Method for forming contoured composite stiffeners

BACKGROUND INFORMATION

1. Field

0001This disclosure generally relates to the fabrication of composite structures, and deals more particularly with a method and apparatus for forming flat composite charges into contoured, reinforcing substructures, such as variable gauge blade stiffeners.

2. Background:

0002Composite reinforcing substructures such as blade stiffeners, sometimes referred to as blade stringers, are frequently used in the marine and aircraft industries. These stringers may be fabricated by combining two or more stiffening members. For example, blade-type stringers can be fabricated by combining two members having L or C cross sectional shapes, back-to-back. These members may be formed by manually hot drape forming multiple composite charges over a mandrel or other tool. After forming, the members are placed back-to-back and co-cured in an autoclave. Fabricating blade stringers using multiple separate charges requires multiple tools, is relatively labor intensive and may add to manufacturing flow times.

0003In some applications, stiffeners such as the blade stringers mentioned above, may need to be contoured along their lengths in order to conform them to a structure such as a contoured aircraft skin, to which they are to be attached. Difficulty may be encountered, however, when attempting to form highly contoured stringers using conventional tooling because of the tendency of the plies in the charge to wrinkle as the charge is being compressed. Accordingly, fabrication of highly contoured stringers using composites is generally limited to hand layup techniques in which each ply is laid up by hand over a die or other tool in order to reduce the possibility of ply wrinkling. The hand layup technique is labor intensive, and thus costly as well as relatively slow. An added challenge is presented where one or more areas of the stringer include ply drop-offs and/or pad-ups in order to conform the stringer to local contouring of the skin.

0004Accordingly, there is a need for a method and apparatus for fabricating composite stiffeners such as blade stringers using a single composite charge formed with relatively simple tooling. There is also a need for a method and apparatus of the type mentioned above that allows contouring of the stringer along its length, including localized contouring using ply drop-offs or pad-ups.

SUMMARY

0005The disclosed embodiments provide a method and apparatus for fabricating blade type stringers using simplified tooling to form a single composite charge into a desired stringer configuration. Tooling costs and process flow times may be reduced by eliminating the need to form multiple charges and assemble multiple stiffener members in order to achieve the desired stringer configuration. The embodiments allow localized contouring of the stringer by accommodating ply pad-ups and ply drop-offs along the length of the stringer. The charge may be contoured along its length during forming with reduced ply wrinkling and/or reduced ply misalignment.

0006According to one disclosed embodiment, apparatus is provided for forming a composite charge contoured blade stringer. The apparatus comprises an elongate punch flexible along its length and an elongate die flexible along its length against which a generally flat composite charge may be press formed by the punch. The apparatus further includes first and second flexible plates respectively backing the first and second plies, and a press coupled with the blades for forming the punch and the die into a desired contour.

0007According to another disclosed embodiment, apparatus is provided for forming a composite charge into a contoured blade stiffener having a flange with at least one thickness variation. The apparatus includes first and second flexible plates, and an elongate punch and an elongate die. A generally flat composite charge may be press formed between the punch and the die. The punch and the die are flexible along their respective lengths and are sandwiched between the first and second plates. The apparatus includes at least a first shim located between one of the plates and the die for maintaining substantially constant pressure on the charge across the thickness variation during press forming. The apparatus further comprises a press for bending the plates to contour the parts and die. The shim is generally flexible.

0008According to a further embodiment, a method is provided of fabricating a composite blade stiffener. The method comprises forming a generally flat charge into a hat-shape having a pair of flanges by using the punch to dry the charge into a cavity in a die. A plate is loaded over the die covering the flanges, and the punch is forced against the plate to compress and hold the flanges. The hat shape is formed into a blade of the stiffener by squeezing the die while the plate is pressed against the flanges by the punch.

0009According to still another embodiment, a method is provided of fabricating a contoured composite blade stiffener. The method comprises placing a substantially flat composite charge on a die and forming the flat charge into a hat using a punch to press the form against the charge into a cavity in the die. The method further comprises contouring the formed the charge by bending the die while the formed charge is in the die. Contouring the formed charge includes bending the punch while the punch is in the die.

0010In summary, according to one aspect of the invention there is provided an apparatus for forming a composite charge into a contoured blade stringer, including an elongate punch flexible along its length; an elongate die flexible along its length against which a generally flat composite charge may be press formed by the punch; first and second flexible plates respectively backing the first and second dies; and a die and punch contour changing mechanism coupled with the plates for changing the contour of the punch and the die.

