COMPOSITE BARREL SECTIONS FOR AIRCRAFT FUSELAGES AND OTHER STRUCTURES, AND METHODS AND SYSTEMS FOR MANUFACTURING SUCH BARREL SECTIONS

• US 20080230652A1
• Filed: 05/20/2004
• Published: 09/25/2008
• Est. Priority Date: 04/06/2004
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: George, Terry J., Ingram, William H., Biornstad, Robert D., Blankinship, Bruce C.
• Granted Patent: US 7,527,222 B2
• Time in Patent Office: Days
• US Class Current: 244/120
• CPC Class Codes: B29C 53/587 having a non-uniform wall-structure, e.g. with inserts, perforations, locally concentrated reinforcements
• CPC Class Codes: B29C 70/32 on a rotating mould, former or core
• CPC Class Codes: B29C 70/382 Automated fiber placement [AFP]
• 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: B29D 99/0014 provided with ridges or ribs, e.g. joined ribs
• CPC Class Codes: B29L 2031/3082 Fuselages
• CPC Class Codes: B64C 1/068 Fuselage sections
• CPC Class Codes: B64C 1/12 Construction or attachment of skin panels
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 428/24636 Embodying mechanically interengaged strand[s], strand-portion[s] or strand-like strip[s] [e.g., weave, knit, etc.]

Abstract

Composite sections for aircraft fuselages and methods and systems for manufacturing such sections are disclosed herein. A composite section configured in accordance with one embodiment of the invention includes a skin and at least first and second stiffeners. The skin can include a plurality of unidirectional fibers forming a continuous surface extending 360 degrees about an axis. The first stiffener can include a first flange portion bonded to an interior surface of the skin and a first raised portion projecting inwardly and away from the interior surface of the skin. The second stiffener can include a second flange portion bonded to the interior surface of the skin and a second raised portion projecting inwardly and away from the interior surface of the skin. A method for manufacturing a section of a fuselage in accordance with one embodiment of the invention includes positioning a plurality of uncured stiffeners on a mandrel assembly. The method can further include applying a plurality of fiber tows around the plurality of uncured stiffeners on the mandrel assembly.

Claims

1. A section of an aircraft fuselage, the section comprising:

a sheet of composite fabric forming at least a first portion of a skin extending continuously for 360 degrees about a longitudinal axis of the section, the sheet of composite fabric having a preformed first width;

a plurality of fiber tows individually applied over the sheet of composite fabric, wherein each of the individual fiber tows has a second width that is narrower than the first width, and wherein the plurality of fiber tows form at least a second portion of the skin extending continuously for 360 degrees about the longitudinal axis of the section;

a first longitudinal stiffener having a first flange portion bonded to an interior surface of the sheet of composite fabric during a cocuring process, and a first raised portion projecting inwardly and away from the interior surface of the sheet of composite fabric;

at least a second longitudinal stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion bonded to the interior surface of the sheet of composite fabric during the cocuring process, and a second raised portion projecting inwardly and away from the interior surface of the sheet of composite fabric; and

a circumferential frame section extending across the first and second stiffeners, wherein the circumferential frame section is mechanically fastened to the skin and the first and second stiffeners after the cocuring process.

2. The section of claim 1 wherein each of the fiber tows includes a bundle of fibers preimpregnated with resin.

3. The section of claim 1 wherein each of the fiber tows includes a bundle of carbon fibers preimpregnated with epoxy resin, and wherein each of the collimated fiber tows has a compressed width from about 0.06 inch to about 0.50 inch.

4. The section of claim 1, further comprising a plurality of mechanical fasteners extending through a portion of the circumferential frame section and the skin.

5. The section of claim 1, further comprising a plurality of mechanical fasteners extending through a portion of the circumferential frame section and the first and second stiffeners.

6. The section of claim 1 wherein the circumferential frame section includes at least first and second openings, and wherein the first raised portion of the first stiffener extends through the first opening and the second raised portion of the second stiffener extends through the second opening.

9. The section of claim 1 wherein the plurality of fiber tows include a plurality of collimated fiber tows.

10. The section of claim 1 wherein the plurality of fiber tows include a plurality of compacted fiber tows.

7. A section of an aircraft fuselage, the section comprising:

a skin having a plurality of fiber tows forming a continuous surface extending 360 degrees about an axis;

a first stiffener having a first flange portion bonded to an interior surface of the skin and a first raised portion projecting inwardly and away from the interior surface of the skin;

at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion bonded to the interior surface of the skin and a second raised portion projecting inwardly and away from the interior surface of the skin, and

a frame section having a base portion mated to the first flange portion of the first stiffener and the second flange portion of the second stiffener without being mated to the skin between the first raised portion of the first stiffener and the second raised portion of the second stiffener.

