Source: https://patents.google.com/patent/US10232532B1/en
Timestamp: 2020-08-09 21:25:06
Document Index: 176446323

Matched Legal Cases: ['art 84', 'art 84', 'art 84', 'art 84', 'art 84', 'art 84', 'art 84', 'art 84', 'art 84', 'art 212', 'art 214', 'art 216', 'art 220', 'art 222', 'art 220', 'art 220', 'art 220', 'art 366', 'art 366', 'art 366', 'art 366', 'art 366', 'Application No. 08728832']

US10232532B1 - Method for fabricating tapered thermoplastic composite parts - Google Patents
Method for fabricating tapered thermoplastic composite parts Download PDF
US10232532B1
US10232532B1 US13/419,187 US201213419187A US10232532B1 US 10232532 B1 US10232532 B1 US 10232532B1 US 201213419187 A US201213419187 A US 201213419187A US 10232532 B1 US10232532 B1 US 10232532B1
US13/419,187
Randall Dow Wilkerson
Sharon Sher Ying Wong
2007-01-29 Priority to US11/699,653 priority patent/US9102103B2/en
2010-08-26 Priority to US12/868,896 priority patent/US8795457B2/en
2012-03-13 Priority to US13/419,187 priority patent/US10232532B1/en
2012-03-13 Application filed by Boeing Co filed Critical Boeing Co
2012-03-14 Assigned to THE BOEING COMPANY reassignment THE BOEING COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FOX, JAMES R., PREBIL, CHARLES R., WILKERSON, RANDALL DOW, WONG, SHARON SHER YING
2019-03-19 Publication of US10232532B1 publication Critical patent/US10232532B1/en
229920001169 thermoplastics Polymers 0.000 title claims abstract description 90
239000004416 thermosoftening plastic Substances 0.000 title claims abstract description 90
239000002131 composite material Substances 0.000 title description 55
238000000748 compression moulding Methods 0.000 claims abstract description 14
238000009787 hand lay-up Methods 0.000 description 4
229920002430 Fibre-reinforced plastic Polymers 0.000 description 3
Consolidation tooling is used in a continuous compression molding machine to produce a fiber reinforced thermoplastic part having a varying height. The tooling includes first and second tool dies adapted to compress and form a multi-ply stack of thermoplastic prepreg into a part, and at least a first tooling sleeve movable through the first and second tool dies. The tooling sleeve has at least a first tapered portion engageable with the multi-ply stack.
This application is a continuation-in-part of copending U.S. patent application Ser. No. 11/697,378 filed Apr. 6, 2007; Ser. No. 12/868,896 filed Aug. 26, 2010; Ser. No. 11/584,923 filed Oct. 20, 2006; Ser. No. 11/699,653 filed Jan. 29, 2007; Ser. No. 12/398,071 filed Mar. 4, 2009; and U.S. Pat. No. 7,807,005 issued Oct. 5, 2010, all of which are incorporated by reference herein. This application is also related to copending U.S. patent application Ser. No. 12/711,401 filed Feb. 24, 2010; and Ser. No. 11/701,789 filed Feb. 3, 2007, all of which applications are incorporated by reference herein.
The disclosed embodiments generally relate to fabrication processes using plastic materials, and deals more particularly with a method and apparatus for fabricating thermoplastic composite parts that are tapered along their length.
Numerous processes exist for the fabrication of Thermoplastic composite (TPC) laminates of constant thickness and straight length. In addition to non-continuous processes such as pressing, stamping and autoclave forming, there are continuous processes such as extrusion, pultrusion, roll forming, and compression molding. Although these latter processes are capable of producing parts in continuous lengths, they lack the ability to produce parts of varying thickness that are needed for lightweight aerospace structures and other structures where weight is of particular importance. Moreover, the processes mentioned above are not capable of producing parts that have tapered features, curvature and/or tailored or varying thickness along their length. Additionally, the above mentioned processes rely on the in-feed of multiple discrete lengths of TPC materials that must be cut, sorted, labeled, stored and individually fed into a fabrication machine. The use of discrete lengths of TPC material may reduce automation of the fabrication process, and may increase factory space requirements as well as material costs.
Accordingly, there is a need to provide a method and apparatus that are capable of fabricating TPC laminates having one or more tapered features along their length, including those that are curved or have tailored thicknesses. There is also a need for a method and apparatus of the type mentioned that allow the laminates to be fabricated in continuous lengths using automated continuous compression molding.
The disclosed embodiments provide a method and apparatus for fabricating thermoplastic composite laminates such as beams with tapered or varying height including moldline curvature in a semi-continuous production process. The method utilizes automated equipment or hand lay-up to collate parts or components into a multi-layer stack. Each stack contains all plies, including ply build-up areas, tacked in the proper location to maintain orientation and location. The materials forming the stack may be fed continuously from spools, thereby reducing the need for cutting, sizing, labeling, sorting and storing individual lengths of the thermoplastic material. The apparatus includes consolidation tooling containing all necessary part features and is coordinated to the customized multiple ply stacks to form a single integrated composite laminate part having one or more features that change in height along the length of the part. The change in height can be a constant taper or a variable taper, potentially matching the moldline contour of an airfoil. Molding laminate parts with varying heights is accomplished using constant cross section universal dies and tooling sleeves as the part moves through a semi-continuous compression molding machine. Variable height parts can be made in several general cross sectional forms, including but not limited to I, J, Z, T and C cross sectional shaped beams. The tooling sleeves adapt the universal mold tool dies to the necessary tool surfaces for the parts. Composite laminate parts formed by the disclosed method may find use in a wide variety of applications, including, for example and without limitation, automotive and aerospace applications.