0011Advantageously the apparatus wherein the punch is generally planar and includes a plurality of individual punch segments.

0012Advantageously the apparatus wherein the die includes first and second spaced apart die portions defining a die cavity between which the punch may be received.

0013Advantageously the apparatus wherein the die portions are laterally displaceable toward each other for squeezing the charge therebetween, and the apparatus further comprises: <ul id="ul0001" list-style="none" compact="compact"><li>expandable members for applying a lateral force on the die portions that squeeze the charge.</li></ul>

0014Advantageously the apparatus wherein the expandable members include a pair of inflatable hoses respectively on opposite sides of the die portions and adapted to be coupled with a source of pressurized air.

0015Advantageously the apparatus further including at least one shim adapted to engage the charge and having a contour generally matching a local contour in the charge.

0016Advantageously the apparatus further including a press coupled with the first and second plates for contouring the plates while the charge is between the punch and the die.

0017Advantageously the apparatus further including a plate removably installable between the die and the punch for holding a portion of the charge during forming of the charge.

0018According to another aspect of the invention there is provided an apparatus for forming a composite charge into a contoured blade stiffener having a flange with at least one thickness variation, including first and second flexible plates; an elongate punch and an elongate die between which a generally flat composite charge may be press formed, the punch and the die being flexible along their respective lengths and sandwiched between the first and second plates; and at least a first shim located between one of the plates and the die; and a press for bending the plates to contour the punch and the die.

0019Advantageously the apparatus wherein the shim is generally flexible.

0020Advantageously the apparatus further including a second shim, and wherein the first shim is located between a first side of the die and the first plate, and the second shim is located between a second side of the die and the second plate.

0021Advantageously the apparatus wherein the punch is generally planar and includes a plurality of individual punch segments, and the die includes first and second spaced apart flexible die portions defining a die cavity between which the punch may be received.

0022Advantageously the apparatus further including a pair of inflatable hoses respectively on opposite sides of the die portions and adapted to be coupled with a source of pressurized air for applying a lateral force on the die portions.

0023Advantageously the apparatus wherein the first shim includes a taper generally corresponding to the thickness variation.

0024According to a yet further aspect of the present invention there is provided a method of fabricating a composite blade stiffener, including forming a generally flat charge; using a punch to form the charge into a hat shape having a pair of flanges by driving the generally flat charge into a cavity in a die; withdrawing the punch from the die cavity; loading a plate over the die covering the flanges; holding the flange portions against the die by forcing the punch against the plate; and forming the resulting hat shape into a blade by using the die to squeeze the hat while the flange portions are held against the die.

0025Advantageously the method further including placing the charge in the die.

0026Advantageously the method further including placing a heating blanket on the charge on the die; and heating the charge to a forming temperature using the heating blanket.

0027Advantageously the method further including contouring the charge along its length by contouring the die and the punch before the blade is formed.

0028Advantageously the method further including contouring the charge along its length by contouring the die and the punch after the blade is formed.

0029Advantageously the method further including placing a filler between the flange portions after the blade has been formed; reloading the plate over the flange portions and the filler; and compressing the filler by driving the punch down against the plate.

0030According to another aspect of the present invention there is provided a method of fabricating a contoured composite blade stiffener, including placing a substantially flat composite charge on a die having a die cavity; press forming the flat charge against the die, including using a punch to press form the charge into a hat within the die cavity; and contouring the formed charge by bending the die while the formed charge is in the die.

0031Advantageously the apparatus wherein the press forming includes forming flange portions of the charge against the die while the punch is forming the charge into the hat within die cavity, withdrawing the punch from the die cavity, and using the die to laterally compress the hat into a blade.

0032Advantageously the apparatus wherein the contouring is performed before the hat is compressed into a blade.

0033Advantageously the apparatus wherein contouring the formed charge includes bending the punch along with the die.

0034According to another aspect of the present invention there is provided an apparatus for forming a variable gauge contoured composite blade stringer, including first and second spaced apart, elongate flexible plates; a die mounted on the first plate facing the second plate, the die including first and second die portions having a die cavity therebetween, each of the die portion being segmented into a plurality of independently movable die blocks slidable on the first plate, the die further including flexible straps coupling the die blocks together; a pair of brackets secured to the first plate on opposite sides of the die for laterally retaining the die blocks; a pair of hose respectively between the die blocks and the brackets adapted to be coupled with a source of pressurized air for applying a lateral force on the die portions; a first tapered shim between each of the die portions and the first plate for transmitting constant force to areas of the charge having thickness variations as the charge is being formed; a substantially flat, elongate punch mounted on and extend substantially perpendicular to the second plate for forming a portion of the charge into the die cavity, the punch being segmented into a plurality of independently movable punch portions; a second tapered shim on each side of the punch and secured to the second plate for transmitting constant force to areas of the charge having thickness variations as the charge is being formed; and a plurality of actuators coupled with the first and second plates for forming the punch and the die into a desired contour by bending the plates.

