Reinforced stiffeners and method for making the same

Abstract

A composite stiffener is fabricated using preforms of laminated, unidirectional composite tape. The stiffener includes a void that is reinforced by a filler wrapped with a structural adhesive. The surfaces of the preforms surrounding the void include a layer of composite fabric which is bonded to the filler by the adhesive, thereby increasing the toughness of stiffeners around the void and improving pull-off strength of the stiffener.

Claims

1. A composite stiffener, comprising: first, second and third members formed from laminated composite tape, the first and second members defining a web and a pair of flanges extending from the web, the third member being joined to the flanges and extending generally transverse to the web, the first, second and third composite members intersecting to form a void, at least the first and second members comprising unidirectional fibers; a filler disposed in and substantially filling the void, the filler comprising a composite laminate; at least one layer of composite fabric disposed across the first member and the second member in the area of the filler, the layer of composite fabric comprising woven or knitted fibers having at least one orientation that extends traverse to an orientation of fibers in at least one of the first member or the second member; and, a layer of adhesive wrapped around and surrounding the filler and joining the filler to the composite fabric.

2. The composite stiffener of claim 1, wherein the first and second members include radius areas between the web and each of the flanges, and the layer of composite fabric covers the radius areas in each of the first member and the second member.

3. The composite stiffener of claim 1, wherein the layer of adhesive includes a folded sheet of structural adhesive surrounding a surface of the filler.

4. The composite stiffener of claim 1, wherein the at least one layer of composite fabric includes graphite fibers held in an epoxy matrix.

5. The composite stiffener of claim 1, wherein the layer of adhesive extends beyond the filler into an interfacial layer between the third member and the pair of flanges.

6. The composite stiffener of claim 1, wherein the at least one layer of composite fabric of the composite members are offset relative to each other.

7. A composite stiffener, comprising: a pair of composite channels joined together, each of the channels including a web, flanges extending from the web, and radius areas between the web and each of the flanges, each composite channel comprising laminated layers of composite tape having unidirectional reinforcing fibers; a base extending transverse to the web and joined to each of the flanges, the base comprising laminated layers of composite tape having unidirectional reinforcing fibers, the radius areas of the channels and the base forming at least one radius filler zone; a reinforcing member filling the radius filler zone, the reinforcing member comprising a titanium member; a first layer of composite fabric covering a first radius area defined by one of the channels and one of the flanges, the first layer of composite fabric comprising woven, bi-directional tape, the layer positioned such that at least one fabric orientation of the layer is substantially transverse the unidirectional reinforcing fibers of the pair of composite channels; a second layer of composite fabric covering a second radius area defined by a second of the channels and the flanges, the second layer of composite fabric comprising woven, bi-directional tape, the second layer positioned such that at least one fabric orientation of the second layer is substantially transverse the unidirectional reinforcing fibers of the pair of composite channels; a third layer of composite fabric covering an area of the base in the area of the radius filler zone, the third layer of composite fabric comprising woven, bi-directional tape, the third layer positioned such that at least one fabric orientation of the third layer is substantially transverse the unidirectional reinforcing fibers of the base; and, a layer of adhesive wrapped around all sides of the reinforcing member so as to surround the reinforcing member and joining the reinforcing member to the first layer of composite fabric and the second layer of composite fabric.

8. The composite stiffener of claim 7, wherein the woven, bi-directional tape comprises graphite.

9. The composite stiffener of claim 7, wherein the layer of adhesive includes a sheet of structural adhesive fully wrapped around the filler, and wherein the layer of adhesive partially bleeds into at least one layer of fabric.

10. The composite stiffener of claim 7, wherein the layer of adhesive extends beyond the radius filler zone into interfacial layers between the channels and between the base and each of the flanges.

