A method of designing and manufacturing a power electronics converter for an electrical power system is provided. A circuit design for the power electronics converter is selected. A shape constraint for integrating the power electronics converter into the electrical power system is determined, and at least one multi-layer carrier substrate is obtained according to the determined shape constraint. A plurality of power semiconductor prepackages are obtained. Each power semiconductor prepackage includes a power semiconductor switching element embedded in a solid insulating material and an electrical connection extending through the solid insulating material from a terminal of the power semiconductor switching element to a connection surface of the prepackage. The power electronics converter is assembled by forming electrically conductive connections in a z-direction connecting terminals of the power semiconductor switching elements of the power semiconductor prepackages and one or more electrically conductive layers of the multi-layer carrier substrate.

A method of designing and manufacturing a power electronics converter for an electrical power system is provided. A circuit design for the power electronics converter is selected. A shape constraint for integrating the power electronics converter into the electrical power system is determined, and at least one multi-layer carrier substrate is obtained according to the determined shape constraint. A plurality of power semiconductor prepackages are obtained. Each power semiconductor prepackage includes a power semiconductor switching element embedded in a solid insulating material and an electrical connection extending through the solid insulating material from a terminal of the power semiconductor switching element to a connection surface of the prepackage. The power electronics converter is assembled by forming electrically conductive connections in a z-direction connecting terminals of the power semiconductor switching elements of the power semiconductor prepackages and one or more electrically conductive layers of the multi-layer carrier substrate.

A system includes a low pressure machine, a high pressure machine, a motor controller device, a first set of switches configured to selectively couple the low pressure machine to an inverter or a rectifier included in the motor controller device, based on a control signal, and a second set of switches configured to selectively couple the high pressure machine to the inverter or the rectifier, based on the control signal.

A system includes a low pressure machine, a high pressure machine, a motor controller device, a first set of switches configured to selectively couple the low pressure machine to an inverter or a rectifier included in the motor controller device, based on a control signal, and a second set of switches configured to selectively couple the high pressure machine to the inverter or the rectifier, based on the control signal.

Systems and techniques for state control of a flight component of an electric aircraft that includes a high voltage connection to a power supply of the electric aircraft and a communication connection to a communication system of the electric aircraft. The flight component is configured with a hardware circuit designed and configured to receive and/or read a signal on the communication system, compare an identifier of the signal against a stored identifier of the flight component, and in response to the identifier matching the stored identifier, cause the flight component to change from a first state to a second state.

Systems and techniques for state control of a flight component of an electric aircraft that includes a high voltage connection to a power supply of the electric aircraft and a communication connection to a communication system of the electric aircraft. The flight component is configured with a hardware circuit designed and configured to receive and/or read a signal on the communication system, compare an identifier of the signal against a stored identifier of the flight component, and in response to the identifier matching the stored identifier, cause the flight component to change from a first state to a second state.

An electrical generation system for supplying at least one electrical network of an aircraft. The electrical generation system includes a control device configured to receive a general operating setpoint and to output a first parameterization setpoint for the first converter and a second parameterization setpoint for the second converter. Each parameterization setpoint being either a voltage regulation setpoint for slaving the converter to a distribution voltage or an auxiliary regulation setpoint for the turbomachine. The control device being configured to output a parameterization setpoint in relation to an auxiliary transition with a stabilization delay relative to a parameterization setpoint in relation to a voltage transition so that the voltage regulation is extended during an auxiliary transition.

A turbomachine may include a high-pressure turbine connected to a high-pressure shaft and a low-pressure turbine connected to a low-pressure shaft, the hot gases leaving the high-pressure turbine driving the low-pressure turbine. A method for regulating the turbomachine includes electrically assisting the high-pressure shaft in order to provide said high-pressure shaft with electrical energy in addition to thermal energy obtained from a combustion chamber of the turbomachine, for an assistance period, and correcting the speed of the low-pressure shaft to achieve a reference speed of the low-pressure shaft that was previously determined in the absence of electrical assistance.

In accordance with at least one aspect of the present disclosure, there is provided a method for controlling power in an aircraft. The method includes, monitoring an electric energy storage module electrically connected to an electrical bus for an exceedance of a first current limit and monitoring a generator module connected to the electrical bus for an exceedance of a second current limit. If the current limit of either of the electric energy storage module or the generator module is exceeded by a predetermined exceedance amount, the method includes reducing a power consumption for an electric machine by a predetermined bias until the exceedance of the electrical energy storage and the exceedance of the generator module are both less than or equal to zero.

In accordance with at least one aspect of the present disclosure, there is provided a method for controlling power in an aircraft. The method includes, monitoring an electric energy storage module electrically connected to an electrical bus for an exceedance of a first current limit and monitoring a generator module connected to the electrical bus for an exceedance of a second current limit. If the current limit of either of the electric energy storage module or the generator module is exceeded by a predetermined exceedance amount, the method includes reducing a power consumption for an electric machine by a predetermined bias until the exceedance of the electrical energy storage and the exceedance of the generator module are both less than or equal to zero.