STRUCTURAL MEMBERS CONTAINING VIBRATION DAMPING MECHANISMS AND METHODS FOR MAKING THE SAME

Abstract: Contoured structural members (2) containing vibration damping mechanisms (12) and methods for making the same. The contoured structural members (10) comprise composite or metal materials sandwiching a support or stabilizing structure (6). The contoured structure can be provided by tube rolling (or roll wrapping) the composite or metal materials and the support structure together and then, if necessary, bonding them or connecting them. With a contoured and generally non-flat structure, applications for the structural members (2) of the present invention are nearly limitless. As well, by incorporating a vibration damping mechanism, (12) the structural impact of oscillations caused by varying mechanical loads is diminished.

Description: STRUCTURAL MEMBERS CONTAINING VIBRATION DAMPING MECHANISMS AND METHODS FOR MAKING THE SAME REFERENCES TO RELATED APPLICATIONS This application claims priority from U.S. provisional patent application number 60/216,636, the entire disclosure of which is incorporated herein by reference. FIELD OF THE INVENTION The present invention relates to structural members and methods for making the same, h particular, the present invention relates to metal and composite contoured parts containing a vibration damping material and methods for making the same. BACKGROUND OF THE INVENTION In recent years there has been an increasing emphasis on the use of lightweight materials. One application, for example, has been their use to improve the efficiency of motor vehicles. To that end, the United States Government and the U.S. Council for Automotive Research (USCAR) — which represents Daimler Chrysler, Ford, and General Motors have partnered to form the Partnership for a New Generation of Vehicles (PNGV). One goal of PNGV is to develop technology that can be used to create environmentally friendly vehicles with up to triple the fuel efficiency, while providing today's affordability, performance and safety. For example, PNGV wants to improve the fuel efficiency of today's vehicles from about 28 miles per gallon (mpg) to about 83 pg and a 40-60% decrease in the present curb weight (3200 pounds). One method to improve the fuel efficiency is to decrease the weight of today's vehicles and use lighter weight materials, such as composite materials. The materials used in today's vehicles, such as steel and aluminum, are quite heavy relative to composite materials, but have been necessary to provide sufficient structural properties, including tensile, compression, flexural, interlaminar shear, and in-plane shear strengths and other mechanical and material properties, to meet vehicle design requirements. Many other applications of lightweight materials have been made to supplement or replace the use of heavier structural materials, such as steel, cast iron, and aluminum. These applications include buildings, bridges, recreational vehicles, aerospace, defense, and sporting goods, as well as others. One method to increase the structural properties of materials, particularly the torsional or flexural strength, is to make them in a more structurally efficient form. In one more structurally efficient form, metals — like aluminum and steel — as well as composites have been combined with a supporting structure, such as a honeycomb core material, by sandwiching the honeycomb between panels of the metal or composite. Examples of such combinations have been described in U.S. Patent Nos. 4,291,205, 5,140,913, 5,192,623, 5,635,306, 5,875,593, 5,899,037, 5,006,391, 5,195,779, 5,652,039, 5,834,082, 5,848,767, 5,849,122, and 5,875,609, the disclosures of which are incorporated herein by reference. Such combinations, however, have been generally limited to relatively flat structures. Consequently, the use of such combinations have been quite limited. Moreover, structures formed from such combinations of materials can become unstable because of the oscillations caused by varying mechanical loads, either axial loads, bending and shear loads, or torsional loads. SUMMARY OF THE INVENTION The present invention provides contoured structural members containing vibration damping mechanisms and methods for making the same. The contoured structural members comprise composite or metal materials sandwiching a support or stabilizing structure. The contoured structure can be provided by tube rolling (or roll wrapping) the composite or metal materials and the support structure together and then, if necessary, bonding them or connecting them. With a contoured and generally non-flat structure, applications for the structural members of the present invention are nearly limitless. As well, by incorporating a vibration damping mechanism, the structural impact of oscillations caused by varying mechanical loads is diminished. BRIEF DESCRIPTION OF THE DRAWINGS Figures 1-17 are views of structural members and methods of making the same according to the present invention. Figures 1-17 presented in conjunction with this description are views of only particular — rather than complete — portions of the structural members and methods of making the same. DETAILED DESCRIPTION OF THE INVENTION The following description provides specific details in order to provide a thorough understanding of the present invention. The skilled artisan, however, would understand that the present invention can be practiced without employing these specific details. Indeed, the present invention can be practiced by modifying the illustrated structural member and method and can be used in conjunction with apparatus and techniques conventionally used in the industry. Figure 1 illustrates one contoured structural member — a tubular member with a substantially circular cross-section — according to the present invention. In the context of the present invention, a "contoured" structural member is any shape, size, or configuration where at least one portion of the outer or inner