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.

A device for the automated vertical take-off, vertical landing, and/or handling of an aerial vehicle with the aid of a robot, the device including a first connection module and a second connection module, each including a capture and/or release section that is active in a capture and/or release phase and a guide section that is active in a guide phase, and the first connection module and the second connection module being lockable in a holding position. An aerial vehicle capable of automatedly vertically taking off, vertically landing, or being handled with the aid of a robot, the aerial vehicle including a first connection module or a second connection module of such a device. An end effector for a robot for the automated vertical take-off, vertical landing, and/or handling of an aerial vehicle, the end effector including a second connection module or a first connection module of such a device.

This drone comprises a sensor for measuring representative data, comprising at least one measurement cell that is open to the atmosphere, at least a first laser source configured to inject, into the measurement cell, a first laser beam at a first wavelength characteristic of a first gas to be detected and a second laser source configured to inject, into the measurement cell, a second laser beam at a second wavelength characteristic of a second gas to be detected. The measuring sensor comprises a detector common to the two laser sources, said detector being configured to detect a first measurement signal originating from the measurement cell and resulting from injection of the first laser beam into the measurement cell and a second measurement signal originating from the measurement cell and resulting from injection of the second laser beam into the measurement cell.

This drone comprises a sensor for measuring representative data, comprising at least one measurement cell that is open to the atmosphere, at least a first laser source configured to inject, into the measurement cell, a first laser beam at a first wavelength characteristic of a first gas to be detected and a second laser source configured to inject, into the measurement cell, a second laser beam at a second wavelength characteristic of a second gas to be detected. The measuring sensor comprises a detector common to the two laser sources, said detector being configured to detect a first measurement signal originating from the measurement cell and resulting from injection of the first laser beam into the measurement cell and a second measurement signal originating from the measurement cell and resulting from injection of the second laser beam into the measurement cell.

In an aspect, a system for battery ventilation of an electric aircraft. A system includes an electric aircraft. An electric aircraft includes a plurality of battery cells. Each battery cell of the plurality of battery cells includes a battery tab. A system includes a sensor in electronic communication with a plurality of battery cells. A sensor is configured to measure battery cell data. A system includes a plurality of vents. Each vent of the plurality of vents is positioned by each battery tab of the plurality of battery cells. A system includes a flight controller. A flight controller is configured to receive battery cell data from a sensor. A flight controller is configured to determine a vent arrangement as a function of battery cell data. A flight controller is configured to position at least a vent of a plurality of vents as a function of a vent arrangement.

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.

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.

Battery modules for unmanned and human piloted electric aircraft comprise two planar substrates with electrochemical cells secured between to form load-bearing structural components from which fixed-wing aircraft with greater endurance can be constructed. The cells can be oriented perpendicular or parallel to the substrates, and in the latter case the substrates can include slots that the cells fit into. The cells can be secured to the substrates by adhesives, welding, soldering and the like. Battery modules can be formed to the shapes of fixed-wing aircraft parts such as wings.

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.

Thermal management system for unmanned aerial vehicles are disclosed. An example housing for an unmanned aerial vehicle includes a central portion defining a cavity. The housing also includes a first arm to support a first propeller. The first arm has a first proximal end coupled to the central portion and a first distal end spaced from the central portion. The first distal end defines an inlet. The first arm defines a first fluid path in communication with the inlet and the central cavity. The housing also includes a second arm to support a second propeller. The second arm has a second proximal end coupled to the central portion and a second distal end spaced from the central portion. The second distal end defines an outlet. The second arm defines a second fluid path in communication with the outlet and the central cavity. The inlet and outlet are in fluid communication via the first path, the central cavity and the second path.