A propulsion system for an aircraft comprises a closed cooling circuit which has at least one main segment and at least two secondary segments, in which a heat-transfer fluid circulates. Each secondary segment has: a leak detection device, a shut-off valve, and a non-return valve. The cooling circuit also has electronic circuitry configured to close the shut-off valve of a secondary segment when a leak is detected by the leak detection device of said secondary segment.

A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.

The invention relates to a sanitation treatment system and methods for use in association with commercial passenger vehicles such as aircraft. The sanitation system may operate along with a filtration system in an air distribution system associated with an aircraft or like commercial passenger vehicles and/or to provide disinfected air and surfaces in the passenger cabin associated with the aircraft or like vehicle.

An embodiment of an electric motor assembly includes a stator assembly extending generally along the longitudinal axis and at least partially enclosing a rotor assembly also extending along the longitudinal axis. The rotor assembly includes a rotating portion and one or more sets of rotor windings. The stator assembly includes a stationary housing having at least an inner wall and an outer wall, and one or more sets of stator windings in electromagnetic communication with the one or more sets of rotor windings. A heat exchanger is integrally formed into the housing, and includes a plurality of dividing walls extending between the inner and outer housing walls. The plurality of dividing walls are arranged at least partially circumferentially around the longitudinal axis to define, with the inner and outer walls, a corresponding plurality of integral heat exchanger channels arranged at least partially circumferentially around the one or more sets of stator windings. A plurality of rib turbulators are disposed on at least a channel-facing surface of the inner wall.

A louvre system controls a flow of cooling air to a heat-generating element mounting inside a wing of an aircraft. The louvre system includes a louvre operably connected to the wing and structured to be rotatable to control airflow through an air intake of the wing into an interior of the wing. A louvre actuation mechanism is operably connected to the louvre and configured to control rotation of the louvre. A memory is communicably coupled to a processor and stores a louvre control module configured to autonomously control operation of the louvre actuation mechanism to control rotation of the louvre responsive to a temperature of a heat-generating element mounted in the wing interior.

A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.

A vertical takeoff and landing unmanned aerial vehicle and a cooling system for the unmanned aerial vehicle. Heat dissipation in an arm of an unmanned aerial vehicle is achieved by providing a forward-facing opening at the front end of each of a left linear support and a right linear support of the unmanned aerial vehicle, thereby achieving the purposes of lowering temperature in the arm and protecting equipment in the arm.

A battery system includes a plurality of battery modules each formed from a plurality of battery cells. A shared cooling structure is thermally coupled to each of the battery modules. The shared cooling structure is configured to conduct heat relative to the battery modules. A thermal interface is disposed between the battery cells of each battery module and the shared cooling structure. Each thermal interface is configured to transition from a first thermal conductivity state to a second thermal conductivity state when heat generated by the respective battery cells exceeds a threshold level. The second thermal conductivity state is lower than the first thermal conductivity state such that after one of the thermal interfaces has transitioned from the first thermal conductivity state to the second thermal conductivity state, heat transfer from the respective battery cells to the shared cooling structure is reduced.

In an aspect of the present disclosure is a system for cooling a high voltage (HV) cable on an electric aircraft, including a fuselage configured to receive the HV cable, including a first side comprising a first venting closure movable between an open position and a closed position. The fuselage may further comprise a second side opposite the first side, the second side comprising a second venting closure movable between an open position and a closed position; wherein the first and second venting closures are configured to create a cooling channel between the first and second venting closures when the first and second venting closures are in the open position, wherein the cooling channel contacts the HV cable.

A UAV including a shroud with cooling openings to cool electronics in the UAV. The shroud includes propeller openings surrounding respective propellers. The propeller openings include intake openings that draw air from outside the shroud into the shroud to cool UAV components. The propeller openings are formed at an interface between an upper portion of the shroud and a lower portion of the shroud. The UAV includes a selector, such as a dial, including exit openings under the selector that provide air outflow from the shroud.