Composite barrel sections for aircraft fuselages and other structures, and methods and systems for manufacturing such barrel sections
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/00
출원번호
US-0236355
(2008-09-23)
등록번호
US-8157212
(2012-04-17)
발명자
/ 주소
Biornstad, Robert D.
Blankinship, Bruce C.
George, Terry J.
Ingram, William H.
출원인 / 주소
The Boeing Company
대리인 / 주소
Perkins Coie LLP
인용정보
피인용 횟수 :
23인용 특허 :
164
초록▼
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 unid
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.
대표청구항▼
1. A section of an aircraft fuselage, the section comprising: an uncured inner fabric ply forming a continuous inner surface extending 360 degrees about an axis, wherein the inner fabric ply is comprised of a plurality of individual fabric sheets of fiber reinforced epoxy, and wherein each of the in
1. A section of an aircraft fuselage, the section comprising: an uncured inner fabric ply forming a continuous inner surface extending 360 degrees about an axis, wherein the inner fabric ply is comprised of a plurality of individual fabric sheets of fiber reinforced epoxy, and wherein each of the individual fabric sheets has a preformed first width parallel to the axis;a plurality of uncured unidirectional fiber strands individually laminated to an outer portion of the uncured inner fabric ply, wherein each of the individual unidirectional fiber strands has a second width parallel to the axis that is substantially less than the preformed first width, and wherein the plurality of uncured unidirectional fiber strands wrap continuously around the axis multiple times to cover a width of the inner fabric ply equal to the first width; andan uncured outer fabric ply laminated to an outer portion of the plurality of uncured unidirectional fiber strands, the uncured outer fabric ply forming a continuous outer surface extending 360 degrees about the axis, wherein the inner fabric ply, the plurality of unidirectional fiber strands, and the uncured outer fabric ply are cocured after the outer fabric ply is laminated to the outer portion of the unidirectional fiber strands. 2. The section of claim 1 wherein the inner fabric ply includes a woven ply of composite material having a width of from about 12 inches to about 36 inches. 3. The section of claim 1 wherein the inner fabric ply includes a woven ply of composite material having a width of about 24 inches. 4. The section of claim 1 wherein the outer fabric ply includes a plurality of metallic wires for lightning strike protection. 5. The section of claim 1 wherein the plurality of unidirectional fiber strands are preimpregnated with resin. 6. The section of claim 1 wherein the plurality of unidirectional fiber strands include a plurality of fiber tows. 7. The section of claim 1 wherein the plurality of unidirectional fiber strands include a plurality of fiber tapes. 8. The section of claim 1 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. 9. The section of claim 1 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. 10. The section of claim 1, 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. 11. The section of claim 1, 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; andat 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. 12. The section of claim 1, further comprising a frame section attached to the inner surface of the inner fabric ply. 13. A section of an aircraft fuselage having a longitudinal axis, the section comprising: a first ply of uncured, woven composite fabric forming at least a first portion of an uncured skin extending continuously for 360 degrees about the longitudinal axis of the section;a second ply of automatically-placed, uncured unidirectional fibers laminated to an outer portion of the woven composite fabric, wherein the unidirectional fibers form at least a second portion of the uncured skin extending continuously for 360 degrees about the longitudinal axis of the section;a first composite stiffener having a first flange portion and a first raised portion, wherein the first raised portion projects inwardly and away from an interior surface of the skin;at least a second composite stiffener spaced apart from the first composite stiffener, the second composite stiffener having a second flange portion and a second raised portion, wherein the second raised portion projects inwardly and away from the interior surface of the skin, and wherein the first flange portion of the first composite stiffener and the second flange portion of the second composite stiffener are bonded to the interior surface of the skin during a cocuring process in which the first ply of uncured composite fabric, the second ply of uncured unidirectional fibers, and the first and second composite stiffeners are cocured; anda frame section attached to the interior surface of the skin and extending across the first and second stiffeners. 14. The section of claim 13 wherein the frame section is a composite frame section having at least first and second openings, wherein the first raised portion of the first composite stiffener extends through the first opening and the second raised portion of the second composite stiffener extends through the second opening, and wherein the section further comprises: a third ply of woven composite fabric laminated to an outer portion of the unidirectional fibers, wherein the third ply of woven composite fabric forms at least a third portion of the skin extending continuously for 360 degrees about the longitudinal axis of the section; anda plurality of fasteners extending through the frame section and the skin to mechanically attach the frame section to the skin and the first and second stiffeners after the cocuring process. 15. The section of claim 13, further comprising a plurality of fasteners extending through the frame section and the skin to mechanically attach the frame section to the skin. 16. The section of claim 13, further comprising a plurality of fasteners, wherein a first portion of the fasteners extends through the frame section and the skin to attach the frame section to the skin, and wherein a second portion of the fasteners extends through the frame section, the first flange portion of the first stiffener, and the skin to attach the frame section to the first stiffener. 17. The section of claim 13 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. The section of claim 13 wherein the first ply sheet of uncured, woven composite fabric is preimpregnated with epoxy resin, and wherein the plurality of unidirectional fiber strands are preimpregnated with epoxy resin.
