WO2009023346A2 - Shaped composite stringers and methods of making - Google Patents

Shaped composite stringers and methods of making Download PDF

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Publication number
WO2009023346A2
WO2009023346A2 PCT/US2008/064427 US2008064427W WO2009023346A2 WO 2009023346 A2 WO2009023346 A2 WO 2009023346A2 US 2008064427 W US2008064427 W US 2008064427W WO 2009023346 A2 WO2009023346 A2 WO 2009023346A2
Authority
WO
WIPO (PCT)
Prior art keywords
stringer
composite
panel
stiffened
skin panel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/US2008/064427
Other languages
English (en)
French (fr)
Other versions
WO2009023346A3 (en
Inventor
Juan C. Guzman
Douglas A. Mccarville
Daniel M. Rotter
Brian G. Robins
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Priority to JP2010509536A priority Critical patent/JP2010527836A/ja
Priority to CN2008800165238A priority patent/CN101678890B/zh
Priority to EP08827299.2A priority patent/EP2152574B1/en
Priority to ES08827299.2T priority patent/ES2608817T3/es
Publication of WO2009023346A2 publication Critical patent/WO2009023346A2/en
Publication of WO2009023346A3 publication Critical patent/WO2009023346A3/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/02—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of definite length, i.e. discrete articles
    • B29C43/10—Isostatic pressing, i.e. using non-rigid pressure-exerting members against rigid parts or dies
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/064—Stringers; Longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/182—Stringers, longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C43/00—Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor
    • B29C43/32—Component parts, details or accessories; Auxiliary operations
    • B29C43/36—Moulds for making articles of definite length, i.e. discrete articles
    • B29C43/3642—Bags, bleeder sheets or cauls for isostatic pressing
    • B29C2043/3649—Inflatable bladders using gas or fluid and related details
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2022/00—Hollow articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/54—Balls
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1002—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina
    • Y10T156/1028—Methods of surface bonding and/or assembly therefor with permanent bending or reshaping or surface deformation of self sustaining lamina by bending, drawing or stretch forming sheet to assume shape of configured lamina while in contact therewith
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/31504—Composite [nonstructural laminate]