11. The composite stiffener of claim 7, the channels are generally C-shape in cross section.

12. A composite stiffener for aircraft applications, comprising: an I-section structure formed of laminated composite tape and including a web and first and second sets of flanges on each end of the web, the structure including a pair of C-channels, a base, and a cap, the C-channels including radius areas between the web and the flanges and being joined together face-to-face to define the web, the cap being joined to the first set of the flanges and the base being joined to the second set of flanges, the cap and the base each intersecting the web in the radius areas to define a radius filler zone, each C-channel comprising laminated layers of composite tape having unidirectional reinforcing fibers, the base comprising laminated layers of composite tape having unidirectional reinforcing fibers; a first layer of composite fabric covering areas of the I-section structure defining the radius filler zone, the first layer contacting both flanges of the C-channels; the first layer of composite fabric comprising woven, bi-directional tape, the layer positioned such that at least one fabric orientation of the layer is substantially transverse the unidirectional reinforcing fibers of the C-channels; a second layer of composite fabric covering an area of the base in the area of the radius filler zone, the second layer of composite fabric comprising woven, bi-directional tape, the second layer positioned such that at least one fabric orientation of the second layer is substantially transverse the unidirectional reinforcing fibers of the C-channels; a reinforcing filler disposed in the radius filler zone, the reinforcing filler comprising a hybrid of composite laminate and formed unidirectional composite tape; and a layer of adhesive wrapped around all sides of the reinforcing filler and joining the reinforcing filler to the first layer of composite fabric and the second layer of composite fabric in the radius filler zone.

13. The composite stiffener of claim 12, wherein the layer of adhesive further extends beyond the radius filler zone into an interfacial layer between the base and a set of flanges of the I-section structure.

Description

BRIEF DESCRIPTION OF THE ILLUSTRATIONS

(1) FIG. 1 is an end view of a reinforced stiffener according the disclosed embodiments.

(2) FIG. 2 is a side view of the reinforced stiffener shown in FIG. 1.

(3) FIG. 3 is a sectional view showing a reinforced stiffener bonded to a skin.

(4) FIG. 4 is a diagram illustrating the pull-off forces acting on the stiffener shown in FIG. 1.

(5) FIG. 5 is an enlarged view of the area designated as A in FIG. 4.

(6) FIG. 6 is an exploded, sectional view of one end of the stiffener shown in FIG. 1.

(7) FIG. 7 is a sectional view taken along the line 7-7 in FIG. 6.

(8) FIG. 8 is a view similar to FIG. 6 but showing the components in their assembled form.

(9) FIGS. 9-11 illustrate steps for installing an adhesive wrap and a filler in the radius filler zone of the stiffener shown in FIG. 1.

(10) FIG. 12 is a sectional view of one end of a stiffener forming an alternate embodiment.

(11) FIG. 13 is a perspective view showing tools used in applying localized fabric patches used in a method for fabricating the fastener illustrated in FIG. 1.

(12) FIG. 14 is a side view of the tools shown in FIG. 14 after the tools have been pushed together.

(13) FIG. 15 is a top view of the tools shown in FIG. 14.

(14) FIG. 16 is a flow diagram illustrating a method for producing the reinforced stiffener.

(15) FIG. 17 is a flow diagram of aircraft production and service methodology.

(16) FIG. 18 is a block diagram of an aircraft.

DETAILED DESCRIPTION

(17) Referring first to FIGS. 1, 2 and 3, a reinforced stiffener generally indicated by the numeral 20 has a generally I-shaped cross section and may be used in a variety of applications to carry loads and/or stiffen structural members. For example, and without limitation, in an aircraft wing, the stiffener 20 may be used to stiffen a wing panel (not shown) or other component of the wing (not shown), or to stiffen a skin 38 forming part of a fuselage section (not shown).

