A method and system for operating a hybrid propulsion system, includes controllably providing a first power to a first bus and a first inverter, electrically coupling a first motor with a second inverter by way of a second bus, operably converting, by the second inverter, the first power received by the first inverter to a starting power adapted for starting the first motor, and increasing, by the second inverter, the starting power to match the first power received.

A power reduction system for an energy storage system of an aircraft includes a controller configured to control power reduction of power supplied from the energy storage system to an aircraft engine supply bus; and an override switch configurable in an override state and a non-override state. The override switch is configured to: in the non-override state, permit the controller to control the power reduction according to a default configuration comprising one or more parameters that trigger the power reduction; and in the override state, control the power reduction to be performed according to a relaxed configuration that at least one of relaxes and omits the one or more parameters in the default configuration.

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 connects the electric motor and the BMU. The MS controller is in communication with the AI model, the electric motor, the BMU, and a memory storing instructions. The instructions when executed cause the MS controller to: receive a first operational parameter from the BMU unit; control the AI model to produce a predicted first operational parameter utilizing at least one electric motor operating parameter; and determine the presence of series arcing within the electrical distribution bus using the first operational parameter and the predicted first operational parameter.

An aircraft power plant is disclosed having a plurality of bladed rotors in flow communication driven by separate work producing devices. The work producing devices can take a variety of forms including an internal combustion engine and electric motor, for example. The bladed rotors can be associated with an aircraft pylon and can be driven independently to separate operating conditions to provide optimum performance. For example, the bladed rotors can be driven to separate operating conditions that improve a noise signature or performance of the aircraft.

A hybrid powertrain system and method includes a prime mover driving a generator/motor to produce an AC power output. The AC power output is applied to a rectifier which is controlled to transform the applied AC power to DC power to supply a DC Power bus at a selected voltage and current. An energy storage device is also connected to the DC power bus and the current flow between the energy storage device and the DC power bus is monitored and compared to preselected values and the results of that comparison are used to alter the operation of the rectifier to increase or decrease, as needed, the current provided to the DC power bus as electrical loads on the DC power bus change.

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 methods, and associated aircraft include a highly efficient plug-in series hybrid-electric powertrain (specifically optimized for aircraft operating in regional ranges), a forward compatible, range-optimized aircraft design, enabling an earlier impact of electric-based air travel services as the overall transportation system and associated technologies are developed, and platforms for the semi-automated optimization and control of the powertrain, and for the semi-automated optimization of determining the flight path for a regional distance hybrid-electric aircraft flight.

A vertical take-off aircraft with a propulsion drive for generating a driving force being effective in a horizontal direction and with a lift drive for generating a lifting force being effective in a vertical direction includes a motor for providing mechanical energy for the propulsion drive and a first generator for providing electrical energy for the lift drive. Moreover, the aircraft includes an exhaust gas turbocharger for the motor with a first turbine being driven by an exhaust gas flow of the motor, wherein the first turbine is configured to provide mechanical energy for the propulsion drive.

An aircraft engine includes a low pressure spool, a high pressure spool, and an alternative power source. The alternative power source is configured to add power to the high pressure spool. A controller is configured to determine a noise sensitive condition; and control, in response to determining the noise sensitive condition, the alternative power source to add power to the high pressure spool.

A flight controller of a flight vehicle includes an electric motor control unit for controlling each of a plurality of electric motors, and in a case where the plurality of electric motors are driven by electric power stored in a battery or in a case where the battery is charged with electric power generated by a generator, the electric motor control unit controls the plurality of electric motors in accordance with the state of the battery.

A vehicle includes a body, at least one propulsion system including an electric component, a strut extending between the body and the at least one propulsion system, and a cooling system operably coupled to the electric component of the at least one propulsion system. A portion of the cooling system is arranged within the strut.