Definitions

  • the embodiments described herein generally relate to aircraft stringers, and more particularly relate to shaped composite stringers and methods of making these.
  • Aircraft generally include an airframe, which may be regarded as an underlying skeleton, to which skin panels are attached to form a smooth aerodynamic outer surface.
  • the wings also include underlying structure covered with skin panels.
  • skin panels are light and thin to minimize the weight of the aircraft and increase its payload and range. Since skin panels are thin, they are generally flexible and require stiffening to prevent undesired movement, flexing and vibration during flight.
  • Hat stringers have been used for decades in the aerospace industry for stiffening metal fuselage sections and metal wing skins on both commercial and military aircraft. These stringers are formed of thin metal panel with acute angles that result in a trapezoidal shape. Relatively simple metal-forming techniques are used to bend the metal into the acute angles required for this shape. These metal forming techniques include brake forming or rolling the metal into the hat stringer shape. These techniques allow the production of hat stringers with tight, constant angular bends and straight or flat legs. In FIG. 1 , for example, a hat stringer 10 is attached to a fuselage skin panel 20 by a series of fasteners 25 (two shown) that are attached at intervals along the leg 16 of the hat stringer 10.
  • the hat stringer 10 is trapezoidal having a flat upper surface 12 and sloping sides 14 that are at an angle to the legs 16, which are substantially aligned with the flat upper surface 12.
  • the intersection between sides 14 and legs 16 may be characterized as sharp, tight or having a small radius of curvature.
  • Composite materials that include a resin matrix and filler have found increasing application in the aerospace industry because of their relatively light weight and favorable physical properties.
  • the fillers may be reinforcing or non-reinforcing in nature and may be in a variety of shapes, for example, powders, particulates, fibers tapes of unidirectional fibers, woven fabrics, and the like.
  • the resins are organic polymeric materials that may include for example the commonly used epoxy resins.
  • hat stringers As composite materials (e.g., carbon fiber and epoxy matrix resin) became more prevalent in the industry for fuselage skin and wing skin panels, hat stringers remained popular for a variety of reasons. For example, while hat stringers can be made from a single stack of material, other less common shapes such as I-shaped, J-shaped, or T-shaped stiffeners require the combination of multiple stacks and radius fillers.
  • composite materials e.g., carbon fiber and epoxy matrix resin
  • FIG. 2 An example of a process for attaching composite stringers to a fuselage section is illustrated in FIG. 2.
  • a hat stringer 10 rests on fuselage skin which is backed by a semi-rigid caul sheet 35.
  • the interior of the hollow hat stringer 10 has an inflatable rubber bladder 36, and the exterior of the hat stringer 10 is covered by an inside mold line (IML) tool.
  • the bladder 36 is inflated while the IML tool provides outside pressure on the hat stringer 10.
  • the hat stringer 10 is consolidated to the fuselage skin 20 by pressure of the IML tool 30 (and the bladder 36) and curing of resin, while the caul sheet 35 controls the contour of the fuselage skin 20.
  • the composite material must be precisely located in the IML tool cavities to avoid over or under stuffing gaps.
  • the bladders must inflate during cure to apply compaction and cure pressure.
  • the caul sheet must be flexible enough to account for variations in material thickness and/or ply mislocation while at the same time being sufficiently rigid to create a smooth aerodynamic surface.
  • OML outside mould line
  • FIG. 3 An OML (outside mould line) cure process is shown in FIG. 3.
  • These cauls panels 42 shaped like the hat stringers 10, assist in forcing the composite material into the radius during the cure cycle and in smoothing out irregularities.
  • OML outside mold line tool
  • the fuselage skin 20 is backed by an outside mold line tool (OML) 32 and the hat stringer 10 rests on the fuselage 20, with a bladder 36 in its interior.
  • a caul panel 42 conforming to the exterior shape of the hat stringer 10 rests on the stringer 10.
  • a bag 40 envelopes at least the caul panel 42 and the upper surface of the fuselage skin 20.
  • a vacuum is pulled on the bag 40 while bladder 36 is inflated and pressure is applied via IML tool 32 to consolidate the hat stringer 10 to the fuselage as the resin cures to bond the composite fuselage skin to the composite stringer 10.
  • This caul panel-assisted co-cure method requires the fabrication and use of hundreds of uniquely designed, high maintenance, cauls and associated master tools which imposes a significant cost burden. Accordingly, it is desirable to develop composite stringers and methods of making these that simplify processes and reduce costs. In addition, it is desirable that the composite stringers have large radii to facilitate forming the stringer out of a composite blank.
  • the stringer shapes should perform as well, or better, structurally (e.g., resist column buckling and four-point bending) than traditional trapezoidal shaped hats, when made with composite materials.
  • other desirable features and characteristics of the composite stringers will become apparent from the subsequent detailed description and the appended claims, taken in conjunction with the accompanying drawings and the foregoing technical field and background.
