Molding process and apparatus for producing unified composite structures
A method of forming a unitary, composite structural member, and a member formed in accordance with the process. The process involves stitching a plurality of warp knit panel sections together to generally form a plurality of independent panel sections. The sections are placed within the dies of a molding tool such that a rib portion of each section aligns. Inflatable bladders are then slipped into voids formed in between the various panel sections of the assembly. The bladders are inflated to hold the panel sections in the shape of the final product and to hold the rib portions in contact with one another. Resin is then infused into the panels that make up the assembly. The assembly is then cured. When the panels are removed from the molding tool a unitary, complexly shaped, composite structural member is formed.
This application is a divisional of U.S. patent application Ser. No. 10/393,195 filed on Mar. 20, 2003, the disclosure of which is incorporated herein by reference.
FIELD OF THE INVENTIONThis invention relates to molding processes and apparatus', and more particularly to a molding process and apparatus for producing large and complex structural components especially well suited for aircraft structural components through a single step molding process.
BACKGROUND OF THE INVENTIONDue to the size and complexity of structural components such as aircraft wings, sections of aircraft fuselage, etc., the formation of such structures using composite materials in a single step molding procedure has historically not been possible. Until recently, a process capable of holding critical dimensional features within narrow tolerance ranges for large complex composite structures did not exist.
In previous manufacturing operations, typically the complex part is broken down into multiple pieces of simple design that are subsequently assembled into a single large complex structure. The cost to manufacture the structure thus increases significantly through the additional manufacturing steps needed to fabricate separately and then assemble (i.e., often bond adhesively or mechanically attach) two or more independent component parts to form a single overall structure.
SUMMARY OF THE INVENTIONThe present invention is directed to a molding process in which two or more dry fiber material preforms are stitched together to form preform assemblies that represent an approximate shape of the final component. The stitched-together preform assemblies are then placed within a suitable tool that maintains the part loft. A plurality of inflatable bladders are then placed inside the preform assemblies to serve as internal vacuum bags. Inflating the bladders serves to urge the dry fiber material forms against interior surfaces of the tool. In one preferred embodiment each dry material form comprises a portion of rib, and the two portions are urged into contact with one another as the bladders are inflated.
After inflating the bladders, the entire stitched-together assembly is then infused with resin. Various areas of the stitched-together preforms, such as possibly ribbed elements of the assembly, are formed by balancing the force applied to the preform through bladder pressure.
Once the stitched-together dry fiber preform assembly is fully infused with resin, it is then cured inside a suitable oven for a predetermined period of time to allow the resin infused into the stitch-together assembly to thoroughly cure. When removed from the tool, the stitched-together assembly forms a finished, unitary part. The bladders may then be extracted through small holes formed at various portions of the assembly such as holes within rib webs of the assembly if the assembly includes such webs. The resulting unitized structure thus forms a single piece structural assembly that is co-cured and reinforced with z-direction stitching. Accordingly, no subsequent manufacturing steps involving bonding of individual molded details or elements or mechanical fastening of individual molded panels together is required. The co-curing and the stitching of the independent dry fiber material forms together to create a single piece unit further eliminates local stress concentrations at the interfaces of independent component sections of the assembly and results in a more durable, light weight structure that is especially well suited for use in high-performance aircraft manufacturing applications.
Further areas of applicability of the present invention will become apparent from the detailed description provided hereinafter. It should be understood that the detailed description and specific examples are intended for purposes of illustration only and are not intended to limit the scope of the invention.
BRIEF DESCRIPTION OF THE DRAWINGSThe present invention will become more fully understood from the detailed description and the accompanying drawings, wherein:
The following description of the preferred embodiment(s) is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses.
Referring to
With further reference to
A particularly unique feature of the rib assembly 26 is the “tongue-in-groove” arrangement by which rib sections 20 and 22 are coupled together. In this example, section 22 includes sections 22c and 22d which receive an end portion 32 of panel 20. Fillet inserts 36 are also typically inserted into the voids formed in between skin 12 and section 20, and in between skin 14 and section 22 prior to stitching the skins 12 and 14 to their respective panel sections 20 and 22.
