WO2004076769A2 - Contact stiffeners for structural skins - Google Patents
Contact stiffeners for structural skins Download PDFInfo
- Publication number
- WO2004076769A2 WO2004076769A2 PCT/US2004/005585 US2004005585W WO2004076769A2 WO 2004076769 A2 WO2004076769 A2 WO 2004076769A2 US 2004005585 W US2004005585 W US 2004005585W WO 2004076769 A2 WO2004076769 A2 WO 2004076769A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- stiffening member
- internal stiffening
- member according
- flange
- rib
- Prior art date
Links
- 239000003351 stiffener Substances 0.000 title description 4
- 239000000463 material Substances 0.000 claims abstract description 52
- 239000000853 adhesive Substances 0.000 claims abstract description 44
- 230000001070 adhesive effect Effects 0.000 claims abstract description 44
- 239000000945 filler Substances 0.000 claims abstract description 42
- 230000002093 peripheral effect Effects 0.000 claims abstract description 22
- 230000006835 compression Effects 0.000 claims abstract description 16
- 238000007906 compression Methods 0.000 claims abstract description 15
- 230000014759 maintenance of location Effects 0.000 claims abstract description 9
- 239000007787 solid Substances 0.000 claims abstract description 7
- 238000000034 method Methods 0.000 claims description 19
- 230000007246 mechanism Effects 0.000 claims description 7
- 238000006073 displacement reaction Methods 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 6
- 230000003213 activating effect Effects 0.000 claims description 4
- 239000013536 elastomeric material Substances 0.000 claims description 2
- 239000000696 magnetic material Substances 0.000 claims description 2
- 239000011800 void material Substances 0.000 claims description 2
- 239000007788 liquid Substances 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 11
- 238000004519 manufacturing process Methods 0.000 description 11
- 230000008901 benefit Effects 0.000 description 7
- 229920005989 resin Polymers 0.000 description 6
- 239000011347 resin Substances 0.000 description 6
- 230000008569 process Effects 0.000 description 5
- 238000012546 transfer Methods 0.000 description 5
- 239000000835 fiber Substances 0.000 description 4
- 238000009730 filament winding Methods 0.000 description 4
- 238000001721 transfer moulding Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 3
- 230000006641 stabilisation Effects 0.000 description 3
- 238000011105 stabilization Methods 0.000 description 3
- 230000004913 activation Effects 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 2
- 238000009954 braiding Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 238000009787 hand lay-up Methods 0.000 description 2
- 230000006698 induction Effects 0.000 description 2
- 238000001802 infusion Methods 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 229920000914 Metallic fiber Polymers 0.000 description 1
- 239000004677 Nylon Substances 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000009734 composite fabrication Methods 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 238000010107 reaction injection moulding Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 229920001169 thermoplastic Polymers 0.000 description 1
- 229920001187 thermosetting polymer Polymers 0.000 description 1
- 239000004416 thermosoftening plastic Substances 0.000 description 1
Classifications
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- 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
- B64C1/068—Fuselage sections
-
- 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
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
-
- 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
-
- 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
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic 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
Definitions
- the present invention relates to structural skin.
- the present invention relates to methods and apparatuses for stiffening structural skin.
- Structural skin is often used in manufacturing large parts, such as aircraft wing torque boxes, fuselages or control surface structures. This type of structure utilizes thin skins that would not be stable under bending and torsion loads that produce significant shear or compression in the walls. This type of construction is typical of most aerospace structures including wings, fuselages, control surfaces, tail booms, etc. Structural skins can be made thinner, and are, therefore, more weight efficient, when internal stiffening elements are used.
- a rib for example, is a structural stiffening element that is disposed perpendicular to the longitudinal axis of a box beam, i.e., the rib lies in a cross-sectional plane of the beam structure.
- Ribs serve a variety of purposes in thin-skinned structure, including: (1 ) to provide support for the skin/skin stringer or spar panels against catastrophic buckling; (2) to maintain shape and contour of the skin; (3) to provide stiffness at major load introduction points; (4) to distribute concentrated loads into surrounding thinner structure; (5) to provide a shear redistribution path in the case of failure of any structural elements; and (6) to distribute pressure into the skin.
- These ribs are typically located at major load introduction points. In most instances, the entire rib is used to react loads; however, in some instances only certain regions of the rib is used to react loads. In addition, some ribs do not have any load introduction points, but react internal pressure loads.