  • An exemplary embodiment provides a stiffened skin panel of an aircraft that includes an aircraft skin panel of composite material and a composite stringer consolidated with the aircraft skin panel.
  • the stringer has a pair of stringer sides that each extend from a stringer top to a stringer leg. The stringer sides each curve smoothly and continuously through a wide radius curve to the stringer leg.
  • Another exemplary embodiment provides a stiffened panel of composite material and a composite stringer consolidated with the panel.
  • the stringer has a pair of stringer sides, each stringer side extending from a stringer top to a stringer leg.
  • An attachment zone includes a portion of the stringer and a portion of the panel proximate stringer point of attachment to the panel. The attachment zone is substantially free of broken or separated filler of the stringer composite material.
  • a further example of an embodiment provides a method of stiffening a composite panel with a stringer.
  • the method includes the steps of determining the location and spacing of stringers on a composite panel to be stiffened and positioning the composite panel on a mold tool. It further includes laying down forms conforming to the shapes of the stringers to be formed on the composite panel, at determined locations and intervals. Further the method includes preparing lay ups of composite material for forming into stringers; laying the prepared lay up of composite material over each of the forms; and enclosing at least the composite panel and lay up- covered forms with a vacuum bag.
  • the stringers are consolidated to the composite panel under heat and pressure to produce a stiffened composite panel.
  • the produced panel is characterized in that the stringers each have a pair of stringer sides that extend smoothly through a wide radius, continuous curve to a stringer leg.
  • FIG. 1 is a perspective view of a prior art hat stringer attached to an aircraft skin panel
  • FlG. 2 is a schematic end view depicting a prior art inside mold line lay up using an inflatable bladder and caul sheet
  • FIG. 3 is a schematic end view of a prior art outside mold line lay up using a caul panel and an inside bladder
  • FIG. 4 is a schematic end view of an exemplary embodiment of a lay up using an OML tool to fabricate a shaped composite stringer
  • FIGS. 5-9 illustrate a non-limiting list of exemplary embodiments of composite stringer shapes in end view.
  • FIG. 10 illustrates an exemplary embodiment of a method of making a stiffened panel.
  • Exemplary embodiments provide improved stringer structure and consolidation with a panel to be stiffened.
  • embodiments provide a smooth shape with large radius curvature, at least where the stringer sides merge into the stringer legs.
  • the sides of the stringer may have an inflexion point that is a smooth transition point.
  • the composite material used to form the stringer drapes naturally to conform to the smooth shape.
  • the contouring is sufficiently smooth and gradual (i.e., without sharp transitions and tight radii) that it permits the use of tape plies instead of fabric, resulting in significant weight savings. Structural integrity is maintained without impai ⁇ nent of stringer performance.
  • some of the exemplary embodiments of the stringers have sides that include an intermediate zone that in turn includes an inflexion point where the curvature of the stringer side transitions smoothly from a convex curve to a concave curve or from a concave curve to a convex curve.
  • smooth as it relates to the curvature of the stringer means transitioning from a straight line to a curve at a tangent point to the curve or from one curve to another curve at a mutual tangent point.
  • continuous as it pertains to curves means there are no discontinuities in the smooth curvature and no sharp bends or kinks.
  • the intermediate zone may be located along the stringer side proximate the center of the stringer (with reference to stringer height) or proximate the lower end or upper end of the stringer side.
  • Exemplary embodiments of the stringers are symmetrical on either side of a vertical center line, as shown in FIGS. 5-9, for example, and as described below.
  • Exemplary embodiments allow the fabric to drape to shape via its natural path based on its own inherent flexibility. This simplifies the fabrication process. Tape or fabric is applied over a shaped cure-mandrel without need for a stringer pre-forming operation, as is required for the tight radii of the traditional trapezoid hat stringer.
  • the cure mandrel used with these special shaped stringers may be selected from a variety of materials and may include for example a mandrel of a flyaway material (i.e., low density foam which eliminates the need for inflation bladders), an inflatable rubber bladder, or a removable solid or hollow mandrel.
  • Foam mandrels may be selected based on specific performance properties such as, acoustical attenuation, flame retardation and structural load carrying capability. By increasing the load carrying capability of the stringer through unique shaping, the cross sectional area may be reduced and weight savings may be realized
  • FIG. 4 is an exemplary embodiment of a lay up 100 that includes an OML tool 200 which supports the underside of an aircraft skin panel 150, such as a fuselage or wing panel.
  • a mandrel or inflatable bladder 120 rests on the upper surface of the aircraft skin panel 150, and flexible composite plies 110 are draped over the mandrel or bladder 120.
