Source: https://insight.rpxcorp.com/pat/US20110111183A1
Timestamp: 2019-07-20 01:18:30
Document Index: 669941249

Matched Legal Cases: ['art 310', 'art 310', 'art 310', 'art 310', 'art 310', 'art 310', 'art 310', 'art 310', 'art 310', 'art 310', 'art 310', 'art 310', 'art 310']

Patent US 20110111183A1
US 20110111183A1
Est. Priority Date: 11/08/2007
a composite part having a first channel; and
foam located in the first channel, wherein the foam has a set of channels.
A method and apparatus for a composite stringer. A method is used for manufacturing a hollow composite stringer. Foam is formed with a mandrel installed into the foam. A composite material and the foam is laid up onto a tool in a form of a stringer. The composite material and the foam in the form of the stringer is cured to form a cured stringer. The mandrel from the foam is removed to form the hollow composite stringer.
US 20130036595A1
VENT MEMBER, WING PANEL, AND MAIN WING FOR AIRCRAFT
US 20140299713A1
US 9,193,114 B2
Elongated structures and related assemblies
US 9,527,572 B2
US 9,926,082 B2
US 9,950,779 B2
US 10,207,786 B2
FIRE RETARDANT PANEL APPARATUS AND METHOD OF MAKING AND USING SAME
US 20110049935A1
Method for producing a fibre composite component for aviation and spaceflight
US 20110076461A1
HIGH PULLOFF CAPABILITY HAT STRINGER
US 20110139932A1
US 20110250384A1
Kyoraku Co.Ltd.
Composite Flange, Duct Incorporating a Flange and Method of Making a Flange
US 20110254267A1
Helicopter blade mandrel
US 20080157429A1
Structural panels for use in aircraft fuselages and other structures
US 7,159,822 B2
System and method for microwave non-destructive inspection
US 20070046298A1
Structural waveguide formed in a leg of an antenna tower and method of use
US 7,205,956 B1
Seat power bus with discrete connection ports
US 7,207,523 B2
Terahertz imaging non-destructive inspection systems and methods
US 20070090294A1
Method of assembling a single piece co-cured structure
US 7,216,832 B2
Tuttle Steven T., Larry J. Ashton, Allman Mike G., Craig B. Simpson
Dielectric/conductive waveguide
US 5,363,464 A
RAIDO LOCAL AREA NETWORKS INC. DBA RADIOLAN INC.
US 6,198,445 B1
US 7,001,082 B2
Data communication and power transmission system for sensing devices
US 6,999,857 B1
Structurally integrable electrode and associated assembly and fabrication method
US 7,018,217 B2
Tubular members integrated to form a structure
US 7,063,763 B2
Composite material-stiffened panel and manufacturing method thereof
US 7,074,474 B2
US 20060226287A1
Composite spar drape forming machine
US 7,118,370 B2
US 20050003145A1
Apparatus and methods for forming composite stiffeners and reinforcing structures
US 20050056362A1
Single piece co-cure composite wing
US 6,889,937 B2
Rocky Mountain Composites Inc.
US 20050128028A1
ERA PATENTS LIMITED
US 20050211843A1
Contoured crushable composite structural members and methods for making the same
US 6,949,282 B2
Co-cured stringers and associated mandrel and fabrication method
US 20050230552A1
Optical connector arrangement
US 20050259919A1
Device for transmitting signals and/or energy to a vehicle seat rail system
US 6,960,993 B2
Low power, high speed data communications in vehicles
US 6,963,728 B2
Method of making composite airfoil structures
US 6,689,246 B2
Japan Aircraft Development Corporation Tokyo-To JP, Japan Aircraft Development Corporation
Co-cured vacuum-assisted resin transfer molding manufacturing method
US 20040051214A1
Device for transmitting signals and/or energy
US 20040048582A1
High pressure co-cure of lightweight core composite article utilizing a core having a plurality of protruding pins
US 6,739,861 B2
Composite panel adapted for point compressive loads and method for making same
US 6,755,998 B1
Composites Intellectual Holdings Inc.
