Power distribution center

• US 5,612,579 A
• Filed: 06/06/1995
• Issued: 03/18/1997
• Est. Priority Date: 08/27/1993
• Status: Expired due to Fees

• Current Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Rateike, Lee R., Wisbey, Peter J.
• Primary Examiner(s): Shoop, Jr., William M.
• Assistant Examiner(s): KAPLAN, JONATHAN STUART
• Application Number:
  US08/469,959
• Time in Patent Office: 651 Days
• Field of Search: 307/18, 307/19, 307/29, 307/38, 307/39, 307/40, 307/41, 307/42, 307/85-87, 307/71, 307/84, 307/57, 307/43, 307/64, 307/66, 307/9.1, 307/23, 307/24, 290/4 R, 322/28, 322/33, 364/492
• US Class Current: 307/18
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: H02B 1/015 Boards, panels, desks; Parts thereof or accessories therefor
• CPC Class Codes: H02H 3/28 involving comparison of the voltage or current values at two spaced portions of a single system, e.g. at opposite ends of one line, at input and output of apparatus for transformers H02H7/045
• CPC Class Codes: H02J 2310/44 for aircrafts
• CPC Class Codes: H02J 4/00 Circuit arrangements for mains or distribution networks not specified as ac or dc
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

An electric power distribution center for use on aircraft comprises a space frame having a first surface defining a plurality of sockets, and a second, generally parallel, surface defining a plurality of connector ports; a plurality of conducting bus bars utilizing a three dimensional routing configuration encapsulated within the space frame; current sensors integrally mounted within the space frame for monitoring the flow of electrical current through the conducting bus bars; and a printed circuit board encapsulated within the space frame for providing electrical circuit pathways within the power distribution center. Further, a plurality of load protection and control devices, seated within the sockets of the first surface, provide a switchable coupling between the bus bars and the printed circuit board to control the distribution of electric power to the individual aircraft loads. Connectors mounted on the second surface of the power distribution center provide the interface connection from the internal circuit connection means and current sensing means to external devices.

Claims

1. An electric power generation and distribution system for an aircraft, comprising:

a first source of electrical energy having a predetermined rated capacity of electric power generation;

a first power distribution center having a main power input, a secondary power output, and a plurality of load distribution outputs;

a first set of main power feeders coupling said source of electrical energy to said main power input of said first power distribution center for conducting electrical energy thereto, said first set of main power feeders being of a gauge sufficient to conduct at least the rated capacity of said source of electrical energy;

a second power distribution center remotely located from said first power distribution center, said second power distribution center having a secondary power input and a plurality of load distribution outputs;

a first set of secondary power feeders coupling said secondary power output of said first power distribution center to said secondary power input of said second power distribution center for conducting electrical energy thereto, said first set of secondary power feeders being of a gauge sufficient to conduct the electrical energy required by said second power distribution center;

a second source of electrical energy having a predetermined rated capacity of electric power generation;

a third power distribution center having a main power input, a secondary power output, and a plurality of load distribution outputs;

a second set of main power feeders coupling said second source of electrical energy to said main power input of said third power distribution center for conducting electrical energy thereto, said second set of main power feeders being of a gauge sufficient to conduct at least the rated capacity of said second source of electrical energy;

a fourth power distribution center remotely located from said third power distribution center, said fourth power distribution center having a secondary power input and a plurality of load distribution outputs;

a second set of secondary power feeders coupling said secondary power output of said third power distribution center to said secondary power input of said fourth power distribution center for conducting electrical energy thereto, said second set of secondary power feeders being of a gauge sufficient to conduct the electrical energy required by said fourth power distribution center; and

wherein said first power distribution center is located in close proximity to said third power distribution center in the center of the aircraft, and wherein said second power distribution center is located in the fore section of the aircraft, and wherein said fourth power distribution center is located in the aft section of the aircraft.

2. An electric power generation and distribution system as recited in claim 1, further comprising tie bus feeders coupling said first power distribution center to said third power distribution center, said tie bus feeders being of a gauge sufficient to conduct the electrical energy required by both said first power distribution center and said second power distribution center, and by both said third power distribution center and said fourth power distribution center.

3. An electric power distribution system for an aircraft having at least two engines, the aircraft generating electric power by electric generators driven by the engines, comprising:

a central power distribution center centrally located within the aircraft near the wing root, said central power distribution center electrically coupled to the generators for receiving electric power therefrom, said central power distribution center distributing electric power to utilization equipment in close proximity thereto;

a fore power distribution center located in the nose of the aircraft, said fore power distribution center electrically coupled to said central power distribution center and receiving electric power therefrom, said fore power distribution center distributing electric power to utilization equipment in close proximity thereto;

an aft power distribution center located near the tail of the aircraft, said aft power distribution center electrically coupled to said central power distribution for receiving electric power therefrom, said aft power distribution center distributing electric power to utilization equipment in close proximity thereto.

4. The system of claim 3, further comprising first means included within said central power distribution center for sensing current flow to said fore power distribution center, and second means included within said central power distribution center for sensing current flow to said aft power distribution center.

5. The system of claim 4, further comprising third means included within said fore power distribution center for sensing current flow from said central power distribution center, and fourth means included within said aft power distribution center for sensing current flow from said central power distribution center, said first means producing a first output signal proportional to sensed current flow to said fore power distribution center, said second means producing a second output signal proportional to sensed current flow to said aft power distribution center, said third means producing a third output signal proportional to sensed current flow from said central power distribution center, said fourth means producing a fourth output signal proportional to sensed current flow from said central power distribution center, and wherein differential current faults are detected by external control means between said central power distribution center and said fore power distribution center by monitoring said first and said third output signals from said first and said third means, and between said central power distribution center and said aft power distribution center by monitoring said second and said fourth output signals from said second and said fourth means.

6. The system of claim 3 wherein the aircraft additionally has an external power receptacle for receiving electric power from an external ground source, said fore power distribution center being electrically coupled to the external power receptacle for receiving electric power therefrom.

7. The system of claim 6, wherein said fore power distribution center additionally comprises an external power contactor for switchably allowing and interrupting electric power flow from the external power source.