According to one disclosed embodiment, consolidation tooling is provided for use in a continuous compression molding machine to produce a fiber reinforced thermoplastic composite part having a varying height. The consolidation tooling comprises first and second tool dies adapted to compress and mold a multi-ply stack of thermoplastic prepreg into a part, and at least a first tooling sleeve. The first tooling sleeve is moveable through the first and second tool dies and has at least a first tapered portion engageable with the multi-ply stack. The first tool die is tapered along its length substantially complementary to the first tapered flange portion of the first tooling sleeve. The first tapered portion may be a tapered flange portion and the first tooling sleeve may further include a second tapered flange portion engageable with the multi-ply stack. The second tool die is tapered substantially complementary to the second tapered flange portion of the first tooling sleeve. In one embodiment, the first and second tapered flange portions of the first tooling sleeve are tapered in opposite directions. The first tooling sleeve may include a generally U-shaped cross section. The consolidation tooling further comprises third and fourth tool dies adapted to compress and mold the multi-ply stack of thermoplastic prepreg into a web region of the part, wherein one of the third and fourth tool dies is received within the first and second tooling sleeves. The first tooling sleeve may include areas of non-uniform thickness contours and may be curved along at least a portion of its length. The first tooling sleeve may be configured to mold the multi-ply stack into a beam having a cross sectional shape selected from the group including: an I-shape, a J-shape, a Z-shape, a T-shape, and a C-shape. The consolidation tooling may further comprise a second tooling sleeve moveable through the first and second dies, wherein the second tooling sleeve has at least one tapered flange portion.
According to another embodiment, continuous compression molding machine tooling is provided for producing a fiber reinforced polymer stiffener having a height that varies along a length of the stiffener. The tooling broadly comprises tool dies adapted to compress a multi-stack of thermoplastic prepreg, and at least a first elongate tooling sleeve adapted to be engaged by one of the tool dies and having a cross section that varies along its length. The first elongate tooling sleeve includes outer faces against which the multi-ply stack of thermoplastic prepreg may be molded into a shape of the stiffener. The first elongate tooling sleeve includes a web portion having a height that varies along the length of sleeve. The first elongate tooling sleeve may further include at least one flange portion extending from the web portion, wherein the flange portion has a thickness that is tapered along a length of the sleeve.
According to a further embodiment, a method is provided of continuous compression molding an elongate fiber reinforced polymer stiffener. The method comprises assembling a generally flat stack of prepreg plies and moving the flat stack of prepreg plies through a consolidation structure. The method further comprises molding and consolidating the flat stack of prepreg plies as the flat stack of prepreg plies moves through the consolidation structure, including molding a taper into the stiffener along a length of the stiffener. Molding the taper may include bringing at least a first tapered tooling sleeve into engagement with the flat stack of prepreg plies, and compressing the flat stack of prepreg plies against the first tapered tooling sleeve. Compressing the flat stack of prepreg plies against the first tapered tooling sleeve is performed by pressing a pair of tapered tool dies against the tapered tooling sleeve.
FIG. 1 is an exploded view and perspective view of a thermoplastic composite laminate formed in accordance with the disclosed embodiments.
FIGS. 7a-7f are perspective views representing examples of curved, thermoplastic composite laminate parts formed in accordance with the disclosed method.
FIG. 9 is a perspective view of tooling used to form the curved thermoplastic composite parts in accordance with the disclosed method.
FIG. 19 is an illustration similar to FIG. 4 but showing the use of spools to continuously feed plies of thermoplastic material into the pre-forming zone of the consolidation structure.
FIG. 20 is a fragmentary illustration showing a pre-formed stack of plies being fed to the pre-forming zone along with plies continuously fed from spools.
FIGS. 21-25 are cross sectional illustrations of various joints formed between a thermoplastic composite laminate and a metal fitting.
FIG. 26 is a diagrammatic illustration of the steps used in a method for fabricating thermoplastic composite laminates having integrated metal fittings according to an embodiment of the disclosure.
FIG. 27 is a cross sectional illustration of a laminate structure having an integrated metal fitting positioned between consolidation tooling.
FIG. 28 is a perspective illustration showing a lay-up and consolidation tooling being fed to a continuous compression molding machine.
FIG. 29 is an illustration of a side view of a stiffener having a tapered feature along its length.
FIG. 29A is an illustration of a sectional view taken along the line 29A-29A in FIG. 29.
FIGS. 30-32 are illustrations of side views respectively showing other stiffeners having tapered features along their lengths.
FIG. 33 is an illustration of a side view of a curved stiffener having a tapered feature along its length.
FIG. 34 is a broad functional block diagram of consolidation tooling employed to compression mold stiffeners having tapered features along their length.
FIG. 35 is an illustration of a perspective view of a tapered beam having an I-shaped cross section.
FIG. 36 is an illustration of a perspective view of the beam of FIG. 35, also showing parts of the consolidation tooling used in fabricating the beam.
FIG. 37 is an illustration of a top view of consolidation tooling used to compression mold the tapered beam shown in FIGS. 35 and 36.
FIG. 38 is an illustration of an end view in the direction shown as 38 in FIG. 37.
FIG. 39 is an illustration of a perspective view of a tapered beam having a J-shaped cross section.
FIG. 40 is an illustration perspective view similar to FIG. 39 but also showing parts of the consolidation tooling used in fabricating the tapered beam.
FIG. 41 is an illustration of a perspective view of a tapered beam having a C-shaped cross section.
FIG. 42 is an illustration of a perspective view similar to FIG. 41 but also showing parts of the consolidation tooling used in fabricating the tapered beam.
FIG. 43 is an illustration of a perspective view of a tapered beam having a Z-shaped cross section.
FIG. 44 is an illustration of a perspective view showing parts of the consolidation tooling used in fabricating the tapered beam shown in FIG. 43.
FIG. 45 is an illustration of a flow diagram showing the steps of a method of continuous compression molding of tapered stiffeners.
FIG. 46 is an illustration of a flow diagram of aircraft production and service methodology.
FIG. 47 is an illustration of a block diagram of an aircraft.
The disclosed embodiments provide a method and apparatus for forming a thermoplastic composite (“TPC”) laminate material with one or more tapers, as well as tailored and varying thicknesses and/or curvatures in a continuous process. The embodiments have uses in a wide variety of potential applications, including for example, in the aerospace industry. The embodiments are well suited for forming thermoplastic composite stiffened members in the supporting framework of an aircraft fuselage. Potential examples of thermoplastic composite stiffened members include but are not limited to fuselage skins, wing skins, control surfaces, door panels and access panels. Stiffening members include but are not limited to keel beams, floor beams, and deck beams. For illustrative purposes only, embodiments will initially be described in reference to forming a thermoplastic composite floor beam 20 for use in a commercial aircraft fuselage. However, while an I-section is shown, other stiffened member geometries such as Z-section, U-section, T-section, etc. will also be later described, including those having curvature along their length.
