Method for making freeform-fabricated core composite articles

• US 6,630,093 B1
• Filed: 08/17/2000
• Issued: 10/07/2003
• Est. Priority Date: 08/21/1999
• Status: Expired due to Fees

• Current Assignee: Ronald D. Jones
• Original Assignee: Ronald D. Jones
• Inventors: Jones, Ronald D.
• Primary Examiner(s): Tentoni, Leo B.
• Application Number:
  US09/641,405
• Time in Patent Office: 1,146 Days
• Field of Search: 264/136, 264/137, 264/160, 264/162, 264/236, 264/257, 264/308, 264/313, 264/401, 264/497, 264/510, 700/118, 700/119, 700/120
• US Class Current: 264/401
• CPC Class Codes: B29C 2035/0827 using UV radiation
• CPC Class Codes: B29C 35/02 Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mouldcold vulcanisation B29C35/18 ; vulcanising tyres, presses therefor B29D30/0601
• CPC Class Codes: B29C 70/088 and with one or more layers of non-plastics material or non-specified material, e.g. supports
• CPC Class Codes: B29C 70/44 using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• CPC Class Codes: B29C 70/542 Placing or positioning the reinforcement in a covering or packaging element before or during moulding, e.g. drawing in a sleeve
• CPC Class Codes: B29C 70/545 Perforating, cutting or machining during or after moulding
• CPC Class Codes: B29L 2012/00 Frames
• CPC Class Codes: B29L 2022/007 integrally moulded or formed
• CPC Class Codes: B29L 2031/608 Honeycomb structures
• CPC Class Codes: B29L 2031/737 Articles provided with holes, e.g. grids, sieves nets B29L2028/00
• CPC Class Codes: B33Y 10/00 Processes of additive manufacturing

Abstract

A method for making freeform-fabricated core composite articles using freeform-fabricated machine. The articles are capable of being utilized as end products rather than prototype models by creating a core having an interior structure to provide strength to the core and to enhance the strength to weight ratio of the article.

Claims

1. A method for creating a freeform-fabricated core composite article comprising the steps of:

a. creating a freeform-fabricated core having an exterior surface structure and an interior structure from freeform material, said freeform material being a material having a transition temperature of at least higher than the intended curing temperature of the freeform-fabricated core article, said interior structure having at least one structural pattern located therein, with a freeform-fabrication machine from a three-dimensional design generated by a computer of the freeform-fabricated core, wherein the freeform-fabricated core is dimensionally accurate;

b. preparing a plurality of composite skins for mating with the exterior surface structure of the freeform-fabricated core;

c. mating the plurality of composite skins to the exterior surface structure of the freeform-fabricated core forming a composite lay-up;

d. disposing a vacuum bag over the composite lay-up forming a cavity between the vacuum bag and the composite lay-up;

e. evacuating the cavity to urge the vacuum bag against the plurality of composite skins thereby compressing the plurality of composite skins against the exterior surface structure of the freeform-fabricated core preventing displacement of the composite skins; and

f. curing the composite lay-up to form the freeform-fabricated core composite article.

2. The method as recited in claim 1 in which the interior structure of the freeform-fabricated core comprises a solid interior structure.

3. The method as recited in claim 1 in which the interior structure of the freeform-fabricated core comprises a non-solid interior structure.

4. The method as recited in claim 1 in which the interior structure of the freeform-fabricated core comprises a combination of a solid interior structure and a non-solid interior structure.

5. The method as recited in claim 1 in which the interior structure of the freeform-fabricated core comprises a plurality of non-solid interior structures.

6. The method as recited in claim 1 in which the interior structure of the freeform-fabricated core comprises non-solid interior structures having a network of interconnected support walls defining the shape of the freeform-fabricated core composite article and leaving voids between the support members and is further characterized by infiltrating the voids with a reinforcing substance.