8. A section of an aircraft fuselage, the section comprising:

a skin having a plurality of fiber tows forming a continuous surface extending 360 degrees about an axis;

a first stiffener having a first flange portion bonded to an interior surface of the skin and a first raised portion projecting inwardly and away from the interior surface of the skin, wherein the first flange portion has a first outer edge;

at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion bonded to the interior surface of the skin and a second raised portion projecting inwardly and away from the interior surface of the skin, wherein the second flange portion has a second outer edge facing the first outer edge of the first flange portion; and

a frame section having a base portion, wherein at least one of the first flange portion of the first stiffener and the second flange portion of the second stiffener extends toward the other of the first flange portion and the second flange portion to form an at least approximately continuous support surface extending between the first raised portion of the first stiffener and the second raised portion of the second stiffener, and wherein the base portion of the frame section mates to the at least approximately continuous support surface.

11. A section of an aircraft fuselage, the section comprising:

a sheet of composite fabric forming at least a first portion of a skin extending continuously for 360 degrees about a longitudinal axis of the section, the sheet of composite fabric having a preformed first width;

a plurality of fiber tapes individually applied over the sheet of composite fabric, wherein each of the individual fiber tapes has a second width that is narrower than the first width, and wherein the plurality of fiber tapes forms at least a second portion of the skin extending continuously for 360 degrees about the longitudinal axis of the section;

a first longitudinal stiffener having a first flange portion bonded to an interior surface of the sheet of composite fabric during a cocuring process, and a first raised portion projecting inwardly and away from the interior surface of the sheet of composite fabric;

at least a second longitudinal stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion bonded to the interior surface of the sheet of composite fabric during the cocuring process, and a second raised portion projecting inwardly and away from the interior surface of the sheet of composite fabric; and

a circumferential frame section extending across the first and second stiffeners, wherein the circumferential frame section is mechanically fastened to the skin and the first and second stiffeners after the cocuring process.

12. The section of claim 11 wherein each of the fiber tapes includes a plurality of unidirectional fiber strands preimpregnated with resin.

13. The section of claim 11 wherein each of the fiber tapes includes a plurality of unidirectional fiber strands interwoven into a fabric tape.

14. The section of claim 11 wherein each of the fiber tapes includes a plurality of unidirectional carbon fiber strands.

15. The section of claim 11, further comprising a plurality of mechanical fasteners extending through the circumferential frame section and the skin.

16. The section of claim 11, further comprising a plurality of mechanical fasteners extending through a portion of the circumferential frame section and the first and second stiffeners.

17. The section of claim 11 wherein the circumferential frame section includes at least first and second openings, and wherein the first raised portion of the first stiffener extends through the first opening and the second raised portion of the second stiffener extends through the second opening.

18. A section of an aircraft fuselage, the section comprising:

a skin having a plurality of fiber tapes forming a continuous surface extending 360 degrees about an axis;

a first stiffener having a first flange portion bonded to an interior surface of the skin and a first raised portion projecting inwardly and away from the interior surface of the skin, wherein the first flange portion has a first edge;

at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion bonded to the interior surface of the skin and a second raised portion projecting inwardly and away from the interior surface of the skin, wherein the second flange portion has a second edge opposite the first edge of the first flange portion; and

a frame section having a base portion, wherein at least one of the first flange portion of the first stiffener and the second flange portion of the second stiffener extends toward the other of the first flange portion and the second flange portion to form an at least approximately continuous support surface extending between the first raised portion of the first stiffener and the second raised portion of the second stiffener, and wherein the base portion of the frame section mates to the at least approximately continuous support surface.

19. A section of an aircraft fuselage, the section comprising:

a skin having a plurality of unidirectional fibers forming a continuous surface extending 360 degrees about an axis;

a first stiffener having a first flange portion mated to an interior surface of the skin and a first raised portion projecting inwardly and away from the skins wherein the first flange portion has a first edge; and

at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion mated to the interior surface of the skin and a second raised portion projecting inwardly and away from the skin, wherein the second flange portion has a second edge positioned adjacent to the first edge, and wherein at least one of the first flange portion of the first stiffener and the second flange portion of the second stiffener extends toward the other of the first flange portion and the second flange portion to form an at least approximately continuous support surface extending between the first raised portion of the first stiffener and the second raised portion of the second stiffener.

20. The section of claim 19, further comprising a frame section in contact with the support surface between the first raised portion of the first stiffener and the second raised portion of the second stiffener.

21. The section of claim 19, further comprising a frame section having at least first and second openings, wherein the first raised portion of the first stiffener extends through the first opening and the second raised portion of the second stiffener extends through the second opening.

