A configurable unmanned aerial vehicle (UAV) may include swappable avionics that may be selectable for use with other UAV components to build a customized UAV just prior to deployment of the UAV that is configured to deliver a package to a destination. Various factors may be involved in the selection of the avionics, such as an availability of different avionics, payload requirements (size, weight, etc.), environmental conditions along an anticipated route of flight, a region of use of the UAV, compatibility, a distance of the flight, power considerations, security considerations, and/or other factors. The avionics may include various hardware and/or software which may provide control output (e.g., data, power, and/or mechanical) to other components and/or systems, including a propulsion system. Coupling devices may selectively couple the avionics to other components of the UAV, such as to a battery, a cargo bay or package, and/or to a propulsion system.

There is disclosed a multicopter vertical takeoff and landing (VTOL) aircraft. The aircraft comprises am airframe with spatial design, a pilot seat, a cockpit, controls, engine units, engine compartment, control system, remote control system. The airframe consists of a central section and, at least, two peripheral sections, wherein peripheral sections can be folded up or down, or be retracted under the central section. The central section and peripheral sections of the airframe have spatial design. Each of the peripheral sections comprises at least three standard engine compartments which are connected to each other. Inside each engine compartment there is an engine unit which comprises at least one engine and at least one horizontally rotating propeller together with the control hardware. Each engine unit is an autonomous member of the distributed control system (DCS).

An unmanned aerial vehicle adapted for hover and short/vertical take-off and landing (S/VTOL) is disclosed. The vehicle comprises: a body having an aspect-ratio less than two and having therein a payload volume, at least one propeller located forward of the body, at least one rudder. The body may have an inverse Zimmerman planform which provides lift as air flows across the body in horizontal flight/fixed wing mode, and further adapted such that during hover and/or short/vertical take-off and landing (S/VTOL) the vehicle operates as a rotorcraft with the body oriented with the at least one propeller substantially above the body. The vehicle is suited to a method of inspection, such as power line inspection where large distances can be analysed efficiently by flying in fixed wing mode, but by transitioning to hover mode allows detailed inspection of selected areas.

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.

The present invention is aimed to provide a multi-functional flying platform with a simple structure, which is easy to operate and can achieve the mounting of different functional equipment. It includes rotor arm system and mounting plate (1). A plurality of evenly distributed fixing devices (2) are provided on the mounting plate (1). Mounting plate (1) is fixedly connected to rotor arm (3) of the rotor arm system by fixing device (2). A plurality of mounting positions (4) are provided on the lower side of the mounting plate (1). The present invention can be used in the field of agricultural aviation.

A vertical takeoff and landing aerial vehicle and a cooling system for the aerial vehicle. The vertical takeoff and landing aerial vehicle comprises at least one air inlet provided on the top side of a linear support below a lift propeller, and at least one air outlet provided on the linear support. In the vertical takeoff and landing stage of the aerial vehicle provided by the disclosure, airflow generated by rotation of a lift propeller forms a rapid-flowing spatial flow field, which can achieve efficient heat dissipation of a motor and an electronic speed controller in an arm; and in the vertical takeoff and landing unmanned aerial vehicle provided by the utility, the takeoff weight of the unmanned aerial vehicle cannot be increased, power consumption of airborne equipment cannot be increased, and interior space of the arm cannot be occupied.

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.

The present invention extends to a container venting system. A wall portion of a container includes a (e.g., thermo-sensitive) panel. Any portion of the panel exposed to sufficient heat crumbles or ruptures (e.g., without burning) creating an opening in the wall portion. In one aspect, a container is included in a vehicle (e.g., an Unmanned Aerial Vehicle (UAV)). The container includes a panel in an external wall of the vehicle. Any portion of the panel exposed to sufficient heat crumbles to create an opening in the external wall of the vehicle. A container can be a sealed container with the panel sealed to the wall portion or to the external wall of the vehicle. The interior of the sealed container can contain a battery cell. Creating an opening allows gases to vent out of the sealed container and/or to vent outside of the vehicle.

A gimbal configured to be implemented in an unmanned aerial system. The gimbal includes a payload interface; an end effector; a structure that includes composite skins, an internal structure, and integrated seals; integrated drive components; and at least one computer, where excess heat generated by the at least one computer is disposed of through a heat transfer surface integrated into the composite skin of the gimbal.

A system and method for converting onboard battery-powered, free-flight drones into ground-powered tethered drones that overcome the impediments designed into safeguarded free-flight drones. In combination with a ground-sourced power supply for the drone, power being delivered to the drone through a tether, the system comprises a battery emulating module that provides false signals to the drone's battery circuit board such that the onboard batteries may be removed and the alternative ground-based power source utilized without causing the drone's main circuit board to initiate a systems shutdown.