Structurally integrated wire and associated fabrication method
US 20040166408A1
Power harvesting sensor for monitoring and control
US 20040150529A1
Integrally-reinforced braided tubular structure and method of producing the same
US 6,510,961 B1
US 20030098520A1
Method for fabricating an advanced composite aerostructure article having an integral co-cured fly away hollow mandrel
US 6,632,502 B1
US 20030192990A1
US 20030216149A1
Antenna for transmission / reception of radio frequency waves and an aircraft using such an antenna
US 6,653,980 B2
US 20020011047A1
SYSTEM FOR REMOTE POWERING AND COMMUNICATION WITH A NETWORK OF ADDRESSABLE MULTICHANNEL SENSING MODULES
US 20020050925A1
Interior decorating item and use of an optical wave guide as decorative thread on such interior decorating items
US 6,450,678 B1
US 6,458,309 B1
CONFORMABLE COMPOSITE STRUCTURAL MEMBER AND METHOD THEREFOR
US 20020178992A1
US 6,497,190 B1
Stitch-reinforced sandwich panel and method of making same
US 6,187,411 B1
Composite airfoil structures and their forming methods
US 20010017336A1
Hirahara Makoto, Amaoka Kazuaki, Shimizu Ryuhei, Isano Yasuo
Thermoplastic titanium honeycomb panel
US 6,039,832 A
Mounting of machinery within a vessel
US 6,116,179 A
Method of making foam-filled composite products
US 6,117,376 A
MERKEL MICHAEL
Large composite core structures formed by vacuum assisted resin transfer molding
US 6,159,414 A
TPI Technology Inc.
Composite detail having Z-pin stubble
US 5,863,635 A
Z-pin-reinforced sandwich structure
US 5,958,550 A
Process for preparing silicone elastomer compositions
US 5,854,336 A
CHEESEBROUGH-PONDS USA CO. DIVISION OF CONOPCO INC.
Method of forming a truss reinforced foam core sandwich structure
US 5,624,622 A
Method of making an integrally stiffened article
US 5,632,940 A
COMPOSITE WORKS LLC.
Whatley Bradford L.
Fiber-optic lighting system
US 5,647,658 A
Ziadi Bouchaib
Method for high pressure co-cure molding of lightweight honeycomb core composite articles having ramped surfaces utilizing low density, stabilized ramped honeycomb cores
US 5,527,414 A
Process for the manufacture of multi-layer composites with sensitive outer surfaces
US 5,403,424 A
3A TECHNOLOGY MANAGEMENT LTD.
ALUSUTSSE-LONZA SERVICES LTD.
Nest drill tube
US 5,415,504 A
BARRY WOLF FARMS LTD.
US 5,438,330 A
Composite baseball bat with cavitied core
US 5,458,330 A
BAUM RESEARCH DEVELOPMENT COMPANY INC. THE
Composite wing and manufacturing process thereof
US 5,332,178 A
Method of making an offset corrugated sandwich construction
US 5,348,601 A
Aircraft fiber optic data distribution system
US 5,222,166 A
Caul and method for bonding and curing intricate composite structures
US 5,242,523 A
Structural member having a stiffener bead therein and comprising plies of composite material extending for the full length and width of the structural member and continuously through the stiffener bead, and the article so made
US 5,271,986 A
Deteriorated structure repair method and substratum for restoring and lining corroded structure
US 5,268,392 A
Bertram Richard L.
US 5,170,666 A
Larsen Lawrence E.
Method of providing resin free surfaces adjacent a bonded joint
US 4,776,907 A
Corrosion resistant coating and liner combination
US 4,792,493 A
Bertram Richard L., Belcher Vernie L.
Aircraft shorted loop antenna with impedance matching and amplification at feed point
US 4,510,500 A
Ultralight composite wing structure
US 4,538,780 A
US 4,197,545 A
Lightweight contoured load carrying structure
US 4,079,903 A
Fiber Science Inc.