Referring now to FIG. 1, a thermoplastic composite laminate, here a thermoplastic composite laminate floor beam 20 having tailored and varying thickness regions t1 and t2 is illustrated as having a web region 22 coupled at either end to a respective pair of cap regions 24. The web region 22 and pair of cap regions 24 are formed as a single integrated laminate structure by consolidating a pair of non-uniform thickness tacked multi-layer ply sheet stacks 76 with a pair of thermoplastic composite filler nuggets 26 and further with a pair of uniform thickness tacked multi-layer ply sheet stacks 74. Although sheet stack 76 is shown as comprising 2 plies, it is to be understood that either of the sheet stacks 74 and 76 may include any number of plies, depending on the application. It will also be understood that cap regions 24, which are shown in FIG. 1 as having a uniform thickness and one ply, may similarly be provided with regions of varying thicknesses and/or a plurality of plies. Furthermore, while the cross sectional shape of the floor beam 20 shown in FIG. 1 is substantially constant along its length, the cross sectional shape may vary at a constant or non-constant rate along the length of the beam 20, as will be discussed later in more detail.
Next, in Step 170, some or all of various plies 32, 34 of the untacked stacks 58, 60 formed in FIG. 2 may be tacked together at various predetermined locations to form either a uniform or non-uniform thickness tacked multi-layer ply sheet stack 74, 76. Preferably, the stacks 58, 60 are tacked together using a soldering iron or ultrasonic welder (not shown) to form the respective stack 74, 76, although other devices used to couple together various plies 32, 34 of thermoplastic materials known to those of ordinary skill are also specifically contemplated. The amount and location of tacking among the plies 32, 34 is dependent upon numerous factors, including but not limited to the number and location of the various plies 32, 34 and pockets formed by possible partial plies 64. Moreover, the amount of tacking should be sufficient to form a substantially integrated tacked stack 74, 76 that can be transported as a single part.
Next, in Step 180, a combination of at least one uniform or non-uniform thickness tacked stack 74, 76, and at least one of either a non-uniform thickness tacked stack 76, a uniform thickness tacked stack 74, or a single ply 32, and optionally at least one filler nugget 26 of thermoplastic material 30, 37 are fused together in a consolidation structure 78 to form a single integrated thermoplastic composite laminate such as floor beam 20. One preferred consolidation structure 78 specifically designed to form the thermoplastic composite laminate floor beam 20 of FIG. 1 is illustrated in FIGS. 4 and 5, and is sometimes referred to as a continuous compression molding (“CCM”) machine.
The consolidating structure 102 has a pulsating structure 106 that incrementally moves the preformed part 84 forward within the consolidation zone 82 and away from the pre-forming zone 80. As the part 84 moves forward, the part first enters a heating zone 108 that heats the part to a temperature which allows the free flow of the polymeric component of the matrix resin 40, 42 of the stacks 74, 76 and nuggets 26. Next, the part 84 moves forward to a pressing zone 112, wherein standardized dies 104 are brought down collectively or individually at a predefined force (pressure) sufficient to consolidate (i.e. allow free flow of the matrix resin) the various plies 32, 34 of the tacked stacks 74, 76 and nuggets 26 into its desired shape and thickness, here forming the web region 22 and pair of cap regions 24 of the floor beam 20. Each die 104 is formed having a plurality of different temperature zones with insulators. The dies 104 do not actually contact the part 84, but contact the outer surfaces of the U-shaped channels 86 and sidetooling sheet members 92 opposite the part 84. Thus, the respective inner surfaces of the channels 86, and sheet members 92 compress against the portion of the part 84. The compression may occur wherein all of the dies 104 compress in one independent yet coordinated step. The dies 104 are opened, and the part 84 is advanced within the consolidating zone 102 away from the pre-forming zone 80. The dies 104 are then closed again, allowing a portion of the part 84 to be compressed under force within a different temperature zone. The process is repeated for each temperature zone of the die 104 as the part 84 is incrementally advanced along the guide rollers 105 towards the cooling zone 114.
One preferred consolidating zone structure 102 that may be utilized is the so-called continuous compression molding (CCM) process as described in German Patent Application Publication No. 4017978, published on Sep. 30, 1993, and herein incorporated by reference. However, other molding processes known to those of ordinary skill in the art are specifically contemplated by the embodiments, including but not limited to pultrusion or roll forming.
While the embodiments are described in terms of forming a thermoplastic composite floor beam 20 having essentially an I-beam shape, other potential shapes are specifically contemplated. This includes thermoplastic composite laminates having an L-shape, a C-shape, a T-shape, or even a flat panel shape in which tapers or thickness transitions may occur in any section of the part. These alternatively shaped laminates, or even other forms of the floor beam 20, are formed by consolidating one or more uniform or non-uniform tacked multi-layer ply sheets 74, 76 with either one or more plies 32 of a thermoplastic composite material 30, one or more partial plies 34 of a thermoplastic material 30, or one or more uniform or non-uniform thickness tacked multi-layer tacked stacks 74, 76, and any combination thereof, in a similar method to that described herein. Further, one or more filler nuggets 26 may also be used to form additional alternative versions of the thermoplastic composite laminates 20. To accomplish any of these alternative preferred variations, modifications to the tooling within the pre-forming zone 80 is necessary so as to match the desired thickness variations for the TPC laminate 20. For example, the U-shaped channel 86 of FIG. 5 is specific for forming I-beams such as floor beam 20 of FIG. 1, an alternatively shaped tool having gaps 90 is used in forming C-shaped laminates, L-shaped laminates or flat beams having a taper between respective ply layers. Similar to the U-shaped channel 86, these alternative tools include regions not contacting the stacks 74, 76 that are matched to the standardized dies 104 within the consolidating zone 102.
