EPE Association: EPE 2011 - LS3a: Topic 19: Aerospace and Space Applications

EPE 2011 - LS3a: Topic 19: Aerospace and Space Applications
You are here: EPE Documents > 01 - EPE & EPE ECCE Conference Proceedings > EPE 2011 ECCE Europe - Conference > EPE 2011 - Topic 19: Electrical systems in aerospace, space, surface and marine transport (not road) > EPE 2011 - LS3a: Topic 19: Aerospace and Space Applications

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   Design and optimization techniques for the current return path in a composite aircraft
By Anca Lucia GOLEANU, Jean Michel GUICHON, Michel DUNAND, Pierre GLIZE, Arthur FREYCON, Jean-Luc SCHANEN, Jean-Louis COULOMB [View]
[Download]

Abstract: The emergence of new composite materials in the aeronautical domain requires a paradigm shift in the electrical system design, especially concerning the current return path. The composite fuselage cannot comply with the required functionalities, as the aluminium skin does, due to its heating and conductive natural limitations. The aim of this paper is to propose some solutions for the design and the optimisation of the current return path in this new aeronautical environment, using a complex modelling method (PEEC-AMLFMM) coupled with, firstly, a path finding algorithm followed by an optimization process, secondly, with a global routing tool followed by an optimisation process and, thirdly, with a multi-agent system approach. A comparison between these methods is made. The first results obtained using our methodologies are promising, providing some solutions for the current return path in a composite aircraft.

   Piezoelectric 10W DC/DC converter for space applications
By Yuan-Ping LIU, Dejan VASIC, Francois COSTA, Denis SCHWANDER [View]
[Download]

Abstract: This paper implemented a 10W DC/DC converter based on the piezoelectric transformer (PT) for the space application. The PT operating frequency is fixed at zero voltage switching (ZVS) conditions in order to obtain the good efficiency. The input driving circuit of the PT was adopted the half-bridge circuit with a filtering inductor. The full-wave rectifier was adopted to obtain the DC load voltage. To fix the switching frequency and the duty cycle simultaneously, the hysteresis control and the burst mode operation were used. The results show the difficulty of this hysteresis control in the burst-mode operation is the accuracy of the load voltage.

   Solid state circuit breakers enabling optimised protection of DC aircraft power systems
By Steven FLETCHER, Patrick NORMAN, Stuart GALLOWAY, Graeme BURT [View]
[Download]

Abstract: Greater utilisation of DC power distribution within aircraft systems is still largely prevented by the significant challenge of developing lightweight, effective DC protection systems. By considering circuit breaker, fault detection and power network design aspects, this paper proposes new performance criteria for optimised protection of DC aircraft power systems and discusses the resulting system level design and operability benefits which can be attained. Through the analysis and simulation of a representative DC aircraft electrical system, fast acting fault detection and solid state circuit breaker technologies are identified as being critical to this scheme. This paper then presents analysis to help assess the impact of successfully implementing this protection scheme on the circuit breaker’s design and operation requirements.

EPE 2011 - LS3a: Topic 19: Aerospace and Space Applications
You are here: EPE Documents > 01 - EPE & EPE ECCE Conference Proceedings > EPE 2011 ECCE Europe - Conference > EPE 2011 - Topic 19: Electrical systems in aerospace, space, surface and marine transport (not road) > EPE 2011 - LS3a: Topic 19: Aerospace and Space Applications
	[return to parent folder]

	Design and optimization techniques for the current return path in a composite aircraft By Anca Lucia GOLEANU, Jean Michel GUICHON, Michel DUNAND, Pierre GLIZE, Arthur FREYCON, Jean-Luc SCHANEN, Jean-Louis COULOMB	[View] [Download]
Abstract: The emergence of new composite materials in the aeronautical domain requires a paradigm shift in the electrical system design, especially concerning the current return path. The composite fuselage cannot comply with the required functionalities, as the aluminium skin does, due to its heating and conductive natural limitations. The aim of this paper is to propose some solutions for the design and the optimisation of the current return path in this new aeronautical environment, using a complex modelling method (PEEC-AMLFMM) coupled with, firstly, a path finding algorithm followed by an optimization process, secondly, with a global routing tool followed by an optimisation process and, thirdly, with a multi-agent system approach. A comparison between these methods is made. The first results obtained using our methodologies are promising, providing some solutions for the current return path in a composite aircraft.

	Piezoelectric 10W DC/DC converter for space applications By Yuan-Ping LIU, Dejan VASIC, Francois COSTA, Denis SCHWANDER	[View] [Download]
Abstract: This paper implemented a 10W DC/DC converter based on the piezoelectric transformer (PT) for the space application. The PT operating frequency is fixed at zero voltage switching (ZVS) conditions in order to obtain the good efficiency. The input driving circuit of the PT was adopted the half-bridge circuit with a filtering inductor. The full-wave rectifier was adopted to obtain the DC load voltage. To fix the switching frequency and the duty cycle simultaneously, the hysteresis control and the burst mode operation were used. The results show the difficulty of this hysteresis control in the burst-mode operation is the accuracy of the load voltage.

	Solid state circuit breakers enabling optimised protection of DC aircraft power systems By Steven FLETCHER, Patrick NORMAN, Stuart GALLOWAY, Graeme BURT	[View] [Download]
Abstract: Greater utilisation of DC power distribution within aircraft systems is still largely prevented by the significant challenge of developing lightweight, effective DC protection systems. By considering circuit breaker, fault detection and power network design aspects, this paper proposes new performance criteria for optimised protection of DC aircraft power systems and discusses the resulting system level design and operability benefits which can be attained. Through the analysis and simulation of a representative DC aircraft electrical system, fast acting fault detection and solid state circuit breaker technologies are identified as being critical to this scheme. This paper then presents analysis to help assess the impact of successfully implementing this protection scheme on the circuit breaker’s design and operation requirements.