Modular equipment center distributed equipment packaging truss

• US 9,561,760 B2
• Filed: 10/11/2013
• Issued: 02/07/2017
• Est. Priority Date: 10/11/2013
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Shander, Mark S., Larsen, Ty A., Johnson, Robert T, Liffring, Mark E., Douglas, Margaret, Severns, Christopher M.
• Primary Examiner(s): Fureman, Jared
• Assistant Examiner(s): Yeshaw, Esayas
• Application Number:
  US14/052,304
• Publication Number:
  US 20150102660A1
• Time in Patent Office: 1,215 Days
• Field of Search: 307/9.1
• US Class Current: 1/1
• CPC Class Codes: B60R 16/0238 Electrical distribution centers
• CPC Class Codes: B64C 1/06 Frames; Stringers; Longerons ; Fuselage sections
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: B64C 1/18 Floors
• CPC Class Codes: B64C 2001/0072 from composite materials
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• 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
• CPC Class Codes: H02G 3/30 Installations of cables or lines on walls, floors or ceilings
• CPC Class Codes: Y02T 10/70 Energy storage systems for electromobility, e.g. batteries
• CPC Class Codes: Y02T 10/7072 Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A modular truss assembly configured to be placed in small or narrow spaces such as within the floor, sidewall, or crown of a vehicle for mechanically and electrically mounting system components of a modular equipment center (MEC). A plurality of MECs is spatially distributed throughout the vehicle to service equipment loads. The modular truss assembly provides different voltage levels for powering the system components of the MEC and for powering the equipment loads. In one or more configurations, all or part of the modular truss assembly can be removed from the vehicle for repair or replacement.

Claims

1. A truss assembly for a composite air vehicle, comprising:

a mounting structure configured to electrically and mechanically mount system components for the vehicle, the mounting structure extending between support structure of the composite air vehicle, the mounting structure configured such that different portions provide different voltage levels for the system components within the vehicle.

2. The truss assembly of claim 1 wherein at least a portion of the mounting structure is detachable from the support structure of the composite air vehicle such that at least a portion of the mounting structure is replaceable within the composite air vehicle.

3. The truss assembly of claim 1 wherein the mounting structure defines part of a modular equipment center (MEC).

4. The truss assembly of claim 3 wherein at least one portion of the mounting structure transfers power from one portion of the MEC to another portion of the MEC.

5. The truss assembly of claim 4 wherein the one portion is a high power portion of a primary MEC and the other portion is a low power portion of the primary MEC.

6. The truss assembly of claim 5 wherein the low power portion of the primary MEC provides secondary power to equipment loads serviced by the primary MEC.

7. The truss assembly of claim 1 wherein at least one portion of the mounting structure provides data communication to at least one system component mounted to the mounting structure.

8. The truss assembly of claim 1 wherein separate portions of the mounting structure are configured to provide separate communication channels to system components mounted to the mounting structure.

9. The truss assembly of claim 1 wherein the mounting structure comprising a plurality of structural elements such that the truss assembly is modular.

10. The truss assembly of claim 9 wherein the structural elements have a similar shape.

11. The truss assembly of claim 9 wherein at least a portion of at least a pair of structural elements overlap.

12. The truss assembly of claim 11 wherein at least one electrical connection is defined where the pair of structural elements overlap.

13. The truss assembly of claim 11 wherein mechanical and electrical connections are defined where the pair of structural elements overlap.

14. The truss assembly of claim 9 wherein at least a portion of at least a pair of structural elements overlap in a mirror image relationship.

15. The truss assembly of claim 9 wherein the structural elements are detachable from one another such that a damaged structural element may be replaced without removing undamaged structural elements from the composite air vehicle.

16. The truss assembly of claim 1 mounted within a thin structural volume defined between support structure of the composite air vehicle.

17. The truss assembly of claim 1 wherein at least a portion of the truss assembly is configured to conform to at least a portion of the support structure of the composite air vehicle.

18. The truss assembly of claim 17 wherein at least a portion of the truss assembly conforms to at least a portion of a floor beam of an aircraft.

19. The truss assembly of claim 1 wherein the truss assembly is configured as a barrier to obstruct smoke from entering a passenger area of the composite air vehicle.

20. The truss assembly of claim 1 wherein the truss assembly is configured as a barrier to obstruct water from contacting electronics mounted to the truss assembly.

21. The truss assembly of claim 1 wherein the composite air vehicle is an aircraft and the truss assembly is mounted in a floor between a passenger compartment and a cargo compartment.

22. The truss assembly of claim 21 wherein system components on the truss assembly mounted in the floor are coupled to equipment loads in proximity of the truss assembly.