While the embodiments are well suited for forming thermoplastic composite laminates, by using a modified single-step consolidation zone, thermosetting laminate composites can also be formed. In this modified version of the consolidation process, the heating and pressing zones achieve a temperature above the reaction or curing temperature of the matrix resin to form a thermosetting part. Accordingly, the single pressing process achieves a part having its ultimate desired shape without subsequent pressing steps.
The embodiments provide a method and apparatus to fabricate complex thermoplastic tapered composite laminates that may have tailored and varying thickness, and/or curvatures in a continuous process. This innovative process utilizes automated equipment or hand lay-up to collate parts or components into a multi-layer stack. Each stack contains all plies, including ply build-up areas, tacked in the proper location to maintain orientation and location. The consolidation structure utilizes a two-stage method for forming the composite laminates from the multi-layer stacks and contains all necessary part features to achieve this result. The tooling, such as the U-shaped channel or tool 86 in the pre-forming zone 80 is created with an appropriate shape to create the desired thickness variations in the formed TPC laminates 20 and is further designed to mate with standardized dies with the consolidation zone 82
The composite part formed by the above method may find use in a wide variety of applications, including, for example, automotive and aerospace applications. One example of a composite part formed in accordance with the embodiments is ideally suited for use as structural stiffened members, including thermoplastic composite laminate floor beams 20, in a commercial aircraft.
Referring now to FIGS. 7-15, an alternate embodiment may be used to manufacture thermoplastic laminate parts that are both curved and have tailored and/or varying thickness along their length. Further, as will be discussed later, the cross sectional shape of these parts may vary along the length of the part, resulting in one of more longitudinal tapers in the part. Curved laminates can be produced in which the curvature is either constant (circular) or variable along the length of the laminate part. Also, the longitudinal taper may be constant or may vary along the length of the part. As in the case of the embodiment previously described, the curved thermoplastic laminate part may include tailored areas and areas of varying thickness achieved by adding partial or local plies, or areas containing pockets. “Tailored” or “tailoring” refers to the profile of the part surface, wherein the selective addition or reduction of plies in specific areas of the part can be used to achieve a desired surface profile after the plies are consolidated during the compaction process. Curved parts produced by this embodiment of the method may be used in a variety of applications such as frames, rings, formers and structural aircraft stiffened members or fuselage skins, wing skins, door panels and access panels, keel beams, floor beams, and deck beams. The curved parts can be produced with a variety of cross sections, such as those shown in FIGS. 7a-7f . A fabricated part 212 having an I-section is shown in FIG. 7a while a part 214 having a U-section is shown in FIG. 7b . An L-section part 216 is shown in FIG. 7c and a T-section part is shown in FIG. 7d . A part 220 having a Z-section as shown in FIG. 7e and a part 222 having a simple rectangular section is shown in FIG. 7f . The parts shown in FIGS. 7a-7f may have either constant or variable curvature as previously mentioned, and may include areas of varying or tailored thickness at one or more points along their lengths, as well as one or more longitudinal tapers.
The consolidation tooling 235 is shown in FIG. 9 and comprises curved inner and outer tooling sleeves 228, 230 as well as upper and lower tooling sleeves 232, 234. The upper and lower tooling sleeves 232, 234 each possess a curvature corresponding to that of the blanks 226, while the inner and outer tooling sleeves 228, 230 may be either similarly curved, or flexible so as to conform to the curvature of the part blank 226 during the pre-forming process. In the example illustrated in FIGS. 9, 14 and 15, the tooling sleeves 228-234 are configured to produce the Z-section part 220 shown in FIG. 7e . Although not specifically shown in the drawings, the part-side surfaces of the tooling sleeves 228-234 contain tooling features that produce mirror image features in the part, such as varying thicknesses, varying curvature, pockets, etc.
Referring now particularly to FIGS. 14 and 15, the upper and lower tooling sleeves 232, 234 are assembled around the part blank 226 before the blank is fed in a curved path 280 into the pre-forming station 275 which includes a plurality of forming devices 268 and a set of guides 270. The part blank 226 can be seen to include a flat tacked stack 262 that comprises the web 220 a and cap 220 b (FIG. 7e ) of the Z-section part 220, and a set of buildup plies 264 which form a local reinforcement of the beam web 220 a.
As the sandwiched assembly comprising the part blank 226 and the tooling sleeves 232, 234 is fed into pre-forming station 275, the inner and outer tooling sleeves 228, 230 are fed into contact with the sandwiched assembly. Forming devices 268 function to deform edge portions of a blank 226 against flanges 265 on tooling sleeves 232, 234, thereby pre-forming the caps 220 b of the Z-section part 220. Simultaneously, additional cap reinforcement plies 266 are fed between the forming devices 268 and the tooling flange 265. Guides 270 bring the inner and outer tooling sleeves 228, 230 into contact with the edges of the blank 226 which form the caps 220 b. The preformed blank 226 along with the consolidation tooling 235 continue their movement in the curve path 280 through a curved press 284 such as a CCM machine 78 (FIG. 4 which contains dies that impose force on the consolidation tooling 235. This force results in compaction and consolidation of the plies of the preformed part. Although not specifically shown in the drawings, heaters or ovens are provided as necessary to heat the part blank 226 to a temperature at which the polymeric component of the matrix resin in the part blank 226 has the consistency of a viscous liquid. Heating of the part blank 226 in this manner facilitates ply consolidation. In some cases, pre-heating of the part blank 226 may also be required to facilitate the pre-forming process. The need for pre-heating of the part blank 226 can depend on a number of factors, such as the number of plies, ply orientation, the type of material, the shape being preformed, etc.
Referring now to FIG. 19, a method is provided for the continuous fabrication of thermoplastic composite laminate parts using flat sheets 334 of pre-plied thermoplastic material that is continuously fed into the pre-forming zone 80 from one or more spools 300. Each of the sheets 334 may comprise one or more plies, any or all of which may be reinforced with fibers, such as carbon fibers, for example. The number of spools 300 will depend upon the particular application and the geometry of the part; however the continuously formed part may typically comprise multiple laminated plies of thermoplastic material. The thermoplastic material forming the sheets 334 may comprise any of the thermoplastic materials 30 previously described in reference to FIG. 1. Side tooling sheets 92 or “mandrels” may be fed along with the sheets 334 into the pre-forming zone 80.