22-62. -62. (canceled)

63. A section of an aircraft fuselage, the section comprising:

an inner fabric ply forming a continuous inner surface extending 360 degrees about an axis;

a plurality of unidirectional fiber strands laminated to an outer portion of the inner fabric ply to form a medial layer that is structurally different than the inner fabric ply; and

an outer fabric ply laminated to an outer portion of the plurality of unidirectional fiber strands, the outer fabric ply forming a continuous outer surface extending 360 degrees about the axis.

64. The section of claim 63 wherein the inner fabric ply includes a woven ply of composite material having a width of from about 12 inches to about 36 inches.

65. The section of claim 63 wherein the inner fabric ply includes a woven ply of composite material having a width of about 24 inches.

66. The section of claim 63 wherein the outer fabric ply includes a plurality of metallic wires for lightning strike protection.

67. The section of claim 63 wherein the plurality of unidirectional fiber strands are preimpregnated with resin.

68. The section of claim 63 wherein the plurality of unidirectional fiber strands include a plurality of fiber tows.

69. The section of claim 63 wherein the plurality of unidirectional fiber strands include a plurality of fiber tapes.

70. The section of claim 63 wherein the plurality of unidirectional fiber strands include a plurality of fiber tapes, and wherein each of the fiber tapes has a width of from about 0.06 inch to about 12 inches.

71. The section of claim 63 wherein the plurality of unidirectional fiber strands include a plurality of fiber tapes, and wherein each of the fiber tapes has a width of from about 0.125 inch to about 0.5 inch.

72. The section of claim 63, further comprising a stiffener having first and second flange portions bonded to the inner surface of the inner fabric ply, the stiffener further including an interior surface extending between the first and second flange portions, wherein the interior surface is spaced apart from the inner fabric ply and at least a portion of the interior surface faces the inner surface of the inner fabric ply.

73. The section of claim 63, further comprising:

a first stiffener having a first flange portion bonded to the inner surface of the inner fabric ply and a first raised portion projecting inwardly and away from the inner surface; and

at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion bonded to the inner surface of the inner fabric ply and a second raised portion projecting inwardly and away from the inner surface.

74. The section of claim 63, further comprising a frame section attached to the inner surface of the inner fabric ply.

75. A section of an aircraft fuselage, the section comprising:

an inner fabric ply forming a continuous inner surface extending 360 degrees about an axis, the inner fabric ply having a preformed first width;

a plurality of unidirectional fiber strands individually laminated to an outer portion of the inner fabric ply, wherein each of the individual unidirectional fiber strands have a second width that is narrower than the first width;

an outer fabric ply laminated to an outer portion of the plurality of unidirectional fibers, the outer fabric ply forming a continuous outer surface extending 360 degrees about the axis;

a first stiffener having a first flange portion bonded to the inner surface of the inner fabric ply and a first raised portion projecting inwardly and away from the inner surface;

at least a second stiffener spaced apart from the first stiffener, the second stiffener having a second flange portion bonded to the inner surface of the inner fabric ply and a second raised portion projecting inwardly and away from the inner surface; and

a frame section attached at least proximate to the inner surface of the inner fabric ply, wherein the frame section includes at least first and second openings, and wherein the first raised portion of the first stiffener extends through the first opening and the second raised portion of the second stiffener extends through the second opening.

76. The section of claim 75 wherein at least one of the first flange portion of the first stiffener and the second flange portion of the second stiffener extends toward the other of the first flange portion and the second flange portion to form an at least approximately continuous support surface extending between the first raised portion of the first stiffener and the second raised portion of the second stiffener, and wherein the frame section further includes a base section that is mated to the at least approximately continuous support surface.

77. (canceled)

78. An aircraft structure comprising:

a section of a passenger cabin, wherein the passenger cabin is configured to hold at least about 50 passenger seats, and wherein the section includes;

a skin extending continuously for 360 degrees about a longitudinal axis of the section, wherein the skin includes;

an inner fabric ply forming at least a portion of an inner surface of the skin, the inner fabric ply having a preformed first width;

a plurality of unidirectional fiber strands individually laminated to an outer portion of the inner fabric ply, wherein each of the individual unidirectional fiber strands has a second width that is narrower than the first width; and

an outer fabric ply laminated to an outer portion of the plurality of unidirectional fiber strands, the outer fabric ply forming at least a portion of an outer surface of the skin;

a first longitudinal stiffener bonded to the inner surface of the inner fabric ply during a cocuring process in which the skin and at least the first stiffener are cocured;

at least a second longitudinal stiffener spaced apart from the first stiffener and bonded to the inner surface of the inner fabric ply during the cocuring process; and

a circumferential frame section extending across the first and second stiffeners, wherein the circumferential frame section is mechanically fastened to the skin and the first and second stiffeners after the cocuring process.