7. The method of claim 6 in which the reinforcing substance comprises glass beads in a binding matrix.

8. The method of claim 6 in which the reinforcing substance comprises carbon based material in a binding matrix.

9. The method of claim 1 further characterized by modifying the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of imbedded functionality within the interior structure of the freeform-fabricated core.

10. The method of claim 9 in which the plurality of imbedded functionality within the interior structure of the freeform-fabricated core comprises a plurality of space for components within the interior structure and is further characterized by adding a plurality of components where the plurality of components are received by the plurality of space for components in the interior structure.

11. The method in claim 10 in which the plurality of space for components within the interior structure comprises a space for the first conduit and a space for the second conduit, and the plurality of components comprises a first conduit and a second conduit, where the first conduit is received in the space for the first conduit and the second conduit is received in the space for the second conduit.

12. The method of claim 1 in which the freeform-fabricated core further comprises a plurality of freeform-fabricated core segments, the plurality of freeform-fabricated core segments are joined together at core joints, wherein the joined freeform-fabricated core segments form the freeform-fabricated core.

13. The method as recited in claim 12 in which the interior structure of the freeform-fabricated core comprises a solid interior structure.

14. The method as recited in claim 12 in which the interior structure of the freeform-fabricated core comprises a non-solid interior structure.

15. The method as recited in claim 12 in which the interior structure of the freeform-fabricated core comprises a combination of a solid interior structure and a non-solid interior structure.

16. The method as recited in claim 12 in which the interior structure of the freeform-fabricated core comprises a plurality of non-solid interior structures.

17. The method as recited in claim 12 in which the interior structure of the freeform-fabricated core comprises non-solid interior structures having a network of interconnected support walls defining the shape of the freeform-fabricated core composite article and leaving voids between the support members and is further characterized by infiltrating the voids with a reinforcing substance.

18. The method of claim 17 in which the reinforcing substance comprises glass beads in a binding matrix.

19. The method of claim 17 in which the reinforcing substance comprises carbon based material in a binding matrix.

20. The method of claim 12 further characterized by modifying the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of imbedded functionality within the interior structure of the freeform-fabricated core.

21. The method of claim 20 in which the plurality of imbedded functionality within the interior structure of the freeform-fabricated core comprises a plurality of space for components within the interior structure and is further characterized by adding a plurality of components where the plurality of components are received by the plurality of space for components in the interior structure.

22. The method in claim 21 in which the plurality of space for components within the interior structure comprises a space for the first conduit and a space for the second conduit, and the plurality of components comprises a first conduit and a second conduit, where the first conduit is received in the space for the first conduit and the second conduit is received in the space for the second conduit.

23. A method for creating a freeform-fabricated core composite article comprising the steps of:

a. designing a freeform-fabricated core having an exterior surface structure and an interior structure from freeform material, said freeform material being a material having a transition temperature of at least higher than the intended curing temperature of the freeform-fabricated core article, said interior structure having at least one structural pattern located therein, for the freeform-fabricated core composite article for fabrication with a freeform-fabrication machine, with a three-dimensional design generated by a computer of the freeform-fabricated core, wherein the three-dimensional design generated by a computer of the freeform-fabricated core is dimensionally accurate;

b. fabricating the freeform-fabricated core with the freeform-fabrication machine and the fabrication material from the three-dimensional design generated by a computer of the freeform-fabricated core such that the freeform fabrication machine cooperates with the fabrication material to fabricate the freeform-fabricated core on substantially a layer by layer basis;

c. preparing the fabricated freeform-fabricated core for mating with a plurality of composite skins;

d. preparing the plurality of composite skins for mating with the exterior surface of the freeform-fabricated core, the plurality of composite skins comprises fibrous reinforcement material disposed in a binding matrix;

e. mating the plurality of composite skins to the exterior surface structure of the freeform-fabricated core forming a composite lay-up;

f. disposing a vacuum bag over the composite lay-up forming a cavity between the vacuum bag and the composite lay-up;

g. evacuating the cavity to urge the vacuum bag against the plurality of composite skins thereby compressing the plurality of composite skins against the exterior surface structure of the freeform-fabricated core preventing displacement of the plurality of composite skins and removing excess binding matrix from the plurality of composite skins; and

h. curing the composite lay-up to form the freeform-fabricated core composite article.

