The invention provides systems and methods for isolating one or more sensors within an unmanned aerial vehicle (UAV). The method may comprise providing a UAV that includes a housing forming a central body of the UAV. The UAV may also include a first compartment of the central body with one or more electrical components (1) disposed therein, and (2) adapted to affect operation of the UAV. Further, the UAV may include a second compartment of the central body that is isolated from the first compartment such that the barometric pressure in the second compartment is independent of the barometric pressure in the first compartment. Additionally, the method may comprise disposing the one or more sensors within the second compartment of the UAV.

A heat dissipation structure includes a housing configured to receive a heat generating device. The housing includes a first air inlet, a first air outlet, and an alloy heat dissipation device disposed in the housing and including heat dissipation fins disposed in parallel. A heat dissipation air channel is formed between two adjacent heat dissipation fins. The heat dissipation air channel includes a second air inlet and a second air outlet, the second air outlet being connected with the first air outlet. The heat dissipation structure further includes a heat dissipation fan configured to provide a heat dissipation air flow to an inside space of the housing. The heat dissipation fan is disposed inside the housing, and includes a third air inlet and a third air outlet. The third air inlet is connected with the first air inlet and the third air outlet is connected with the second air inlet.

An unmanned aerial vehicle (UAV) includes a vehicle body and a flight control circuit. The vehicle body includes a housing and a fan. The housing includes two vents arranged at two ends of the housing and in communication with an internal space of the housing. The two vents and the internal space form a heat dissipation air passage. The fan is arranged at one of the two vents, and is configure to drive external air into the heat dissipation air passage and expel internal air from the heat dissipation air passage. The flight control circuit is arranged inside the housing and is configured to control flight parameters of the UAV. The heat dissipation air passage is configured to dissipate heat generated by the flight control circuit.

A turbocharged gas turbine engine with an electric generator to provide electrical power for an aircraft (e.g., UAV) with multiple propulsor fans each driven by an electric motor, where the engine includes a low spool that drives a main fan and a high spool that drives a high speed electric generator. The low pressure compressor supplies low pressure air to an inlet of the high pressure compressor. A row of stator vanes in the high pressure turbine is cooled using cooling air bled off from the low pressure compressor outlet that is passed through an intercooler and a boost compressor, where the spent vane cooling air is discharged into the combustor. The low pressure turbine and the two compressors each include a variable inlet guide vane to control the power level of the engine. Bypass flow from the main fan is used to cool hot parts of the engine.

A vibration isolating thermally conductive connector includes a first thermally conductive element configured to draw heat from a heat source, a second thermally conductive element separated from the first thermally conductive element, and a flexible seal connected with the first and second thermally conductive elements and defining an enclosed cavity between the elements. The enclosed cavity contains a thermally conductive liquid, and allows limited movement of the second and first thermally conductive elements with respect to each other while maintaining thermal connection.

In some embodiments, systems and methods are provided that limit the change in temperature and/or control a temperature of a product during delivery. Some embodiments provide systems comprising an unmanned delivery vehicle (UDV) comprising: a body comprising a nanotechnology insulation material, wherein the nanotechnology insulation material comprises material having been manipulated at a molecular level during the macroscale fabrication of the nanotechnology insulation material to enhance insulation effectiveness; at least one propulsion system; a control circuit coupled with the at least one propulsion system to control the operation of the at least one propulsion system and control a direction of travel of the UDV, wherein the body physically supports the propulsion system and the control circuit; and a product cavity defined within the body and configured to receive at least one product while the at least one product is transported by the UDV to a delivery location.

A power module includes a turbine arranged along a rotation axis, an interconnect shaft fixed in rotation relative to the turbine, and a compressor with a regenerative compressor wheel. The regenerative compressor wheel is fixed in rotation relative to the interconnect shaft supported for rotation with the turbine about the rotation axis. Generator arrangements, unmanned aerial vehicles, and methods of generating electrical power are also described.

The present disclosure is directed to unmanned aerial vehicle (UAV) comprising a convertible body operably coupled to at least one sensor, and further configured to rotate at least about a longitudinal axis, thereby providing a full field of regard for the at least one sensor, and a plurality of arms extending laterally from the convertible body, each arm of the plurality of arms having a rotor assembly coupled thereto.

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.

An unmanned vehicle capable of operating in harsh environments is disclosed. The unmanned vehicle includes an aerial platform, a piloting system supported by the aerial platform, a medium source supported by the aerial platform, and a control system having a processor running computer executable code that actuates the medium source to emit a medium away from the aerial vehicle with an intensity sufficient to disorient a subject when the medium interacts with an exteroceptive sense of a subject.