Abstract: An aircraft hybrid electrical system includes an electric power generating system in signal communication with a thermal combustion engine, a secondary power system in signal communication with the electric power generating system, and a battery in signal communication with the electric power generating system and the secondary power system. The aircraft hybrid electrical system further comprises a system controller in signal communication with the electric power generating system, secondary power system, and the battery. The system controller is configured to monitor a charge capacity of the battery and selectively operate in a current charge mode and a voltage charge mode to charge the battery. The system controller invokes the current charge mode in response to detecting the charge capacity falls below a charge capacity threshold, and invokes the voltage charge mode in response to detecting the charge capacity reaches a target value.

Abstract: A hybrid propulsion system for driving an air mover about a rotation axis, has: a heat engine driving a heat engine shaft; an electric motor driving a motor shaft, the heat engine and the electric motor being axially offset from one another relative to the rotation axis; a gearbox having at least one input in driving engagement with the heat engine shaft and the motor shaft, and an output drivingly engageable to the air mover; and a disconnect mechanism disposed between one of the heat engine and the electric motor and the gearbox, the disconnect mechanism having an engaged configuration in which the one of the heat engine and the electric motor is drivingly engaged to the gearbox through the disconnect mechanism and a disengaged configuration in which the disconnect mechanism disengages the one of the heat engine and the electric motor from the gearbox.

Abstract: A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor is configured to drive a motor shaft. A transmission system includes at least one gear box. The transmission system is configured to receive rotational input power from each of the heat engine shaft and the motor shaft and to convert the rotation input power to output power. The motor shaft includes a disconnect mechanism to allow the heat engine to rotate with the electric motor stopped. The heat engine shaft includes a disconnect mechanism to allow the electric motor to rotate with the heat engine stopped.

Abstract: A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor is configured to drive a motor shaft. A transmission system includes at least one gear box. The transmission system is configured to receive rotational input power from each of the heat engine shaft and the motor shaft and to convert the rotation input power to output power. The motor shaft includes a disconnect mechanism to allow the heat engine to rotate with the electric motor stopped. The heat engine shaft includes a disconnect mechanism to allow the electric motor to rotate with the heat engine stopped.

Abstract: A fuel system for an engine including a first flow line, an electrically driven startup pump in fluid communication with the first flow line to provide a startup flow, a main flow line, a main pump in fluid communication with the main flow line to provide a main flow, and a switching valve connected to the first flow line and the main flow line, the switching valve configured to select between the first flow line and the main flow line to output either the startup flow or the main flow.

Abstract: A generator arrangement includes a generator and a pneumatic turbine. The pneumatic turbine is operably connected to the generator. A gas turbine engine compressor section is in fluid communication with the pneumatic turbine through a bleed air conduit to provide pressurized air to the pneumatic turbine for applying mechanical rotation to the generator.

Abstract: An example aircraft electrical system includes a generator coupled with a gas turbine engine and a controller operable to distribute power of the generator. The controller includes a first control module positioned at a first location remote from the generator and a second control module positioned at a second location proximate the generator. The first control module is configured to verify at least one output of the generator, detect a fault condition of the generator, and control operation of at least one power bus in communication with the first control module. The second control module is configured to regulate the at least one output of the generator, where the at least one output includes a voltage. An example method of operating an electrical system is also disclosed.

Abstract: A generator arrangement includes a generator and a pneumatic turbine. The pneumatic turbine is operably connected to the generator. A gas turbine engine compressor section is in fluid communication with the pneumatic turbine through a bleed air conduit to provide pressurized air to the pneumatic turbine for applying mechanical rotation to the generator.

Abstract: An example aircraft electrical system includes a generator coupled with a gas turbine engine and a controller operable to distribute power of the generator. The controller includes a first control module positioned at a first location remote from the generator and a second control module positioned at a second location proximate the generator. The first control module is configured to verify at least one output of the generator, detect a fault condition of the generator, and control operation of at least one power bus in communication with the first control module. The second control module is configured to regulate the at least one output of the generator, where the at least one output includes a voltage. An example method of operating an electrical system is also disclosed.

Abstract: A system for coating a surface comprises providing a source of amorphous metal, providing ceramic particles, and applying the amorphous metal and the ceramic particles to the surface by a spray. The coating comprises a composite material made of amorphous metal that contains one or more of the following elements in the specified range of composition: yttrium (?1 atomic %), chromium (14 to 18 atomic %), molybdenum (?7 atomic %), tungsten (?1 atomic %), boron (?5 atomic %), or carbon (?4 atomic %).

Abstract: A method of coating a surface comprising providing a source of amorphous metal that contains manganese (1 to 3 atomic %), yttrium (0.1 to 10 atomic %), and silicon (0.3 to 3.1 atomic %) in the range of composition given in parentheses; and that contains the following elements in the specified range of composition given in parentheses: chromium (15 to 20 atomic %), molybdenum (2 to 15 atomic %), tungsten (1 to 3 atomic %), boron (5 to 16 atomic %), carbon (3 to 16 atomic %), and the balance iron; and applying said amorphous metal to the surface by a spray.