Although not specifically shown in FIG. 19, additional materials such as filler nuggets may be fed along with the sheets 334 in order to form specific features of the part. As will be discussed below, the plies forming each of the sheets 334 supplied by each spool 300 may include fibers aligned at differing angles relative to a reference direction of orientation in order to increase the strength and rigidity of the fabricated part. The arrangement shown in FIG. 19 is well suited for continuously fabricating relatively simple parts such as flat beams and beams having an “L” shaped cross section, for example.
As shown in FIG. 20, sheets 334 from spools 300 may be continuously fed into the pre-forming zone 80 along with the previously described multi-layer stack 58 and filler nuggets 26. The multi-layer stack 58 may or may not include tailored thicknesses, pockets or curvatures along its length.
Referring now to FIGS. 21-25, a metal part or fitting such as the metal fitting 304 shown in FIG. 21 may be bonded and integrally formed with a TPC laminate structure 306 according to a method which will be discussed below in more detail. The TPC composite material in structure 306 may comprise, for example without limitation, AS4D/PEKK. The metal fitting 304 may be formed from any suitable material, depending upon the application such as, without limitation, aluminum or titanium. The metal fitting 304 may have any of various geometries and features depending on the application and purpose of the fitting 304. In the case of the application shown in FIG. 21, the metal fitting at 304 acts as a “doubler” which reinforces a location section of the TPC laminate structure 306.
FIG. 22 illustrates a double lap splice 316 between two TPC laminates 312, 314. A pair of metal fittings 308, 310 are integrally bonded to opposite sides of laminates 312, 314, overlying the splice joints 316.
FIG. 23 illustrates the use of a scarf joint 322 between a TPC laminate 320 and a metal fitting 318.
FIG. 24 illustrates a stepped lap joint 328 between a metal fitting 324 and a TPC laminate 326. The metal fitting 324 includes a series of symmetrical steps 325 along one edge thereof, which complementally receive one or more individual plies 327 of the laminate 326.
FIG. 25 illustrates a rabbet joint 335 formed between a metal fitting 330 and a TPC laminate 332.
The joints illustrated in FIGS. 21-25 are merely representative of a wide range of joint constructions and geometries that may be used in carrying out the embodiments of the disclosure.
Referring now to FIGS. 26-28, a method continuously fabricating TPC laminate structures or parts having integrated metal fittings begins with the provision of raw materials and parts, shown in FIG. 26 as “Step A”. The materials include a fiber reinforced composite material 338 with PEKK (Polyetherketoneketone) as the matrix resin (or other TPC composite material), PEKK film 340 and metal fittings 336. The reinforced composite material 338 may be in unidirectional or fabric prepreg forms. The metal fittings 336 may be machined from titanium or other suitable metals. The fittings 336 are cleaned and a high temperature bonding primer is applied to the bonding surfaces on the fittings 336. Additional components (not shown), such as the filler nuggets 26 (FIG. 5) used in manufacturing the I-beam shown in FIG. 1, are extruded or molded into discrete lengths.
Next, at “Step B”, a lay-up 345 is prepared, comprising metal fittings 342, 343, 350, multiple TPC plies 346, and layers 344, 348 of PEKK film. A layer 340 of the PEKK film is applied to the primed bonding surfaces of the metal fittings 342, 343 and 350. Depending upon the type of joint and the particular application, an automated process or hand lay-up may be used to create customized stacks comprising multiple plies 346 of the reinforced composite materials from the supply of material 338, which may be in spool form. The automated process, which has been previously described, produces material blanks for multiple parts or components for a wide variety of lay-up configurations. The plies 336 in the stack may be tacked together in multiple locations using a heating or ultrasonic welding device as previously described. In the particular embodiment shown in FIG. 25, fittings 342, 343 are joined to the ends of the stack of plies 346 using any of the joints shown in FIGS. 21-25 (or other joint configurations), and the metal fitting 350 is positioned on top of the plies 346 and acts as a doubler in the finished part.
The lay-up 345 is positioned between consolidation tools 352 of the type previously mentioned, as shown in “Step C” in FIG. 26. The consolidation tools 352 may include surface features that are transferred to the laminate plies 346 in order to create thickness tailoring, thickness variations and curvatures or other part features. These part features may include pockets to accommodate features of the fittings 342, 343 and 350, as well as ply buildup ramps, part curvatures, etc. The sides of the tool 352 which mate with a CCM machine 368 is of a constant size and shape to match standard dies on the CCM machine 368. The locations of the features on the tools 352 are coordinated with the features of the stack of plies 346. Thin steel sheets (not shown) of the type previously described, may be used on the non-tool side of the laid-up plies 346.
“Step D” in FIG. 26, and FIG. 27 better illustrate the relationship between the tools 352 and the lay-up 345. The consolidation tools 352 include tool members 358, 360 engaging opposite sides of the lay-up 345. The tool members 358, 360 are engaged by press platens 354, 356 which squeeze the tool members 358, 360 together in order to consolidate the plies 346 of the lay-up 345. One of the tools 358 includes a pocket having a shape matching that of the doubler fitting 350. The second tool member 360 is smooth on both of its opposite faces.
As shown in FIG. 28, the lay-up 345 is fed along with the tool members 358, 360 into the CCM machine 368, in the direction of the arrow 347. Although not specifically shown in FIG. 28, the lay-up 345 along with the consolidation tool members 358, 360 may pass through a pre-forming station such as that shown in FIG. 5, where the lay-up 345 is preformed into the approximate shape of the final part 366.
Referring again to FIG. 26, at “Step E” following consolidation, the tooling 352 is removed from the consolidated part 366 and the part 366 is trimmed. At step “F”, the part 366 is inspected, using nondestructive inspection techniques. The final part 366 shown in “Step G” is a monolithic, fully consolidated structure in which the metal fittings 342, 343 and 350 are formed integral with the consolidated plies 346 of the TPC laminate.