- One-piece closed cell structures can economically be produced with a variety of methods, including filament winding, automated tape placement, resin transfer molding, and others.
- these assembly-tolerance issues often preclude the use of one-piece closed-cell torque box structures with secondarily attached internal ribs, i.e., slipped-in ribs.
- a substantial cost savings could be realized if the assembly tolerance issues could be overcome.
- Several composite fabrication technologies are available to economically produce such a joint-free torque-box structure, including filament winding, automated tape placement, resin transfer molding, and others. Practical application of one-piece, jointless torque box structures has been limited because of the difficulty of installing the internal stiffening ribs. A rib installation design that allowed for large assembly tolerances and the resulting gaps between the rib and the torque box skins would enable more widespread application of these cost-saving technologies.
- a slip-in rib or other stiffening member, of varying configurations in which the stiffening elements support the skin using a compression-only load path.
- the stiffening element has a peripheral edge that is adapted to be press fit into contact with the skin.
- the stiffening member may be held in place by various retention devices.
- Another configuration is a slip-in rib having a flange with a peripheral channel in which a filler material is disposed. The rib is inserted into an assembled structural box beam, and the filler material is used to fill any gaps between the slip-in rib and the interior surface of the structural box beam.
- the filler material is preferably an expandable material, such as an expandable foam-type material.
- the filler material is preferably a structural adhesive or liquid shim material.
- a solid adhesive or filler would not crush under the clamping forces from fasteners or bolts at localized fitting attachments.
- the present invention provides significant advantages, including: (1 ) costs associated with manufacturing closed-box structures are reduced due to relaxed tolerances and the ability to reduce part count; (2) failure of the rib/box bond is not a significant structural concern, because shear transfer through the rib/box bond is a secondary load path; (3) tolerance build-up is accommodated, because the slip-in ribs can be bonded in place as one-piece ribs; and (4) manufacturing labor is reduced, because fastener installation is reduced or eliminated.
- Figure 1 is a perspective view of a conical tail boom of an aircraft having stiffening members according to the present invention
- Figure 2 is a longitudinal cross-sectional view of the tail boom of Figure 1 showing several types of stiffening members according to the present invention installed therein;
- Figure 3 is an exploded perspective view of a box beam structure having a slip-in rib according to the present invention
- Figure 4 is an exploded top view of the box beam structure having a slip-in rib of Figure 3 showing the installation location of the slip-in rib;
- Figure 5 is a cross-sectional view of the box beam structure having a slip-in rib of Figure 4 taken at V-V;
- Figure 6 is a cross-sectional view of the box beam structure having a slip-in rib of Figure 5 taken at VI-VI;
- Figures 7A and 7B are alternate embodiments of the box beam structure having a slip-in rib according to the present invention.
- Figure 8 is another alternate embodiment of the box beam structure having a slip-in rib according to the present invention.
- Figure 9 is another alternate embodiment of the box beam structure having a slip-in rib according to the present invention.
- Figure 10 is a perspective view of the slip-in ribs of Figures 8 and 9.
- a curved structural skin can be stabilized with circumferential stiffening elements, such as frames or ribs, or longitudinal stiffening elements, such as longerons, stringers, or caps.
- the present invention represents the basic discovery that the internal support mechanism for reacting buckling and retaining shape in structural skin can perform functionally through compressive load transfer only. In other words, the structural attachment of internal stiffening elements to the skin and other frame elements is redundant and unnecessary. As such, either type of stiffening element can be allowed to float relative with the skin using compression- only "contact" support, provided the stiffening element is trapped or supported by the attached or integral stiffening elements in the other primary direction.
- the present invention is useful over a wide range of industries, and provides valuable benefits and advantages in any application in which it is desirable to internally support a structural skin.
- the present invention is described herein with reference to certain aircraft applications, it will be appreciated that the methods and apparatuses of the present can be used in many different applications.
- Non-linear finite element analysis of box beam structures has shown that ribs with only enough structural connection to hold them in place are quite effective in supporting skins against initial buckling, and in allowing load redistribution to occur in post-buckled skins.
- the reason for this is that in order for the beam cross-section to deform when a panel buckles, for example, the members supporting the edges of that panel must move toward one another. This collapsing deformation is resisted by internal ribs, which prevent the edge members from moving toward one another.