Abstract: A method of coating a surface comprising providing a source of amorphous metal that contains manganese (1 to 3 atomic %), yttrium (0.1 to 10 atomic %), and silicon (0.3 to 3.1 atomic %) in the range of composition given in parentheses; and that contains the following elements in the specified range of composition given in parentheses: chromium (15 to 20 atomic %), molybdenum (2 to 15 atomic %), tungsten (1 to 3 atomic %), boron (5 to 16 atomic %), carbon (3 to 16 atomic %), and the balance iron; and applying said amorphous metal to the surface by a spray.

Abstract: A method of coating a surface comprising providing a source of amorphous metal that contains manganese (1 to 3 atomic %), yttrium (0.1 to 10 atomic %), and silicon (0.3 to 3.1 atomic %) in the range of composition given in parentheses; and that contains the following elements in the specified range of composition given in parentheses: chromium (15 to 20 atomic %), molybdenum (2 to 15 atomic %), tungsten (1 to 3 atomic %), boron (5 to 16 atomic %), carbon (3 to 16 atomic %), and the balance iron; and applying said amorphous metal to the surface by a spray.

Abstract: A method of coating a surface comprising providing a source of amorphous metal that contains manganese (1 to 3 atomic %), yttrium (0.1 to 10 atomic %), and silicon (0.3 to 3.1 atomic %) in the range of composition given in parentheses; and that contains the following elements in the specified range of composition given in parentheses: chromium (15 to 20 atomic %), molybdenum (2 to 15 atomic %), tungsten (1 to 3 atomic %), boron (5 to 16 atomic %), carbon (3 to 16 atomic %), and the balance iron; and applying said amorphous metal to the surface by a spray.

Abstract: A system for coating a surface comprises providing a source of amorphous metal, providing ceramic particles, and applying the amorphous metal and the ceramic particles to the surface by a spray. The coating comprises a composite material made of amorphous metal that contains one or more of the following elements in the specified range of composition: yttrium (?1 atomic %), chromium (14 to 18 atomic %), molybdenum (?7 atomic %), tungsten (?1 atomic %), boron (?5 atomic %), or carbon (?4 atomic %).

Abstract: A system for coating a surface comprises providing a source of amorphous metal, providing ceramic particles, and applying the amorphous metal and the ceramic particles to the surface by a spray. The coating comprises a composite material made of amorphous metal that contains one or more of the following elements in the specified range of composition: yttrium (?1 atomic %), chromium (14 to 18 atomic %), molybdenum (?7 atomic %), tungsten (?1 atomic %), boron (?5 atomic %), or carbon (?4 atomic %).

Abstract: A system for coating a surface comprises providing a source of amorphous metal, providing ceramic particles, and applying the amorphous metal and the ceramic particles to the surface by a spray. The coating comprises a composite material made of amorphous metal that contains one or more of the following elements in the specified range of composition: yttrium (?1 atomic %), chromium (14 to 18 atomic %), molybdenum (?7 atomic %), tungsten (?1 atomic %), boron (?5 atomic %), or carbon (?4 atomic %).

Abstract: A system for coating a surface comprises providing a source of amorphous metal, providing ceramic particles, and applying the amorphous metal and the ceramic particles to the surface by a spray. The coating comprises a composite material made of amorphous metal that contains one or more of the following elements in the specified range of composition: yttrium (?1 atomic %), chromium (14 to 18 atomic %), molybdenum (?7 atomic %), tungsten (?1 atomic %), boron (?5 atomic %), or carbon (?4 atomic %).

Abstract: A method for automatically replenishing oil in a coolant system of an electric generator produces a first signal representative of the speed of the generator and a second signal representative of the pressure of oil in the coolant system of the generator. These signals are combined with a reference signal to produce a control signal representative of a low oil condition in the coolant system. When such low oil condition exists, additional oil is delivered to the coolant system in response to the control signal. In the preferred embodiment, this additional oil is supplied from a source of high pressure oil.

Abstract: The invention relates to improved mechanism systems for controlling and assisting the operating effort of a mechanical member and is especially applicable to automatic assisted steering systems for automobile vehicles. The said servo-mechanism comprises essentially a steering shaft including two coaxial sections, the first section being coupled to a steering wheel for its rotation about the common axis of the two sections, while the second section is coupled to the mechanical member to be servo-controlled, this second section being fixed on an end sleeve which is coaxial and surrounds one part of the first, which is provided with a pin mounted in one of its diametral planes, the wings of said pin being identical and projecting over the same length from each side of the common axis, the second section co-operating with the first by means of the wings of said pin and an elastic member interposed between the pin and the second section.