CONFIGURABLE HARNESS

• US 20180286531A1
• Filed: 06/17/2016
• Published: 10/04/2018
• Est. Priority Date: 06/19/2015
• Status: Active Grant

• Current Assignee: Airbus Canada Limited Partnership
• Original Assignee: Bombardier Incorporated
• Inventors: EL HADDAD, Anthony, DESY, Philippe, GAUDREAU, Jean-Guy
• Granted Patent: US 10,304,588 B2
• Time in Patent Office: Days
• CPC Class Codes: B60R 16/0207 Wire harnesses
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: B64D 47/00 Equipment not otherwise provided for
• CPC Class Codes: F16D 66/00 Arrangements for monitoring working conditions, e.g. wear, temperature
• CPC Class Codes: H01B 7/0045 Cable-harnesses
• CPC Class Codes: H01B 7/009 Cables with built-in connecting points or with predetermined areas for making deviations
• CPC Class Codes: H01R 24/28 Coupling parts carrying pins, blades or analogous contacts and secured only to wire or cable

Abstract

There is described herein a harness (106) that remains neutral until configured by a configuration device (110). Wires that connect to specific pins responsible for the configuration of a system are taken out and connected to a configuration port (108) on the harness (106). The configuration port (108), when mated with the configuration device (110), sets a configuration setting of the system. The configuration device (110) may be used to set the power and/or signal parameters of the harness (106) for a system or to configure various options within the system itself or another system.

Claims

1. An aircraft assembly comprising:

a structural component adapted to receive a system having at least a first configuration setting and a second configuration setting; and

a cable harness installed within the structural component and comprising;

a set of conducting wires having at least a first end and a second end;

a connector at the first end of the conducting wires for connecting to the system to provide signals or electrical power thereto; and

a configuration port intermediate to the first end and the second end and adapted for receiving a configuration device for configuring the cable harness to one of the first configuration setting and the second configuration setting, wherein the cable harness is neutral to the first configuration setting and the second configuration setting until the configuration device is mated with the configuration port.

2. The aircraft assembly of claim 1, wherein the first configuration setting and the second configuration setting comprise a first power level and a second power level, respectively, and wherein the cable harness is configurable to one of the first power level and the second power level by the configuration device.

3. The aircraft assembly of claim 1, wherein the first configuration setting and the second configuration setting comprise a first aircraft option and a second aircraft option, respectively, and wherein the cable harness is configurable to one of the first aircraft option and the second aircraft option by the configuration device.

4. The aircraft assembly of claim 1, wherein the configuration port is one of a male and a female connector, and the configuration device is the other of the male and female connector.

5. The aircraft assembly of claim 1, wherein the structural component is suitable for at least two aircraft models, the first configuration setting corresponding to a first aircraft model and the second configuration setting corresponding to a second aircraft model.

6. The aircraft assembly of claim 1, wherein the configuration port comprises at least three output pins, and wherein the configuration device shorts two of the at least three output pins together to configure the cable harness.

7. The aircraft assembly of claim 1, wherein the at least a first configuration setting and a second configuration setting comprises a plurality of configuration settings, the plurality of configuration settings corresponding to configurable options on the aircraft specified for one of at least two aircraft models.

8. The aircraft assembly of claim 1, wherein the system is a line replaceable unit (LRU).

9. The aircraft assembly of claim 8, wherein the LRU is one of an avionics system, a brake system, a fly by wire system, a fuel system, and a landing gear system.

10. A kit for configuring an aircraft system to one of at least two configuration settings, the kit comprising:

(a) a cable harness comprising;

a set of conducting wires having at least a first end and a second end;

a connector at the first end of the conducting wires for connecting to the aircraft system and adapted for providing signals or electrical power thereto; and

a configuration port intermediate to the first end and the second end; and

(b) at least one configuration device matable with the configuration port and adapted for configuring the cable harness to one of the first configuration setting and the second configuration setting, wherein the cable harness is neutral to the first configuration setting and the second configuration setting until the configuration device is mated with the configuration port.

11. The kit of claim 10, wherein the at least one configuration device comprises a first configuration device adapted for configuring the cable harness to the first configuration setting and a second configuration device adapted for configuring the cable harness to the second configuration setting.

12. The kit of claim 10, wherein the first configuration setting and the second configuration setting comprise a first power level and a second power level, respectively, and wherein the cable harness is configurable to one of the first power level and the second power level by the configuration device.

13. The kit of claim 10, wherein the first configuration setting and the second configuration setting comprise a first aircraft option and a second aircraft option, respectively, and wherein the cable harness is configurable to one of the first aircraft option and the second aircraft option by the configuration device.

14. The kit of claim 10, wherein the configuration port is one of a male and a female connector, and the configuration device is the other of the male and female connector.

15. The kit of claim 10, wherein the configuration port comprises at least three output pins, and wherein the configuration device shorts two of the at least three output pins together to configure the cable harness.

16. The kit of claim 10, wherein the at least a first configuration setting and a second configuration setting comprises a plurality of configuration settings, the plurality of configuration settings corresponding to configurable options on the aircraft specified for one of at least two aircraft models.

17. A method for configuring an aircraft system to one of at least two configuration settings, the method comprising:

receiving an aircraft assembly comprising a structural part and a cable harness installed therein, the aircraft assembly as received being neutral to the at least two configuration settings, the cable harness having a configuration port for receiving a configuration device;

assembling the aircraft assembly with the aircraft system at a final assembly line; and

mating the configuration device with the configuration port of the cable harness at the final assembly line, thereby configuring the system to a given one of the at least two configuration settings.

18. The method of claim 17, wherein assembling the aircraft assembly with the aircraft system comprises assembling the aircraft assembly with a line replaceable unit (LRU) selected from a group comprising an avionics system, a brake system, a fly by wire system, a fuel system, and a landing gear system.

19. The method of claim 17, wherein mating the configuration device with the configuration port comprises inserting a connector into the configuration port to short two of at least three output pins together to configure the cable harness.

20. The method of claim 17, wherein receiving an aircraft assembly comprises receiving an aircraft assembly suitable for at least two aircraft models, and each one of the at least two configuration settings correspond to one of the at least two aircraft models.