Embodiments of a propulsion system are provided herein. In some embodiments, a propulsion system for an aircraft may include an electrical power supply; a motor coupled to the electrical power supply, wherein the electrical power supply provides power to the motor; and a fan disposed proximate a rear portion of an aircraft and rotatably coupled to the motor, wherein the fan is driven by the motor.

A flying vehicle propulsion system comprises a propulsor, a drive system, a heat exchanger, and a housing in which the heat exchanger is provided. The propulsor produces a propulsor fluid flow. In a first operation configuration of the propulsion system, at least part of the propulsor fluid flow is incident on the exchanger. A propulsor fluid flow inlet port of the housing fluidly communicates with a chamber of the housing on an inlet side of the exchanger. The inlet port receives the propulsor fluid flow for ingestion into the chamber and exchanger and comprises a valve to close the port when the valve is closed and open the port when the valve is open. The valve is biased such that at least one of: the valve opens passively under a propulsor fluid flow rate influence above a pre-defined threshold impinging on the valve; and the valve closes passively under a biasing influence.

A flying vehicle propulsion system comprises a propulsor, a drive system, a heat exchanger, and a housing in which the heat exchanger is provided. The propulsor produces a propulsor fluid flow. In a first operation configuration of the propulsion system, at least part of the propulsor fluid flow is incident on the exchanger. A propulsor fluid flow inlet port of the housing fluidly communicates with a chamber of the housing on an inlet side of the exchanger. The inlet port receives the propulsor fluid flow for ingestion into the chamber and exchanger and comprises a valve to close the port when the valve is closed and open the port when the valve is open. The valve is biased such that at least one of: the valve opens passively under a propulsor fluid flow rate influence above a pre-defined threshold impinging on the valve; and the valve closes passively under a biasing influence.

A variable-geometry cooling airflow management system and method for managing the cooling of a fuel cell on an aerodynamic vehicle (such as an aircraft). The cooling management is achieved by providing a conduit having a fan, radiator, and variable-geometry openings (such as variable-geometry inlet and variable-geometry outlet) at the conduit ends. Heat from the fuel cell is transferred to a coolant, which then flows through the radiator in the conduit. Cooling airflow passes over the radiator to provide fuel cell cooling. The amount of cooling airflow over the radiator is adjusted by varying the size of the variable-geometry inlet, the variable-geometry outlet, or both. Adjustments are made based on the operational parameters of the aircraft such as airspeed and flight configuration. A fan also may be located in the conduit, a speed of which is varied by the control system based on the operational parameters of the aircraft.

A variable-geometry cooling airflow management system and method for managing the cooling of a fuel cell on an aerodynamic vehicle (such as an aircraft). The cooling management is achieved by providing a conduit having a fan, radiator, and variable-geometry openings (such as variable-geometry inlet and variable-geometry outlet) at the conduit ends. Heat from the fuel cell is transferred to a coolant, which then flows through the radiator in the conduit. Cooling airflow passes over the radiator to provide fuel cell cooling. The amount of cooling airflow over the radiator is adjusted by varying the size of the variable-geometry inlet, the variable-geometry outlet, or both. Adjustments are made based on the operational parameters of the aircraft such as airspeed and flight configuration. A fan also may be located in the conduit, a speed of which is varied by the control system based on the operational parameters of the aircraft.

An aircraft comprises a fuselage; wings; engines connected to the wings; a set of liquid hydrogen tanks; a vent located on the tail on the fuselage; a conduit system connecting the liquid hydrogen tanks to the vent; and a controller. The controller is configured to control the conduit system to remove gaseous hydrogen in the set of liquid hydrogen tanks to travel through the conduit system and exit at the vent in response to pressure in the set of liquid hydrogen tanks being greater than a specified tolerance.

An aircraft and method, including a power distribution network and a set of dischargeable power system modules. The dischargeable power system module can include a chassis, a set of replaceable dischargeable energy modules selectively interconnected within the chassis, and an energy management module having a controller module configured to operably control the power distribution from the set of energy modules during aircraft operations, based on the energy demands of the respective subset of the power-consuming subsystems.

An aircraft and method, including a power distribution network and a set of dischargeable power system modules. The dischargeable power system module can include a chassis, a set of replaceable dischargeable energy modules selectively interconnected within the chassis, and an energy management module having a controller module configured to operably control the power distribution from the set of energy modules during aircraft operations, based on the energy demands of the respective subset of the power-consuming subsystems.

A fuel cell air mobility vehicle includes a fuel cell stack that provides power required for flight; a drain valve that discharges condensate generated through power generation of the fuel cell stack to an outside; and a controller that controls opening and closing of the drain valve based on a state of the power generation of the fuel cell stack, a flight state of an air mobility vehicle, a flight position of the air mobility vehicle, or a state of an external environment of the air mobility vehicle.

A fuel cell air mobility vehicle includes a fuel cell stack that provides power required for flight; a drain valve that discharges condensate generated through power generation of the fuel cell stack to an outside; and a controller that controls opening and closing of the drain valve based on a state of the power generation of the fuel cell stack, a flight state of an air mobility vehicle, a flight position of the air mobility vehicle, or a state of an external environment of the air mobility vehicle.