0035According to yet another aspect of the present invention there is provided another method of forming a variable gauge contoured composite blade stringer, including providing a substantially flat, multiply composite prepreg charge; placing a first filler on the charge; placing the flat charge on a die having two opposite die portions and a die cavity therebetween; heating the charge to a forming temperature; using a punch to drive a first portion of the charge and the first filler into the die cavity to form a hat; using a first plate to compress second portions of the charge against the die to form flange portions of the stringer as the hat is being formed by the punch; retracting the punch from the die cavity; loading a second plate over the flange portions of the stringer; holding the flange portions against the die by using the punch to apply pressure to the second plate; removing the second plate; using a pair of pressurized hoses to respectively apply lateral pressure to the die portions; using the die portions to form the hat into a blade by squeezing the hat between the die portions; contouring the formed charge by contouring each of the punch and the die along their respective lengths while the blade is being squeezed; placing a second composite filler in a groove between the flange portions; applying an adhesive and a fabric layer over the second filler; reloading the second plate over the flange portions, overlying the second filler, the adhesive and the fabric layer; using the punch to apply pressure to the second plate and compress the second filler, the adhesive and the fabric layer; retracting the punch after the second filler has been compressed; moving the die portions away from each other; removing the second plate; and removing the formed stringer from the die.

BRIEF DESCRIPTION OF THE DRAWINGS

0036The novel features believed characteristic of the advantageous embodiments are set forth in the appended claims. The advantageous embodiments, however, as well as a preferred mode of use, further objectives and advantages thereof, will best be understood by reference to the following detailed description of an advantageous embodiment of the present disclosure when read in conjunction with the accompanying drawings, wherein: <ul id="ul0002" list-style="none" compact="compact"><li><figref idref="f0001">FIG. 1</figref> is an illustration of a side view of a contoured composite blade stringer fabricated with the disclosed method and apparatus.</li><li><figref idref="f0001">FIG. 2</figref> is an illustration of a sectional view taken along the line 2-2 in <figref idref="f0001">FIG. 1</figref>.</li><li><figref idref="f0001">FIG. 3</figref> is an illustration similar to <figref idref="f0001">FIG. 2</figref>, but showing an alternate form of the stringer.</li><li><figref idref="f0002">FIG. 4</figref> is an illustration of a perspective view of tooling apparatus used to form a substantially flat charge into the blade stringers shown in <figref idref="f0001">FIGS. 1-3</figref>.</li><li><figref idref="f0003">FIG. 5</figref> is an illustration of a sectional view taken along the line 5-5 in <figref idref="f0003">FIG. 6</figref>, but showing a charge being formed.</li><li><figref idref="f0003">FIG. 6</figref> is an illustration of a sectional view taken along the line 6-6 in <figref idref="f0003">FIG. 5</figref>.</li><li><figref idref="f0003">FIG. 6A</figref> is a plan view of a portion of a blade having a pad-up, showing how the die blocks shift to conform to the contours of the blade during the forming process.</li><li><figref idref="f0004">FIG. 7</figref> is an illustration of a plan view of a die and punch contour changing mechanism employing the tooling apparatus shown in <figref idref="f0002">FIG. 4</figref>.</li><li><figref idref="f0005">FIG. 8</figref> is an illustration of a flow diagram of a method of fabricating the contoured blade stringer shown in <figref idref="f0001">FIGS. 1 and 2</figref>.</li><li><figref idref="f0006 f0007 f0008">FIGS. 9-25</figref> are diagrammatic illustrations of the tooling apparatus shown in <figref idref="f0002">FIG. 4</figref>, respectively showing the sequential steps of the fabrication method shown in <figref idref="f0005">FIG. 8</figref>.</li><li><figref idref="f0009">FIG. 26</figref> is an illustration of a flow diagram of a method of fabricating the contoured blade stringer shown in <figref idref="f0001">FIG. 3</figref>.</li><li><figref idref="f0010 f0011 f0012">FIGS. 27-43</figref> are diagrammatic illustrations of the tooling apparatus shown in <figref idref="f0002">FIG. 4</figref>, respectively showing the sequential steps of the fabrication method shown in <figref idref="f0009">FIG. 26</figref>.</li><li><figref idref="f0013">FIG. 44</figref> is an illustration of a flow diagram of aircraft production and service methodology.</li><li><figref idref="f0013">FIG. 45</figref> is an illustration of a block diagram of an aircraft.</li></ul>