US 4,019,291 A
AMSTORE CORPORATION A MI CORP
American Store Equipment Corporation
Stiffened structural laminate and method of molding laminate with stiffener beads
US 4,053,667 A
US 3,963,425 A
Imperial Metal Industries Kynoch Limited
LIGHT WEIGHT CONTOURED LOAD CARRYING STRUCTURE
US 3,779,487 A
Larry J. Ashton, Abildskov Dale P.
Running board light for automobiles
US 2,561,756 A
Filed 10/07/1949
Shook Paul M.
Method of manufacturing plastic rotor blades
US 3,028,292 A
Filed 05/27/1957
Hinds James A.
Airfoil radar antenna
US 3,390,393 A
Upton Hubert W.
Method and apparatus for inspecting cavities
US 2,630,472 A
Filed 07/01/1948
Mcarthur Elmer D.
METHOD OF PRODUCING FIBER-REINFORCED PANELS OF SYNTHETIC RESIN
US 3,530,021 A
Filed 12/05/1966
REICHL KARL JOHANN
Method of manufacture of hollow reinforced plastic articles
US 3,205,288 A
Filed 07/24/1961
Bates William E.
a set of removable mandrels located in the set of channels in the foam.
3. The apparatus of claim 1, wherein the composite part is a composite stringer.
an aircraft, wherein the composite stringer is located in the aircraft.
This application is a divisional of application Ser. No. 11/937,006, filed Nov. 8, 2007.
The present disclosure relates generally to aircraft parts and in particular to aircraft stringers. Still more particularly, the present disclosure relates to a method and apparatus for a composite stringer.
Aircraft generally include an airframe, which may be regarded as an underlying skeleton, to which skin panels are attached to form a smooth aerodynamic outer surface. The wings also include an underlying structure covered with skin panels. Typically, skin panels are light and thin to minimize the weight of the aircraft and increase its payload and range. Since skin panels are thin, they are generally flexible and require stiffening to prevent undesired movement, flexing, and vibration during flight.
Hat stringers have been used for decades in the aerospace industry for stiffening metal fuselage sections and metal wing skins on both commercial and military aircraft. These stringers are composed of thin metal panels with acute angles that result in a trapezoidal shape. Relatively simple metal-forming techniques are used to bend the metal into the acute angles required for this shape. These metal-forming techniques include brake forming or rolling the metal into the hat stringer shape. These techniques allow the production of hat stringers with tight, constant angular bends and straight or flat legs.
In manufacturing composite hat stringers, a hat stringer may be placed on a fuselage skin in which the interior of the hat stringer has a hollow section that is formed with a bladder. These bladders are inserted into the composite stringer prior to performing curing processes. A curing process is a process that toughens or hardens a polymer material in the composite stringer. These bladders are inflated to support the internal structure of the composite stringer during the curing process in an oven or autoclave.
One drawback with the use of bladders is that in some cases a bladder may have a defect resulting in a deflation of the bladder inside of a composite stringer during the curing process. This deflation may result in an improperly formed composite stringer. As a result the stringer is discarded and manufactured again. The problems that may occur with deflation of a bladder during curing of a composite stringer include, for example, an improper shape for the stringer, ply movement, ply wrinkling, or porosity.
Therefore, it would be advantageous to have a method and apparatus that overcomes the above-described problems.
The advantageous embodiments provide a method and apparatus for a composite stringer. In one advantageous embodiment, a method is used for manufacturing a hollow composite stringer. Foam is formed with a mandrel installed into the foam. A composite material and the foam is laid up onto a tool in a form of a stringer. The composite material and the foam in the form of the stringer is cured to form a cured stringer. The mandrel from the foam is removed to form the hollow composite stringer.
In another advantageous embodiment, a method is present for manufacturing a hollow composite part. A composite part is formed with a first channel extending from a first end to a second end of the composite part. A foam core is formed within the first channel. A set of channels is created within the foam core to form the hollow composite part.
In yet another advantageous embodiment, an apparatus comprises a composite part having a first channel and foam located in the first channel, wherein the foam has a set of channels.
