A power generation controller of an aircraft includes a low-temperature start-up control section and a power generation control section. When it is determined that an oil temperature of a hydraulic actuator configured to change an operation position of a speed change element of a hydraulic transmission satisfies a predetermined low-temperature condition when starting up an aircraft engine, the low-temperature start-up control section sets a power generator to a power non-generating state and controls the hydraulic actuator such that the speed change element is positioned at an acceleration side of a median in a speed change range. When it is determined that the oil temperature satisfies a predetermined low-temperature start-up completion condition, the power generation control section sets the power generator to a power generating state and controls the hydraulic actuator in accordance with a rotational frequency of the aircraft engine.

Systems and methods are provided for braking a translator of a linear multiphase electromagnetic machine. The system detects a fault event, and in response to detecting the fault event, causes the translator to brake using an electromagnetic technique. Braking includes causing the translator to stop reciprocating, by applying a force opposing an axial motion, which may occur within one cycle, or over many cycles. The fault event may include, for example, a fault associated with an encoder, a controller, an electrical component, a communications link, a phase, or a subsystem. The system includes a power electronics system configured to apply current to the phases. The system may use position information, current information, operating parameters, or a combination thereof to brake. Alternatively, the system need not use position information, current information, and operating parameters, and may brake the translator independent of such information.

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.

A transport refrigeration (TRU) system is provided and includes an air management system, a compressor, a generator which generates alternating current (AC) from operations of an engine to power operations of the air management system and the compressor and an AC inverter operably interposed between the generator and the compressor to decouple a drive frequency of the compressor from a frequency of the generator.

A turbo-generator system for generating propulsive electrical power for an aircraft includes an electric machine comprising: a rotor configured to be rotated by a gas-turbine of the turbo-generator system; a stator comprising: a first active section comprising first windings surrounding a first portion of the rotor; and a second active section comprising second windings surrounding a second portion of the rotor.

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 generator control system is coupled to a motor generator. The system includes a DC port, a first switch unit, a DC bus, a first power conversion circuit, a second power conversion circuit, and a second switch unit. The first power conversion circuit has a first side coupled to the DC bus and a second side coupled to the first switch unit. The second power conversion circuit has a first side coupled to the DC bus and a second side coupled to the motor generator. One end of the second switch unit is coupled to the first power conversion circuit and the first switch unit, and the other end of the second switch unit is coupled to the DC port.

The present disclosure provides a generator pulley system and methods thereof. Atop the generator pulley system may be a generator and battery for actuating at least one motor. A pull line may be retractably coupled to the front of the system. Alternatively, the pull line is not retractable. At least one sensor may be used to monitor the line. In an illustrative embodiment, the system may actuate the at least motor to steer in the direction of the pulled line. The battery may be recharged by the generator depending on its state of charge and period of time after requesting a movement of the generator.

A system comprises a generator and an engine coupled thereto. The engine is configured to provide mechanical power to the generator. A controller is coupled to the engine and the generator and is configured to compare an engine operating parameter value to a load demand value indicative of a load exerted by the generator on the engine. The controller determines that the engine operating parameter value fails to match the load demand value. The controller determines an engine operating parameter threshold value at which the engine operating parameter value failed to match the load demand value, and sets the engine operating parameter threshold value as a maximum allowable engine operating parameter value for the engine.

A turboelectric generator system includes a gas turbine engine which includes, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a variable-speed free power turbine. The system further comprises a variable-frequency electric machine rotatably connected with the free power turbine and a power converter configured to convert a variable frequency electrical output from the electric machine to a fixed frequency output.