24. The method of claim 23 further including the step of applying adhesive film between the exterior surface structure of the freeform-fabricated core and the plurality of composite skins.

25. The method as recited in claim 23 in which the interior structure of the freeform-fabricated core comprises a solid interior structure.

26. The method as recited in claim 23 in which the interior structure of the freeform-fabricated core comprises a non-solid interior structure.

27. The method as recited in claim 23 in which the interior structure of the freeform-fabricated core comprises a combination of a solid interior structure and a non-solid interior structure.

28. The method as recited in claim 23 in which the interior structure of the freeform-fabricated core comprises a plurality of non-solid interior structures.

29. The method as recited in claim 23 in which the interior structure of the freeform-fabricated core comprises non-solid interior structures having a network of interconnected support walls defining the shape of the freeform-fabricated core composite article and leaving voids between the support members and is further characterized by infiltrating the voids with a reinforcing substance.

30. The method of claim 29 in which the reinforcing substance comprises glass beads in a binding matrix.

31. The method of claim 29 in which the reinforcing substance comprises carbon based material in a binding matrix.

32. The method of claim 23 further characterized by modifying the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of imbedded functionality within the interior structure of the freeform-fabricated core.

33. The method of claim 32 in which the plurality of imbedded functionality within the interior structure of the freeform-fabricated core comprises a plurality of space for components within the interior structure and is further characterized by adding a plurality of components where the plurality of components are received by the plurality of space for components in the interior structure.

34. The method in claim 33 in which the plurality of space for components within the interior structure comprises a space for the first conduit and a space for the second conduit, and the plurality of components comprises a first conduit and a second conduit, where the first conduit is received in the space for the first conduit and the second conduit is received in the space for the second conduit.

35. The method of claim 23 in which the freeform-fabricated core further comprises a plurality of freeform-fabricated core segments, the plurality of freeform-fabricated core segments are joined together at core joints with fabrication material, wherein the joined freeform-fabricated core segments form the freeform-fabricated core.

36. The method as recited in claim 35 in which the interior structure of the freeform-fabricated core comprises a solid interior structure.

37. The method as recited in claim 35 in which the interior structure of the freeform-fabricated core comprises a non-solid interior structure.

38. The method as recited in claim 35 in which the interior structure of the freeform-fabricated core comprises a combination of a solid interior structure and a non-solid interior structure.

39. The method as recited in claim 35 in which the interior structure of the freeform-fabricated core comprises a plurality of non-solid interior structures.

40. The method as recited in claim 35 in which the interior structure of the freeform-fabricated core comprises non-solid interior structures having a network of interconnected support walls defining the shape of the freeform-fabricated core composite article and leaving voids between the support members and is further characterized by infiltrating the voids with a reinforcing substance.

41. The method of claim 40 in which the reinforcing substance comprises glass beads in a binding matrix.

42. The method of claim 40 in which the reinforcing substance comprises carbon based material in a binding matrix.

43. The method of claim 35 further characterized by modifying the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of imbedded functionality within the interior structure of the freeform-fabricated core.

44. The method of claim 43 in which the plurality of imbedded functionality within the interior structure of the freeform-fabricated core comprises a plurality of space for components within the interior structure and is further characterized by adding a plurality of components where the plurality of components are received by the plurality of space for components in the interior structure.

45. The method in claim 44 in which the plurality of space for components within the interior structure comprises a space for the first conduit and a space for the second conduit, and the plurality of components comprises a first conduit and a second conduit, where the first conduit is received in the space for the first conduit and the second conduit is received in the space for the second conduit.