As previously discussed, continuous compression molding techniques may be used to fabricate fiber reinforced polymer stiffeners, for example, using polymers resins discussed above including, for instance, thermoplastic matrix polymers, for instance, as shown as 40 in FIG. 3, and combinations thereof having constant or variable geometries, including a constant or variable thickness and/or one or more curvatures along the length of the stiffener. As will be discussed below in connection with FIGS. 29-44, these stiffeners may also include one or more tapered features along their lengths. For example, referring to FIG. 29, a stiffener in the form of an I-beam 362 has an upper cap 366 connected to a lower cap 369 by a tapered web region 370. The upper and/or lower caps 366, 369 of the beam 362 may be similar to the cap regions 24 of the beam 20 shown in FIG. 1. The beam 362 includes at least one feature that is tapered along the length of the beam 362. In this example, the height H and thus the web region 370 of the beam 362 is tapered, varying in height H along the beam's length. In this example, the lower cap 369 of the beam 362 extends substantially parallel to the longitudinal axis 364 of the beam 362, while the upper cap 366 is inclined relative to the longitudinal axis 364.
FIG. 30 illustrates another example of a tapered beam 362 in which the beam height H varies nonlinearly. In this example, the beam 362 has two differing tapered web sections 366 a that vary in height H at differing linear rates.
FIG. 31 illustrates a further example of a tapered beam 362 in which the upper cap 366 is curved along the length of the beam 362 and the height H of the web region 370 varies continuously along the beam's length.
Still another example of a tapered beam 362 is shown in FIG. 32 in which the web region 370 is symmetrically tapered about the longitudinal axis 364 of the beam 362.
The tapered beams shown in FIGS. 29-32 are merely illustrative of a wide range of tapered features that may be possible. For example, a beam 362 may have a combination of differing tapers, including linear or nonlinear tapers along its length.
As previously noted, the tapered beam 362 may include one or more features of the beams previously described in connection with FIGS. 1-28. For example, as shown in FIG. 33, a tapered beam 362 may have a web region 370 possessing both a curvature and a variable or tapered height H, as well as caps 366, 369 that are also curved along the length of the beam 362.
Attention is now directed to FIG. 34 which broadly illustrates the components of consolidation tooling 375 used to mold and consolidate fiber reinforced thermoplastic parts having one or more features that are tapered along the length of the part, such as the beams 362 shown in FIGS. 29-33. The consolidation tooling 375 may be employed in a consolidation structure 78 such as that shown in FIG. 4, to compression mold and consolidate a flat stack, 74 or 76 of prepreg in a semi-continuous process into a cross section with tapered height or width. The consolidation tooling 375 comprises first, second, third and fourth elongate tool dies 256 a, 256 b, 256 c, 256 d respectively, and first and second elongate tooling sleeves 376, 378 respectively.
The flat stack of prepreg 74 is sandwiched between the first and second tooling sleeves 376, 378 which are compressed by the first, second, third and fourth tool dies 256 a-256 d. At least one of the first and second tooling sleeves 376, 378 is tapered along its length to produce a tapered feature of the part being fabricated, which, in the case of the beams 362 shown in FIGS. 29-33, comprises the web region 370. The taper of the tooling sleeves 376, 378 may be linear, non-linear or curved along all of only a portion of the length of the part, depending on the geometry of the part being fabricated. As will become later apparent in this description, depending on the geometry of the part, both of the first and second tooling sleeves 376, 378 may have a cross sectional shape that varies along the length of the tooling sleeve 376, 378 to form the desired taper. Also depending on the geometry of the part being fabricated, at least one of the first and second tool dies 256 a, 256 b is tapered along its length, and in some embodiments, both of the first and second tool dies 256 a, 256 b are tapered along their respective lengths. Each of the third and fourth tool dies 256 c, 256 d may be a universal tool die that has a cross sectional shape, such as a rectangular shape, that is substantially constant along its length.
FIG. 35 illustrates an embodiment of a tapered beam 362 a that is substantially similar to the beam 362 shown in FIG. 32. Beam 362 a has a substantially I-shaped cross section defined by first and second cap regions 372, 374 that are connected by a web region 370. While the illustrated beam 362 a is substantially symmetrically tapered about the longitudinal axis 364 of the beam 362 a, in other embodiments, the tapering may not be symmetric.
FIGS. 36, 37 and 38, illustrate the consolidation tooling 375 used to continuously compression mold the beam 362 a shown in FIG. 35. As previously discussed in connection with FIG. 34, the consolidation tooling 375 comprises first, second, third and fourth tool dies 256 a-256 d respectively, e.g. first, second, third and fourth elongate tool dies 256 a-256 d respectively, and first and second tooling sleeves 376, 378 respectively, e.g. first and second elongate tooling sleeves 376, 378 respectively. In this example, each of the tooling sleeves 376, 378 is tapered along its length. Each of the first and second tooling sleeves 376, 378 is generally U-shaped in cross section and includes first and second laterally spaced, flange portions 382, 384 respectively, and a tapered web portion 380. The flange portions 382, 384 are respectively tapered along their length. In the illustrated embodiment, the flange portions 382, 384 are tapered in opposite directions to each other, however in other embodiments, they may be tapered in the same direction. The thickness t1 of the web portion 380 may be substantially constant along the length of the tooling sleeve 376, 378, whereas the thickness t2 of the flange portions 382, 384 may vary along the length of the sleeve, depending upon the geometry of the beam being fabricated.
In some embodiments, only one of the flange portions 382, 384 may be tapered. In other embodiments the flange portions 382, 384 may be tapered differently from each other. In still other embodiments, the thickness t1 may vary along the length of the tooling sleeve 376, 378. Tapering of either or both of the flange portions 382, 384, results in the web portion 380 also being tapered along its length, in accordance with the varying height H. The tooling sleeves 376, 378 function to apply substantially uniform pressure on the surface of the part (e.g. beam 362 a) being fabricated, and may be made of a durable material such as, without limitation, stainless steel that is capable of handling the repetitious, high heat cycles. The sides 379 of the tooling sleeves 376, 378 mating the laminate part may be fabricated with all of the desired part features such as ply buildups, ramps, pockets, part curvature, variable overall height, etc.
