An unmanned aerial vehicle (UAV) is described. The UAV includes a first battery to power multiple first and multiple second electronic components of UAV. A power consumption of each first electronic component is greater than a power threshold. A power consumption of each second electronic component is less than or equal to the power threshold. The UAV includes a generator and a battery management system (BMS). The generator generates an electrical power through rotation of a shaft of a motor of UAV. The BMS charges the first battery using the electrical power generated by the generator when the UAV is during operation and a stored charge of the first battery drops to a first predefined level, and charges a second battery using the stored charge of the first battery when a stored charge of the second battery drops to a second predefined level.

An unmanned aerial vehicle (UAV) is described. The UAV includes a first battery to power multiple first and multiple second electronic components of UAV. A power consumption of each first electronic component is greater than a power threshold. A power consumption of each second electronic component is less than or equal to the power threshold. The UAV includes a generator and a battery management system (BMS). The generator generates an electrical power through rotation of a shaft of a motor of UAV. The BMS charges the first battery using the electrical power generated by the generator when the UAV is during operation and a stored charge of the first battery drops to a first predefined level, and charges a second battery using the stored charge of the first battery when a stored charge of the second battery drops to a second predefined level.

A mobile object includes a battery, a coolant, and a discharger. The coolant in a solid state is disposed around the battery and is liquefied by heat transferred from the battery. The discharger discharges the coolant liquefied out of the mobile object.

Techniques for deicing propellers for mobile platforms are disclosed. In one embodiment, a system is provided. The system may include a propeller comprising a propeller blade having a channel extending from an ingress aperture to an egress aperture along a longitudinal axis of the propeller blade. The system may further include a cowl comprising an air duct configured to direct heated air into the channel to deice the propeller blade. The cowl may be configured to selectively couple to the propeller and an electric motor and form a seal between the cowl and the electric motor to capture the heated air exuded by the electric motor. Additional systems and methods are also disclosed.

An unmanned aerial vehicle (UAV) includes a heat dissipation device, an inertial measurement unit (IMU), and a control module. The heat dissipation device includes an air guiding cover and a heat conduction plate. The air guiding cover includes an air duct configured to guide an airflow, and the heat conduction plate directly constitutes a portion of a sidewall of the air duct. The IMU module is received within the air duct. The control module is located outside the air duct and disposed at a side of the heat conduction plate that faces away from the IMU module. Heat generated by the IMU module is taken away directly by the airflow within the air duct.

A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

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.

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.

A heat dissipation device includes an air guiding cover and a heat conduction plate. The air guiding cover includes an air duct configured to guide an airflow and including a mounting window formed on a sidewall of the air duct, an air inlet formed at a first end of the air duct, and an air outlet formed at a second end of the air duct. The heat conduction plate is disposed at the mounting window and covers the mounting window.