(18) The stiffener 20 broadly comprises a pair of C-shaped channels 22, 24 arranged in back-to-back relationship, a cap 26, and a base 28. The C-channels 22, 24, cap 26 and base 28 may be formed of reinforced composite tape in which the reinforcing fibers are unidirectionally oriented and are held in a synthetic matrix such as, by way of example and without limitation, epoxy. The C-channels 22, 24 respectively include web portions 34a, 34b and a pair of oppositely facing flanges 30, 32 on each end of the web portions 34a, 34b. The web portions 34a, 34b are joined together to form a web 34. Each of the web portions 34a, 34b transitions to one of the flanges 30, 32 at a radius 35. The cap 26 and base 28 are joined to the outer faces of the flanges 30, 32 respectively. As a result of the radii 35, a generally triangularly shaped void 37 is created at each intersection of the radii 35 with the cap 26 and the base 28. The voids 37, which are also referred to herein as radius filler zones, are filled with an elongate reinforcing filler 36 also known as a noodle that has a cross sectional shape generally matching the generally triangular cross section of the voids 37.

(19) The fillers 36 may be fabricated from many of various materials that are compatible with the materials used in the channels 22, 24, cap 26 and base 28, but typically may comprise a composite unidirectional formed composite tape, a composite laminate, a hybrid tape-fabric member or machined titanium. The fillers 36 function to more evenly distribute and transmit loads between the web 34, the base 28 and the cap 26.

(20) Referring particularly to FIG. 3, in some applications, an alternate form 20a of the stiffener may be used in which either the cap 26 or base 28 is formed by a structural element to which the stiffener 20a may be attached, which in the illustrated example, is a skin 38. Accordingly, in this example, the radius filler zone 37 is defined by the radii 35 and the inner face 39 of the skin 38.

(21) Attention is now directed to FIGS. 4 and 5 which illustrate typical tension forces acting on the stiffener 20. A tension force indicated by the arrow 40 acting through the web 34 creates a reaction force indicated by the arrows 42 which is normal to the planes of the lamina forming the flanges 32 and the base 28. Due to the presence of the radius filler zone 37, the reaction forces 42 may tend to separate or pull-off the lamina and the area surrounding the radius filler zone 37. It is therefore desirable that the fillers 36 assist, to the extent possible, in reinforcing the area surrounding the radius filler zone 37, thus increasing the pull-off strength of the stiffener 20.

(22) Referring now to FIGS. 6, 7 and 8, the pull-off strength of the stiffener 20 may be increased by employing a layer of composite fabric 48 in the area of the radius filler zone 37, and by wrapping all sides of the filler 36 with a layer of adhesive 46. Although a single layer of fabric 48 may be adequate, in some applications more than one layer of the fabric 48 may be desirable or beneficial. The fabric 48 may comprise sets of woven or knitted fibers that extend traverse to each other, thereby providing axial stiffness in more than one direction, i.e., in the orientation directions of the woven or knitted fibers. In contrast, the fibers in the tape 50 forming the underlying plies 44 are oriented in a single direction and therefore may exhibit high axial stiffness only in their direction of orientation. Additionally, the layer of fabric 48 may provide additional stiffness due to the fact that the fibers in the fabric 48 have been structurally linked or intertwined together through weaving or knitting. The fabric layer 48 may comprise, for example without limitation, carbon or graphite fibers that are woven or knitted in 0-90 or +/?45 degree orientations, although other bidirectional orientations are possible. The matrix used in the fabric layer 48 may be epoxy or other suitable materials well known in the art of composite materials. The layer of adhesive 46 may comprise, for example and without limitation, an epoxy based structural adhesive. As will be discussed below in more detail, during processing, the layer of adhesive 46 may tend to bleed into the layer of fabric 48, thereby creating a stronger bond between the filler 36 the C-channels 22, 24 and base 28. This stronger bond increases the toughness of the stiffener 20 in the area of the radius filler zone 37, which in turn may increase the pull-off strength of the stiffener 20.