  • a vacuum bag 130 envelopes at least the ply-draped mandrel or bladder 120 to apply pressure to the press the plies 110 to the mandrel or bladder 120 when a vacuum is pulled on the bag 130. Because of the gradual smooth curves formed by draping of plies 1 10, the exemplary embodiment has no sharp or tight angles and has an inflexion point 102 along sides of the stringer to be formed when the plies 110 are cured.
  • the stringer 300 formed (FIG 6) from plies 1 10 is smoothly curved and the legs 308 of the stringer extend from the sides 304 of the stringer 300 in a smooth curve devoid of any sharp turns, "kinks" or tight angles.
  • Stringer 300 may be characterized as parabolic or bell-shaped.
  • the "attachment zone" of a composite stringer to a skin panel means the most inboard (relative to the stringer) zone where the stringer attaches to the panel, which is also known as the flange.
  • Other shapes are, of course, also possible and within the scope of the presently disclosed technology.
  • stringer 300 is substantially parabolic in shape and has a rounded top 302 curving downward to sides 304 in a convex curve. The sides 304 transition from the rounded top 302 at tangent points 305 to the curvature of the top 302 and then descend in a straight line before a transition at the tangent point of a wide radius curve 306 to the stringer legs 308.
  • Stringer 310 shown in FIG. 6 has a substantially flat top 312 with rounded curves 313 leading to sides 314 that extend smoothly downward, substantially vertically.
  • Each of the sides 314 in this example form an inflexion point 315.
  • the lower ends of sides 314 curve through a large radius turn 318 and extend to legs 316.
  • Stringer 320 shown in FIG. 7 may be characterized as substantially bell-shaped and also has a substantially flat top 322 with rounded extremities 325 extending to sides 324 that extend downward and curve through a large radius turn 328 to legs 326. As indicated, sides 324 may extend straight downward at a 90° angle to at and angle ⁇ that may range from about 90 to about
  • Stringer 340 shown in FIG. 8 has a rounded top 342 and is substantially parabolic or bell- shaped.
  • the rounded top 342 extends smoothly in a convex curvature to sides 344 that spread outward as they extend downward.
  • the sides 344 then extend through a wide angle curve 345 to form legs 346.
  • the angle ⁇ as indicated, may range from about 35 to about 65°
  • Stringer 350 shown in FIG. 9 has a rounded top 352 and is substantially parabolic or bell- shaped and has a rounder overall shape with shorter straight sides than stringer 340 of FIG. 8.
  • the rounded top 352 extends smoothly in a convex curvature to sides 354 that spread outward as they extend downward.
  • the sides 354 then extend through a wide angle curve 355 to form legs 356.
  • the angle ⁇ as indicated, may range from about 35 to about 65°.
  • FIG. 10 illustrates an exemplary embodiment of a method 400 of making the shaped composite stringers.
  • an OML tool is used.
  • process 410 a determination is made about stringer spacing and location on the skin panel, wing, fuselage or other component to be stiffened with stringers.
  • the component is laid down on the OML tool, in process 420.
  • Bladders or mandrels in the shape of the stringer are then laid on the component at predetermined positions and intervals, in process 430.
  • a tape lay up (or other composite fiber lay up) is then prepared in process 440.
  • the tape lay up may have a series of oriented stacked layers and the tape may be pre- impregnated with a suitable resin, such as epoxy resin.
  • a suitable resin such as epoxy resin.
  • the tape lay up is laid over the bladder or mandrel, in process 450.
  • the assembly of component, bladder or mandrel, and tape lay up is bagged within a vacuum bag, in process 460.
  • a vacuum is pulled on the bag, and the tape lay up is consolidated to the component, in process 470.
  • Typical temperature may be about 350 0 F for a typical epoxy resin matrix, and pressure may be about 85 psi. Other temperature and pressure conditions may apply to other resins.
  • the resin of the panel and of the stringer is the same.
  • the resin of the stringer and the resin of the panel are concurrently cured or "co- cured.”
  • This facilitates formation of a strong bond between the stringer and the panel as resin flows and consolidates into a matrix in the attachment zone includes both panel and stringer fillers.
  • the bag is removed, in process 480.
  • the stringer is now consolidated with the component.
  • the flexible draped tape forms a smoothly curved stringer thereby minimizing the possibility of structural issues in the stringer.
  • the stringer is free of tight radius curves or abrupt bends and has smooth, continuous, wide-radius curves. Further in some exemplary embodiments, the use of caul panels or caul sheets is not required. This eliminates the costs associated with using these devices.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Laminated Bodies (AREA)
PCT/US2008/064427 2007-05-24 2008-05-21 Shaped composite stringers and methods of making Ceased WO2009023346A2 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
JP2010509536A JP2010527836A (ja) 2007-05-24 2008-05-21 成形複合ストリンガー及び成形複合ストリンガーを作製する方法
CN2008800165238A CN101678890B (zh) 2007-05-24 2008-05-21 成形的复合长桁及其制造方法
EP08827299.2A EP2152574B1 (en) 2007-05-24 2008-05-21 Method of making shaped composite stringers
ES08827299.2T ES2608817T3 (es) 2007-05-24 2008-05-21 Método de fabricación de largueros conformados de material compuesto

