Electrical power distribution system (HV270DC), for application in more electric aircraft

In the new designs of military aircraft and unmanned aircraft there is a clear trend towards increasing demand of electrical power. This fact is mainly due to the replacement of mechanical, pneumatic and hydraulic equipments by partially or completely electrical systems. Generally, use of electrical power onboard is continuously increasing within the areas of communications, surveillance and general systems, such as: radar, cooling, landing gear or actuators systems. To cope with this growing demand for electric power, new levels of voltage (270 VDC), architectures and power electronics devices are being applied to the onboard electrical power distribution systems. The purpose of this paper is to present and describe the technological project HV270DC. In this project, one Electrical Power Distribution System (EPDS), applicable to the more electric aircrafts, has been developed. This system has been integrated by EADS in order to study the benefits and possible problems or risks that affect this kind of power distribution systems, in comparison with conventional distribution systems.

[1]  Yan Yangguang,et al.  Electrical power distribution system based on 1553B bus for advanced aircraft , 2005, 2005 International Conference on Electrical Machines and Systems.

[2]  J.A. Ortega,et al.  Moving towards a more electric aircraft , 2007, IEEE Aerospace and Electronic Systems Magazine.

[3]  S. J. Cutts,et al.  A collaborative approach to the More Electric Aircraft , 2002 .

[4]  Douglas K. Lindner,et al.  Power Systems and Requirements for Integration of Smart Structures into Aircraft , 2004 .

[5]  A. Lazaro,et al.  SSPC model with variable reset time, environmental temperature compensation and thermal memory effect , 2008, 2008 Twenty-Third Annual IEEE Applied Power Electronics Conference and Exposition.

[6]  N. M. Shah,et al.  Power management and distribution system for a more-electric aircraft (MADMEL)-program status , 1996 .

[7]  Rebecca Todd,et al.  Ultra-compact Intelligent Electrical Networks , 2008 .

[8]  P. Zumel,et al.  Protection devices for aircraft electrical power distribution systems: a survey , 2008, 2008 34th Annual Conference of IEEE Industrial Electronics.

[9]  M. David Kankam,et al.  A Survey of Power Electronics Applications in Aerospace Technologies , 2001 .

[10]  Cary Spitzer The All-Electric Aircraft: A Systems View and Proposed NASA Research Programs , 1984, IEEE Transactions on Aerospace and Electronic Systems.

[11]  I. Cotton,et al.  Higher voltage aircraft power systems , 2008, IEEE Aerospace and Electronic Systems Magazine.

[12]  David Howe,et al.  Small-signal Stability Studies of 270 V DC Power System for More Electric Aircraft Employing Switched Reluctance Generator Technology , 2006 .

[13]  Mehrdad Ehsani,et al.  Aircraft power systems: technology, state of the art, and future trends , 2000 .

[14]  M. Howse,et al.  All-electric aircraft , 2003 .

[15]  Boeing Phantom,et al.  SUBSYSTEM DESIGN AND INTEGRATION FOR THE MORE ELECTRIC AIRCRAFT , 2007 .