DETAILED DESCRIPTION

0037Referring first to <figref idref="f0001">FIGS. 1 and 2</figref>, the disclosed embodiments relate to a method and apparatus for fabricating an elongate, composite stiffener, such as a blade type stringer 50 having a substantially flat blade 52 and a flange 54 extending substantially perpendicular to the blade 52. The flange 54 includes a pair of flange portions 54a laterally extending from one end of the blade 52, and connected to the blade 52 by a radius section 60. The blade stringer 50 may have one or more contours 58 along its length. In the illustrated embodiment, the stringer 50 has a substantially constant contour 58 in the curved plane 56 of a flange 54. In other embodiments, the stringer 50 may have one or more of the contours 58 which may or may not be of constant curvature. Also, as will be discussed later in more detail, the flange 54 may have a variable gauge or thickness <b>T₁</b> at one or more locations along its length in order to conform the stringer 54 to localized contours of a structure to which it is attached, such as an aircraft skin 61. Also, the thickness <b>T₂</b> and/or a height <b>H</b> of the blade 52 may vary along the length of the stringer 50.

0038The disclosed method and apparatus may be used to fabricate other configurations of blade-type stringers 50, such hybrid-I stringer 50a shown in <figref idref="f0001">FIG. 3</figref>. Stringer 50a comprises a blade 52 having an angularly shaped outer end 62, and a flange 54. The blade end 62 includes a triangularly shaped, composite filler 64, however other filler shapes are possible. The flange 54 includes a V-shaped groove 57 at the intersection of flange portions 54a with the blade 52. The groove 57 is filled with a composite filler 66 having a triangularly shaped cross section substantially matching that of the groove 57. Each of the fillers 64, 66 may comprise an adhesive that may or may not be reinforced with fibers, or alternatively, may comprise strips (not shown) of prepreg tape.

0039<figref idref="f0002 f0003">FIGS. 4-6</figref> illustrate tooling apparatus 68 that may be employed to form the stringers shown in <figref idref="f0001">FIGS. 1-3</figref> using a single, substantially flat, multi-ply composite charge 55. The charge may comprise multiple plies 59 of composite material, such as, without limitation, a carbon fiber epoxy prepreg, and may include pad-ups 98 to conform the flange 54 (<figref idref="f0001">FIG. 2</figref>) of the stringer 50 to local contours, such as local contours of the skin 61. The tooling apparatus 68 broadly comprises a lower die 70, an upper punch 88 and a pair of flexible plates 72, 74, upon which the die 70 and punch 88 are respectively mounted. Die 70 comprises a pair of die portions 70a, 70b which are spaced apart to form a die cavity 86 and are slideable, substantially laterally, toward and away from each other on plate 72. Each of the die portions 70a, 70b is segmented at 75 and comprises a plurality of die blocks 76 which, in the illustrated example have a generally rectangular cross section, however other cross sectional shapes are possible.

0040The die blocks 76 are aligned in side-by-side relationship along the length of the plates 72, 74 and are joined together by flexible connectors 78 which may comprise, for example and without limitation, a flexible metal strap. The die blocks 76 are mounted on plate 72 and are interconnected by connectors 78 such that their respective axes remain neutral during the forming and contouring of the charge 55. The die blocks 76 may comprise any suitable, relatively rigid material, such as wood, metal, ceramic or a composite, and include inner forming surfaces 76a and upper forming surfaces 76b. A pair of L-shape, elongate brackets 82 are mounted on the plate 72, on opposite sides of die 70, and function to both retain the die blocks 76 on the plates 72 as well as react lateral forming forces generated by the die blocks 76. A pair of inflatable hoses 84, sometimes referred to as bags or bladders, are sandwiched between the brackets 82 and the die blocks 76, which are adapted to be coupled with a suitable source of pressurized air (not shown). The hoses 84 may be selectively pressurized in order to apply a lateral force on the die blocks 76 during forming and/or contouring operations. Other mechanisms, however, may be provided to apply lateral force to the die blocks 76.