- the ribs react collapsing deformations in compression, so no shear attachment to the skins or spars is required.
- the rib perimeter bond can then be considered very damage tolerant, because local discontinuities and damage do not impact the performance of the rib.
- the present invention is a means of supporting the skin/skin stringer or spar panels against catastrophic buckling, and for maintaining the shape and contour of a structural box beam, such as aircraft wing torque boxes or control surface structures.
- a structural box beam such as aircraft wing torque boxes or control surface structures.
- the subject invention covers two main concepts: (1) that structural stiffening elements can be installed into assembled thin-skinned structures without fasteners or shims; and (2) that the structural attachment of these stiffening elements to the skins of the structural box beam and spars is redundant and not necessary.
- Tail boom 11 includes a skin 13 that is supported longitudinally by a plurality of elongated spaced apart longerons 15 and circumferentially by a plurality of slip-in ribs 17.
- Skin 13 is made with using a number of methods, including filament winding, braiding, fiber placement, or hand lay-up with either prepreg, thermoset or thermoplastic, or resin infusion methods, such as resin transfer molding, or variations, such as pultrusion, extrusion, or roll forming from metallic or composite sheets or panels of fiber composite laminates.
- Longerons 15 are co- cured or integral with skin 13.
- Slip-in ribs 1 include castellations 18 to fit around longerons 15.
- Slip-in ribs 17 are simply inserted through the large end opening of conical tail boom 11 and pressed into place. The peripheral edges of slip-in ribs 17 are press fit into contact with the interior surface of skin 13. Thus, there is no need for any filler between the peripheral edges of slip-in ribs 17 and the interior surface of skin 13 to account for tolerances. In most applications, slip-in ribs 17 are held in place by retention means, such as snap-in clips, springs, or detent devices. Slip-in ribs 17 may have a wide variety of shapes and configurations. Four possible configurations are shown in Figure 2. Slip-in rib 19 is a solid plug, slip-in rib 21 has a C-channel configuration with a solid web portion 27. Slip-in rib 23 has an open C-channel configuration with a central aperture or truss structure 29, and slip-in rib 25 has an open I-beam configuration having a central aperture or truss structure
- tail boom 11 is formed by a flat skin with longitudinal stiffeners wrapped into a conical shape to form a tailboom structure.
- Box beam 111 is a one-piece, thin- walled hollow structure having walls 113, 115, 117, and 119. Walls 113 and 115 form upper and lower surfaces of box beam 111 , and walls 117 and 119 form side walls of box beam 111. As is shown, walls 113, 115, 117, and 119 may include additional material at corners 114, 116, 118, and 120 to provide longitudinal stiffness to box beam 111 , if desired.
- Box beam 111 is internally supported by at least one slip-in rib 121.
- Slip-in rib 121 has an internal web portion 123 and a peripheral flange portion 125.
- web portion 123 has been shown as a solid plate member, it should be understood that web portion 123 may include apertures and/or a truss arrangement (not shown) that would allow cables, wiring, and other component parts to pass longitudinally through box beam 111.
- Flange portion 125 includes a recessed channel 127 that extends along the periphery of slip-in rib 121. Web portion 123 and flange portion 125 cooperate to allow slip-in rib 121 to function as an I-beam. This configuration allows slip-in rib 121 to be very strong in compression, which the primary functional load transfer path of the present invention.
- Walls 113, 115, 117, and 119 are typically integrally formed by filament winding, braiding, fiber placement or hand lay-up with either prepreg or resin infusion methods such as resin transfer molding, or variations such as, pultrusion, or extrusion, or roll forming from metallic sheets or panels of fiber composite laminates, and slip-in ribs 121 are preferably fabricated from either a metallic or non-metallic fiber filled machining-tolerant plate material. Compression or injection molding or reaction injection molding may also be used to produce net molded ribs. However, it will be appreciated that walls 113, 115, 117, and 119 and slip-in ribs 121 may be formed from other suitable materials, depending upon load, assembly, and application requirements.
- walls 113, 115, 117, and 119 cannot be integrated or pre-assembled without attaching the internal ribs and other support structures.
