ENERGY-ABSORBING STRUCTURAL COMPOSITE ELEMENTPatent application title: ENERGY-ABSORBING STRUCTURAL COMPOSITE ELEMENT
https://www.faqs.org/patents/app/20100155537
Inventors: Benjamin Scott McKinnie David Eugene Barland
Agents: HOVEY WILLIAMS LLP
Assignees: Spirit AeroSystems, Inc.
Origin: OVERLAND PARK, KS US
IPC8 Class: AB64C100FI
USPC Class: 244133
Publication date: 06/24/2010
Patent application number: 20100155537
Abstract:
A structural, energy absorbing composite element for aircraft structures includes a metallic or nonmetallic skin shell with a porous filler material insert positioned within the skin shell. The porous filler material is a material having ligaments that collapse resulting in a densification of the porous filler material in response to impact loading or a compression force sufficient to cause failure of the combined assembly.
Claims:
1. A structural, energy absorbing composite element comprising:a skin shell; anda porous filler material insert positioned within said skin shell.
2. The structural, energy absorbing composite element according to claim 1 wherein said porous filler material insert contains open cells and ligaments.
3. The structural, energy absorbing composite element according to claim 2 wherein said ligaments collapse in response to a force created by an impact to said skin of said structural, energy absorbing composite element.
4. The structural, energy absorbing composite element according to claim 2 wherein said ligaments collapse in response to said structural, energy absorbing composite element experiences high compression stresses.
5. The structural, energy absorbing composite element according to claim 3 wherein said collapse of said ligaments results in a densification of said porous filler material insert.
6. The structural, energy absorbing composite element according to claim 4 wherein said collapse of said ligaments results in a densification of said porous filler material insert.
7. The structural, energy absorbing composite element according to claim 1 wherein said porous filler material insert is formed of a metallic material.
8. The structural, energy absorbing composite element according to claim 7 wherein said metallic material is one of the group consisting of aluminum, steel, nickel, copper, zinc, lead cobalt, cadmium and alloys thereof.
9. The structural composite element according to claim 1 wherein the skin shell comprises a metal selected from the group of aluminum, steel, nickel, copper, zinc, and alloys thereof.
10. The structural, energy absorbing composite element according to claim 1 wherein the skin shell comprises a composite material selected from the group of carbon/epoxy, thermal set materials, thermoplastic materials and metal matrix composite materials.
11. The structural, energy absorbing composite element according to claim 1, wherein at least one end of the porous filler material insert is substantially tapered.
12. The structural energy absorbing composite element according to claim 1, further comprising:an attachment fitting, wherein at least a portion of the attachment fitting is positioned inward of the skin shell and adjacent at least one end of the porous filler material insert; anda fuse pin configured to attach the attachment fitting to the skin shell.
13. A passenger floor stanchion for an aircraft comprising:a tubular skin shell; anda porous filler material insert having open cells and ligaments positioned within said skin shell, wherein said ligaments collapse in response to a force created by an impact to said skin or when the passenger floor stanchion experiences excessive compression or impact load.
14. The passenger floor stanchion according to claim 13 wherein said collapse of said ligaments results in a densification of said porous filler material insert.
15. The passenger floor stanchion according to claim 13 wherein said porous filler material is formed of a metallic material.
16. The passenger floor stanchion according to claim 15 wherein said metallic material is one of the group consisting of aluminum, steel, nickel, copper, zinc, lead cobalt, cadmium and alloys thereof.
17. The passenger floor stanchion according to claim 13 wherein said tubular skin shell comprises a metal selected from on of the group of aluminum, steel, nickel, copper, zinc, and alloys thereof.
18. The passenger floor stanchion according to claim 13 wherein said tubular skin shell comprises a composite material comprised of the group of carbon/epoxy, thermal set materials, thermoplastic materials and metal matrix composite materials.
19. The passenger floor stanchion according to claim 13, wherein at least one end of the porous filler material insert is substantially tapered.
20. The passenger floor stanchion according to claim 19, further comprising:an attachment fitting, wherein at least a portion of the attachment fitting is positioned inward of the skin shell and adjacent at least one end of the porous filler material insert; anda fuse pin configured to attach the attachment fitting to the skin shell.
21. A passenger floor stanchion for an aircraft comprising:a tubular skin shell; anda metallic porous filler material insert having open cells and ligaments positioned within said skin shell, wherein said ligaments collapse resulting in a densification of said metallic porous filler material in response to a force created by an impact to said skin or when the passenger floor stanchion experiences high compression stresses.
22. The passenger floor stanchion according to claim 21 wherein said metallic porous filler material is one of the group consisting of aluminum, steel, nickel, copper, zinc, lead cobalt, cadmium and alloys thereof.