0041The punch 88 is substantially flat and includes slits 90 that segment the punch 88 into a plurality of punch portions 92 that allow the punch 88 to flex along its length in a plane (not shown) that is substantially perpendicular to the plane 56 (<figref idref="f0001">FIGS. 1 and 2</figref>) of the flange 54. The punch 88 may be formed of any suitable rigid material, such as metal, ceramic or a composite.

0042As previously mentioned, the stringer 50 may have a variable flange thickness <b>T₁</b> in localized areas along its length in order to conform the stringer 50 to local contours of the skin 61 (<figref idref="f0001">FIG. 1</figref>). In order to accommodate these thickness variations so that constant pressure is applied to the charge 55 in these localized areas, suitable contoured lower and upper shims 80, 94 respectively may be provided. For example, as shown in <figref idref="f0002">FIGS. 4</figref> and <figref idref="f0003">6</figref>, the charge 55 may include pad-up plies 98 in the area of the flange portions 54a (<figref idref="f0001">FIG. 2</figref>). In order to assure that substantially even forming pressure is applied over the area of the pad-up plies 98, the upper shims 94 includes a contour 96 that substantially conforms to the cross sectional shape of the pad-up plies 98. Although not shown in the Figures, the lower shims 80 may also contain one or more contours along their lengths beneath the die blocks 76 in order to accommodate thickness variations in the flange portions 54a of the stringer 50. Also, the lower shim 80 may be tapered (not shown) in the area beneath the die cavity 86 (<figref idref="f0002">FIG. 4</figref>) in order to alter the blade height along its length. The shims 80, 94 may be formed of any substantially non-compressible material that will transmit force to the charge 55, yet is flexible to the degree necessary to allow the shims 80, 94 to bend during contouring of the tooling apparatus 68.

0043Referring to <figref idref="f0003">FIG. 6A</figref>, as previously mentioned, the thickness <b>T₂</b> of the stringer blade 52 may vary along its length. For example, the blade 52 may have local pad-ups 97 which increase the blade thickness <b>T₂.</b> During the forming process, the die blocks 76 in the area 99 of the pad-up 97 slide 101 laterally outward on the lower plate 72, so as to conform to the contour presented by the pad-up 97, and maintain substantially constant forming pressure on blade 52.

0044<figref idref="f0004">FIG. 7</figref> illustrates a die and punch contour changing mechanism 105 incorporating the tooling apparatus 68 shown in <figref idref="f0002 f0003">FIGS. 4-6</figref>. The die and punch contour changing mechanism 105 may comprise, for example and without limitation, a press 105. A plurality of individual, spaced apart actuators 100 are respectively mounted on opposing press plates 104 which are adapted for movement toward and away from each other, as shown by the arrows 106. The tooling apparatus 68 is disposed between the press plates 104. The press plates 104 may be coupled with suitable power operated mechanisms such as cylinder actuators (not shown) for displacing the press plates 104, which open and close the tooling apparatus 68 during a charge forming operation. Each of the actuators 100 includes a plunger 102 coupled with one of the plates 72, 74 that applies a force to the plates 72, 74, in order to bend the plates 72, 74 which in turn longitudinally contours the tooling apparatus 68, and thus the formed charge 55. Other mechanisms may be employed to longitudinally contour the tooling apparatus 68 such as that disclosed in <patcit id="pcit0001" dnum="US20100102482A"><text>US Patent Publication 20100102482 published April 29, 2010</text></patcit>, the entire disclosure of which is incorporated by reference herein.

0045Attention is now directed to <figref idref="f0005">FIG. 8</figref> which describes the individual steps of a method of fabricating contoured blade stringers; these steps are also sequentially shown, in diagrammatic form, in <figref idref="f0006 f0007 f0008">FIGS. 9-25</figref>. Beginning at step 110, a substantially flat, multi-ply composite charge 55 is loaded 146 onto the die blocks 76 (<figref idref="f0006">FIG. 9</figref>), with punch 88 in a raised position. A central blade portion 52 of the charge 55 overlies die cavity 86, and the outer flange portions 54a of the charge 55 extend laterally beyond the die blocks 76. Strips of adhesive 148 may be placed on the charge 55, either before or after the charge 55 is loaded onto the die blocks 76. Next, as shown at 112 in <figref idref="f0005">FIG. 8</figref>, a heating blanket 150 (<figref idref="f0006">FIG. 10</figref>) is loaded 152 onto the charge 55. Next, at 114, the charge is heated (<figref idref="f0006">FIG. 11</figref>) using the heating blanket 150, thereby softening the charge 55 to a suitable forming temperature. Other types of heating devices may be used to heat the charge 55, including but not limited to radiant and inductive type heaters (not shown). At step 116, the heating blanket 150 is unloaded at 154, as shown in <figref idref="f0006">FIG. 12</figref>. At step 118, a blade portion 52 of the charge 55 is formed into a hat 156 (<figref idref="f0006">FIG. 13</figref>) by forcing 158 the punch 88 into the die cavity 86. As the hat 156 is being formed as shown in <figref idref="f0006">FIG. 13</figref>, a first intermediate level of pressure <b>P1</b> is applied to the die blocks 76 by the hoses 82 in order to maintain the die blocks 76 loaded against the charge 55. However this intermediate level of pressure <b>P1</b> is less than the laterally outward pressure developed by the punch 88, consequentially although loaded against the hat 156, the die blocks 76 move laterally outwardly 168 until the hat section 156 is fully formed within the cavity 86.