- One major benefit of the present invention is that walls 113, 115, 117, and 119 can be integrally produced or assembled prior to installation of the internal support network. This is because slip-in ribs 121 are configured to facilitate installation into an integral or one piece box beam 111.
- slip-in rib 121 The location of slip-in rib 121 after installation into box beam 111 is shown in dashed lines in Figure 4. As is shown, a small clearance, or gap 131, exists between the exterior edges of flange 125 and the interior surfaces of walls 113, 115, 117, and 119. This gap allows slip-in ribs 121 to be quickly and easily inserted into the interior of box beam 111. As will be explained in more detail below, gap 131 allows slip-in ribs 121 to accommodate certain manufacturing tolerances, as well. Although only one slip-in rib 121 is shown, it will be appreciated that as many slip-in ribs 121 as are necessary to provide the desired support for box beam 111 may be installed into box beam 111. Slip-in ribs 121 may be installed from either end of box beam 111.
- box beam 111 with slip-in rib 121 installed is shown in a cross-sectional view taken at V-V of Figure 4.
- the peripheral shape and contour of slip-in rib 121 closely match the internal shape and contour of box beam 111. This ensures that gap 131 between the exterior edges of flange 125 and the interior surfaces of walls 113, 115, 117, and 119 is generally uniform, even though manufacturing tolerances may dictate that there be a finite gap of varying size therebetween.
- box beam 111 with slip-in rib 121 installed is shown in a cross-sectional view taken at VI-VI of Figure 5.
- a filler material 141 is disposed in channel 127.
- Filler material 141 may partially fill channel 127, fully fill channel 127, or overfill channel 127.
- the filler material 141 is an expandable foam-type adhesive that is installed in channel 127 prior to the insertion of slip-in rib 121 into the interior of box beam 111 , and then activated so as to make the adhesive expand and fill channel 127 and gap 131.
- the process for activating expandable adhesive 141 is typically an increased temperature and or increased pressure curing process in which the temperatures and duration of curing depend upon the particular expandable adhesive used and the load and response characteristics desired. This process allows a relatively large clearance to be maintained for ease of insertion and assembly of slip-in ribs 121.
- the entire structure can be heated in a large oven to activate the expandable adhesive
- local means of heat can also be used including by placing resistive heating elements or strips in proximity of the adhesive or inside or adjacent to the adhesive and passing a current through the resistive material through contacts.
- Resistive heating elements can be embedded into the skin lay-up adjacent to the rib and a network of contacts or wires can be routed to a point of external access.
- Induction heating can be employed by using magnetic material in proximity or in the adhesive and introducing a magnetic field.
- Induction heating can also be used with a magnetic layer embedded into the skin lay-up in proximity of the adhesive.
- channel 127 shows expandable filler material 141 prior to activation, and the lower portion of channel 127 shows expandable filler material after activation and expansion. As is shown, after expandable filler material
- channel 127 and gap 131 are filled with expandable filler material 141.
- filler material 141 is an expandable filler material that may not bond with slip-in rib 121 or walls 113, 115, 117, and 119, but still provides an acceptable mechanical lock to react lateral pressure loads on slip-in rib 121.
- a recessed groove or slot 118 is added to the interior surface of walls 113, 115, 117, and 119 opposite flange 125.
- Channel 127 and slot 118 are filled with filler material 141.
- filler material 141 forms a mechanical lock which provides longitudinal stability and helps prevent slip-in rib 121 from moving longitudinally relative to walls 113, 115, 117, and 119.
- circumferential grooves 151 are added at the bond interface to trap filler material 141 as filler material 141 expands. After curing filler material 141 , grooves 151 provide longitudinal stability and help prevent slip-in rib
- slip-in rib 121 and the interior of walls 113, 115, 117, and 119 is not critically loaded.
- Slip-in rib 121 can provide buckling support and shape retention through compressive load transfer only.
- the structural bond formed by filler material 141 is only secondary.
- slip-in ribs according to the present invention that are suitable for use as both secondary and primary structural ribs are illustrated.
- the rib For primary structural ribs, the rib must be bonded using a structural adhesive and/or mechanically fastened to the skin of the structural box beam in the local area of load introduction. Other regions of the primary rib can still rely on compression only contact.
- mechanical fasteners may be used, in the preferred embodiment of the present invention, structural adhesives are used to form the bond between the slip-in rib and the skin of the box beam and fasteners are installed after this adhesive material cures as necessary.
