Power distribution architecture for aircraft

• US 8,890,355 B2
• Filed: 04/01/2010
• Issued: 11/18/2014
• Est. Priority Date: 08/13/2009
• Status: Expired due to Fees

• Current Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Maier, Josef, Beutel, Michael
• Primary Examiner(s): Fureman, Jared
• Assistant Examiner(s): VU, TOAN T
• Application Number:
  US12/752,447
• Publication Number:
  US 20110037315A1
• Time in Patent Office: 1,692 Days
• Field of Search: 307/9.1, 307/19, 244/58, 244/53.R, 244/135.R, 244/118.5
• US Class Current: 307/9.1
• CPC Class Codes: H02G 3/00 Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles installations of bus-bars H02G5/00; overhead installations H02G7/00; installations in or on the ground H02G9/00

Abstract

An aircraft power distribution architecture includes a power rail extending generally along the length of an aircraft for receiving power from a generator, and for distributing power through plug-in modules located along the length of the power rail.

Claims

1. An aircraft power distribution architecture comprising:

a power rail, said power rail extending generally along the length of an aircraft and receiving power directly from a generator, for distributing power through a plurality of plug-in modules located along the length of the power rail; and

said power rail receiving power directly from said generator at an intermediate position, said power rail directly connected to said generator without an intermediate power distribution center, and wherein said power rail supplies power in both a forward and rearward direction relative to the aircraft.

2. The architecture as set forth in claim 1, wherein an external power source may also communicate power into the power rail.

3. The architecture as set forth in claim 1, wherein some of said plurality of plug-in modules allow the connection of a plurality of components to the power rail.

4. The architecture as set forth in claim 3, wherein the plug-in modules may receive a secondary power distribution module, and control elements may be associated with the plug-in module.

5. The architecture as set forth in claim 4, wherein said control elements may include a transformer rectifier unit.

6. The architecture as set forth in claim 5, wherein said control elements include a generator control unit.

7. The architecture as set forth in claim 1, wherein said plug-in modules include solid state power control modules.

8. The architecture as set forth in claim 1, wherein an auxiliary power unit supplies power directly into said power rail without an intermediate power distribution center.

9. The architecture as set forth in claim 8, wherein said auxiliary power unit is to be located adjacent a rear portion of the aircraft.

10. The architecture as set forth in claim 9, wherein at least some of said modules are located at a location intermediate said generators and said auxiliary power unit.

11. The architecture as set forth in claim 8, wherein at least some of said modules are located at a location intermediate said generators and said auxiliary power unit.

12. An aircraft power distribution architecture comprising:

a power rail, said power rail extending generally along the length of an aircraft and receiving power directly from a generator, for distributing power through a plurality of modules located along the length of the power rail;

said power rail receiving power directly from said generators at an intermediate position, said power rail directly connected to said generator without an intermediate power distribution center, and wherein said power rail supplies power in both a forward and rearward direction relative to the aircraft;

an auxiliary power unit supplying power directly into said power rail without an intermediate power distribution center;

said auxiliary power unit to be located adjacent a rear portion of the aircraft; and

at least some of said modules being located at a location intermediate said generator and said auxiliary power unit.