46. The method in claim 23 further including a step modifying the three-dimensional design generated by a computer of the freeform-fabricated core to allow for the plurality of composite skins to be attached to the exterior surface structure of the freeform-fabricated core by reducing the exterior dimensions of the freeform-fabricated core to compensate for the thickness of the plurality of composite skins such that the freeform-fabricated core and the plurality of composite skins cooperate to provide the desired exterior dimension of the freeform-fabricated core composite article.

47. The method of claim 46 is further characterized by adding a plurality of ridges in the exterior surface structure of the freeform-fabricated core to cooperate with the plurality of composite skins having a predetermined number of layers in a predetermined region of the freeform-fabricated core composite article and to cooperate with the plurality of composite skins having a different predetermined number of layers in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

48. The method of claim 46 is further characterized by adding a plurality of ridges in the exterior surface structure to cooperate with the plurality of composite skins having a predetermined thickness in a predetermined region of the freeform-fabricated core composite article and to cooperate with the plurality of composite skins having a different predetermined thickness in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

49. A method for creating a freeform-fabricated core composite article comprising the steps of:

a. designing a freeform-fabricated core having an exterior surface structure and an interior structure from freeform material, said freeform material being a material having a transition temperature of at least higher than the intended curing temperature of the freeform-fabricated core article, said interior structure having at least one structural pattern located therein, for the freeform-fabricated core composite article with a three-dimensional computer aided design program to create a software file of a three-dimensional design generated by a computer of the freeform-fabricated core, wherein the three-dimensional design generated by a computer of the freeform-fabricated core is dimensionally accurate;

b. modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to allow for a plurality of composite skins to be attached to the exterior surface structure of the freeform-fabricated core by reducing the exterior dimensions of the freeform-fabricated core to compensate for the thickness of the plurality of composite skins such that the freeform-fabricated core and the plurality of composite skins cooperate to provide the desired exterior dimension of the freeform-fabricated core composite article;

c. exporting the modified software file of the three-dimensional design generated by a computer of the freeform-fabricated core into a machine language software file of the freeform-fabricated core;

d. importing the machine language software file of the freeform-fabricated core into a computer workstation, the computer workstation being of the type which produces control signals that control a freeform fabrication machine, the freeform fabrication machine having a build platform situated in a fabrication material storage area which holds fabrication material, the fabrication material being capable of cooperating with the freeform-fabrication machine to fabricate the freeform-fabricated core;

e. processing the machine language software file of the freeform-fabricated core by the computer workstation to create a freeform fabrication software file that contains a plurality of contiguous planar cross-sectional layers of the freeform-fabricated core to allow the freeform-fabricated core to be fabricated by the freeform fabrication machine on substantially a layer by layer basis;

f. fabricating the freeform-fabricated core with the freeform-fabrication machine and fabrication material from the freeform-fabrication software file in the computer workstation such that the combination of the freeform-fabrication software file, the computer workstation, the freeform-fabrication machine and the fabrication material cooperate to fabricate the freeform-fabricated core on substantially a layer by layer basis on the build platform;

g. removing the fabricated freeform-fabricated core from the build platform of the freeform-fabrication machine;

h. cleaning the freeform-fabricated core to remove any contaminants and any sacrificial build support material that may exist from the freeform-fabricated core;

i. curing the freeform-fabricated core;

j. finishing the cured freeform-fabricated core, wherein the imperfections, blemishes or excess cured fabrication material are eliminated from the freeform-fabricated core;

k. cutting the plurality of composite skins into a predetermined pattern wherein the pattern of the plurality of composite skins mates with the exterior surface structure of the freeform-fabricated core, the plurality of composite skins comprises fibrous reinforcement material disposed in a binding matrix;

l. mating the plurality of composite skins to the exterior surface structure of the freeform-fabricated core forming a composite lay-up;