FIG. 3 is a diagram illustrating components used to manufacture a foam stiffened hollow composite stringer in accordance with an advantageous embodiment;
FIG. 4 is a diagram illustrating an example lay up of composite materials on an inside mold line for a composite stringer in accordance with an advantageous embodiment;
FIG. 5 is a diagram illustrating an example lay up of composite materials on an outside mold line for a composite stringer in accordance with an advantageous embodiment;
FIG. 6 is a perspective view of composite stringers containing foam with hollowed channels or sections in accordance with an advantageous embodiment;
FIGS. 7-31 are diagrams illustrating cross-sections of composite stringers with foam stiffened hollow cores with different channel configurations in accordance with an advantageous embodiment;
FIGS. 32-35 are diagrams illustrating cross-sections of composite stringers with foam stiffened hollow cores with different channel configurations in accordance with an advantageous embodiment;
FIG. 36 is a high level flowchart of a process for forming a hollow composite part in accordance with an advantageous embodiment; and
FIG. 37 is a flowchart of a process for manufacturing a composite stringer with a foam core in accordance with an advantageous embodiment.
Referring more particularly to the drawings, embodiments of the disclosure may be described in the context of aircraft manufacturing and service method 100 as shown in FIG. 1 and aircraft 200 as shown in FIG. 2. Turning first to FIG. 1, a diagram illustrating an aircraft manufacturing and service method is depicted in accordance with an advantageous embodiment. During pre-production, exemplary aircraft manufacturing and service method 100 may include specification and design 102 of aircraft 200 in FIG. 2 and material procurement 104. During production, component and subassembly manufacturing 106 and system integration 108 of aircraft 200 in FIG. 2 takes place. Thereafter, aircraft 200 in FIG. 2 may go through certification and delivery 110 in order to be placed in service 112. While in service by a customer, aircraft 200 in FIG. 2 is scheduled for routine maintenance and service 114, which may include modification, reconfiguration, refurbishment, and other maintenance or service.
With reference now to FIG. 2, a diagram of an aircraft is depicted in which an advantageous embodiment may be implemented. In this example, aircraft 200 is produced by aircraft manufacturing and service method 100 in FIG. 1 and may include airframe 202 with systems 204 and interior 206. Examples of systems 204 include one or more of propulsion system 208, electrical system 210, hydraulic system 212, and environmental system 214. 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 automotive industry.
The different advantageous embodiments recognize that other materials may be used in place of an inflatable bladder to form a cavity or channel within a composite part. A composite part with a channel is also referred to as a hollow composite part. The illustrative examples of the advantageous embodiments described herein are directed towards a composite part in the form of a stringer. Of course, the advantageous embodiments may be employed with other types of composite parts other than composite stringers. For example, the different advantageous embodiments may be applied to composite parts, such as, for example, without limitation truss, fluted, hat, and beaded core structures.
The advantageous embodiments recognize that hard tools may be used to form a composite stringer. These hard tools may be made from, for example, silicone rubber or machined aluminum. The different advantageous embodiments, however, realize that in various components such as fuselage barrels, wing skins, and door plan panels, the shape of the composite stringers may have complex contours making these types of tooling options hard or impossible to remove from long panels to form a hollow composite stringer. A long panel may be, for example, a panel that is around 50 feet to around 100 feet long.
The different advantageous embodiments recognize that an alternative material that may be used is foam in place of hard tools to help shape the composite stringer. Further, this type of material may remain in the stringer as part of the structure. Foam filled composite stringers have numerous advantages over conventional hollow composite stringers. These advantages include, for example, increased impact resistance, improved structural properties, acoustical deadening, moisture infiltration reduction, simplified fabrication, reduced handling needs, elimination of a need for noodles (radius support fillers) or wrap plies, reduced tendency to bow out when placed over padups, and flow time reductions.
The different advantageous embodiments, however, also recognize that the weight added through the use of foam within composite stringers may be greater than desired as compared to a hollow composite stringer. Lower density foams with less weight often are unfeasible because these types of foams may not survive or remain intact during the heating that occurs in curing the stringer. Higher density foams have increased weight.