23. The passenger floor stanchion according to claim 21 wherein said tubular skin shell comprises a metal selected from on of the group of aluminum, steel, nickel, copper, zinc, and alloys thereof.
24. The passenger floor stanchion for an aircraft according to claim 21 wherein said tubular skin shell comprises a composite material comprised of the group of carbon/epoxy, thermal set materials, thermoplastic materials and metal matrix composite materials.
25. The passenger floor stanchion according to claim 21, further comprising:an attachment fitting comprising a clevis fitting, an interface portion, and a shoulder between the clevis fitting and the interface portion having a chamfered face engaging an end portion of the skin shell, wherein the interface portion of the attachment fitting is positioned inward of the skin shell and adjacent at least one end of the porous filler material insert; anda fuse pin configured to attach the attachment fitting to the skin shell,wherein at least one end of the porous filler material insert is substantially tapered.
26. A structural, energy absorbing composite element comprising:a skin shell;a porous filler material insert positioned within said skin shell, wherein at least one end of the porous filler material insert is substantially tapered; andan attachment fitting adjacent the at least one end of the porous filler material and attached to the skin shell, wherein at least a portion of the attachment fitting has a chamfered face engaging an end portion of the skin shell, such that when excessive compression or impact load is applied to the attachment fitting, the chamfered face induces a local shear force, pressing into the skin shell as the attachment fitting compresses the porous filler material insert.
Description:
FIELD OF THE INVENTION
[0001]The present invention relates to stanchions, struts and other supports for aircraft and other vehicles. More particularly, the invention relates to a composite element for structural applications having an outer shell composed of a metallic or nonmetallic composite skin and a collapsible core material. The composite element is lightweight and has high-energy absorption properties under buckling and impact conditions.
BACKGROUND
[0002]Long structural elements such as columns are utilized to vertically support other members such as a floor and must be capable of withstanding compressive, buckling, and impact loads. These structural elements must support the load of the structure it supports and added loads such as vehicles and people.
[0003]The load bearing capabilities of these structural elements is determined by the shape of their cross-section, length and material. For lighter weight applications, C or L-channels and hollow structural beams such as round, square or rectangular tubing of aluminum or composite materials are often used. Although strong by design, one disadvantage of these conventional support columns and stanchions is their lower energy absorbing properties during a failure. In crash conditions where the structure may be in compression, composite materials often buckle suddenly and absorb little energy. Failure of these structural elements, known as compressive failure, occurs when the structural elements experience ultimate compressive stresses that are beyond what the material is capable of withstanding. Additionally, buckling failure may result from column instability as a function of the height and width of the structural element.
[0004]Composite materials having multiple layered materials are often used in structural applications due to their inherent strength properties. These materials also provide great design flexibility due to the large various material selections and the ability to create various shapes. Structural composite elements often are composed of sandwich-type structure having an outer skin and a filler or core material. The outer skin, or shell, defines the shape and structure of the element whereas the filler material supports the shell.
[0005]Various materials are used for both the skin and core of a structural element and are typically chosen based upon the application and environment of use. For example, weight is often a design consideration in aerospace applications. Structural elements such as support beams of wall structures often need to be both lightweight and capable of carrying a mechanical load. In these applications, lightweight metallic skins made of aluminum and nonmetallic skins of thin carbon/epoxy or graphite/epoxy skins are often utilized. Environmental factors such as temperature and corrosive conditions are also considered when selecting skin materials.
[0006]The filler material provides both structural support and maintains the shape of the composite element. A variety of filler materials are known and range from the simple, such as balsa wood or other metallic and nonmetallic stiffeners, to complex structures such as aluminum or other nonmetallic honeycomb cores. Core materials are selected based upon their material properties such as flexibility, stiffness and strength-to-weight ratios, energy and sound absorption properties and others.
[0007]Environment must also be considered when selecting filling materials. It is not uncommon for carbon/epoxy skinned materials to absorb water, especially in aircraft applications where the structure undergoes pressurizing and depressurizing and are constantly exposed to changing atmospheric conditions. Water trapped in a composite may degrade the filler materials. Water may vaporize in warm conditions and even freeze at low temperatures and high altitudes and when undergoing these phase changes may damage the filler structure especially honeycomb-style core fillers, or disbond the filler from the skin.
[0008]Accordingly, there is a need for a lightweight composite structural element that has low structural weight, high structural strength and is capable of absorbing impact or crash energy and stabilizing long-column buckling that does not suffer from the problems and limitations of the prior art.