m. disposing a vacuum bag assembly over the composite lay-up, the vacuum bag assembly comprising a vacuum bag, a separator film, a breather ply, and a vacuum pump where the separator film is disposed over the composite lay-up, the breather ply is disposed over the separator film, and the vacuum bag is disposed over the breather ply forming a plurality of cavities between the vacuum bag and the composite lay-up;

n. evacuating the plurality of cavities between the vacuum bag and the composite lay-up with the vacuum pump to urge the vacuum bag against the breather ply, to urge the breather ply against the separator film, to urge the separator film against the plurality of composite skins thereby compressing the plurality of composite skins against the exterior surface structure of the freeform-fabricated core preventing displacement of the plurality of composite skins and removing excess binding matrix from the plurality of composite skins;

o. curing the composite lay-up, wherein the composite lay-up is subjected to external stimulus that solidifies and hardens the composite lay-up forming a cured composite lay-up; and

p. finishing the cured composite lay-up, wherein the imperfections, blemishes or excess cured binding matrix are eliminated from the cured composite lay-up forming the freeform-fabricated core composite article.

50. The method as recited in claim 49 in which the interior structure of the freeform-fabricated core comprises a solid interior structure.

51. The method as recited in claim 49 in which the interior structure of the freeform-fabricated core comprises a non-solid interior structure.

52. The method as recited in claim 49 in which the interior structure of the freeform-fabricated core comprises a combination of a solid interior structure and a non-solid interior structure.

53. The method as recited in claim 49 in which the interior structure of the freeform-fabricated core comprises a plurality of non-solid interior structures.

54. The method as recited in claim 49 in which the interior structure of the freeform-fabricated core comprises non-solid interior structures having a network of interconnected support walls defining the shape of the freeform-fabricated core composite article and leaving voids between the support members and is further characterized by infiltrating the voids with a reinforcing substance.

55. The method of claim 49 further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of imbedded functionality within the interior structure of the freeform-fabricated core.

56. The method of claim 55 in which the plurality of imbedded functionality within the interior structure of the freeform-fabricated core comprises a plurality of space for components within the interior structure and is further characterized by adding a plurality of components where the plurality of components are received by the plurality of space for components in the interior structure.

57. The method in claim 56 in which the plurality of space for components within the interior structure comprises a space for the first conduit and a space for the second conduit, and the plurality of components comprises a first conduit and a second conduit, where the first conduit is received in the space for the first conduit and the second conduit is received in the space for the second conduit.

58. The method of claim 49 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined number of layers in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined number of layers in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

59. The method of claim 49 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined thickness in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined thickness in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality, of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

60. The method of claim 49 in which the freeform-fabricated core further comprises a plurality of freeform-fabricated core segments, the plurality of freeform-fabricated core segments are joined together at core joints with fabrication material, wherein the joined freeform-fabricated core segments form the freeform-fabricated core.

61. The method as recited in claim 60 in which the interior structure of the freeform-fabricated core comprises a solid interior structure.

62. The method as recited in claim 60 in which the interior structure of the freeform-fabricated core comprises a non-solid interior structure.

63. The method as recited in claim 60 in which the interior structure of the freeform-fabricated core comprises a combination of a solid interior structure and a non-solid interior structure.

64. The method as recited in claim 60 in which the interior structure of the freeform-fabricated core comprises a plurality of non-solid interior structures.

65. The method as recited in claim 60 in which the interior structure of the freeform-fabricated core comprises non-solid interior structures having a network of interconnected support walls defining the shape of the freeform-fabricated core composite article and leaving voids between the support members and is further characterized by infiltrating the voids with a reinforcing substance.

66. The method of claim 60 further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of imbedded functionality within the interior structure of the freeform-fabricated core.

67. The method of claim 66 in which the plurality of imbedded functionality within the interior structure of the freeform-fabricated core comprises a plurality of space for components within the interior structure and is further characterized by adding a plurality of components where the plurality of components are received by the plurality of space for components in the interior structure.