As a result, the different advantageous embodiments recognize that it would be advantageous to have a method and apparatus for manufacturing a composite part having a channel containing foam in which the foam also has a channel. The amount of foam remaining within the composite part is selected in a manner to provide advantages associated with foam remaining within a composite part while reducing weight.
Thus, the different advantageous embodiments provide a method and apparatus for manufacturing a hollow composite part with foam. The composite part is formed having a first channel. The channel may extend from a first end to a second end of the composite part. A foam core is formed within the first channel. A second channel is created within the foam core to form the hollow composite part.
With reference now to FIG. 3, a diagram illustrating components used to manufacture a foam stiffened hollow composite stringer is depicted in accordance with an advantageous embodiment. In these examples, lay up tool 300, shape forming tool 302, foam tool 304, mold tool 306, and autoclave\oven 308 are used in these examples to manufacture composite part 310.
Composite material 312 and foam 314 are formed on fuselage skin 316 in these examples. Composite material 312 has channel 318 in which foam 314 is located. Channel 318 may extend all the way through composite part 310, from one end of composite part 310 to another end of composite part 310. In other embodiments, channel 318 may only extend partially through composite part 310. Foam 314 has channel 320 in which mandrel 322 is located in these examples.
Composite material 312 may be processed using lay up tool 300 and shape forming tool 302. Lay up tool 300 is used in this example to stack or lay up plies of composite material 312 into a layer for composite part 310. The layer may also be referred to as a flat charge. The flat charge is processed by shape forming tool 302 to form the desired shape for composite part 310. In these examples, composite part 310 is a composite stringer with a hat shape.
Lay up tool 300 may be implemented using various composite material processing tools, such as, for example, an M.Torres lay up, which is a tape layer machine available from M.Torres. Another example of a machine that may be used for lay up tool 300 is Access-Atlas, which is a composite working machine, which is available from Forest-Liné. Shape forming tool 302 may be implemented using a machine or tool that is capable of forming composite material into the desired shape. A forming die or press may be used to implement shape forming tool 302. An example of a press that may be used is a composite spar drape forming machine.
Foam 314 is a foam core located within channel 318. Foam 314 is formed by foam tool 304 in these examples. In these examples, foam 314 may be made from various materials. Foam 314 also is referred to as a polymer or cellular polymer foam. Foam 314 may be manufactured from a two-phased mixture in which gases, bubbles, or cells are disbursed within a solid polymeric resin. These bubbles or cells may be created through chemical additives. For example, a gas may be created by polymerization reaction or thermal decomposition. These cells also may be created within the resin through physical blowing agents, such as inert gases. Cells created in this manner may be open and loosely interconnected or closed and detached.
When a higher percentage of closed cells are present in a foam, the density of the foam is higher as well as the weight. In these examples, foam 314 may be made through a number of different methods including, for example, combining blowing agents in liquid resin and then curing the mixture in a mold, through extrusion, compression or injection molding, or solid-state fabrication.
Foam 314 may be implemented with any foam that can remain intact during a curing process. Examples of foams that may be used for foam 314 include, for example, without limitation, Last-A-Foam containing polyisocyanurate, which is available from General Plastics; Aircell containing aromatic polyester, which is available from Polyumac; Performa-E containing polyimide which is available from GFT Corporation; Corecell containing styrene acrylo-nitrile, which is available from Gurit; RIMA containing polymethacryllmide, which is available from Degussa/Rohacell; Airex containing polyetherimide, which is available from Alcan/Baltek; PrimoSpire/Parmax containing polyphenylenes, which is available from Solvay/Mississippi Poly Tech; LCP containing polyetherether-ketone, which is available from Wright Materials Research Company; Zotek containing polyvinylidene fluoride, which is available from ZoteFoams; Elfoam containing polyisocyanurate, which is available from Elliott Company; and Divinycell ET containing poly vinyl chloride, which is available from Diab.