(23) As previously indicated, the C-channels 22, 24, cap 26 and base 28 (FIGS. 1-3) are each formed from multiple plies 44 (see FIG. 7) of reinforced, unidirectional fibers in the form of tape 50. As will be discussed in more detail below, the top layer of fabric 48 may cover an entire side of the channels 22, 24, cap 26 and base 28, or may comprise a patch that is present only along a section of the length of the filler 36 in those applications where it is important to minimize the weight of the stiffener 20. The combination of the fabric layers 48 and the layer of adhesive 46 may act to resist a path of potential delamination around the reinforcement element 36, thereby creating a tough T section at the opposite ends of the web 34. In some applications it may desirable to increase the radius R (FIG. 6) of the radii 35 in order to reduce the peak tensile force in the area of the radii 35, thereby further improving the pull-off strength of the stiffener 20.

(24) The disclosed embodiments may be advantageously employed in the fabrication of stiffeners having cross sections other than an I, such as a T or a J, or other cross sectional geometries where a cap or base intersects radius areas forming a void requiring fillers and improvements in pull-off strength.

(25) Attention is now directed to FIGS. 9-11 which illustrate a method for wrapping the filler 36 with the layer of adhesive 46 and installing the filler 36 in the radius filler area 37. As shown in FIG. 9, a layer, which may in the form a of a sheet of the layer of adhesive 46 is placed over the radius filler area 37, with one edge of the sheet of adhesive 46 beginning at a tangent point 62a on one of the flanges 30. The sheet forming the layer of adhesive 46 is then forced down into the radius filler area 37 until it reaches another tangent point 62b, following which the remainder of the layer of adhesive 46 is draped over the other flange 32, covering a third tangent point 62c. The width of the sheet forming the layer of adhesive 46 should be sufficient such that a length 64 remains which is equal to or greater than the width of the filler 36. The remaining length 64 of the layer of adhesive 46 is folded over the filler 36, as shown in FIG. 11, and any remaining excess amount (not shown) may be cut away.

(26) The filler 36 having been fully wrapped in the layer of adhesive 46, the cap 26 (or base 28) is then drawn in the direction of the arrows 54, into contact with the flange 30 (or 32) and filler 36 as the parts are assembled in a set of tooling (not shown) used to compress and co-cure the stiffener 20, as will be discussed in more detail below. During the cure process, the layer of adhesive 46 partially bleeds out into the fabric layers 48, creating a strong interfacial bond between the filler 36 and the C-channels 22, 24, the base 28 and cap 26. As previously indicated, in some applications, the layer 48 of composite fabric and the layer adhesive 46 may extend the entire length of the stiffener 20, whereas in other applications the fabric 48 and the layer of adhesive 46 may be present only along a section of the length of the stiffener 20 in areas, for example, where tension loads on the stiffener 20 may be particularly high.

(27) Referring now to FIG. 12, in some applications, it may be desirable to extend the length of the layer of adhesive 46 beyond the tangent points 62 (FIG. 9) into the direct interfacial areas 56, 58 and 60 between the C-channels 22, 24 and the base 28 (or cap 26). These extended areas of adhesive 56, 58 and 60 bond the directly facing layers 48 of fabric and may further strengthen the stiffener 20 in the radius filler area 37, thus further improving the pull-off strength.

(28) Reference is now made to FIGS. 13-15 which illustrate a method and related tooling that may be used to form stiffeners 20 in which the fabric layers 48 are localized, i.e. they are applied as patches. The C-channels 22, 24 may be drape formed over a pair of tools 62, 64. Composite fabric patches 48a, 48b are then respectively placed in appropriate areas over the corresponding C-channels 22, 24 as best seen in FIG. 13. In some applications, it may be desirable that the fabric patches 48a, 48b be slightly offset from each other. For example, as may be seen in FIG. 13, the depth x of patch 48a draped over web portion 34a is less than the depth y of the fabric patch 48b. Similarly, as shown in FIG. 14, patches 48a, 48b are longitudinally offset by a distance Z.