68. The method in claim 67 in which the plurality of space for components within the interior structure comprises a space for the first conduit and a space for the second conduit, and the plurality of components comprises a first conduit and a second conduit, where the first conduit is received in the space for the first conduit and the second conduit is received in the space for the second conduit.

69. The method of claim 60 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined number of layers in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined number of layers in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

70. The method of claim 60 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined thickness in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined thickness in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

71. The method of claim 49 further including the step of applying an adhesive film between the exterior surface structure of the freeform-fabricated core and the plurality of composite skins.

72. The method as recited in claim 71 in which the interior structure of the freeform-fabricated core comprises a solid interior structure.

73. The method as recited in claim 71 in which the interior structure of the freeform-fabricated core comprises a non-solid interior structure.

74. The method as recited in claim 71 in which the interior structure of the freeform-fabricated core comprises a combination of a solid interior structure and a non-solid interior structure.

75. The method as recited in claim 71 in which the interior structure of the freeform-fabricated core comprises a plurality of non-solid interior structures.

76. The method as recited in claim 71 in which the interior structure of the freeform-fabricated core comprises non-solid interior structures having a network of interconnected support walls defining the shape of the freeform-fabricated core composite article and leaving voids between the support members and is further characterized by infiltrating the voids with a reinforcing substance.

77. The method of claim 71 further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of imbedded functionality within the interior structure of the freeform-fabricated core.

78. The method of claim 77 in which the plurality of imbedded functionality within the interior structure of the freeform-fabricated core comprises a plurality of space for components within the interior structure and is further characterized by adding a plurality of components where the plurality of components are received by the plurality of space for components in the interior structure.

79. The method in claim 78 in which the plurality of space for components within the interior structure comprises a space for the first conduit and a space for the second conduit, and the plurality of components comprises a first conduit and a second conduit, where the first conduit is received in the space for the first conduit and the second conduit is received in the space for the second conduit.

80. The method of claim 71 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined number of layers in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined number of layers in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

81. The method of claim 71 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined thickness in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined thickness in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

82. The method of claim 71 in which the freeform-fabricated core further comprises a plurality of freeform-fabricated core segments, the plurality of freeform-fabricated core segments are joined together at core joints with fabrication material, wherein the joined freeform-fabricated core segments form the freeform-fabricated core.

83. The method as recited in claim 82 in which the interior structure of the freeform-fabricated core comprises a solid interior structure.

84. The method as recited in claim 82 in which the interior structure of the freeform-fabricated core comprises a non-solid interior structure.

85. The method as recited in claim 82 in which the interior structure of the freeform-fabricated core comprises a combination of a solid interior structure and a non-solid interior structure.

86. The method as recited in claim 82 in which the interior structure of the freeform-fabricated core comprises a plurality of non-solid interior structures.

87. The method as recited in claim 82 in which the interior structure of the freeform-fabricated core comprises non-solid interior structures having a network of interconnected support walls defining the shape of the freeform-fabricated core composite article and leaving voids between the support members and is further characterized by infiltrating the voids with a reinforcing substance.

88. The method of claim 82 further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of imbedded functionality within the interior structure of the freeform-fabricated core.

89. The method of claim 88 in which the plurality of imbedded functionality within the interior structure of the freeform-fabricated core comprises a plurality of space for components within the interior structure and is further characterized by adding a plurality of components where the plurality of components are received by the plurality of space for components in the interior structure.

90. The method in claim 89 in which the plurality of space for components within the interior structure comprises a space for the first conduit and a space for the second conduit, and the plurality of components comprises a first conduit and a second conduit, where the first conduit is received in the space for the first conduit and the second conduit is received in the space for the second conduit.

91. The method of claim 82 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined number of layers in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined number of layers in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

92. The method of claim 82 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined thickness in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined thickness in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

93. The method of claim 49 further including the step of impregnating the plurality of composite skins with the binding matrix.

