Example systems, methods, and apparatus are disclosed herein. Disclosed systems include a superconducting (SC) motor to power a propulsor of an aircraft and a liquid hydrogen (LH2) subcooling system including a primary flowline fluidly coupled to a cooling assembly of the SC motor, a secondary…
An electric power conversion system (300) comprising: an alternating current (AC) source (302) comprising a plurality of AC terminals (306) for conducting AC power; a voltage source (334) electrically coupled to the AC terminals (306); and a controller (80) operably coupled to the voltage source…
A governor of an integrated drive generator includes a housing (38), and a rotating sleeve extending at least partially through a housing opening in the housing (38). The rotating sleeve is configured to rotate about a sleeve axis. A gear (78) is secured to the rotating sleeve and rotatable…
An electrical propulsion system includes an electrical motor configured to drive one or more propellers of the aircraft, a capacitor configured to stabilize a direct current (DC) bus voltage, a first inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to alternate…
A motor assembly for a propulsion system, the motor assembly including a motor housing; a rotor; a power inverter; a main shaft; wherein the main shaft extends through the rotor; and a fluid distribution system including a fluid reservoir; a pump configured to distribute a fluid to a component of…
An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL…
An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL…
The present disclosure relates to a fuel cell system (100) comprising a fuel cell (110), a fuel tank (130), a fuel distribution pipe (135) fluidly connecting the fuel tank (130) with a fuel inlet (116) of the fuel cell (110), a shroud (137) surrounding at least a portion of the fuel distribution…
A hybrid-electric propulsion system is provided that includes a thermal engine, an electric motor, a battery, a battery management unit (BMU), an electrical distribution bus, an artificial intelligence (AI) model, and a monitoring system (MS) controller. The electrical distribution bus electrically…
An expansion tank system (2) for a liquid cooling system (54) is proposed, comprising a first chamber (30) for receiving a coolant, the first chamber (30) having a first coolant port (8), a second chamber (30) for storing a pressurized gas, a first gas conveying device (36) connected to the first…
A method for balancing a rotor of an electric engine, comprising: identifying an axis of rotation of the rotor, determining an imbalance present in the rotor by rotating the rotor about the axis of rotation, wherein determining the imbalance includes rotating the rotor and detecting an amplitude of…
Systems, apparatuses, and methods for overcoming the disadvantages of current air transportation systems that might be used for regional travel by providing a more cost effective and convenient regional air transport system. In some embodiments, the inventive air transport system, operational…
An electric engine for a vertical takeoff-and-landing aircraft comprising an electric motor assembly including a stator and a rotor. The electric engine may comprise an inverter assembly, a gearbox assembly including a sun gear, and a main shaft including a length of the main shaft that extends…
A hybrid electric propulsion (HEP) system of an aircraft includes a gas turbine engine configured to generate rotational power, and an electric propulsion system configured to generate at least one of thrust or lift for operation of the aircraft. The propulsion system includes a propulsor and an…
L'invention concerne un ensemble de connexion (10) entre deux portions (10a, 10b) d'une canalisation comprenant un conduit intérieur (10i) pour le transport d'un fluide cryogénique, l'ensemble (10) comprenant deux brides (11a, 11b) respectivement agencées aux extrémités des portions (10a, 10b) de…
An electrical propulsion system includes an electrical motor configured to drive one or more propellers of the aircraft, a capacitor configured to stabilize a direct current (DC) bus voltage, a first inverter circuit coupled to the capacitor and configured to convert the DC bus voltage to alternate…
A vertical takeoff and landing aircraft includes a starboard wing, a port wing, first and second tilt rotors coupled to the port and starboard wings respectively, and first and second batteries. A pair of control surfaces are arranged on a first side of the mid-sagittal plane of the aircraft, the…
An aircraft having a fuel cell () and an air supply device () for supplying air for operating the fuel cell () and for cooling a heat exchanger () connected to the fuel cell (), the aircraft () having at least one air duct () whose cross section widens in the direction of flow () of the air…
An electric propulsion system comprising an electric motor assembly. The electric motor assembly may include a housing having an internal volume, a stator ring disposed about a perimeter of the internal volume, and a rotor positioned within the stator. The electric motor assembly may include a main…
An electric propulsion system comprising an electric motor assembly. The electric motor assembly may include a housing having an internal volume, a stator ring disposed about a perimeter of the internal volume, and a rotor positioned within the stator. The electric motor assembly may include a main…
An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL…
An electrical propulsion system for a vertical take-off and landing (VTOL) aircraft comprises an electrical motor assembly and an inverter assembly. The inverter assembly comprises a housing, a capacitor assembly, at least one printed circuit board assembly (PCBA), and a plurality of positioning…
In an embodiment, a system may comprise at least two power supplies which may comprise a first power source, a first step-down converter, a first switching device, a first bus, a second power source, a second step-down converter, a second switching device, and a second bus, the first and second…
L'invention a pour objet un dispositif de regroupement de piles à combustible comprenant :- au moins deux piles à combustible (32),- un support (58) comportant un carter (60),- au moins une nourrice (40) configurée pour alimenter en fluide les piles à combustible (32),- au moins un collecteur (42)…
A propulsion assembly for an aircraft, having a T-shaped chassis with a horizontal structure and a vertical structure, a gearbox fastened to a front of the chassis, and a propulsion system having the following propulsion elements: an electric motor driving the components of the gearbox, a fuel…
Fuel cell and power train (FCPT) systems are provided and adapted to being operatively mounted at a tail section of an aircraft fuselage. The FCPT systems will include port and starboard subsystems each being comprised of a nacelle adapted to being laterally attached to a respective side of the…
In an embodiment, a system may comprise at least two power supplies which may comprise a first power source, a first step-down converter, a first switching device, a first bus, a second power source, a second step-down converter, a second switching device, and a second bus, the first and second…
A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric…
A voltage converter for an aircraft electrical system includes an input power line configured to receive input electrical power, an output power line configured to supply output electrical power to aircraft loads, conversion circuitry, and a controller. The conversion circuitry is configured to…
In an aspect, a modular battery configuration with a centralized bus on an electric aircraft, including an electric aircraft which comprises a propulsor configured to generate thrust and a centralized electrical bus connected to the propulsor. A plurality of modular battery packs is configured to…