0046Next, at step 120, while laterally inward pressure <b>P1</b> is maintained against the hat 156 by the die blocks 76 (<figref idref="f0006">FIG. 14</figref>), the top plate 74 applies pressure 164 to the flange portions 54a, forming the latter down against the die blocks 76. Optionally, at step 122, the partially formed charge 55 is contoured (<figref idref="f0007">FIG. 15</figref>) by contouring 85 the tooling apparatus 68 while laterally inward pressure <b>P1</b> continues to be maintained on the hat 156 by the die blocks 76. Contouring 85 of the tooling apparatus 68 may be performed by the press shown in <figref idref="f0004">FIG. 7</figref> previously described which bends the plates 72, 74 in a plane (not shown) that is substantially parallel to the plane 56 of the flange 54 (see <figref idref="f0001">FIGS. 1 and 2</figref>). As plates 72, 74 are bent into a desired curvature, both the punch 88 and the die 78 flex and conform to the curvature of the plates 72, 74. As previously described in connection with <figref idref="f0002 f0003">FIGS. 4-6</figref>, the upper and lower shims 80, 94 maintain substantially constant forming pressure on the flange portions 54a as the tooling apparatus 68 is being contoured 85 to the desired shape.

0047At step 124 in <figref idref="f0005">FIG. 8</figref>, the punch 88 is retracted from the die cavity 86 (<figref idref="f0007">FIG. 16</figref>). Next, at step 126, a substantially flat plate 160 (<figref idref="f0007">FIG. 17</figref>) is loaded 162 onto the flange portions 54a. At step 128, the punch 88 is lowered 158 (<figref idref="f0007">FIG. 18</figref>) into contact with the plate 160, thereby loading the plate 160 against the flange portions 54a, thereby immobilizing the flange portions 54a. Next, at step 130, while the flange portions 54a are held in place against the die blocks 76 by the force applied by the plate 160 and the punch 88, pressure <b>P2</b> (<figref idref="f0007">FIG. 19</figref>) is applied to the die blocks 76 by the hoses 82 which squeeze the hat 156 into a blade 52. The pressure <b>P2</b> is a forming pressure that is greater than pressure <b>P1</b> applied to the die blocks 76 during steps 118-122.

0048At step 134 shown in <figref idref="f0005">FIG. 8</figref>, the punch 88 is retracted 180 (<figref idref="f0007">FIG. 20</figref>), and the plate 160 is removed 167 leaving a V-shaped groove 165 between the flange portions 54a. At step 136 shown in <figref idref="f0005">FIG. 8</figref>, a composite filler 66 is placed in the groove 165, as shown in <figref idref="f0008">FIG. 21</figref>. Next, at step 138, a strip of adhesive 174 (<figref idref="f0008">FIG. 22</figref>) and a layer of fabric 172 are placed over the filler 66. At step 140, plate 160 is reloaded, overlying the flange 54 (<figref idref="f0008">FIG. 23</figref>). Then, as shown in step 142, the fabric layer 172, adhesive strip 174 and the filler 66 are compressed by displacing the punch downwardly as shown in <figref idref="f0008">FIG. 24</figref> into contact with plate 160. Finally, at step 144, and is shown in <figref idref="f0008">FIG. 25</figref>, the punch 88 is retracted 180, the plate 160 is removed 184, allowing the fully formed blade stringer 50 to be withdrawn from the tooling apparatus 68.