Foam 314 may be formed with mandrel 322 in place or mandrel 322 being inserted into foam 314 afterwards. Foam tool 304 may be implemented using any machine that is capable for forming foam 314. An example of a machine that may be used to implemented foam tool 304 is a TVZ series machine, such as TVZ 4P manufactured by Teubert
In this illustrative embodiment, mandrel 322 is a removable mandrel that is placed into foam 314. Mandrel 322 may have various shapes depending on the desired shape for channel 320. Mandrel 322 is an elongate member that may be made out of various materials.
Examples of materials from mandrel 322 include, for example, hard silicone rubber, protruded fiberglass, extruded Teflon, aluminum, combinations of these materials, or any other suitable material. Mandrel 322 may be made from any relatively inflexible material that can stay intact within autoclave\oven 308. Further, mandrel 322 does not need to inflate or swell to introduce pressure to the surface of channel 318.
Composite part 310 on fuselage skin 316 and mold tool 306 are placed into autoclave\oven 308 to perform a curing process. Mold tool 306 may be, for example, an inside mold line tool or an outside mold line tool, depending on the implementation. The temperatures in autoclave\oven 308 may be around 350 degrees Fahrenheit. Additionally, autoclave\oven 308 also may introduce pressure in performing the curing process for composite part 310. The pressure may be, for example, around 100 pounds per square inch. The heating causes polymer materials, such as resins, in composite material 312 to flow. When polymers harden, composite part 310 is considered to be cured in these examples.
Autoclave\oven 308 may be implemented using any machine that is capable of curing composite components. For example, an autoclave\oven may be used. An Anchor autoclave from Anchor Autoclave Systems or an autoclave available from Taricco Corporation are examples of autoclaves that may be used to implement autoclave\oven 308. Composite part 310 also may be cured using other mechanisms other than autoclave\oven 308 in other embodiments. For example, electron beam curing may be used to cure composite material 312.
After curing has occurred, composite part 310 is removed from autoclave\oven 308 and mandrel 322 is removed from foam 314 to leave channel 320 within foam 314. In these examples, foam 314 may provide features and advantages as described above with respect to having foam located inside the composite part. Channel 320 within foam 314 aids in reducing weight. The size and configuration of the channel may be selected based on properties and features provided by these configurations.
Turning now to FIG. 4, a diagram illustrating an example lay up of composite materials on an inside mold line tool for a composite stringer is depicted in accordance with an advantageous embodiment. In this example, composite stringer 400 includes composite material 402 and foam 404. Composite material 402 is laid up over foam 404. Foam 404 is placed into inside mold line tool 406. Then fuselage skin 408 is placed or laid up onto composite material 402, foam 404, and inside mold line tool 406. Caul 410 is placed against fuselage skin 408 in these examples.
Foam 404 has mandrel 412, which is removable. In other advantageous embodiments, mandrel 412 is not present within foam 404. Instead, a channel cavity may be formed after the curing process has occurred. The channel may be formed, for example, by drilling the cavity with a drill or other tool. Typically, this type of lay up is used to manufacture a hat composite stringer, which is a stringer with acute angles in a trapezoidal shape.
Turning now to FIG. 5, a diagram illustrating an example lay up of composite materials on an outside mold line tool for a composite stringer is depicted in accordance with an advantageous embodiment. In this example, composite stringer 500 includes foam 502 and composite material 504. Foam 502 is placed on fuselage skin 506. Composite material 504 is placed or laid up over foam 502 and fuselage skin 506. As in the other example, foam 502 includes mandrel 508, which is a removable component. These components form composite stringer 500 in a pre-cured state on outside mold line tool 510. In this example, bag 512 is placed over composite stringer 500 for curing composite stringer 500.
In these examples, mandrel 508 is located within foam 502. In other advantageous embodiments, mandrel 508 is not present within foam 502. Instead, a channel cavity may be formed after the curing process has occurred. The channel may be formed, for example, by drilling the cavity with a drill or other tool.
