A multicopter includes: a support; rotors supported by the support; an electrical equipment that supplies power for rotationally driving the rotors; a circuitly that controls a flight of an airframe by individually adjusting a rotor speed of each of the rotors; and a cooling unit that cools the electrical equipment. The cooling unit includes a heat exchanger, a refrigerant circulating through the heat exchanger and the electrical equipment, and a pump that circulates the refrigerant.

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 (UAV) includes a fuselage, electronics disposed with the fuselage, a heat sink, and a solar shield. The heat sink is thermally connected to the electronics and includes a cooling plate disposed on or extends through an exterior surface of the fuselage. The cooling plate is exposed to an external environment of the UAV to conduct heat from the electronics to the external environment via convection. The solar shield extends over the cooling plate and defines an air scoop within which the cooling plate is disposed. The air scoop directs airflow from the external environment across the cooling plate. The solar shield shades the cooling plate from solar radiation to prevent or reduce solar heating of the cooling plate.

Systems for wing structure and attachment to frame for Unmanned Autonomous Vehicle (UAV) are disclosed herein. In one embodiment, a UAV includes an H-frame having a wing spar secured to two or more boom carriers. The wing spar includes two or more mounting locations, where each of the two or more mounting locations of the wing spar secures a horizontal propulsion unit. The boom carriers include a plurality of mounting locations, each of the plurality of mounting locations of the boom carriers securing a vertical propulsion unit. The UAV also includes a pre-formed wing shell attached to the H-frame.

An innovative passive cooling solution with sealed UAV enclosure system allows heat from a semiconductor chip to be dissipated to the ambient environment through evaporation/condensation phase-change cooling and air cooling a heat sink such as a fin without any additional power consumption to operate cooling solution. One example of such a solution may include a pipe with a fin and a fluid. The pipe may include a wick structure along an inner surface of the pipe configured to allow the fluid to travel within the wick structure and to allow a vapor form of the fluid to exit the wick structure towards a center of the pipe.

Temperature management systems for aerial vehicles may include heat pipes that are thermally connected to components that generate heat. The heat pipes may be routed through or adjacent to a propeller or propulsion airflow, or within or across a vehicle airflow, to dissipate heat from the components. A heat pipe may be selected from a plurality of heat pipes based on measured temperatures of components that generate heat, operational characteristics of the aerial vehicle and/or one or more propellers, and/or measured temperatures of other components that may be heated. Additional temperature management systems may include cool air ducts and cool air pipes that may be routed from a propeller or propulsion airflow, or a vehicle airflow, to components that generate heat or other components that may be cooled.

A vehicle such as an unmanned aerial vehicle (UAV) can include a heat-generating electronic device coupled with a heat exhaust element by a vibration isolating thermal connector. The thermal connector includes a first heat-conducting element configured to draw heat from the electronic device, a second heat-conducting element separated from the first heat-conducting element, and a flexible seal connected with the first and second heat-conducting elements and defining an enclosed cavity between the elements. The enclosed cavity contains a heat conducting liquid, and allows limited movement of the first and second heat conducting elements with respect to each other while maintaining thermal connection.

An integrated multimode thermal energy transfer system, method and apparatus for full-scale clean fuel electric-powered multirotor aircraft with automatic on-board-capability to provide sensor-based temperature awareness and adjustment to critical components and zones of the aircraft. Automatic computer monitoring, including by a programmed triple-redundant digital autopilot computer, controls each motor-controller and motor to produce pitch, bank, yaw and elevation, while simultaneously measuring, calculating, and adjusting temperature and heat transfer of aircraft components and zones, to protect critical components from exceeding operating parameters and to provide a safe, comfortable environment for occupants during flight. By using the results of the measurements to inform computer monitoring, the methods and systems can use byproducts including thermal energy disparities and differentials related to both fuel supply systems and power generating systems to both add and remove heat from different aircraft zones to improve aircraft function, comfort, and efficiency.

Unmanned aerial vehicles and methods for unmanned aerial vehicles are described in various aspects herein. In at least one aspect, an unmanned aerial vehicle (UAV) includes a cooling structure configured to dissipate heat, and an air channel configured to dissipate heat from the cooling structure via an airflow. The UAV also includes at least one fan configured to provide the airflow through the air channel, and one or more sensors configured to receive ambient condition information associated with an ambient condition in a vicinity of the UAV. The UAV further includes one or more processors configured to trigger a reduction of the airflow through the air channel based on the ambient condition information. The ambient condition information may include dust information indicating a dust pollution in the vicinity of the UAV. Additionally or alternatively, the ambient condition information may include weather information indicating rain in the vicinity of the UAV.

The present disclosure provides an Unmanned Ariel Vehicle (UAV). The UAV includes a fuselage including a housing, a core control board disposed in the housing, and a battery, the housing including a battery compartment, and the battery being disposed in the battery compartment; an arm disposed on the fuselage; and a power assembly disposed on the arm. The core control board is disposed above the battery, a payload receiving cavity is disposed at a front lower end of the housing, a rear-bottom view component is disposed at a rear end of the housing and electrically connected to the core control board, and the battery compartment is disposed at a middle position under the housing.