- a structural box beam 211 includes a skin 213 and a slip-in rib
- Slip-in rib 221 includes an internal web portion 223 and a peripheral flange portion 225. As with slip-in rib 121 , although web portion 223 has been shown as a solid plate member, it should be understood that web portion 223 may include void spaces and/or a truss arrangement (not shown) that would allow cables, wiring, and other component parts to pass longitudinally through box beam 211.
- Flange portion 225 includes a recessed channel 227 that extends along the periphery of slip-in rib 221 to receive a structural adhesive material 241.
- a small clearance, or gap 231 exists between the exterior edges of flange 225 and the interior surfaces of skin 213.
- small peripheral grooves 235 may be included in both sides of flange 225 for receiving optional seal members, such as an O-rings 237. O-rings 237 help to initially seat slip-in rib 221 and help to contain adhesive 241 if required.
- Figure 10 is a perspective view of slip-in rib 221.
- channel 227 is lined with a self-contained displacement mechanism, such as an evacuated or collapsed inflatable tubular bladder 245.
- Structural adhesive 241 is then located on top of the displacement mechanism, inflatable bladder 245 in this example.
- Channel 227 is sized and shaped to accommodate the reduced volume of bladder 245 and additional volume to accommodate enough structural adhesive 241 to fill the interface area between slip-in rib 221 and skin 213.
- Bladder 245 is preferably made of a material, such as nylon, rubber, or other elastomeric material, such that when inflated or otherwise activated, structural adhesive 241 is displaced outward into contact with the interior surface of skin 213, thereby forming the structural bond between slip-in rib 221 and skin 213.
- Bladder 245 may then be sealed so as to remain inflated, become a sacrificial "fly-away" tool, or be extracted from channel 227 after structural adhesive
- apertures 243 may be used to allow access to one or more valve stems 247 for inflating bladder 245.
- a self-contained displacement mechanism such as bladder 245 allows a measured or metered volume of a fluid adhesive to be dispensed. This eliminates the requirement to control adhesive volume using conventional methods, such as calendared or film adhesive.
- slip-in rib 221 is inserted dry into place within skin 213. Then, structural adhesive 241 is injected through apertures 243, so as to flow around and fill channel 227.
- Channel 227 is sized and shaped to allow adhesive 241 to flow around the perimeter of slip-in rib 221 without squeezing out of flange 227.
- apertures 243 which may be located at varying locations around flange 225, and which may be simple inspection ports, may be used to ensure that adhesive 241 has adequately filled channel 227. Structural adhesive 241 is forced into channel 227 with sufficient pressure to force structural adhesive into contact with the interior surface of skin 213, thereby forming the structural bond between slip-in rib 221 and skin 213.
- mechanical retainers may be used instead of structural adhesive to secure the slip-in ribs in place within the box beam.
- Some mechanical retainers include: shims with snap-in receivers, spring biased buttons, and leaf springs, to name a few.
- the slip-in ribs of the present invention reduce the complexity of the assembly of box beam structures, particularly in applications where the number of parts has been reduced. This is because the slip-in ribs of the present invention are not directly dependent upon the number of joints where manufacturing tolerances are accommodated. Also, the installation of fasteners into box beam structure presents difficulties such as access to small interior spaces and sealing requirements. The process by which the slip-in ribs of the present invention are installed accommodates tolerance buildup, resulting in reduced part count. This reduces manufacturing labor because fastener installation is eliminated.
- the costs associated with manufacturing a closed-box structure can be reduced due to relaxed tolerances and the ability to reduce part count without incurring additional assembly cost. Because the rib/box bond is secondary, failure of the rib/box bond is not a significant structural concern as long as the rib position in the box is retained.
- slip-in ribs that can be bonded in place with a process that accommodates tolerance build-up results in reduced part count, as installing one- piece ribs in one-piece structural box beams is possible; and manufacturing labor is reduced, as fastener installation is eliminated.
