Abstract: A power distribution system, includes a first current loop connected with a set of low voltage electrical loads, a second current loop connected with a set of high voltage electrical loads, at least two generator systems having respective power outputs, and a controller module configured to selectively connect the respective power outputs to at least one of the first or second current loops.

Abstract: A power system for an aircraft having a plurality of power-consuming components, some of which have transient power requirements, which is greater than the average power requirement, the power system includes at least one generator, a power distribution buss, a non-battery power source, a battery power source, and a power controller selectively coupling the non-battery power source and the battery power source to the power distribution buss to satisfy the transient power requirements.

Abstract: An apparatus and method for a generator assembly for a drive train such as a rotatable turbine engine assembly. The generator assembly includes at least first and second generators mechanically coupled to the drive train. First and second dampers are operably coupled to the first and second generators, respectively, to selectively damp the first and second generators. Damping the first and second generators can reduce or eliminate both common mode and differential mode torsional oscillations from the generators to the drive train.

Abstract: An electrical fault detecting system (10) for a circuit includes a conductor (20) delivering an electrical signal from a source (12) to a destination (14), a sheath (22) encircling the conductor, and a fault detection circuit (18). The sheath further includes an electrical insulator layer (24) and a conductive shield (26) encircling the conductor. The fault detection circuit is configured to detect a change in the electrical characteristics of the conductor and/or conductor sheath.

Abstract: An aircraft power distribution system includes a first DC power distribution bus, a second DC power distribution bus, and a DC power source coupled with at least one of the first or second DC power distribution buses, wherein the DC power distribution buses are electrically coupled by a plurality of electrical couplings.

Abstract: A method for operating a gas turbine engine having a starter-electric generator driven by one of a plurality of shafts of the gas turbine engine is provided. The method includes determining a desired amount of thrust to be produced by the gas turbine engine, as well as a desired amount of electrical power to be drawn from the starter-electric generator of the gas turbine engine. The method operates the gas turbine engine to produce the desired amount of thrust, while drawing less than the desired amount of electrical power from the starter-electric generator. Drawing less than the desired amount of electrical power from the starter-electric generator allows for the desired amount of thrust production, allows for the desired amount of thrust production more quickly, or allows for maintenance of a stall margin for any purpose (such as to increase an efficiency of the engine or to allow for certain engine designs).

Abstract: An aircraft power distribution system (22) includes at least one DC power source, a first DC power distribution bus and a second DC power distribution bus (36), a tie bus (33) coupling the at least one DC power source, first DC power distribution bus, and second DC distribution bus, wherein the first or second DC power distribution buses are selectively coupled and decoupled to the tie bus by means of a solid-state poer controller (SSPC) (46, 48, 62, 64, 66).

Abstract: A method for controlling the supply of power to a power system for an aircraft having a plurality of power-consuming components includes supplying power to the power system with a generator having a power output, determining a power requirement of the power system, and supplying the power to the power-consuming components.

Abstract: A power system for an aircraft having a plurality of power-consuming components, some of which have transient power requirements, which is greater than the average power requirement, the power system includes at least one generator, a power distribution buss, a non-battery power source, a battery power source, and a power controller selectively coupling the non-battery power source and the battery power source to the power distribution buss to satisfy the transient power requirements.

Abstract: A switched capacitive device includes a stator including a plurality of first electrodes extending substantially in a longitudinal dimension. The switched capacitive device also includes an armature including a plurality of second electrodes proximate the plurality of first electrodes. The plurality of second electrodes is translatable with respect to the plurality of first electrodes. The plurality of second electrodes extends substantially in the longitudinal dimension. The plurality of first electrodes and the plurality of second electrodes are configured to induce substantially linear motion of the second plurality of electrodes in the longitudinal dimension with respect to the first plurality of electrodes as a function of an electric field induced by at least a portion of the first plurality of electrodes.

Abstract: An aircraft power distribution system includes a first DC power distribution bus, a second DC power distribution bus, and a DC power source coupled with at least one of the first or second DC power distribution buses, wherein the DC power distribution buses are electrically coupled by a plurality of electrical couplings.

Abstract: An apparatus for use with a flight control actuator and method for assembling the same is provided. The apparatus includes a motor drive system and a control unit. The motor drive system includes a capacitor-based energy storage configured to store and provide energy within or proximate to the actuator. The control unit is coupled to the motor drive system and is configured to facilitate managing power within or proximate to the actuator.

Abstract: A method for transferring power in an aircraft between an energy storage device and a power system. The method includes determining an amount of power required by the power system, determining a predetermined amount of power from a generator, comparing the power required by the power system to the predetermined power of the generator, and transferring power to the energy storage device from the power system or to the power system from the energy storage device based on the comparing.

Abstract: A circuit board assembly is configured to attenuate and prevent electro-magnetic fields from interfering with operation below a desired cutoff frequency, of electro-magnetic interference (EMI) susceptible circuit board electronics disposed within a shielded enclosure, while allowing signals to be transmitted between the EMI susceptible circuit board electronics at frequencies below the desired cutoff frequency, and circuits or devices external to the shielded enclosure.

Abstract: A bus centering device for use in an aircraft electrical power distribution system that includes a positive bus rail, a negative bus rail, and a ground is described. The device includes a central node, a first and second switching component configured to couple the central node to the positive rail and the negative rail for a first and second predetermined duty cycle, respectively. The device includes an inductive component coupled between the central node and ground, and is configured to maintain a voltage at the central node substantially equal to ground, wherein a voltage between the positive rail and the central node is maintained substantially equal to a voltage between the negative rail and the central node. The device includes a first and second current limiting device configured to maintain a continuity of current from the inductive component when the first and second switching components are turned off.

Abstract: A method for transferring power in an aircraft between an energy storage device and a power system. The method includes determining an amount of power required by the power system, determining a predetermined amount of power from a generator, comparing the power required by the power system to the predetermined power of the generator, and transferring power to the energy storage device from the power system or to the power system from the energy storage device based on the comparing.

Abstract: A circuit board assembly is configured to attenuate and prevent electromagnetic fields from interfering with operation below a desired cutoff frequency, of electromagnetic interference (EMI) susceptible circuit board electronics disposed within a shielded enclosure, while allowing signals to be transmitted between the EMI susceptible circuit board electronics at frequencies below the desired cutoff frequency, and circuits or devices external to the shielded enclosure.

Abstract: An apparatus for use with a flight control actuator and method for assembling the same is provided. The apparatus includes a motor drive system and a control unit. The motor drive system includes a capacitor-based energy storage configured to store and provide energy within or proximate to the actuator. The control unit is coupled to the motor drive system and is configured to facilitate managing power within or proximate to the actuator.