Systems and methods are provided for braking a translator of a linear multiphase electromagnetic machine. The system detects a fault event. A polarity indicative of an electromotive force in determined in at least one phase of the linear multiphase electromagnetic machine caused by a motion of the translator. In response to detecting the fault event, the system causes, based on the polarity, a current to be applied to a respective phase of the at least one phase to cause a force acting on the translator that opposes an axial motion of the translator to cause the translator to brake. Braking includes causing the translator to reciprocate at a reduced velocity by opposing axial motion over one or more cycles. The system may use one or more of position information, current information, operating parameters, to brake, or may brake the translator independent of such information.

A propulsion channel for aircraft at least one first dual-fed polyphase asynchronous rotating electric machine configured to be mechanically coupled to a turbine engine. The propulsion channel further includes at least one second polyphase rotating electric machine electrically coupled to the first asynchronous rotating electric machine, and a control and storage module configured to control the first polyphase asynchronous rotating electric machine. The module is connected to the first dual-feed polyphase asynchronous rotating electric machine as well as to the at least second polyphase rotating electric machine. The at least second polyphase rotating electric machine includes a polyphase synchronous rotating electric machine with permanent magnet.

There is described a method and system for operating a hybrid electric aircraft propulsion system. The method comprises modulating AC electric power applied to a first electric propulsor or a second electric propulsor from at least one motor inverter to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of a generator.

A generator including an internal combustion engine having an exhaust outlet, a proximity sensor structured to detect a distance value indicative of a distance between the exhaust outlet and an object, and a controller. The controller includes a proximity circuit structured to receive the distance value from the proximity sensor and a shutdown circuit. The shutdown circuit is structured to receive the distance value from the proximity circuit, determine whether to initiate at least one of an alarm and a shutdown of the generator based on the distance value and a predetermined distance value minimum, and initiate at least one of the alarm and the shutdown of the generator based on determining that the distance value is less than the predetermined distance value minimum.

An electronic device, in particular an alternator regulator, comprising a power stage to be connected to an inductive load, in particular to an alternator inductor, comprising at least one first pair of power transistors connected to a terminal of a DC bus, and a control circuit for said transistors, the transistors being disposed in parallel between said terminal of the DC bus and a first output to be connected to the load, at least one flyback diode connecting the opposite terminal of the DC bus to the first output, the control circuit being designed to generate a pulsed control signal for regulating the current in the load and for detecting a failure of one of the transistors, the control circuit being designed, during normal operation, to send the control signal to one of the transistors of the first pair, while maintaining the other transistor of said pair in an off-state.

A load adaptive linear electrical generator system is provided for generating DC electrical power. The electrical generation system includes one or more power generation modules which will be selectively turned on or off and additively contribute power depending on the DC power demand. Each power generating module includes a pair of linear electrical generators connected to respective ones of a pair of internal combustion piston based power assemblies. The piston in the internal combustion assembly is connected to a magnet in the linear electrical generator. The piston/magnet assembly oscillates in a simple harmonic motion at a frequency dependent on a power load of the electrical generator. A stroke limiter constrains the piston/magnet assembly motion to preset limits.

A control circuit for a dual fuel generator includes a primary fuel valve to control the supply of a primary fuel, a secondary fuel valve to control the supply of a secondary fuel, a primary fuel pressure switch to detect the primary fuel, a secondary fuel pressure switch to detect the secondary fuel, and a controller. The controller is configured to receive a primary signal for availability of the primary fuel from the primary fuel pressure switch and a secondary signal for availability of the secondary fuel from the secondary and operate the primary fuel valve and the secondary fuel valve in response to the primary signal and the secondary signal. When the secondary fuel valve is open so that the secondary fuel is provided to the dual fuel generator, the control circuit is configured to ground the primary signal by connecting the primary fuel pressure switch to ground.

A hybrid power generation unit and synchronous condenser system connectable to a power grid includes a combustion turbine coupled to a first shaft and operable to provide rotational energy to the first shaft, a gear box coupled to the first shaft, and a first clutch portion coupled to the first shaft. A motor is selectively coupled to the gear box to turn the gear box and the first shaft, a second clutch portion is connected to a second shaft, and a generator is coupled to the second shaft. The generator is selectively connectable to the grid to operate as a synchronous condenser when the first clutch portion and the second clutch portion are disengaged and to convert rotational energy from the first shaft to electrical power when the first clutch portion and the second clutch portion are engaged.

The hybrid power generation system includes a renewable energy power generation device and a rotary power generation device connected to a common alternating-current power system. In the system, if renewable energy or an output fluctuates, a correction value calculated based on the fluctuation amount is added to a control parameter as a feedforward component, controlling the rotary power generation device.

A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.