0049It should be noted here that in the method embodiment just described, contouring of the tooling apparatus 68 is performed when the charge 55 is in a partially formed state as shown in <figref idref="f0007">FIG. 15</figref>. Alternatively, however, the charge 55 may be contoured at step 132, after the hat 156 has been compressed into the blade 52 shown in <figref idref="f0007">FIG. 19</figref>. Contouring of the tooling apparatus 68 is optional and not required when using the tooling apparatus 68 to form substantially straight stringers (not shown). When stringer contouring is not required, it is not necessary to perform steps 122-132. In either case, the disclosed method may advantageously allow ply slippage during the forming and/or contouring processes which may reduce ply wrinkling and result in finished parts that have superior characteristics and/or exhibit improved performance. Furthermore, in another embodiment, contouring of the charge 55 along its length is performed after the blade portion 52 is formed, but prior to forming the flange portions 54a onto the die blocks 76. The filler 66 is placed in the groove 165 after the flange portions 54a have been formed on the contoured blade portion 52. This latter mentioned method embodiment may facilitate the contouring process, particularly where more highly contoured stringers 50 are being fabricated, resulting in improved part quality with less wrinkling and/or easier contouring of the charge 55.

0050Attention is now directed to <figref idref="f0009">FIG. 26</figref>, along with related <figref idref="f0010 f0011 f0012">FIGS. 27-43</figref> which illustrate steps of a method of fabricating a hybrid type blade stringer 50a, such as that shown in <figref idref="f0001">FIG. 3</figref>. As can be seen from <figref idref="f0010 f0011 f0012">FIGS. 27-43</figref>, the tooling apparatus 68 use to fabricate the stringer 50a shown in <figref idref="f0001">FIG. 3</figref> is substantially similar to that previously described, with two exceptions. Specifically, as shown in <figref idref="f0010">FIG. 27</figref>, the end of the punch 88 includes a generally V-shaped groove 88a along the length of the punch 88 which substantially matches the size and shape of a triangular filler 64. Additionally, each of the die blocks 78 includes a bevel or chamfer 155 along a bottom edge which assists in forming the angularly shaped outer end 62 of the blade 52 shown in <figref idref="f0001">FIG. 3</figref>.

0051Referring now to <figref idref="f0009">FIG. 26</figref>, at step 188 a substantially flat composite charge 55 (<figref idref="f0010">FIG. 27</figref>) is loaded 220 onto the die blocks 76. Strips of adhesive 148 may be applied to the charge 55, following which the upper filler 64 is placed over the central adhesive strip 148. Next, at 190, a heating blanket 150 (<figref idref="f0010">FIG. 28</figref>) is loaded 222 onto the charge 55. At step 192 in <figref idref="f0009">FIG. 26</figref>, the blanket 150 is used to heat the charge 55 (FUG. 29) to a suitable forming temperature. At step 194 in <figref idref="f0009">FIG. 26</figref> the blanket 150 is unloaded 224, as shown in <figref idref="f0010">FIG. 30</figref>. At step 196 the punch 88 is displaced downwardly into the die cavity 86 (<figref idref="f0010">FIG. 31</figref>) to form the charge 55 into a hat 156. As the punch 88 continues to move downwardly through the cavity 86, the upper plate 74 comes into contact with the flange portions 54a, and forms the latter down against the die blocks 76. During step 196, lateral pressure <b>P1</b> is applied to the die blocks 76 by the inflatable hoses 82 (see <figref idref="f0002">FIGS. 4</figref> and <figref idref="f0003">5</figref>).

0052At step 198, the punch 88 is retracted (<figref idref="f0011">FIG. 33</figref>) and at step 200, a substantially flat plate 160 (<figref idref="f0011">FIG. 34</figref>) is loaded 226 onto the flange portions 54a of the partially formed charge 55. At step 202, the punch 88 is loaded against the plate 66 (<figref idref="f0011">FIG. 35</figref>) which applies pressure to the flange portions 54a to hold them against the die blocks 76. At 204, lateral pressure <b>P2</b> is applied (<figref idref="f0011">FIG. 36</figref>) by the hoses 82 to the die blocks 76, causing the die blocks 76 to compress the hat 156 (<figref idref="f0011">FIG. 35</figref>) into a blade 52.

0053Next, at step 206 and as shown in <figref idref="f0011">FIG. 37</figref>, the punch 88 is removed the plate 74 and formed stringer 52 may be optionally contoured 85 by contouring the tooling apparatus 68 using a press such as that shown in <figref idref="f0004">FIG. 7</figref> which applies a force 164 to the plates 72, 74 to bend the plates 72 74 to the desired contour. During the contouring 85 of the tooling apparatus 68 in step 206, lateral inward pressure <b>P2</b> is maintained on the die blocks 76 by the hoses 82.

