Abstract: A single phase single stage level-1 electric vehicle (EV) battery charger can control the power flow in both directions. The converter efficiency is high as the devices undergo ZCS which reduces switching loss in the devices. This converter does not require any intermediate DC link capacitor stage and the power density of the converter is high.

Abstract: A single phase single stage level-1 electric vehicle (EV) battery charger can control the power flow in both directions. The converter efficiency is high as the devices undergo ZCS which reduces switching loss in the devices. This converter does not require any intermediate DC link capacitor stage and the power density of the converter is high.

Abstract: A high temperature (HT) gate driver for Silicon Carbide metal-oxide-semiconductor field-effect transistor (SiC MOSFET) uses commercial off-the-shelf COTS discrete components, and has an integrated short-circuit or overcurrent protection circuit and under voltage lock out (UVLO) protection circuit.

Abstract: A single phase single stage level-1 electric vehicle (EV) battery charger can control the power flow in both directions. The converter efficiency is high as the devices undergo ZCS which reduces switching loss in the devices. This converter does not require any intermediate DC link capacitor stage and the power density of the converter is high.

Abstract: A high temperature (HT) gate driver for Silicon Carbide metal-oxide-semiconductor field-effect transistor (SiC MOSFET) uses commercial off-the-shelf COTS discrete components, and has an integrated short-circuit or overcurrent protection circuit and under voltage lock out (UVLO) protection circuit.

Abstract: A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the hybrid turbo electric aero-propulsion system. The control subsystems may include, for example, a propulsion control optimization subsystem and a power plant control optimization subsystem. The optimizations may be based on a system model, which is developed and updated during the operation of the hybrid turbo electric aero-propulsion system.

Abstract: A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the hybrid turbo electric aero-propulsion system. The control subsystems may include, for example, a propulsion control optimization subsystem and a power plant control optimization subsystem. The optimizations may be based on a system model, which is developed and updated during the operation of the hybrid turbo electric aero-propulsion system.

Abstract: A control method for a synchronous generator system is disclosed including performing a first parametric optimization to determine a desired stator current angle assuming fixed stator current magnitude and fixed field current magnitude. A second parametric optimization is then performed to determine a desired field current magnitude assuming fixed stator current magnitude and fixed stator current angle. A desired stator current magnitude is calculated using the desired stator current angle and the desired field current magnitude. Finally, the desired stator current magnitude, the desired stator current angle and the desired field current magnitude are output.

Abstract: One embodiment is a packaged device having multiple layers. Another embodiment is a method of forming a packaged device having multiple layers. Conductive layers and insulating layers can be formed with openings exposing semiconductor devices. The semiconductor devices can be wire-bonded to the conductive layers. In some embodiments, parasitic effects and a relative footprint of the packaged device can be reduced.

Abstract: One embodiment of the present application is directed to a unique method for powering one or more critical loads in an aircraft. Another embodiment is a unique apparatus for powering one or more critical loads upon failure of one or more engines. Other embodiments include unique methods, systems, devices, and apparatus' for powering power loads in an aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique method of controlling the output of a synchronous electrical machine. Another embodiment is a unique method of controlling the output of a synchronous electrical machine for powering a load. Still another embodiment is a unique aircraft power generation system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for fluid driven actuation systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique aircraft. Another embodiment is a unique aircraft propulsion system. Still another embodiment is a unique system for taxiing an aircraft without starting one or more main aircraft propulsion engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft taxiing and propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique aircraft. Another embodiment is a unique propulsion system for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and aircraft propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique aircraft. Another embodiment is a unique aircraft propulsion system. Still another embodiment is a unique system for taxiing an aircraft without starting one or more main aircraft propulsion engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft taxiing and propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment is a packaged device having multiple layers. Another embodiment is a method of forming a packaged device having multiple layers. Conductive layers and insulating layers can be formed with openings exposing semiconductor devices. The semiconductor devices can be wire-bonded to the conductive layers. In some embodiments, parasitic effects and a relative footprint of the packaged device can be reduced.

Abstract: An electrical power system includes an alternating current (AC) power source configured to output an AC signal, a single phase pulse-width modulated (PWM) rectifier coupled to the AC power source and to an electrical load; a DC link capacitor coupled in parallel to the load and the PWM rectifier; and an active ripple energy storage circuit. The active ripple energy storage circuit has a first terminal, a second terminal and a third terminal, the active ripple energy storage circuit being coupled in parallel to the electrical load, the PWM rectifier and the DC link capacitor via the first terminal and the second terminal, the third terminal being coupled to the second terminal, the active ripple energy storage circuit being configured to selectively absorb and discharge at least part of the ripple energy.

Abstract: One embodiment of the present invention is a unique method of controlling the output of a synchronous electrical machine. Another embodiment is a unique method of controlling the output of a synchronous electrical machine for powering a load. Still another embodiment is a unique aircraft power generation system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for fluid driven actuation systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present application is directed to a unique method for powering one or more critical loads in an aircraft. Another embodiment is a unique apparatus for powering one or more critical loads upon failure of one or more engines. Other embodiments include unique methods, systems, devices, and apparatus' for powering power loads in an aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique aircraft. Another embodiment is a unique aircraft propulsion system. Still another embodiment is a unique system for taxiing an aircraft without starting one or more main aircraft propulsion engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft taxiing and propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique aircraft. Another embodiment is a unique aircraft propulsion system. Still another embodiment is a unique system for taxiing an aircraft without starting one or more main aircraft propulsion engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft taxiing and propulsion systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.