A system and method for verifying the response capabilities of a control effector include processing, in a test module, at least command data and sensor data associated with the control effector to generate control effector health data representative of control effector health. The control effector health data are processed in a reasoner to selectively indict and clear one or more faults, determine a failure is uncertain based on the one or more indicted faults, determine one or more test excitation signals to supply to the control effector to verify whether the uncertain failure is present or absent, and supply the one or more test excitation signals to a controller that is in operable communication with the control effector.

Initiated test health management system and method

A pre-charge circuit limits in-rush currents on a direct current (DC) link that includes a first DC link bus and a second DC link bus. The pre-charge circuit includes a switching device connected in series with the first DC link bus. The switching device has an ON state in which power flow is enabled on the DC link and an OFF state in which power is disabled on the DC link. A controller selectively modulates the state of the switching device to limit in-rush currents on the DC link.

Starting/generating system with multi-functional circuit breaker

A generator system includes a generator 102 having a stationary portion 116 and a rotating portion 118. An exciter field winding 120 and a main armature winding 122 are disposed on the stationary portion. An exciter armature winding 128 and a main field winding 138 are disposed on the rotating portion. A frequency demodulator 124 is configured to extract a frequency modulated control signal from the exciter armature winding and to demodulate the frequency modulated control signal to generate a demodulated control signal. The generator includes a main field rotating power converter 136 to selectively control current in the main field winding in response to the demodulated command signal. The generator system includes a generator control unit 104 in electrical communication with the generator to monitor the output voltage at the main armature winding and to output an exciter current including the frequency modulated control signal to the exciter field winding based on the output voltage.

Method of controlling rotating a main field converter

An apparatus for powering an aircraft by generating power from a pressure spool (26, 28) of a turbine engine (10). AC power can be extracted from the turbine engine (10) by a generator (56, 58) having an integrated autotransformer unit (62, 72), and converted to DC power.

Apparatus for generating power from a turbine engine

A method of method of forming a wide band-gap semiconductor transient voltage suppressor (TVS) assembly and a system for a transient voltage suppressor (TVS) assembly are provided. The TVS assembly includes a connecting component configured to electrically couple a first electrical component to a second electrical component located remotely from the first electrical component through one or more electrical conduits and a transient voltage suppressor device positioned within the connecting component and electrically coupled to the one or more electrical conduits wherein the TVS device includes a wide band-gap semiconductor material.

Method and system for lightning protection with distributed transient voltage suppression

A generator and associated power supply system (20) comprises a prime mover (22) for driving a shaft (24) to rotate. A pair of permanent magnets (26,28) is associated with the rotating shaft. A first stator winding (30) is associated with a first (26) of said permanent magnets, and supplies a customer DC bus (38) for providing a first relatively low voltage to the customer DC bus. A second (28) of said permanent magnets is associated with a second stator winding (54), and an engine accessory DC bus (58). The engine accessory DC bus provides power to a motor controller (60) and associated accessory motors (62,64,66) associated with the prime mover. The engine accessory DC bus is provided with a second relatively high voltage from the second stator winding.

More electric engine with regulated permanent magnet machines

A system for configuring a full authority digital engine controller (FADEC) (16,116; 216; 316; 416) for use with an engine (12; 112; 212; 312; 412) and an airframe (14; 114; 214; 314; 414) combination. The system includes the FADEC and a data entry plug (342; 442). The FADEC includes an electronic engine controller (EEC) (20; 120; 320; 420) attached to the engine, an airframe data concentrator (ADC) (18; 118; 318; 418) attached to the airframe, and a digital bus (22; 122; 322; 422) electrically connecting the ADC to the EEC. The ADC includes a data storage device (338; 438) and a data entry plug socket (340; 440). The data entry plug includes electrical components configured for the engine and the airframe combination. The data entry plug is inserted into the data entry plug socket to direct the ADC to recall configuration data from the data storage device for the engine and the airframe combination and send the configuration data over the digital bus to the EEC.

Electronic engine control software reconfiguration for distributed EEC operation

An electronic control configuration (10a) includes at least one secondary microprocessor (32a, 32b) operable to control a device (12). The at least one secondary microprocessor (32a, 32b) assumes protection control of the device responsive to a first type of failure by transmitting a protection control signal to a first effector (18). The at least one secondary microprocessor (32a, 32b) assumes backup control of the device responsive to a second type of failure by transmitting a backup control signal to a second effector (16). The backup control functionality of the at least one secondary microprocessor (32a, 32b) can be selectively disabled.

Architecture using integrated backup control and protection hardware

A fuel metering unit (FMU) for an aircraft engine includes an effector and an electronic engine controller (EEC). The effector is electrically connected to the EEC to adjust a rate of fuel flowing into the engine. The adjustment is in response to a control signal sent from the EEC. The control signal sent from the EEC is responsive to an engine sensor signal and to airframe sensor information.

Fmu mounted eec for small aircraft engine applications

A distributed electronic control system (100) for an aircraft includes an engine data controller (103) arranged on an airframe of the aircraft and a plurality of engine data concentrators (104-106) arranged proximate an engine of the aircraft in signal communication with the engine data controller. The engine data controller (103) is configured to process information related to the engine of the aircraft, the plurality of engine data concentrators (104-106) are configured to receive engine sensor information from a plurality of engine sensors (141-161), and the plurality of engine data concentrators (104-106) are further configured to transmit the engine sensor information to the engine data controller (103).

Distributed electronic engine control architecture

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