0054Following contouring of the stringer 52 at step 206, the punch 88 is retracted 180 as shown at 208, and the plate 160 is removed 228. At step 210 in <figref idref="f0009">FIG. 26</figref>, a lower filler 66 (<figref idref="f0012">FIG. 39</figref>) is loaded into the groove 165 between the flange portions 54a. Next, as shown in step 212 in <figref idref="f0009">FIG. 26</figref>, a strip of adhesive 148 and a layer of fabric 225 is placed over the filler 66 (see <figref idref="f0010">FIG. 30</figref>). As shown in step 214 in <figref idref="f0009">FIG. 26</figref>, the plate 160 is reloaded 230 onto the flange portions 54a (<figref idref="f0012">FIG. 41</figref>). At 216, the punch 88 is displaced downwardly into contact with the plate 160 which compresses the fabric layer 225 and adhesive 148 against the filler 66. During step 216, pressure <b>P1</b> is maintained on the die blocks 76. Finally, at step 218 in <figref idref="f0009">FIG. 26</figref>, the punch 88 is retracted 180 (<figref idref="f0012">FIG. 43</figref>), the plate 160 is removed 232 and the completed stringer 52 is withdrawn from the tooling apparatus 68.

0055As previously mentioned, contouring of the tooling apparatus 68 is optional when carrying out the method shown in <figref idref="f0009 f0010 f0011 f0012">FIGS. 26-43</figref>, and is not required when using the tooling apparatus 68 to form substantially straight stringers (not shown) having the hybrid-I shape shown in FUIG. 3. When stringer contouring is not required, it is not necessary to perform steps 198-206. In the embodiment described in connection with <figref idref="f0010 f0011 f0012">FIGS. 27-43</figref>, contouring of the blade portion 52 is performed after the flange portions 54a have been formed. Alternately, however, it may be preferable in other embodiments to form the flange portions 54a after the blade portions 52 have been formed, following which the upper filler 66 may be installed. By contouring the charge 55 before the flange portions 54a have been formed, the contouring process may be easier and/or part quality may be improved.

0056Embodiments of the disclosure may find use in a variety of potential applications, particularly in the transportation industry, including for example, aerospace, marine, automotive applications and other application where automated layup equipment may be used. Thus, referring now to <figref idref="f0013">FIGS. 44 and 45</figref>, embodiments of the disclosure may be used in the context of an aircraft manufacturing and service method 236 as shown in <figref idref="f0013">Figure 44</figref> and an aircraft 238 as shown in <figref idref="f0013">Figure 45</figref>. Aircraft applications of the disclosed embodiments may include, for example, without limitation, layup of stiffener members such as, without limitation spars and stringers. During pre-production, exemplary method 236 may include specification and design 240 of the aircraft 238 and material procurement 242. During production, component and subassembly manufacturing 244 and system integration 246 of the aircraft 238 takes place. Thereafter, the aircraft 238 may go through certification and delivery 248 in order to be placed in service 250. While in service by a customer, the aircraft 238 is scheduled for routine maintenance and service 250, which may also include modification, reconfiguration, refurbishment, and so on.

0057Each of the processes of method 236 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.

0058As shown in <figref idref="f0013">FIG. 45</figref>, the aircraft 238 produced by exemplary method 236 may include an airframe 254 with a plurality of systems 256 and an interior 258. Examples of high-level systems 256 include one or more of a propulsion system 260, an electrical system 262, a hydraulic system 264, and an environmental system 266. 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.

0059Systems and methods embodied herein may be employed during any one or more of the stages of the production and service method 236. For example, components or subassemblies corresponding to production process 244 may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft 238 is in service. Also, one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during the production stages 244 and 246, for example, by substantially expediting assembly of or reducing the cost of an aircraft 238. Similarly, one or more of apparatus embodiments, method embodiments, or a combination thereof may be utilized while the aircraft 238 is in service, for example and without limitation, to maintenance and service 252.

0060The description of the different advantageous embodiments has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Further, different advantageous embodiments may provide different advantages as compared to other advantageous embodiments. The embodiment or embodiments selected are chosen and described in order to best explain the principles of the embodiments, the practical application, and to enable others of ordinary skill in the art to understand the disclosure for various embodiments with various modifications as are suited to the particular use contemplated.