Aircraft Systems: Mechanical, Electrical, and Avionics Subsystems Integration, Third Edition

Moir, Ian; Seabridge, Allan

doi:10.2514/4.479526

Cited by 315 publications

(311 citation statements)

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“…The mechanical drivetrain transmits power from a rotating spool in the gas turbine core, through a multi-stage accessory gearbox to the auxiliary loads, which include hydraulic and pneumatic pumps, and the electrical generators. The electrical generators (typically 2 per gas turbine) are controlled independently to provide standalone voltage regulation; these electrical networks are not paralleled for redundancy reasons [23]. A wide range of electrical loads exist on the network, which may be high powered, transient (e.g.…”

Section: Aircraft Electrical Power Off-takementioning

confidence: 99%

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Analysis of Electromechanical Interaction in Aircraft Generator Systems

Feehally

Damian

Apsley

2016

IEEE Trans. on Ind. Applicat.

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Abstract-The supply of electrical power is usually achieved by a generator, driven from a prime mover, by some form of mechanical drivetrain. Such an electro-mechanical system will have natural resonant modes in both the electrical and mechanical subsystems. The electrical generator provides a coupling between the subsystems, transferring not only useful power but also disturbances between electrical and mechanical domains: these disturbances may excite resonances resulting in cross-domain (electro-mechanical) interaction. This can lead to lifetime reduction in the mechanical components and instability in the electrical network, resulting in poor reliability for the wider system, and potentially catastrophic component failure. Electro-mechanical interaction is particularly critical in power generation systems onboard aircraft, because the generator is driven by a gas turbine via an inherently low-stiffness drive train. It is then critical to identify electro-mechanical interaction at the design stage so that these issues can be avoided. However, predicting the occurrence of interaction, through simulation, is challenging, requiring multi-domain models, operating with different time scales. This paper analyses an aircraft auxiliary power offtake to produce a reduced-order mechanical drivetrain model, allowing the modal frequencies to be predicted and crossdomain interactions to be modelled. A purpose-built electromechanical test platform is used to validate the model and demonstrate how electrical disturbances are passed through the generator to the mechanical system and affect the electrical network. Future research will use the test bed to demonstrate strategies for avoiding or suppressing unwanted interactions.

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Section: Aircraft Electrical Power Off-takementioning

confidence: 99%

“…radar), or constant power (e.g. motor driven pumps) [23] with negative impedance gradients. These loads contribute to destabilising the electrical network and wider electro-mechanical system.…”

Section: Aircraft Electrical Power Off-takementioning

confidence: 99%

Analysis of Electromechanical Interaction in Aircraft Generator Systems

Feehally

Damian

Apsley

2016

IEEE Trans. on Ind. Applicat.

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“…The combination of short rise time and long cable ultimately leading either to overvoltage at motor terminals. [1][2][3][4][5][6] In this paper, comparative measurements on typical electric motor magnet wires of different grade are made at various pressure using twisted pair of enamel wire. Feeder cable insulation is also studied using DC voltage at low pressure on a specifically designed tool to model a typical aircraft situation.…”

Section: Introductionmentioning

confidence: 99%

Partial discharge testing in aeronautic environment on magnet wire and feeder cables

Billard¹,

Abadie

Lebey

2016

2016 IEEE Electrical Insulation Conference (EIC)

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OATAO is an open access repository that collects the work of Toulouse researchers and makes it freely available over the web where possible. Abstract-Rationalization of energy sources aboard aircraft and improvements in more electric technologies are pushing the aeronautic industry to meet the all-electric aircraft challenge. As a result, onboard power has been steadily increasing, reaching 1MW for B787. AC and HVDC network voltage have followed reaching 230VAC and 540VDC increasing the likeliness of partial discharge. In the future, this shift will lead to the complete redesign of the architecture of onboard power systems. The aim of this study is to characterize the partial discharge inception voltage, with the aforementioned constraints in mind, on two components of the electromechanical chain: magnet wires used in electric actuators and feeder cable used in harness.

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“…Thirdly, ultrasonic of ten minutes found very effective in killing the bacteria in the fuel. Fourthly, for every five minutes of fuel samples (600 millilitres) subjected to ultrasonic with 50 W power intensity, the fuel/water sample temperature increased by average of about 6.2 C. Finally, the amount of fuel temperature rise depends upon the power and duration of ultrasonic [21][22][23][24][25][26][27][28][29][30][31][32][33][34][35][36].…”

Section: Analysis Of the Experimentsmentioning

confidence: 99%