79. The aircraft structure of claim 78 where the first stiffener has a first flange portion bonded to the inner surface of the skin and a first raised portion projecting inwardly and away from the inner surface of the skin, wherein the second stiffener has a second flange portion bonded to the inner surface of the skin and a second raised portion projecting inwardly and away from the inner surface of the skin, and wherein the circumferential frame section further comprises a base portion mated to the first flange portion of the first stiffener and the second flange portion of the second stiffener without being mated to the skin between the first raised portion of the first stiffener and the second raised portion of the second stiffener.

80. The aircraft structure of claim 78, further comprising at least 50 passenger seats, wherein the at least 50 passenger seats are positioned in the section of the passenger cabin.

81. The structure of claim 78 wherein the outer fabric ply includes a plurality of metallic wires for lightning strike protection.

82. The structure of claim 78 wherein the plurality of unidirectional fiber strands include a plurality of individual fiber tows.

83. An aircraft fuselage comprising:

a fuselage barrel section having a skin extending continuously for 360 degrees about a longitudinal axis of the barrel section, wherein the skin includes;

a plurality of composite fabric sheets extending continuously for 360 degrees about a longitudinal axis of the section, wherein each of the individual composite fabric sheets has a preformed first width; and

a plurality of fiber tows individually applied over the plurality of composite fabric sheets and extending continuously for at least 360 degrees about the longitudinal axis of the barrel section, wherein each of the individual fiber tows has a second width that is narrower than the first width;

a first longitudinal stiffener extending parallel to the longitudinal axis of the barrel section, wherein the first stiffener is bonded to an interior surface of the composite fabric sheets during a cocuring process in which the skin and at least the first stiffener are cocured; and

at least a second longitudinal stiffener extending parallel to the longitudinal axis of the barrel section and spaced apart from the first stiffener, wherein the second stiffener is bonded to the interior surface of the composite fabric sheets during the cocuring process.

84. The aircraft fuselage of claim 83 wherein the fuselage barrel section further includes:

an inner fabric ply extending continuously for 360 degrees about the longitudinal axis of the barrel section, wherein the plurality of fiber tows are laminated to an outer portion of the inner fabric ply; and

an outer fabric ply extending continuously for 360 degrees about the longitudinal axis of the barrel section, wherein the outer fabric ply is laminated to an outer portion of the plurality of fiber tows.

85. The aircraft fuselage of claim 83 wherein the fuselage barrel section is a first barrel section, wherein the skin is a first skin, wherein the longitudinal axis is a first longitudinal axis, and wherein the aircraft fuselage further comprises:

a second barrel section having a second skin extending continuously for 360 degrees about a second longitudinal axis of the second barrel section, wherein the second skin includes a plurality of fiber tows extending continuously for at least 360 degrees about the second longitudinal axis of the second barrel section; and

a circumferential joint attaching the first barrel section to the second barrel section so that the first longitudinal axis of the first barrel section is at least approximately aligned with the second longitudinal axis of the second barrel section.

86. The aircraft fuselage of claim 85, further comprising at least 50 passenger seats, wherein at least a portion of the 50 passenger seats are positioned in the first and second barrel sections.

87. The aircraft fuselage of claim 83 wherein the fuselage barrel section is a first barrel section, and wherein the aircraft fuselage further comprises:

a plurality of additional barrel sections, wherein the first barrel section and each of the additional barrel sections is at least substantially similar in construction;

a plurality of circumferential joints, wherein each of the circumferential joints joins one of the first barrel section and the additional barrel sections to another of the first barrel section and the additional barrel sections; and

at least 150 passenger seats, wherein the at least 150 passenger seats are positioned in the first barrel section and the additional barrel sections of the aircraft fuselage.

88. An aircraft fuselage comprising:

a one-piece barrel section having a cross-sectional dimension of at least 12 feet, wherein the barrel section includes;

a skin extending continuously for 360 degrees about a longitudinal axis of the barrel section, wherein the skin includes an inner fabric ply forming at least a portion of an inner surface of the skin, the inner fabric ply having a preformed first width, wherein the skin further includes a plurality of unidirectional fiber strands laminated to an outer portion of the inner fabric ply, the individual unidirectional fiber strands having a second width that is narrower than the first width, and wherein the skin additionally includes an outer fabric ply laminated to an outer portion of the plurality of unidirectional fiber strands, the outer fabric ply forming at least a portion of an outer surface of the skin;

a first stiffener bonded to the inner surface of the skin during a cocuring process in which the skin and at least the first stiffener are cocured; and

at least a second stiffener spaced apart from the first stiffener and bonded to the inner surface of the skin during the cocuring process.

89. The aircraft fuselage of claim 88 wherein the skin extends continuously for 360 degrees about the longitudinal axis of the barrel section in the absence of a longitudinally oriented joint attaching one portion of the skin to an adjacent portion of the skin.

90. The aircraft fuselage of claim 88, further comprising at least about 50 passenger seats, wherein at least a portion of the passenger seats are positioned in the barrel section.