23. The truss assembly of claim 22 wherein the system components on the truss assembly are coupled to equipment loads in the passenger compartment and the cargo compartment that are in proximity of the truss assembly.

24. The truss assembly of claim 1 wherein the composite air vehicle is an aircraft and the truss assembly is mounted in a sidewall of the aircraft in proximity of equipment loads and is configured to correspond with a curvature of a fuselage of the aircraft.

25. The truss assembly of claim 1 wherein the composite air vehicle is an aircraft and the truss assembly is configured to be mounted in a crown of the aircraft.

26. The truss assembly of claim 1 wherein the composite air vehicle is an aircraft and the truss assembly is mounted in a crown of the aircraft in proximity of equipment loads.

27. The truss assembly of claim 1 wherein the composite air vehicle is an aircraft and a portion of the truss assembly is configured to extend between adjacent floor beams within a floor of the aircraft and another portion of the truss assembly is configured to extend below the floor and between adjacent stanchions supporting the floor of the aircraft.

28. The truss assembly of claim 1 without exposed power connections between the truss assembly and a line replaceable unit (LRU) mounted there on.

29. The truss assembly of claim 1 further comprising a barcode wherein a barcode reader coupled to system equipment mounted to the truss assembly is configured to read data relating to the composite air vehicle from the barcode.

30. A truss assembly for a composite air vehicle, comprising:

a first mounting structure and a second mounting structure at least partially overlapping one another to mechanically and electrically interconnect vehicle system components to the vehicle, the first and second mounting structures electrically and mechanically interconnected to one another, and each of the first and second mounting structures electrically conductive and adapted to carry different power levels relative to each other, and the truss assembly extending between support structure of the composite air vehicle.

31. The truss assembly of claim 30 wherein at least one of the first and second mounting structures is detachable from the composite air vehicle.

32. The truss assembly of claim 30 wherein the first mounting structure carries a first voltage and the second mounting structure caries a second voltage, and wherein the first voltage is higher than the second voltage.

33. The truss assembly of claim 32 further comprising a third mounting structure carrying a voltage different from the first and second voltages carried by the first and second mounting structures, respectively.

34. The truss assembly of claim 30 wherein each mounting structure comprises a plurality of elongated segments, the elongated segments interconnected to define a plurality of nodes for mechanical and electrical connections.

35. The truss assembly of claim 34 wherein one or more nodes of the first mounting structure overlap one or more nodes of the second mounting structure.

36. The truss assembly of claim 35 wherein a density of the nodes in at least one of the first and second mounting structures increases in proximity of components mounted to the truss assembly.

37. The truss assembly of claim 30 wherein one of the first and second mounting structures is thicker than the other and the thicker of the first and second mounting structures carries a higher voltage than the other of the first and second mounting structures.

38. The truss assembly of claim 30 wherein electrical isolation is maintained between the first and second mounting structures.

39. The truss assembly of claim 30 wherein when one of the first or second mounting structures is damaged, the damaged mounting structure can be replaced by a third mounting structure without moving the truss assembly.

40. A truss assembly for a composite air vehicle, comprising:

at least first and second grids providing structural support for system equipment electrically and mechanically coupled thereto, each of the first and second grids comprising a plurality of connected segments joined at nodes to other segments to form a pattern of open cells extending between support structure of the composite air vehicle.

41. The truss assembly of claim 40 wherein at least a portion of the first grid overlaps at least a portion of the second grid.

42. The truss assembly of claim 41 wherein at least one node of the first grid overlaps at least one node of the second grid.

43. The truss assembly of claim 42 wherein at least one of the overlapping nodes of the first and second grids is used as a mechanical connection point for a vehicle system.

44. The truss assembly of claim 42 wherein at least one of the overlapping nodes of the first and second grids is used as a mechanical connection point for securing the truss assembly to the composite air vehicle.

45. The truss assembly of claim 40 wherein the first and second grids are configured to carry different voltages relative to one another.

46. The truss assembly of claim 40 wherein the first and second grids are detachable from one another.

47. The truss assembly of claim 40 wherein the pattern of the first grid is different from the pattern of the second grid.

48. The truss assembly of claim 40 wherein the open cells of the first grid are sized and oriented differently than the open cells of the second grid.

49. The truss assembly of claim 40 wherein at least a portion of the open cells are non-rectangular.

50. The truss assembly of claim 40 wherein at least a portion of the open cells are hexagonal.

51. The truss assembly of claim 40 wherein a density of a pattern of open cells in one of first and second grids in greater than a density of a pattern of open cells in the other of the first and second grids.

52. The truss assembly of claim 40 further comprising a third grid, wherein at least one node of the first, second and third grids overlap one another.