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure.

Disclosed is a system and method for calibrating a magnetometer of a compass. With a global navigation satellite system receiver, a current position is determined. The determined position is used to determine a magnetic inclination (e.g., by a global magnetic field model such as the World Magnetic Model). The calibration system may perform different calibration sequences based on the magnetic inclination. In a first calibration sequence, performed responsive to a determination that a magnetic inclination (or the absolute value of the magnetic inclination) is less than a threshold, magnetic field data is measured by the magnetometer as it is rotated through horizontal rotation paths. If the magnetic inclination is greater than the threshold, magnetic field data is measured by the magnetometer as it is rotated through vertical rotation paths. The measured magnetic field data may be used to determine calibration values for the magnetometer compass.