Stitching 16, 18, 28 and 30 preferably comprises a common thread material such as Kevlar™. It will be appreciated, however, that suitable thread material may be employed such as Vectran™.
It will also be appreciated that the exemplary part 10 shown in
Each of the skins 12 and 14, and the independent component parts of the rib 26 are formed from a dry fiber material form, typically warp knit fabric. As will be understood, the dry materials forms are typically not impregnated With resin to facilitate the stitching process by avoiding fiber breakage during needle penetration.
With further reference to
Referring now to
With further reference to
The bladders 44, 46 and 48 may be formed from a variety of light weight, flexible materials, but in one preferred form comprise latex bladders. The bladders 44, 46 and 48 are shaped such that when they are substantially or fully inflated they engage the intersurfaces of the skin panels 12 and 14 and the surfaces of sections 20 and 22 of each of the ribs 26. The bladders 44, 46 and 48 urge the flaps 22c and 22d of each section 30 of each rib 26 against the end portion 32 of each section 28 of each rib 26 such that the sections 22c and 22d are effectively clamped against opposing surfaces of the end portion 32′ of each rib 26. The bladders 44, 46 and 48 further serve to maintain the skins 12 and 14 pressed against interior surfaces of the die portions 50 and 52 of the tool 54.
Referring to
Referring to
When the assembly comprising panels 12, 14, 20 and 22 are removed, the fully formed and cured composite structural assembly 10 is formed. Co-curing the skins 12 and 14 to their respective rib sections 20 and 22, while simultaneously carrying sections 22c and 22d to the end portion 32 of rib section 20, eliminates the need to assemble the two skins 12 and 14 to the rib 26 in a separate manufacturing step. Alternatively, it eliminates the need to assemble the rib sections 20 and 22 to one another in a separate, subsequent manufacturing step by bonding or by mechanical fasteners such as rivets. Accordingly, a single, unitary, composite structural member can be created in a single molding step.
The process of the present invention described above significantly reduces the cost of manufacturing closed, stiffened box structures and other complexly shaped components that would ordinarily have been manufactured with first a molding step, and then a subsequent securing step to secure two or more of the component sections together. Co-curing all of the component sections of the unitary, composite structural assembly 10 further provides a stronger structural part by providing efficient, continuous load paths along the interfaces where two or more components have been molded to one another. Forming the assembly 10 in one step further serves to minimize stress concentrations at the interfaces where two or more independent sections are joined together by eliminating the need for drilling or otherwise forming one or more openings through which fastening elements such as rivets can be installed. The stitching used to form the assembly 10 further helps to provide damage arrestment and further to increase damage tolerance to the assembly. The high-strength stitched interfaces also form stronger joints than what would be possible with co-curing two or more independent panel sections. The process of the present invention further provides for uniform, smooth internal transitions, such as where the flap sections 22c and 22d are bonded to end portion 32 of rib section 20.
A particularly desirable feature of the present invention is how the rib sections 20 and 22 are automatically urged into contact with one another as the bladders 44, 46, 48 are inflated.
After the assembly 10 is cured, the bladders 44, 46 and 48 may then be removed through openings 55 after the bladders 44, 46 and 48 are deflated and rotated in a circular motion to help break the surface tension between the bladders and the inner part surfaces. In this regard it will be appreciated that the bladders 44, 46 and 48 are extremely thin-gauge material and relatively inexpensive components that can be discarded after one molding operation is performed. If a multi-cell bladder is employed, then removal will require urging one or more of the cells through one or more openings 41 in the ribs 26, before removing the bladder from the tool 54, such as through a single one of openings 55.
The description of the invention is merely exemplary in nature and, thus, variations that do not depart from the gist of the invention are intended to be within the scope of the invention. Such variations are not to be regarded as a departure from the spirit and scope of the invention.