94. The method as recited in claim 93 in which the interior structure of the freeform-fabricated core comprises a solid interior structure.

95. The method as recited in claim 93 in which the interior structure of the freeform-fabricated core comprises a non-solid interior structure.

96. The method as recited in claim 93 in which the interior structure of the freeform-fabricated core comprises a combination of a solid interior structure and a non-solid interior structure.

97. The method as recited in claim 93 in which the interior structure of the freeform-fabricated core comprises a plurality of non-solid interior structures.

98. The method as recited in claim 93 in which the interior structure of the freeform-fabricated core comprises non-solid interior structures having a network of interconnected support walls defining the shape of the freeform-fabricated core composite article and leaving voids between the support members and is further characterized by infiltrating the voids with a reinforcing substance.

99. The method of claim 93 further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of imbedded functionality within the interior structure of the freeform-fabricated core.

100. The method of claim 99 in which the plurality of imbedded functionality within the interior structure of the freeform-fabricated core comprises a plurality of space for components within the interior structure and is further characterized by adding a plurality of components where the plurality of components are received by the plurality of space for components in the interior structure.

101. The method in claim 100 in which the plurality of space for components within the interior structure comprises a space for the first conduit and a space for the second conduit, and the plurality of components comprises a first conduit and a second conduit, where the first conduit is received in the space for the first conduit and the second conduit is received in the space for the second conduit.

102. The method of claim 93 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined number of layers in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined number of layers in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

103. The method of claim 93 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined thickness in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined thickness in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

104. The method of claim 93 in which the freeform-fabricated core further comprises a plurality of freeform-fabricated core segments, the plurality of freeform-fabricated core segments are joined together at core joints with fabrication material, wherein the joined freeform-fabricated core segments form the freeform-fabricated core.

105. The method as recited in claim 104 in which the interior structure of the freeform-fabricated core comprises a solid interior structure.

106. The method as recited in claim 104 in which the interior structure of the freeform-fabricated core comprises a non-solid interior structure.

107. The method as recited in claim 104 in which the interior structure of the free form-fabricated core comprises a combination of a solid interior structure and a non-solid interior structure.

108. The method as recited in claim 104 in which the interior structure of the freeform-fabricated core comprises a plurality of non-solid interior structures.

109. The method as recited in claim 104 in which the interior structure of the freeform-fabricated core comprises non-solid interior structures having a network of interconnected support walls defining the shape of the freeform-fabricated core composite article and leaving voids between the support members and is further characterized by infiltrating the voids with a reinforcing substance.

110. The method of claim 104 further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of imbedded functionality within the interior structure of the freeform-fabricated core.

111. The method of claim 110 in which the plurality of imbedded functionality within the interior structure of the freeform-fabricated core comprises a plurality of space for components within the interior structure and is further characterized by adding a plurality of components where the plurality of components are received by the plurality of space for components in the interior structure.

112. The method in claim 111 in which the plurality of space for components within the interior structure comprises a space for the first conduit and a space for the second conduit, and the plurality of components comprises a first conduit and a second conduit, where the first conduit is received in the space for the first conduit and the second conduit is received in the space for the second conduit.

113. The method of claim 104 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined number of layers in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined number of layers in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

114. The method of claim 104 is further characterized by modifying the software file of the three-dimensional design generated by a computer of the freeform-fabricated core to incorporate a plurality of ridges in the exterior surface structure such that the exterior surface structure cooperates with the plurality of composite skins having a predetermined thickness in a predetermined region of the freeform-fabricated core composite article and cooperates with the plurality of composite skins having a different predetermined thickness in a different predetermined region of the freeform-fabricated core composite article to compensate for the thickness of the plurality of composite skins thereby providing the desired exterior dimension of the freeform-fabricated core composite article where the ridges form the boundaries between the regions.

115. The method of claim 71 further including the step of impregnating the plurality of composite skins with the binding matrix.