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Jacobs Jack H. ; Thomas Matthew M. ; Grosskrueger Duane D. ; Carpenter Bernie F. ; Perry Alan R., Composite structure adapted for controlled structural deformation.
Fryc Oldrich (Renton WA) Layton David J. (Federal Way WA) Storhoff Howard A. (Seattle WA), Double edged pressure sensitive folded tape application apparatus.
Jacobs Jack H. (St. Louis MO) Thomas Matthew M. (Madison IL) Grosskrueger Duane D. (Highlands Ranch CO) Carpenter Bernie F. (Littleton CO) Perry Alan R. (Morrison CO), Fabrication method for composite structure adapted for controlled structural deformation.
Barquet Henri (Chateauneuf les Martigues FRX) Negroni Pierre-Paul (Marseilles FRX) Plissonneau Bernard (Aix en Provence FRX), Frame made of a composite material, especially for the fuselage of an aircraft, and its method of production.
Frosch Robert A. Administrator of the National Aeronautics and Space Administration ; with respect to an invention of ( Mercer Island WA) Robinson Robert K. (Mercer Island WA) Tomlinson Harry M. (Bel, Fuselage structure using advanced technology fiber reinforced composites.
Spriggs Donald R. (San Diego CA) Taft William G. (Cardiff CA) Loedel Christian W. (San Diego CA), High strength structure assembly and method of making the same.
Jacobs Loyd D. (Bellevue WA) SenGupta Gautam (Benton WA) Spain Byron R. (Mulvane KS), Method and apparatus for wideband vibration damping of reinforced skin structures.
Maison, Serge; Meunier, Serge; Thibout, Cedric; Mouton, Luc; Payen, Herve; Vautey, Philippe; Coiffier-Colas, Carole; Delbez, Joel, Method for making parts in composite material with thermoplastic matrix.
Kondo, Junichi; Matsui, Nobuo, Method for producing fiber-reinforced composite semi-hardened product having joggle, and method for producing preformed structure using same.
Dublinski Alexander C. (Northford CT) Cooper Ronald J. (Milford CT) Fabian Edward J. (Derby CT) Jacaruso Gary J. (Milford CT) Ramey Philip J. (Milford CT) Toni Darryl M. (North Haven CT) Turner Matth, Method of fabricating a complex part made of composite material.
Caldwell John E. (Kent WA) Chapman Michael R. (Federal Way WA) Goodwin Kenneth J. (Seattle WA) Lowery Patrick A. (Auburn WA), Method of forming composite material articles.
Velicki, Alexander; Thrash, Patrick Joseph; Burgess, Roger Alan; Standish, Cole, Molding process and apparatus for producing unified composite structures.
Johnson,Brice A.; Spoon,Stephen S.; Darras,Randal S., Multiple head automated composite laminating machine for the fabrication of large barrel section components.
Roseburg Lawrence E. (Bellevue WA), Optimum aircraft body frame to body skin shear tie installation pattern for body skin/stringer circumferential splices.