Claims
1. A unitary composite structure comprising:
- a first composite panel having a first rib portion secured thereto;
- a second composite panel secured to a second rib portion;
- said first and second composite panels being simultaneously infused with a resin while placed within a molding tool, wherein said rib portions interengage, and then said composite panels are cured for a desired curing time, wherein upon completion of said curing said first and second composite panels form a unitary composite structure having a rib structure formed by said first and second rib portions linking said first and second composite panels together.
2. The structure of claim 1, wherein at least one of said first and second composite panels are formed from a warp knit fabric.
3. The structure of claim 1, wherein a plurality of inflatable bladders are placed within the tool and inflated prior to infusing the first and second composite panels with resin, to assist in holding portions of said first and second composite panels in contact with interior surfaces of said molding tool, and said rib portions in contact with one another.
4. The structure of claim 1, wherein one of said rib portions comprise a pair of flaps adapted to receive therebetween an end portion of the other one of said rib portions.
5. The structure of claim 1, wherein at least one of said composite panels comprises a plurality of subpanels stitched together.
6. The structure of claim 5, wherein said first composite panel is stitched to an edge of said first rib portion.
7. A unitary, composite structure, comprising:
- a first flexible panel having a first flexible rib portion secured thereto so as to be able to extend non-parallel to said first flexible panel;
- a second flexible panel having a second flexible rib portion secured thereto so as to be able to extend non-parallel to said second flexible panel; and
- wherein said rib portions interengage one another when at least one inflatable bladder is placed between said flexible panels and adjacent said rib portion, and said bladder is inflated; and
- wherein said flexible panels and said interengaging rib portions become rigid to form said composite structure after being placed in a mold, infused with a resin, and then allowed to cure.
8. The structure of claim 7, wherein said first flexible panel and said second flexible panels comprise composite panels.
9. The structure of claim 7, wherein said first and second flexible rib portions each comprise composite rib portions.
10. The structure of claim 7, wherein a plurality of inflatable bladders are placed between said first and second flexible panels.
11. The structure of claim 7, wherein said flexible panels and said flexible rib portions form an elongated, hollow portion within said structure.
12. The structure of claim 7, wherein one of said rib portions includes a hole for enabling said inflatable bladder to be removed after said structure is cured.
13. The structure of claim 7, wherein said flexible panels and said flexible rib portions form an internal I-beam structure when said structure is viewed end-wise.
14. A composite structure comprising:
- a pair of composite panels disposed generally parallel to one another;
- a plurality of composite rib panels stitched to the composite panels to form support ribs;
- wherein said support ribs are formed when a plurality of inflatable bladders are placed between said panels and inflated to urge said composite rib panels to engage to form said support ribs; and
- wherein said structure is formed when said composite panels and said composite rib panels are placed within a mold, infused with a resin and then allowed to cure.
15. The structure of claim 14, wherein said composite rib panels comprise a tongue-in-groove engagement arrangement.
16. The structure of claim 14, wherein at least one of said composite rib panels includes a hole for enabling at least one of said inflatable bladders to be removed after said structure is formed.
17. The structure of claim 14, wherein support ribs define a plurality of elongated voids within said structure running co-extensively with said composite panels.
18. The structure of claim 14, wherein at least one of said composite rib panels includes a pair of flaps adapted to fold over onto and sandwich an end portion of a different, mating one of said composite rib panels, as one of said inflatable bladders is inflated.
19. The structure of claim 14, wherein a plurality of internal voids are formed within said structure, and voids being defined in part by said composite rib panels.
Type: Application
Filed: Mar 23, 2005
Publication Date: Jul 28, 2005
Inventors: Alexander Velicki (Garden Grove, CA), Patrick Thrash (Corona, CA), Roger Burgess (Long Beach, CA), Cole Standish (Long Beach, CA)
Application Number: 11/087,884