SUMMARY
[0009]The present invention provides a structural composite element that provides the required strength and rigidity for support columns and stanchions and provides inherent energy absorbing properties. This is achieved by the configuration of porous filler material and outer shell. The outer shell may be a metallic material made of aluminum alloys or a composite skin such as carbon/epoxy, fiberglass, metal matrix composite or other suitable composite materials.
[0010]A structural composite member constructed in accordance with an embodiment of the invention may comprise a porous core material having high mechanical energy absorption properties in all directions. The porous filler material further allows for the wicking of moisture condensation away from the skin or shell thereby reducing the onset of corrosion and chances of filler material damage.
[0011]Another exemplary embodiment of the present invention provides a lightweight structural composite element for long-columns and stanchions that have a high strength-to-weight ratio. An embodiment of the structural composite element also provides increased stiffness with higher energy absorbing characteristics during failure by compression, impact, or buckling than conventional materials.
[0012]These and other important aspects of the present invention are described more fully in the detailed description below.
DESCRIPTION OF DRAWINGS
[0013]Embodiments of the present invention are described in detail below with reference to the attached drawing figures, wherein:
[0014]FIG. 1 is a fragmentary isometric cut-away view of a structural composite element with a porous filler material constructed in accordance with an embodiment of the invention;
[0015]FIG. 2 is a cross-sectional view of the porous filler material of the structural composite element of FIG. 1;
[0016]FIG. 3 is a fragmentary isometric cut-away view of the structural composite element of FIG. 1 attached to an attachment fitting;
[0017]FIG. 4 is a fragmentary side elevation view of the structural composite element with a skin shown in phantom to provide a view of the porous filler material and the attachment fitting of FIG. 3; and
[0018]FIG. 5 is a fragmentary, cross-sectional side elevation view of the structural composite element and the attachment fitting of FIG. 3.
[0019]The drawing figures do not limit the present invention to the specific embodiments disclosed and described herein. The drawing figures are not necessarily to scale, emphasis instead being placed upon clearly illustrating the principles of the invention.
DETAILED DESCRIPTION
[0020]The following detailed description of the invention references the accompanying drawings that illustrate specific embodiments in which the invention can be practiced. The embodiments are intended to describe aspects of the invention in sufficient detail to enable those skilled in the art to practice the invention. Other embodiments can be utilized and changes can be made without departing from the scope of the present invention. The following detailed description is, therefore, not to be taken in a limiting sense. The scope of the present invention is defined only by the appended claims, along with the full scope of equivalents to which such claims are entitled.
[0021]FIG. 1 illustrates a structural composite element 10 constructed in accordance with an embodiment of the invention and having a skin 12 and an porous filler material 14. The structural composite element may be used as or incorporated in to a stanchion, strut or other support element of an aircraft, vehicle, or building. In one embodiment, skin 12 may be composed of structural, load bearing materials such as aluminum alloys and other metallic materials such as nickel, Inconel or the like. Alternatively, skin 12 may be composed of a composite such as carbon/epoxy, boron/epoxy, metal matrix composite, or other advanced materials. Carbon/epoxy materials are often advantageous due to the unique structural properties of carbon fiber orientation providing excellent strength properties. The thickness of skin 12 depends upon the material selection and strength criteria. For example, thin skinned components may have skins as thin as a few 0.2 inches or for greater load carrying structures having thickness of 1 to 4 inches.
[0022]As shown in FIG. 1, skin 12 of structural composite element 10 may be formed as a rectangular, hollow beam that encases porous filler material 14. Porous filler material 14 may be composed of various metallic and nonmetallic filler materials such as porous cores. One embodiment utilizes an aluminum metallic porous filler material such as Duocel® aluminum foam manufactured by ERG Materials and Aerospace, Inc. or alternatively, stabilized aluminum foam, ("SAF") manufactured by Cymat, Co. of Canada. These porous filler materials of aluminum foam cores provide a metal skeletal structure wherein the foam contains a matrix of cells and ligaments that are regular and uniform throughout the foam. Various densities of foam, number of pores per inch, are available with each density providing different strength characteristics. Alternatively, metallic porous filler material manufactured by Recemat International of the Netherlands may be used. Recemat International produces porous filler manufactured from alternative metallic materials such as copper, nickel, and a corrosion resistant nickel-chromium alloy. Please note that the materials described above are merely examples, and equivalent materials may be produced by other manufacturers not listed herein without departing from the scope of the invention.
[0023]These porous filler materials or metallic foam cores provide ease of assembly since they may be cut, milled, ground, lapped, drilled and rolled similar to metal. Likewise, metallic porous filler material may be anodized, coated or metal plated for corrosion resistance. The metallic porous filler material can also be brazed to the skin material or adhesively bonded.