Referring particularly to FIGS. 36 and 37, each of the first and second tool dies 256 a, 256 b is tapered along it length to substantially match the taper of the tooling sleeve 376, 378. Thus, the taper of the first tool die 256 a is complementary to that of the first tooling sleeve 376, and the taper of the second tool die 256 b is complementary to that of the second tooling sleeve 378. Each of the third and fourth tool dies 256 c, 256 d is a universal tool die having a rectangularly shaped cross section that is substantially constant along the length of the tool die 256 c, 256 d. The third and fourth tool dies 256 c, 256 d are respectively are displaced into and received within the first and second tooling sleeves 376, 378. As in previous embodiments, the first and second tooling sleeves 376, 378 along with the formed beam 362 a move past the tool dies 256 a, 256 b. 256 c, 256 d in an incremental or step-wise manner during the forming and consolidation process previously described in connection with a typical consolidation structure of the type shown in FIGS. 4 and 19.
Referring particularly to FIGS. 37 and 38, the consolidation tooling 375 may further include side tooling sheet members 388 similar to side tooling sheet members 92 previously discussed in connection with FIGS. 4 and 5. The side tooling sheet members 388 are sandwiched between the cap regions 372, 374 of the beam 362 and the first and second tool dies 256 a, 256 b. As indicated by the arrows 386 in FIG. 38, the third and fourth tool dies 256 c, 256 d compress the web region 370 of the beam 362 against the web portions 380 of the first and second tooling sleeves 376, 278. The first and second tool dies 256 a, 256 b laterally compress the cap regions 372, 374 of the beam 362 a against the outer faces 379 of the first and second tooling sleeves 376, 378. The lateral force applied by the first and second tool dies 256 a, 256 b is reacted by the third and fourth tool dies 256 c, 256 d. As best seen in FIG. 38, the inner faces 381 of the first and second tool dies 256 a, 256 b are tapered along their respective lengths in directions opposite the taper of the outer faces 379 of the flange portions 382, 384. Thus, the taper of the inner faces 381 of the tool first and second tool dies 256 a, 256 b is complementary to the taper of the outer faces 379 of flange portions 382, 384 of the first and second tooling sleeves 376, 378.
FIG. 39 illustrates another embodiment of a tapered beam 362 b having a substantially J-shaped cross section. The tapered beam 362 b includes a cap region 372, and a single bottom flange 390 connected to the cap region 372 by a web region 370. In this example, the cap region 372 and the flange 390 are symmetrically tapered along the longitudinal axis 364 of the beam 362 b, however, in other embodiments, the tapering may not be symmetric. FIG. 40 illustrates parts of the consolidation tooling 375 employed to fabricate the tapered beam 362 b shown in FIG. 39. Similar to the consolidation tooling 375 shown in FIGS. 36, 37 and 38, consolidation tooling 375 used to fabricate the tapered beam 362 b employs first and second tapered sleeves 376, 378 each having a flange portion 382, 384 and a web portion 380. The flange 390 of the beam 362 b is formed against the outer face 379 of one of the tapered flange portions 384 of tooling sleeve 378, while the cap region 372 of the tapered beam 362 b is formed against the outer faces 379 of both of the first and second tooling sleeves 376, 378. In one alternative of the present embodiment, the first tooling sleeve 376 and the second tooling sleeve 378 may include a tapered web portion, e.g., web portion 380, for forming a web region of a stiffener and a flange portion 384 for forming a flange region of the stiffener.
FIG. 41 illustrates another embodiment of a tapered beam 362 c having a substantially C-shaped cross section formed by a pair of flanges 390, 392 connected by a web region 370. In this example, the web region 370 is tapered in height along the length of the beam 362 c, and the flanges 390, 392 are symmetrically inclined relative to the longitudinal axis 364 of the beam 362 c, however, in other embodiments they may not be symmetrically inclined. FIG. 42 illustrates parts of the consolidation tooling 375 used to fabricate the tapered beam 362 c shown in FIG. 41. In this example, only a single tapered tooling sleeve 376 is needed to form the web region 370 and the flanges 390, 392 of the tapered beam 362 c. The single tapered tooling sleeve 376 includes a pair of flange portions 382, 384 connected by a web portion 380. The flanges 390 of the beam 362 c are formed against the outer faces 379 of the flange portions 382, 384 of tapered tooling sleeve 378, while the web region 370 of the tapered beam 362 c is formed against the web portion 380 of the tapered tooling sleeve 376. In embodiments where the tapered beam 362 c is not symmetrically tapered, only one of the flange portions 382, 384 of the tooling sleeve 376 need be tapered.
FIG. 43 illustrates still another embodiment of a tapered beam 362 d having a substantially Z-shaped cross section formed by oppositely directed flanges 390, 392 connected by a web region 370. FIG. 44 illustrates parts of the consolidation tooling 375 used to fabricate the tapered beam 362 d of FIG. 43. The consolidation tooling 375 includes first and second tooling sleeves 376, 378 that function along with first and second tapered tool dies 256 a, 256 b (not shown in FIG. 44), and third and fourth universal tool dies 256 c, 256 d to mold and consolidate a flat ply stack into the beam 362 d.
Attention is now directed to FIG. 45 which illustrates the overall steps of a method of fabricating a plastic resin stiffener such as a beam of the type shown in FIGS. 29-44. Beginning at 396, one or more tooling sleeves 376, 378 are fabricated that match the desired tapered part geometry. At 398, loose prepreg plies are assembled into a flat prepreg ply stack 74 according to a predefined ply schedule and layout, and are then tacked, as necessary. At 400, the ply stack 74 is placed in contact with the tooling sleeves 376, 378 at the proper orientation to each other. At 402, the ply stack 74 along with the tooling sleeves 376, 378 are loaded into a consolidation structure 78. During this loading process, the tooling sleeves 376, 378 are placed in contact with tool dies 256 a-256 d. At 404, a continuous molding process is begun to mold and consolidate the part. As previously described, the continuous molding process may be carried out using a consolidation structure 78 of the type shown in FIGS. 4 and 19, in which the part and the tooling sleeves 376, 378 are moved through the tool dies 256 a-256 d as the tool dies 256 a-256 d compress the part against the tooling sleeves 376, 378. At 406, the part is removed from the tooling sleeves 376, 378 after it is fully consolidated, and at 408, the part is trimmed to the desired configuration.