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- Engineering & Computer Science (AREA)
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Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/546,490 US8156711B2 (en) | 2003-02-24 | 2004-02-24 | Contact stiffeners for structural skins |
DE04714198T DE04714198T8 (en) | 2003-02-24 | 2004-02-24 | CONTACT MAKER FOR CONSTRUCTION SKIN |
BRPI0407749-0A BRPI0407749A (en) | 2003-02-24 | 2004-02-24 | contact stiffeners for structural wrappers |
EP04714198A EP1616061B1 (en) | 2003-02-24 | 2004-02-24 | Contact stiffeners for structural skins |
CA2515149A CA2515149C (en) | 2003-02-24 | 2004-02-24 | Contact stiffeners for structural skins |
DE602004032122T DE602004032122D1 (en) | 2003-02-24 | 2004-02-24 | CONTACT MAKER FOR CONSTRUCTION SKIN |
US13/447,440 US8632712B2 (en) | 2003-02-24 | 2012-04-16 | Method of supporting a structural box beam |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US45009603P | 2003-02-24 | 2003-02-24 | |
US60/450,096 | 2003-02-24 |
Related Child Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/546,490 A-371-Of-International US8156711B2 (en) | 2003-02-24 | 2004-02-24 | Contact stiffeners for structural skins |
US13/447,440 Division US8632712B2 (en) | 2003-02-24 | 2012-04-16 | Method of supporting a structural box beam |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2004076769A2 true WO2004076769A2 (en) | 2004-09-10 |
WO2004076769A3 WO2004076769A3 (en) | 2006-05-11 |
Family
ID=32927611
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2004/005585 WO2004076769A2 (en) | 2003-02-24 | 2004-02-24 | Contact stiffeners for structural skins |
Country Status (7)
Country | Link |
---|---|
US (2) | US8156711B2 (en) |
EP (1) | EP1616061B1 (en) |
CN (1) | CN100434634C (en) |
BR (1) | BRPI0407749A (en) |
CA (1) | CA2515149C (en) |
DE (2) | DE602004032122D1 (en) |
WO (1) | WO2004076769A2 (en) |
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WO2008009988A2 (en) * | 2006-07-20 | 2008-01-24 | Airbus Uk Limited | Composite structure and method of manufacture |
WO2008132498A1 (en) * | 2007-04-30 | 2008-11-06 | Airbus Uk Limited | Composite structure comprising a stringer with a pad embedded in the recess of a panel and method of transmitting forces |
JP2009519175A (en) * | 2005-12-16 | 2009-05-14 | エアバス・ユ―ケ―・リミテッド | Assembly of aircraft parts |
WO2010106129A1 (en) * | 2009-03-19 | 2010-09-23 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Method and device for adhesively joining large-surface components in vehicle construction |
WO2010106123A1 (en) * | 2009-03-19 | 2010-09-23 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Method for applying adhesive according to tolerance in vehicle construction |
US8758534B2 (en) | 2008-12-19 | 2014-06-24 | Saab Ab | Method of attaching elements by bonding |
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CN109774911A (en) * | 2017-11-10 | 2019-05-21 | 海口未来技术研究院 | The connection method of utricule and reinforcing rib and air bag and aerostatics |
EP3805091A1 (en) | 2019-10-08 | 2021-04-14 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A bulkhead for a boom of an aircraft |
US11591061B2 (en) | 2020-12-02 | 2023-02-28 | Airbus Helicopters Deutschland GmbH | Watertight bulkhead for a boom of an aircraft |
EP4147967A1 (en) * | 2021-09-13 | 2023-03-15 | Rohr, Inc. | Composite structure and method for forming same |
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Publication number | Priority date | Publication date | Assignee | Title |
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Also Published As
Publication number | Publication date |
---|---|
US8632712B2 (en) | 2014-01-21 |
CA2515149A1 (en) | 2004-09-10 |
DE04714198T1 (en) | 2006-12-28 |
CN1826451A (en) | 2006-08-30 |
DE04714198T8 (en) | 2007-06-06 |
EP1616061A2 (en) | 2006-01-18 |
BRPI0407749A (en) | 2006-02-14 |
US20070011970A1 (en) | 2007-01-18 |
CN100434634C (en) | 2008-11-19 |
CA2515149C (en) | 2011-01-11 |
WO2004076769A3 (en) | 2006-05-11 |
EP1616061A4 (en) | 2009-04-29 |
DE602004032122D1 (en) | 2011-05-19 |
EP1616061B1 (en) | 2011-04-06 |
US20120199269A1 (en) | 2012-08-09 |
US8156711B2 (en) | 2012-04-17 |
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