The invention relates to a circuit arrangement of a converter (1) for the electrical supply of a multi-phase electric motor (2). The arrangement comprises multiple DC-voltage-supplied (+DC, −DC) phase intermediate circuits (13) and multiple inverter circuits (5) that are electrically connected to each phase intermediate circuit (13), wherein a respective phase intermediate circuit (13) and inverter circuit (5) are provided for each phase, together forming a commutation cell (14). The invention also relates to an aircraft having a circuit arrangement of this type, and an operating method with a circuit arrangement of this type.

The invention relates to a circuit arrangement of a converter (1) for the electrical supply of a multi-phase electric motor (2). The arrangement comprises multiple DC-voltage-supplied (+DC, −DC) phase intermediate circuits (13) and multiple inverter circuits (5) that are electrically connected to each phase intermediate circuit (13), wherein a respective phase intermediate circuit (13) and inverter circuit (5) are provided for each phase, together forming a commutation cell (14). The invention also relates to an aircraft having a circuit arrangement of this type, and an operating method with a circuit arrangement of this type.

A power distribution system 100 is installed in an aircraft, and comprises: a first DC power supply unit 10 including a generator 11; a second DC power source unit 20 including a battery 30, a step-up/down converter 41, a voltage sensor 43, and control unit 44; and a diode 50. When the voltage sensor 43 does not detect regenerative power, the control unit 44 executes a running power processing mode in which generated power generated by the first DC power supply unit 10 is supplied to an electric actuator 80 while charging and discharging the battery 30 using the step-up/down converter 41 so as to keep a charge rate A of the battery 30 within a predetermined range. When the voltage sensor 43 detects regenerative power, the control unit 44 executes a regenerative power processing mode in which the battery 30 is charged with the regenerative power using the step-up/down converter 41.

A power distribution system 100 is installed in an aircraft, and comprises: a first DC power supply unit 10 including a generator 11; a second DC power source unit 20 including a battery 30, a step-up/down converter 41, a voltage sensor 43, and control unit 44; and a diode 50. When the voltage sensor 43 does not detect regenerative power, the control unit 44 executes a running power processing mode in which generated power generated by the first DC power supply unit 10 is supplied to an electric actuator 80 while charging and discharging the battery 30 using the step-up/down converter 41 so as to keep a charge rate A of the battery 30 within a predetermined range. When the voltage sensor 43 detects regenerative power, the control unit 44 executes a regenerative power processing mode in which the battery 30 is charged with the regenerative power using the step-up/down converter 41.

A simplex Flight Control Computer (FCC), usable in conjunction with a neighboring FCC, includes an input providing module for receiving sensor, system and neighboring FCC data; a processing unit for executing a command partition and a monitor partition, the processing unit receives the sensor, system data and neighboring FCC data; the monitor partition monitors the neighboring FCC data and provides a monitoring indicative signal to the neighboring FCC, and the command partition generates command signals; a hardware monitoring module provides a validity signal indicating FCC health; an output cutoff module receiving the FCC validity signal and enable signals generated by each monitor partition; the output cutoff module providing an enable signal based on a predetermined enabling strategy; and an enable switch connected with the output cutoff module and the processing unit and providing a received signal from the command partition according to the enable signal.

A method to modify an aircraft including: disconnecting a first engine control device from command cables and transmission cables, wherein the first engine control device is in a fuselage section forward of a pressure bulkhead; replacing the engine control device with a jumper connector positioned in the fuselage section, wherein the jumper connector electrically connects the command cables to the transmission cables; installing a second engine control device in the fuselage aft of the pressure bulkhead, wherein the second engine control device is in an engine compartment of the fuselage; connecting the second engine control device to transmission cables at a location at or near the pressure bulkhead; connecting sensor cabling directly to the second engine control device, and connecting the engine control device directly to the engine.

A method to modify an aircraft including: disconnecting a first engine control device from command cables and transmission cables, wherein the first engine control device is in a fuselage section forward of a pressure bulkhead; replacing the engine control device with a jumper connector positioned in the fuselage section, wherein the jumper connector electrically connects the command cables to the transmission cables; installing a second engine control device in the fuselage aft of the pressure bulkhead, wherein the second engine control device is in an engine compartment of the fuselage; connecting the second engine control device to transmission cables at a location at or near the pressure bulkhead; connecting sensor cabling directly to the second engine control device, and connecting the engine control device directly to the engine.

Disclosed is a throttle quadrant arrangement utilizing a throttle lever mechanically connected to three Rotary Variable Differential Transformers (RVDTs). The signals from the RVDTs are monitored by a process where the processing component. More specifically, RVDT outputs are monitored by the engine control system to determine if they are outside a predetermined range of operability. If an RVDT is not operable, the engine control system establishes a thrust output using the signal from one of the functional two. If only one or none are within the range, the system moves on to a default mode.

Disclosed is a throttle quadrant arrangement utilizing a throttle lever mechanically connected to three Rotary Variable Differential Transformers (RVDTs). The signals from the RVDTs are monitored by a process where the processing component. More specifically, RVDT outputs are monitored by the engine control system to determine if they are outside a predetermined range of operability. If an RVDT is not operable, the engine control system establishes a thrust output using the signal from one of the functional two. If only one or none are within the range, the system moves on to a default mode.

Components of a device may transmit signals between one another using piezo electric transducers (PETs). In a basic system, a first PET may be coupled to and/or in contact with a first location on a member. A second PET may be coupled to and/or in contact with a second location on the member and separated from the first PET by a distance. The first PET may receive a signal (e.g., an electrical voltage) and convert the signal to a mechanical force/stress causing vibration of the member. The vibration may propagate through the member to other locations about the member. The second PET receive the vibration and may convert the vibration back to the signal, such as by converting mechanical force/stress to the electrical voltage (i.e., the signal). A similar process may be performed in reverse to enable the first and second PET to provide two-way communication.