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Solanille, Pierre; Fuchs, Heinrich; Lagrene, Gérad; Spychala, Hans-Jürgen; Christophe, Richard; Zeumer, Norbert, Structural element for an aircraft, especially an aircraft door.
Grantham,Kent; Harrison,Thomas D.; Kay,Robert M.; Kuss,Michael R.; Turnmire,William W.; Venskus,Mark K.; Whitcomb,Tory R.; Christie, legal representative,Rose; Christie, deceased,Peter S., Structural panels for use in aircraft fuselages and other structures.
Lin YouLing ; Hennessey A. Kathleen ; Pattikonda Ramakrishna ; Reddy Rajasekar ; Khaja Veera S. ; Cleavelin C. Rinn, System and method for circuit repair.
Chen Tung Chang (Villanova PA) Chen Thomas M. (Doylestown PA), System for monitoring the production of items which are initially difficult to physically inspect.
Engelbart,Roger W; Hannebaum,Reed; Schrader,Steve; Holmes,Scott T; Walters,Craig, Systems and method for identifying foreign objects and debris (FOD) and defects during fabrication of a composite structure.
Engelbart,Roger W.; Chapman,Michael R.; Johnson,Brice A.; Soucy,Kathryn A.; Hannebaum,Reed; Schrader,Steve, Systems and methods enabling automated return to and/or repair of defects with a material placement machine.
Thrash Patrick J. ; Miller Jeffrey L. ; Pallas Ken ; Trank Robert C. ; Fox Rhoda ; Korte Mike ; Codos Richard ; Korolev Alexandre ; Collan William, Table-driven software architecture for a stitching system.
Westre Willard N. ; Allen-Lilly Heather C. ; Ayers Donald J. ; Cregger Samuel E. ; Evans David W. ; Grande Donald L. ; Hoffman Daniel J. ; Rogalski Mark E. ; Rothschilds Robert J., Titanium-polymer hybrid laminates.
Biornstad, Robert D.; Blankinship, Bruce C.; George, Terry J.; Ingram, William H., Composite barrel sections for aircraft fuselages and other structures.
Chapman, Michael R.; Watson, Robert M.; Anderson, Donald A.; Piehl, Marc J.; Sweetin, Joseph L.; Grose, Douglas L., Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections.
Metschan, Stephen Lee; Phillips, Richard V.; Rotter, Daniel M., Flexible material transfer devices, flexible vacuum compaction devices, flexible vacuum chucks, and systems and methods including the same.
Vail, III, William Banning, Methods and apparatus to prevent failures of fiber-reinforced composite materials under compressive stresses caused by fluids and gases invading microfractures in the materials.
Rotter, Daniel M.; Coxon, Brad Andrew; Berg, Arvid J.; Phillips, Richard V.; Metschan, Stephen Lee; Willden, Kurtis Shuldberg; Nelson, Paul E., Methods and tools for forming composite structures with non-planar patterns of contours.
Rotter, Daniel M.; Berg, Arvid J.; Anderson, Joseph D.; Willden, Kurtis Shuldberg; Phillips, Richard V.; Metschan, Stephen Lee; Coxon, Brad Andrew; Pruss, Joseph J., Methods for assembling a skin of a composite structure.
Rotter, Daniel M.; Berg, Arvid J.; Anderson, Joseph D.; Willden, Kurtis Shuldberg; Phillips, Richard V.; Metschan, Stephen Lee; Coxon, Brad Andrew; Pruss, Joseph J., Systems and methods for assembling a skin of a composite structure.
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Rotter, Daniel M.; Chang, Paul Chih-Yung; Coxon, Brad A.; Nelson, Paul E.; Madden, Kimberlee; Macias, Henry; Noel, Jennifer Sue; Jeppesen, Eugene H.; Willden, Kurtis S.; Berg, Arvid J.; Phillips, Richard V.; Metschan, Stephen Lee; Kirchmeier, Stephen K.; Anderson, Joseph D.; Boner, Scott A., Systems and methods for assembling a skin of a composite structure.
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