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11/753,482 2007-05-24
US11/753,482 US7861969B2 (en) 2007-05-24 2007-05-24 Shaped composite stringers and methods of making

Publications (2)

Publication Number Publication Date
WO2009023346A2 true WO2009023346A2 (en) 2009-02-19
WO2009023346A3 WO2009023346A3 (en) 2009-06-04

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PCT/US2008/064427 Ceased WO2009023346A2 (en) 2007-05-24 2008-05-21 Shaped composite stringers and methods of making

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US (2) US7861969B2 (enExample)
EP (1) EP2152574B1 (enExample)
JP (1) JP2010527836A (enExample)
CN (1) CN101678890B (enExample)
ES (1) ES2608817T3 (enExample)
WO (1) WO2009023346A2 (enExample)

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CN101791821A (zh) * 2010-04-08 2010-08-04 中国航空工业集团公司北京航空制造工程研究所 一种大尺寸复合材料长桁的成形工装
US8419402B2 (en) 2007-11-08 2013-04-16 The Boeing Company Foam stiffened hollow composite stringer
US8570152B2 (en) 2009-07-23 2013-10-29 The Boeing Company Method and apparatus for wireless sensing with power harvesting of a wireless signal
US9694895B2 (en) 2008-11-25 2017-07-04 The Boeing Company Method of forming a reinforced foam-filled composite stringer
US11279462B2 (en) 2016-03-14 2022-03-22 The Boeing Company Heat shield assembly and method
US12252245B2 (en) 2021-01-20 2025-03-18 The Boeing Company Beaded composite structures and methods for manufacturing beaded composite structures

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GB0611875D0 (en) * 2006-06-15 2006-07-26 Airbus Uk Ltd A stringer for an aircraft wing and a method of forming thereof
US7861969B2 (en) 2007-05-24 2011-01-04 The Boeing Company Shaped composite stringers and methods of making
US20080302912A1 (en) * 2007-06-08 2008-12-11 The Boeing Company Bladderless Mold Line Conformal Hat Stringer
US8043554B2 (en) * 2007-06-08 2011-10-25 The Boeing Company Manufacturing process using bladderless mold line conformal hat stringer
US8100361B2 (en) * 2007-12-20 2012-01-24 Airbus Deutschland Gmbh Hull structure
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US9238335B2 (en) * 2008-07-10 2016-01-19 The Boeing Company Mandrel for autoclave curing applications
GB0813584D0 (en) * 2008-07-25 2008-09-03 Airbus Uk Ltd Method of stiffening a rib
FR2940176B1 (fr) * 2008-12-22 2011-02-11 Aircelle Sa Procede de fabrication d'un panneau d'attenuation acoustique, notamment pour l'aeronautique
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CN101791821B (zh) * 2010-04-08 2011-09-14 中国航空工业集团公司北京航空制造工程研究所 一种大尺寸复合材料长桁的成形装置
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EP2152574A2 (en) 2010-02-17
EP2152574B1 (en) 2016-12-07
JP2010527836A (ja) 2010-08-19
US7861969B2 (en) 2011-01-04
CN101678890B (zh) 2013-01-16
US20110088833A1 (en) 2011-04-21
ES2608817T3 (es) 2017-04-17
US20080290214A1 (en) 2008-11-27
CN101678890A (zh) 2010-03-24
WO2009023346A3 (en) 2009-06-04
US8377247B2 (en) 2013-02-19

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