Turning now to FIG. 6, a perspective view of composite stringers containing foam with hollowed channels or sections is depicted in accordance with an advantageous embodiment. In this example, assembly 600 includes composite stringers 602, 604, and 606 mounted on fuselage skin 608. Composite stringer 602 includes composite material 610 and foam 612 with channel 614 being present within foam 612. Composite stringer 604 includes composite material 616 and foam 618 with channel 620 being formed within foam 618. Composite stringer 606 includes composite material 622 and foam 624. Foam 624 has channel 626. The foam with these stringers provides additional advantages over stringers having a channel without foam.
Turning next to FIGS. 7-31, diagrams illustrating cross-sections of composite stringers with foam stiffened hollow cores with different channel configurations is depicted in accordance with an advantageous embodiment. The different composite stringers illustrated in FIGS. 7-31 are examples of composite stringers that may be manufactured using an inside mold line tool.
First, in FIG. 7, composite stringer 700 has trapezoid shaped channel 702 in which foam 704 is located at top side 706 of composite stringer 700. In FIG. 8, composite stringer 800 includes foam 802 in which channel 804 has a trapezoidal shape. In FIG. 9, composite stringer 900 has foam in sections 902, 904, and 906 leaving channel 908 and channel 910. In FIG. 10, composite stringer 1000 includes foam 1002 having a shape of a “space needle”, leaving channels 1004 and 1006 within composite stringer 1000. Composite stringer 1100 in FIG. 11 includes foam 1102 in an I-beam shape with channel 1104 and channel 1106.
Next in FIG. 12, composite stringer 1200 includes foam in sections 1202 and 1204 with channel 1206 dividing sections 1202 and 1204. In FIG. 13, composite stringer 1300 includes foam 1302 at bottom side 1304 of composite stringer 1300 leaving channel 1306. Composite stringer 1400 in FIG. 14 includes foam 1402 with channel 1404 being in an oval shape. Then, composite stringer 1500 in FIG. 15 includes foam 1502 with channels 1504 and 1506 forming a double oval cross-section. Composite stringer 1600 in FIG. 16 shows foam 1602 in an I-beam configuration with channels 1604 and 1606. This type of configuration is in contrast with composite stringer 1100 in FIG. 11 in which foam is not continuous throughout the sides of the composite stringer.
In FIG. 17, composite stringer 1700 includes foam 1702 in an X shape with channels 1704, 1706, 1708, and 1710. With reference to FIG. 18, composite stringer 1800 has foam 1802 in a similar X shape. This X shape is referred to as a supported X-foam shape and includes channels 1804, 1806, 1808, and 1810. In this example, foam 1802 is present along inner surface 1812 of composite stringer 1800. Composite stringer 1900 in FIG. 19 includes foam 1902 with multiple hole channels 1904, 1906, 1908, 1910, and 1912. Composite stringer 2000 in FIG. 20 includes foam 2002. Channel 2004 within foam 2002 has a turtle shape in this example. In FIG. 21, composite stringer 2100 includes foam 2102 with channel 2104 in a circular shape.
Turning to FIG. 22, composite stringer 2200 has foam 2202 in an H shape with channels 2204 and 2206. FIG. 23 depicts composite stringer 2300 with foam 2302 in an H shape in which foam 2302 extends all the way around inner surface 2304 of composite stringer 2300. Channels 2306 and 2308 are present. These channels have a trapezoidal shape and cross-section in these examples. In FIG. 24, composite stringer 2400 includes foam 2402 with a cross H shape having channels 2404, 2406, 2408, and 2410. Next, in FIG. 25, composite stringer 2500 includes foam 2502 in a T shape with channels 2504 and 2506. Composite stringer 2600 in FIG. 26 includes foam 2602 in a down arrow shape with channels 2604, 2606, 2608, and 2610. With reference next to FIG. 27, composite stringer 2700 includes foam 2702 in an inverted T shape with channels 2704 and 2706 being present.
Composite stringer 2800 in FIG. 28 includes foam 2802 in an H shape with channels 2804, 2806, 2808, 2810, 2812, and 2814. In FIG. 29, composite stringer 2900 includes foam 2902 in which channel 2904 has a diamond shape. Composite stringer 3000 includes foam 3002 with channel 3004 being in a cross shape in FIG. 30. In FIG. 31, composite stringer 3100 includes foam 3102 with clover shape channel 3104.
