EPE Association: EPE 2009 - Subtopic 17-6 - LS: 'Marine and Aerospace Applications'

EPE 2009 - Subtopic 17-6 - LS: 'Marine and Aerospace Applications'
You are here: EPE Documents > 01 - EPE & EPE ECCE Conference Proceedings > EPE 2009 - Conference > EPE 2009 - Topic 17: 'Electrical Systems in Aerospace, Space, Surface and Marine Transport' > EPE 2009 - Subtopic 17-6 - LS: 'Marine and Aerospace Applications'

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   Compact Dual-output Power Converter for an Aerospace Electrical Landing Gear Actuation System
By Thiwanka WIJEKOON, Lee EMPRINGHAM, patrick WHEELER, Jon CLARE [View]
[Download]

Abstract: The current trend in the aircraft industry is to evolve in to more â€power-by-wireâ€ or â€More electricâ€ architectures in which electrical power moves aircraft flight surfaces. Benefits of a more electric architecture include improvements in environmental impact and reliability as well as reduced maintenance costs. In this paper power electronic technology used in the â€power-by-wireâ€ type nose landing gear system is investigated for future more electric aircraft. Furthermore, use of a dual-output power converter concept for an electromechanically actuated nose landing gear system is analyzed. The design, construction and testing of above mentioned power converter with higher technology readiness level is detailed. In the dual-output power converter concept large components, such as the dc link capacitor, heat-sink, control electronics and transducers are shared between two Electro Mechanical Actuators (EMA) which are used sequentially in the deployment of aircraft nose landing gear. This mutual component approach combines the advantages of dual-use power converters with the flexibility of one power converter per application. Results of the converter operating with EMAs are presented for a range of test conditions in order to validate the simulation study.

   Design of a 1000 HP Permanent Magnet Synchronous Motor for Ship Propulsion
By Nicola BIANCHI, Silverio BOLOGNANI [View]
[Download]

Abstract: The paper deals with the design of a 1000 HP Permanent Magnet synchronous motor for the propulsion of a 670 tons ship. The paper contains the preliminary design evaluation to define motor specifications and rotor configuration and a description of the main steps of the electromagnetic design and thermal analysis. Prediction of motor performance and preliminary test results are also presented and discussed.

   Permanent magnet synchronous motor for passenger ship propulsion
By Rudolf MECKE [View]
[Download]

Abstract: A special permanent magnet synchronous motor for ship propulsion in the power range between 50 and 250 kW is presented. It is fed by a PWM-voltage source inverter with field oriented control. A motor feature is the very low stator inductance. It leads to low reactive power and high maximum torque, but on the other hand it produces large current ripples and therefore harmonic losses up to 10 \% of the electrical input power. Two methods are investigated to reduce the stator current ripples and therefore the harmonic power content. The first method is the increase of the inverter switching frequency. An increase from 4 kHz to 9 kHz reduces the harmonic power content from 6,3 \% to 1,5 \%. A more simple way is a three-phase inverter output inductance. An inductance of 0,1 mH also reduces the harmonic power content to 1,5 \%.

EPE 2009 - Subtopic 17-6 - LS: 'Marine and Aerospace Applications'
You are here: EPE Documents > 01 - EPE & EPE ECCE Conference Proceedings > EPE 2009 - Conference > EPE 2009 - Topic 17: 'Electrical Systems in Aerospace, Space, Surface and Marine Transport' > EPE 2009 - Subtopic 17-6 - LS: 'Marine and Aerospace Applications'
	[return to parent folder]

	Compact Dual-output Power Converter for an Aerospace Electrical Landing Gear Actuation System By Thiwanka WIJEKOON, Lee EMPRINGHAM, patrick WHEELER, Jon CLARE	[View] [Download]
Abstract: The current trend in the aircraft industry is to evolve in to more â€power-by-wireâ€ or â€More electricâ€ architectures in which electrical power moves aircraft flight surfaces. Benefits of a more electric architecture include improvements in environmental impact and reliability as well as reduced maintenance costs. In this paper power electronic technology used in the â€power-by-wireâ€ type nose landing gear system is investigated for future more electric aircraft. Furthermore, use of a dual-output power converter concept for an electromechanically actuated nose landing gear system is analyzed. The design, construction and testing of above mentioned power converter with higher technology readiness level is detailed. In the dual-output power converter concept large components, such as the dc link capacitor, heat-sink, control electronics and transducers are shared between two Electro Mechanical Actuators (EMA) which are used sequentially in the deployment of aircraft nose landing gear. This mutual component approach combines the advantages of dual-use power converters with the flexibility of one power converter per application. Results of the converter operating with EMAs are presented for a range of test conditions in order to validate the simulation study.

	Design of a 1000 HP Permanent Magnet Synchronous Motor for Ship Propulsion By Nicola BIANCHI, Silverio BOLOGNANI	[View] [Download]
Abstract: The paper deals with the design of a 1000 HP Permanent Magnet synchronous motor for the propulsion of a 670 tons ship. The paper contains the preliminary design evaluation to define motor specifications and rotor configuration and a description of the main steps of the electromagnetic design and thermal analysis. Prediction of motor performance and preliminary test results are also presented and discussed.

	Permanent magnet synchronous motor for passenger ship propulsion By Rudolf MECKE	[View] [Download]
Abstract: A special permanent magnet synchronous motor for ship propulsion in the power range between 50 and 250 kW is presented. It is fed by a PWM-voltage source inverter with field oriented control. A motor feature is the very low stator inductance. It leads to low reactive power and high maximum torque, but on the other hand it produces large current ripples and therefore harmonic losses up to 10 \% of the electrical input power. Two methods are investigated to reduce the stator current ripples and therefore the harmonic power content. The first method is the increase of the inverter switching frequency. An increase from 4 kHz to 9 kHz reduces the harmonic power content from 6,3 \% to 1,5 \%. A more simple way is a three-phase inverter output inductance. An inductance of 0,1 mH also reduces the harmonic power content to 1,5 \%.