Referring now to FIGS. 46 and 47, embodiments of the disclosure may be employed in the context of an aircraft manufacturing and service method 410 as shown in FIG. 46 and aircraft 412 as shown in FIG. 47. Turning first to FIG. 46, an illustration of an aircraft manufacturing and service method 410 is depicted in accordance with an advantageous embodiment. During pre-production, aircraft manufacturing and service method 410 may include specification and design 414 of aircraft 412 in FIG. 47 and material procurement 416.
During production, component and subassembly manufacturing 418 and system integration 420 of aircraft 412 in FIG. 47 takes place. Thereafter, aircraft 412 in FIG. 47 may go through certification and delivery 422 in order to be placed in service 424. While in service 424 by a customer, the aircraft 412 in FIG. 47 is scheduled for routine maintenance and service 424, which may include modification, reconfiguration, refurbishment, and other maintenance or service.
Each of the processes of aircraft manufacturing and service method 410 may be performed or carried out by a system integrator, a third party, and/or an operator. In these examples, the operator may be 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, a leasing company, a military entity, a service organization, and so on.
With reference now to FIG. 47, an illustration of an aircraft 412 is depicted in which an advantageous embodiment may be implemented. In this example, aircraft 412 is produced by aircraft manufacturing and service method 410 in FIG. 46 and may include airframe 428 with plurality of systems 430 and interior 432. Examples of systems 430 include one or more of propulsion system 434, electrical system 436, hydraulic system 438, and environmental system 440. Any number of other systems may be included. Although an aerospace example is shown, different advantageous embodiments may be applied to other industries, such as the marine and automotive industries.
1. Consolidation tooling for use in a continuous compression molding machine to fabricate a fiber reinforced thermoplastic part having a varying height, comprising:
a first tool die and a second tool die, the first tool die and the second tool die each adapted to mold a multi-ply stack of thermoplastic prepreg into a part; and
at least a first tooling sleeve movable between the first tool die and the second tool die, the first tooling sleeve having at least a first tapered portion engageable with the multi-ply stack of thermoplastic prepreg,
wherein the first tool die is tapered along its length substantially complementary to the first tapered portion of the first tooling sleeve,
a third tool die and a fourth tool die, the third tool die and the fourth tool die each adapted to compress and mold the multi-ply stack of thermoplastic prepreg into a web region of the part,
a first tooling member attached to the first tool die and a second tooling member attached to the second tool die, wherein the first tooling member applies a first compressive force directly to the multi-ply stack of thermoplastic prepreg and the second tooling member applies a second compressive force directly to the multi-ply stack of thermoplastic prepreg.
2. The consolidation tooling of claim 1, wherein:
the first tapered portion of the first tooling sleeve is a first tapered flange portion, and
the first tooling sleeve includes a second tapered flange portion engageable with the multi-ply stack of thermoplastic prepreg.
3. The consolidation tooling of claim 2, wherein:
the second tool die is tapered substantially complementary to the second tapered flange portion of the first tooling sleeve.
4. The consolidation tooling of claim 2, wherein the first tapered flange portion and the second tapered flange portion of the first tooling sleeve are tapered in opposite directions.
5. The consolidation tooling of claim 1, wherein the first tooling sleeve includes a web portion connected with a first tapered flange portion.
6. The consolidation tooling of claim 1, wherein the third tool die is disposed within the first tooling sleeve.
7. The consolidation tooling of claim 6, wherein the third tool die is elongate and has a substantially constant cross section along its length.
8. The consolidation tooling of claim 1, wherein at least one of the group consisting of the first tool die, the second tool die, and the first tooling sleeve includes non-uniform thickness contours.
9. The consolidation tooling of claim 1, wherein the first tooling sleeve is generally U-shaped in cross section.
10. The consolidation tooling of claim 1, wherein the first tooling sleeve is elongate and is curved along at least a portion of its length.
11. The consolidation tooling of claim 1, wherein the first tooling sleeve is configured to mold the multi-ply stack of thermoplastic prepreg into a beam having a cross sectional shape selected from the group consisting of:
an I-shape,
a J-shape,
a Z-shape,
a T-shape, and
a C-shape.
12. The consolidation tooling of claim 1, further comprising: a second tooling sleeve movable between the first tool die and the second tool die, the second tooling sleeve having at least one tapered flange portion.
13. Consolidation tooling for use in a continuous compression molding machine to fabricate a fiber reinforced thermoplastic part having a varying height, comprising:
a first tool die and a second tool die, the first tool die and the second tool die each adapted to mold a multi-ply stack of thermoplastic prepreg into a part, wherein the first tool die and the second tool die are horizontally opposed to each other;
a third tool die and a fourth tool die, wherein the third tool die and the fourth tool die are each adapted to apply a compressive force in a vertical direction to the multi-ply stack of thermoplastic prepreg and mold the multi-ply stack of thermoplastic prepreg into a web region of the part, wherein the third tool die and the fourth tool die are vertically opposed to each other;
a first tooling member attached to the first tool die, wherein the first tooling member extends vertically along an inwardly facing surface of the first tool die;
wherein the inwardly facing surface of the first tool die is tapered along its length and the first tooling member applies a first compressive force, in a horizontal direction directly to the multi-ply stack of thermoplastic prepreg;
a second tooling member attached to the second tool die, wherein the second tooling member extends vertically along an inwardly facing surface of the second tool die;
wherein the inwardly facing surface of the second tool die is tapered along its length and the second tooling member applies a second compressive force, in the horizontal direction directly to the multi-ply stack of thermoplastic prepreg;
a first tooling sleeve movable between the first tool die and the second tool die, the first tooling sleeve having at least a first tapered portion and at least a second tapered portion; and
a second tooling sleeve movable between the first tool die and the second tool die, the second tooling sleeve having at least a first tapered portion and at least a second tapered portion.
14. The consolidation tooling of claim 13, wherein the first and second tooling sleeves are configured to mold the multi-ply stack of thermoplastic prepreg into a beam having a cross sectional shape comprising:
a cap region; and
a single bottom flange connected to the cap region by the web region, wherein the cap region extends parallel with a longitudinal axis of the beam along its length and the single bottom flange is angled with respect to the longitudinal axis of the beam along its length.
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