These depicted cross-sections of composite stringers with foam cores and channels are provided for purposes of illustrating some configurations for the different foam cores and channels. Of course, other configurations may be used depending on the particular implementation.
Turning now to FIGS. 32-35, diagrams illustrating cross-sections of composite stringers with foam stiffened hollow cores with different channel configurations is depicted in accordance with an advantageous embodiment. In these examples, cross-sections of stringers are illustrated in which composite stringers are formed using an outside mold line tool.
In FIG. 32, composite stringer 3200 includes foam 3202 with channel 3204. In FIG. 33, composite stringer 3300 includes foam 3302 and foam 3304 with channel 3306. In this example, two types of foam are used within composite stringer 3300.
Next, in FIG. 34, composite stringer 3400 includes foam 3402 and circular shaped channel 3404. Composite stringer 3500 in FIG. 35 includes foam 3502 and foam 3504 with channel 3506. In this example, two types of foam also are used within composite stringer 3500.
Turning now to FIG. 36, a high level flowchart of a process for forming a hollow composite part is depicted in accordance with an advantageous embodiment. The process illustrated in FIG. 36 may be implemented using tools illustrated in FIG. 3.
The process begins by forming a composite part with a first channel (operation 3600). The process also forms a foam core within the first channel (operation 3602). Next, the process cures a composite part (operation 3604). The process then creates a set of channels within the foam core (operation 3606) with the process terminating thereafter. The set of channels is one or more channels in these examples. The phrase “a set”, when used herein, refers to one or more of an item. For example, a set of cores is one or more cores, and a set of mandrels is one or more mandrels.
In these examples, operations 3600 and 3602 may be interchangeable in terms of the order in which the operations are performed. For example, the foam core may be formed first with the composite part being formed around the foam core afterwards. In other embodiments, the composite part may be first formed and then the foam core is inserted into the composite part. The creation of the set of channels may be formed in a number of different ways. For example, a mandrel may be used for each channel within the foam core. In other embodiments, a channel may be formed at a later point in time after the composite part has been cured.
Turning now to FIG. 37, a flowchart of a process for manufacturing a composite stringer with a foam core is depicted in accordance with an advantageous embodiment. The process illustrated in FIG. 37 may be implemented using tools depicted in FIG. 3.
The process begins by forming plies of composite material (operation 3700). This operation may involve cutting plies of composite tape and/or fabric, stacking the plies together, and vacuum compacting the composite material to form a flat charge. Thereafter, the composite material is formed into a stringer shape (operation 3702). Operation 3702 may involve using a dye or press to shape the flat charge into a stringer shape. The process then prepares the form (operation 3704). A removable mandrel is installed into the foam in operation 3704. In other instances, the foam may be formed around the mandrel.
Next, a determination is made as to the type of tool being used (operation 3706). If the tool is an outside mold line tool, the process places the foam onto skin plies (operation 3708). Thereafter, the foam is draped with the composite material (operation 3710).
The process then cures the composite stringer assembly (operation 3712). This curing operation also may include compacting the assembly with a vacuum in the autoclave\oven. The process then removes the mandrel from the foam (operation 3714) with the process terminating thereafter.
With reference again to operation 3706, if the type of tool is an inside mold line tool, the process places the composite material and the foam into the mold (operation 3716). Next, the process places skin plies over the composite material (operation 3718) with the process then proceeding to operation 3712 as described above.
VanWest, Barry P., Rotter, Daniel M., McCarville, Douglas A., Guzman, Juan C.
B29C44/583 : for making articles with ca...
B29C70/086 : and with one or more layers...
B29C70/865 : completely encapsulated
B29D99/0003 : Producing profiled members,...
B29K2715/003 : Cellular or porous
B64C1/064 : Stringers; Longerons
Y02T50/43 : Materials
Y10T428/24744 : Longitudinal or transverse ...
US 7,879,276 B2