[0024]FIG. 2 is a schematic representation of a cross-section of aluminum foam of porous filler material 14 showing open cell 16 and ligament structure 18. Ligament structure 18 creates multiple supports for skin 12. As skin 12 deforms under a load or impact, the load or impact energy is transferred to the ligament structure 18 of porous filler material 14. Under over load conditions or impact, ligament structure 18 fails or crushes resulting in the ligament structure 18 filling open cells 16. This densification process absorbs energy that would otherwise be redistributed to surrounding structure. The collapsing of the cells 16 of porous filler material 14 absorbs the impact energy and prevents or reduces the rebound of composite structural element 10 after compaction. Unlike conventional honeycomb-style filler materials, porous filler material 14 can absorb energy from impacts or compression in any direction. Similarly, under crash conditions that create compressive forces which typically result in buckling of the structure, ligament structure 18 absorbs the energy by collapsing and thereby stops the transfer of energy along skin 12 and reduces the severity of buckling. This advantage increases the crash worthiness of the structure.
[0025]Structural composite element 10 has greater inherent strength provided by porous filler material 14 over hollow beam type structures or those utilizing honeycomb cores. The same or increased strength properties can be realized using lighter weight skins, such as a decreased steel gauge or by material substitution such as aluminum or titanium. Thus, an advantage of the present invention is lighter weight structures having equivalent or increased strength properties.
[0026]Another advantage of open cells 16 of porous filler material 14 is that open cells 16 allow any entrapped moisture to wick away from skin 12, and travel out of the structure. This reduces the risk or effect of environmental corrosion and prolongs the service life of the element.
[0027]Porous filler material 14 also may assist in the manufacturing of the structural composite element. When skin 12 is an epoxy matrix material such as carbon/epoxy, porous filler material 14 may be used as the lay-up tool thereby eliminating the need for a mandrel. Metallic porous filler material 14 may be machined to shape and the carbon/epoxy laid on top of porous filler material 14 for a matched fit. Composite skin 12 may be adhesively bonded after cure or alternatively, adhesive may be applied to porous filler material 14 and composite skin 12 lay-up positioned on porous filler material 14 and the materials co-cured.
[0028]FIGS. 3-5 illustrate an exemplary embodiment of the structural composite element 10, wherein at least one end of the porous filer material 14 may be substantially tapered to a point or a rounded-off nub and may connect with an attachment fitting 20. The attachment fitting 20 may be a clevis fitting as shown, comprising a first flange portion 22, a second flange portion 24, and an interface portion 26 connecting the two flange portions 22,24 in a substantially U-shaped configuration and interfacing with the composite skin 12 and the porous filler material 14.
[0029]The first and second flange portions 22,24 may each have a hole formed therethrough and may be provided with further structural support by at least one brace portion 28,30, connected with at least one of the flange portions 22,24. Additionally, the attachment fitting 20 may comprise a shoulder portion 31 which may be positioned proximate and/or adjacent the brace portions 28,30 between the flange portions 22,24 and the interface portion 26. For example, the shoulder portion 31 may have a chamfered face, such as a 45-degree chamfered face, laterally swept around the attachment fitting 20 which may interface with and/or contact an end portion of the composite skin 12.
[0030]The interface portion 26 may be positioned inward of the composite skin 12 and may cover at least a portion of the tapered end of the porous filler material 14. For example, the interface portion 26 may be shaped to form a cavity 32 at an end opposite the first and second flange portions 22,24, and at least a portion of the tapered end of the porous filler material 14 may be positioned within the cavity 32.
[0031]The interface portion 26 may also have a hole formed therethrough into which a fuse pin 34 may be inserted for connecting the attachment fitting to the composite skin 12. The fuse pin 34 may be a notched fuse pin or any type of fuse pin known in the art and may be inserted through both the composite skin 12 and the interface portion 26 and secured in place.
[0032]The fuse pin 34 may shear off when a predetermined critical load value is applied. Once this happens, the attachment fitting 20 may begin to slide down the structural composite element 10, compressing it. The porous filler material 14 may stabilize the structural composite element 10 from buckling and crippling. Then the brace portions 28,30 and/or the shoulder portion 31 of the attachment fitting 20 may induce a local shear force, pressing into the composite skin 12 and beginning to shred the composite skin 12 as the attachment fitting 20 compresses the structural composite element 10. For example, the chamfered configuration of the shoulder portion 31 may be operable to force the porous filler material 14 to compress to full densification along the structural composite element 10.
[0033]Although the invention has been described with reference to the embodiments illustrated in the attached drawings, it is noted that equivalents may be employed and substitutions made herein without departing from the scope of the invention as recited in the claims.
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