An aircraft propulsion module comprises a hydrogen storage system, an electrochemical converter (7) connected to the hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system (12) into electric energy, and an electric motor (5) electrically connected to the electrochemical converter, wherein the electric motor is adapted to generate thrust; wherein the propulsion module comprises at least one separation means (9) adapted to separate at least one component of the propulsion module from the propulsion module. An aircraft comprises at least one such aircraft propulsion module. A method for operating a propulsion module comprises that: during operation of the propulsion module, at least one separation means is actuated, by which actuation at least one component of the propulsion module is separated from the remaining propulsion module and then falls from the remaining propulsion module.

An aircraft propulsion module comprising a hydrogen storage system (9), at least one electrochemical converter (7) connected to the hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system into electric energy, and at least one electric motor (5) electrically connected to the at least one electrochemical converter, wherein the electric motor is adapted to generate thrust: wherein the propulsion module comprises a first part (1) and a second part (2), each of which comprise a respective fairing (4, 10); the first part and the second part are separable from each other; the first part comprises the at least one electrochemical converter and the at least one electric motor; and the second part comprises a hydrogen storage housing of the hydrogen storage system for storing a reusable hydrogen storage unit. An aircraft comprising at least one such aircraft propulsion module.

An aircraft propulsion module comprising a hydrogen storage system (9), at least one electrochemical converter (7) connected to the hydrogen storage system, wherein the at least one electrochemical converter is adapted to convert hydrogen supplied from the hydrogen storage system into electric energy, and at least one electric motor (5) electrically connected to the at least one electrochemical converter, wherein the electric motor is adapted to generate thrust: wherein the propulsion module comprises a first part (1) and a second part (2), each of which comprise a respective fairing (4, 10); the first part and the second part are separable from each other; the first part comprises the at least one electrochemical converter and the at least one electric motor; and the second part comprises a hydrogen storage housing of the hydrogen storage system for storing a reusable hydrogen storage unit. An aircraft comprising at least one such aircraft propulsion module.

An electric vehicle propulsion system includes an electric motor and a battery pack formed as a single, integrated unit. It is a self-contained, integrated electric propulsion system. It disrupts the long-established engineering paradigm that the electric motor and the battery pack have to be designed, built and installed as separate systems.

This disclosure relates to power sources that are structurally integrated with an airplane wing. The power sources include rechargeable batteries, such as Ni-Cd, NiMH, and/or Li-ion batteries; and/or hydrogen fuel cells. The power sources can be located on the airplane wing, inside of the wing, and/or located on the bottom of the wing, and combinations thereof. The airplane wing can be made of a metallic structural material or a composite structural material. Layers of a Li-ion battery can conformally overlay the upper metallic structural skin of a metallic wing, and the electrically-conductive metallic airplane wing itself acts as a cathode (or anode) of the battery. The airplane wing can be made of laminated sheets of carbon-fiber composites (CFCs). The power sources can be sandwiched inside of an upper and/or a lower section of the composite airplane wing. Lithium-ion batteries can be connected in series to provide a greater voltage.

A power supply system of an aircraft includes a fuel cell that generates electrical energy, a converter device including a mode switch device that supplies power to a first motor device through a first output terminal and switches a connection between an output node of the fuel cell and the first output terminal, a first battery device that supplies a voltage from a first battery to a second motor device through a second output terminal and connects the second output terminal with the first output terminal under control of the mode switch device, and a processor that controls the mode switch device to enter an emergency mode when detecting an error in the converter device or the first battery device and connects the first output terminal with the second output terminal.

A power supply system of an aircraft includes a fuel cell that generates electrical energy, a converter device including a mode switch device that supplies power to a first motor device through a first output terminal and switches a connection between an output node of the fuel cell and the first output terminal, a first battery device that supplies a voltage from a first battery to a second motor device through a second output terminal and connects the second output terminal with the first output terminal under control of the mode switch device, and a processor that controls the mode switch device to enter an emergency mode when detecting an error in the converter device or the first battery device and connects the first output terminal with the second output terminal.

An aircraft includes a chamber (1), a processor, a memory, and a compressor system (12b) in fluid communication with the chamber. The compressor system (12b) configured to selectively pressurize the chamber (1). The chamber supports a fuel cell (26), a motor, and/or electrical components that electrically communicate with the fuel cell (26) and the motor to power the aircraft. The memory includes instructions stored thereon, which when executed by the processor, cause the aircraft to receive an altitude value of the aircraft, and selectively pressurize the chamber using the compressor system based on the received altitude value to reduce corona discharge in the chamber.

An aircraft includes a chamber (1), a processor, a memory, and a compressor system (12b) in fluid communication with the chamber. The compressor system (12b) configured to selectively pressurize the chamber (1). The chamber supports a fuel cell (26), a motor, and/or electrical components that electrically communicate with the fuel cell (26) and the motor to power the aircraft. The memory includes instructions stored thereon, which when executed by the processor, cause the aircraft to receive an altitude value of the aircraft, and selectively pressurize the chamber using the compressor system based on the received altitude value to reduce corona discharge in the chamber.

A power generation system for an aircraft includes: a storage tank for storing hydrogen; a fuel cell configured to generate power from the hydrogen; a fuel supply line configured to supply the hydrogen from storage tank to the fuel cell; a fresh air supply line configured to supply air to a cabin air supply system; and a fuel-air heat exchange system, wherein the fuel supply line and the air supply line pass through the fuel-air heat exchange system such that the hydrogen cools the air in use.