(29) After the patches 48a, 48b have been placed over the drape formed C-channels 22, 24, the tools 62, 64 are pushed together, forcing the web portions 34a, 34b into face-to-face contact. At this point, as shown in FIG. 14, the adhesive wrapped filler 36 is placed into the radius filler zone 37, following which a third fabric patch 48c is placed over the filler 36, overlapping the fabric patches 48a, 48b. In this example, the adhesive layer 48 is wrapped around only a section of the overall length of the filler 36, however in other applications the adhesive layer 48 may extend the full length of the filler 36. Finally, the base 28 and cap 26 may be installed and the entire assembly can then be vacuum bagged and placed in an autoclave (not shown) for compaction and curing.

(30) Attention is now directed to FIG. 16 which illustrates the steps of a method 88 for fabricating the reinforced stiffener 20. At 70, the filler 36 is formed using any of various techniques known in the art of composite processing. At 72, the filler 36 is wrapped with a layer of adhesive 46, which may be carried out by folding the layer of adhesive 46 around each side of the filler 36.

(31) A lay-up is formed at 74 by stacking pre-preg layers of composite tape on appropriate tooling, as shown at step 76, following which, at 78, a layer of composite fabric 48 is placed over the stack of tape plies. The lay-up is then formed into the C-channels 22 or 24 using drape forming or other techniques at step 80.

(32) Next, in those applications where the layer of adhesive 48 extends beyond the boundaries of the reinforcing element 36, an additional layer of adhesive 56, 58, 60 (see FIG. 12) may applied to the C-channel preforms 22, 24, as shown at step 82.

(33) Next, at step 84, the C-channel preforms 22, 24 and the adhesive wrapped filler 36 are assembled as a lay-up in appropriate tooling. Then, at 86, the lay-up is compacted and cured to complete the stiffener 20.

(34) Embodiments of the disclosure may find use in a variety of potential applications, particularly in the transportation industry, including for example, aerospace, marine and automotive applications. Thus, referring now to FIGS. 17 and 18, embodiments of the disclosure may be used in the context of an aircraft manufacturing and service method 90 as shown in FIG. 17 and an aircraft 92 as shown in FIG. 18. During pre-production, exemplary method 90 may include specification and design 94 of the aircraft 92 and material procurement 96. During production, component and subassembly manufacturing 98 and system integration 100 of the aircraft 92 takes place. Thereafter, the aircraft 92 may go through certification and delivery 102 in order to be placed in service 104. While in service by a customer, the aircraft 92 is scheduled for routine maintenance and service 106 (which may also include modification, reconfiguration, refurbishment, and so on).

(35) Each of the processes of method 90 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer). For the purposes of this description, a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors; a third party may include without limitation any number of vendors, subcontractors, and suppliers; and an operator may be an airline, leasing company, military entity, service organization, and so on.

(36) As shown in FIG. 18, the aircraft 92 produced by exemplary method 90 may include an airframe 108 with a plurality of systems 110 and an interior 112. Examples of high-level systems 110 include one or more of a propulsion system 114, an electrical system 116, a hydraulic system 118, and an environmental system 120. Any number of other systems may be included. Although an aerospace example is shown, the principles of the disclosure may be applied to other industries, such as the marine and automotive industries.

(37) Systems and methods embodied herein may be employed during any one or more of the stages of the production and service method 90. For example, components or subassemblies corresponding to production process 98 may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft 92 is in service. Also, one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during the production stages 98 and 100, for example, by substantially expediting assembly of or reducing the cost of an aircraft 92. Similarly, one or more of apparatus embodiments, method embodiments, or a combination thereof may be utilized while the aircraft 92 is in service, for example and without limitation, to maintenance and service 106.

(38) Although the embodiments of this disclosure have been described with respect to certain exemplary embodiments, it is to be understood that the specific embodiments are for purposes of illustration and not limitation, as other variations will occur to those of skill in the art.