periphery of such member is substantially non-flat, including curved, geometric or irregular. Preferably, the contoured structural members have a closed surface configuration, such as a surface which facilitates their manufacture as explained below, hi the context of the present invention, a "closed" structural member is one having any shape, size, or configuration where at least one portion of the surface (inner and/or outer) of such member is a substantially closed or substantially continuous. Examples of a closed configuration include a tubular, substantially spherical, polygonal, conical, or other similar shape, as well as those illustrated and described herein. The structural members of the present invention may have a cylindrical or a non- cylindrical configuration such as cones, pyramid, pods, hemispheres or spheres. The structural members of the present invention may also have a circular or a non-circular cross-section such as rectangular, square, hexagonal, octagonal, or the like. They may also comprise very irregular, non-closed, substantially planar surfaces. Indeed, the structural members of the present invention could have any complex contoured shape or combination of contoured shapes. The structural members of the present invention are characterized by the fact that they are substantially non-flat and thereby distinguished from known sheet-like cored composite structures. In Figure 1, tubular structural member 2 comprises inner section or portion 4, intermediate section or portion 6, outer section or portion 8, and optional core region 10. Inner portion 4, outer portion 8, and optional core region 10, can be made of any suitable composite or metal material as described below. Intermediate portion 6 is a "cored" structure that both attaches to and supports and/or stabilizes the inner and outer portions. Core region 10 is located in an inner section of structural member 2 and, as described below, is about the size of the substrate or mandrel used in forming the structural member. Core region 10 can be of any suitable size, shape, or configuration depending primarily on the removable mandrel(s) in the manufacturing process used to make structural member 2, the configuration of structural member 2, and the desired end application of structural member 2. Core region 10 may be hollow, but may optionally be partially or completely filled with any desired core material such as foam, plastic, conducting or insulating materials, metals and/or the like. Core region 10 containing the core material may be a structural element. The core material may also be added after structural member 2 is formed, or formed integrally into the structure. If the core material is added after the formation of structural member 2, it may be attached to structural member 2 using an adhesive or other suitable bonding means known in the art. The materials for inner section 4 and outer section 8 can be the same or different materials. Preferably, inner portion 4 and outer portion 8 comprise the same material. In one aspect of the invention, the materials for the inner or outer portions can comprise any suitable metal-containing materials, such as a light or heavy metal or alloys thereof. Suitable light metals include magnesium, aluminum, titanium, zinc, molybdenum, or alloys thereof. Suitable heavy metals include iron, copper, nickel, carbon steel, stainless steel, alloy steel, tin, or alloys thereof. Since metal-containing materials comprise isotropic fibers, which exhibit similar strength characteristics in all directions, one layer of the metal-containing material is sufficient to form the respective inner or outer portion and provide the desired structural characteristics. Additional layers of the metal-containing material, depending on cost and structural considerations, can also be used to give the desired thickness of the inner or outer portion. Indeed, successive layers of , different metal-containing materials may be employed as the inner and/or outer portion. In another aspect of the invention, the materials for the inner or outer portions comprise any suitable composite material. Composites are a mixture or combination, on a macro scale, of two or more materials that are solid in the finished state, are mutually insoluble, and differ in chemical nature. Types of composites include laminar, particle, fiber, flake, and filled composites. Composites, however, often have not had the combination of structural properties mentioned above and/or low cost necessary to promote their wide-spread use in motor vehicle and other applications. Preferably, the composite material is a reinforced resin matrix material (RRMM), which is a resin matrix material (RMM) with continuous or discontinuous reinforcement material embedded in the resin matrix, hi one aspect of the invention, the RMM is a orgamc resin matrix material (ORMM). See, for example, U.S. Patent No. 5,725,920 and 5,309,620, the disclosures of which are incorporated herein by reference. one aspect of the invention, the ORMM can be a thermoset resin. Thermoset resins are polymeric materials which set irreversibly when heated. Examples of thermoset resins include epoxy, bismeleimide, polyester, phenolic, polyimide, melamine, xylene, urethane, phenolic, furan, silicone, vinyl ester, and alkyd resins, or combinations thereof. The thermoset resins can contain various additives as known in the art, such as cross-linking agents, curing agents, fillers, binders, or ultraviolet inhibitors. Preferably, epoxy, vinyl ester, or polyester resins are employed as the thermoset resin in the present invention. hi another aspect of the invention, the ORMM can be a thermoplastic resin matrix material. Thermoplastic resins are polymeric materials which do not set irreversibly when heated, e.g., they soften when exposed to heat and then return to their original condition when cooled. Examples of thermoplastic resins include polypropylene, polyethelene, polyamides (nylons), polyesters (PET, PBT), polyether ketone (PEK), polyether ether ketone(PEEK), polyphenylene sulfide (PPS), polyphenylene oxide (PPO) and its alloys, and polyvinyl resins, or combinations thereof. The thermoplastic resins can contain various additives as known in the art, such as cross-linking agents, curing agents, fillers, binders, or ultraviolet inhibitors. Preferably, polyamides (nylons), polyester, polycarbonate and polypropylene resins are employed as the thermoplastic resin in the present invention. The material used to reinforce the RMM of the present invention can be in any form which reinforces the resin matrix. Examples of reinforcement forms include unidirectional tape, multidirectional tapes, woven fabrics, roving fabrics, matt fabrics, preforms, fibers, filaments, whiskers, and combinations thereof. The type of material used to reinforce the RMM can be any type serving such a reinforcing function. Preferably, the form of the reinforcement materials for the resin matrix is a fiberous material, such as continuous or discontinuous fibers. Examples of materials that can be employed in the present invention include glass-s, glass-e, aramid, graphite, carbon, ultra-high molecular weight polyethylene, boron, silicon carbide, ceramic, quartz, metals, isotropic metals ( aluminum, magnesium and titanium), metal coated organic fibers, CAMP, hybrids of these fibers, or combinations of these fibers. See, for example, U.S. Patent No. 6,117,534, the disclosure of which is incorporated herein by reference. i yet another aspect of the invention, non- or partially-cured composite materials are used as the material for the inner and/or outer sections. Composites are a mixture or combination, on a macro scale, of two or more materials that are solid in the finished state, are mutually insoluble, and differ in chemical nature. Any composites known in the art such as laminar, particle, fiber, flake, and filled composites can be employed in the invention. The non- or partially-cured composite materials are a ORMM (thermoset or thermoplastic resin) reinforced with a continuous fiber. Preferable composite materials used for inner section 4 and outer section 8 include B- stage prepreg materials typically in the form of sheets or laminates, which can be formed by impregnating a plurality of fiber reinforcement tows with a formulated resin. Methods of making B-stage prepreg sheets and the sheets themselves are well known. See, for example, those sheets described in U.S. Patent No. 4,495,017, the disclosure of which is incorporated herein by reference. When cured, prepreg materials are generally stronger and stiffer than metals while providing greater resistance to fatigue, chemicals, wear and corrosion. Preferable reinforcement for prepregs include aramids, glass materials, nickel carbide, silicone carbide, ceramic, carbons and ultra-high molecular weight polyethylene, or a combination thereof. See, for example, U.S. Patent Nos. 4,968,545, 5,102,723, 5,499,661, 5,579,609, and 5,725,920, the disclosures of which are incorporated herein by reference. Carbon, glass, metals and especially isotropic metals like aluminum, magnesium and titanium, metal-coated organic fibers, and aramid fibers, or a combination thereof, can also be employed as the fibers. See, for example, U.S. Patent Nos. 5,601,892 and 5,624,115, the disclosures of which are incorporated herein by reference. Preferably, carbon fibers, glass fibers, or aramid fibers and more preferably Kevlar 29 or 49 fibers are employed in the present invention. The fiber volume in the prepregs may be varied so as to maximize the mechanical, electrical, and thermal properties. See, for example, U.S. Patent No. 5,848,767, the disclosure of which is incorporated herein by reference. High fiber volume parts are stiffer and, in the case of thermally conductive fibers, the parts are more thermally conductive. Fiber volumes in the present invention can range from about 5% to about 95%, and preferably range from about 50% to about 65%. The fibers of the prepregs may be oriented within the prepreg material in any desired direction as known in the art, such as about 0 to about 90 degrees, including equal numbers of fibers balanced in opposing directions. See, for example, U.S. Patent No. 4,946,721, the disclosure of which is incorporated herein by reference. yet another aspect of the invention, sheet molding compounds (SMCs) can be used as the materials for the inner or outer portion. SMCs are sheets made up of B-stage thermoset resin reinforced with a discontinuous fiber. SMCs are fully formulated ORMM compounds having discontinuous fiber reinforcement materials which are typically formed into sheet, ply, or laminate — ithout additional preparation. See, for example, U.S. Patent No. 6,103,032, the disclosure of which is incorporated herein by reference. The resins that can be used in the SMCs of the present invention include any of the thermoset resins listed above. Preferably, polyester vinyl esters or epoxy resins are employed as the resin in SMCs of the present invention. The fibers that can be used in the SMCs of the present invention include any of those listed above. Preferably, glass, carbon, or aramid fibers, and more preferably Kevlar 29 or 49 fibers can be used as the fibers in the SMCs. The fiber volume in the SMC may also be varied so as to maximize the mechanical and thermal properties. With an unsaturated resin system as its base, SMCs incorporate other materials for desirable processing and molding characteristics and optimum physical and mechanical properties, such as mechanical strength, impact resistance, stiffness, and dimensional stability. These incorporated materials include polymers, fibers for reinforcement, resins, fillers, initiators to promote polymerization, viscosity agents, lubricants, mold release agents, catalysts, thickeners, pigments, polyethylene powders, flame retardants, ultraviolet absorbing agents, and other additives. Each of the additives can provide important properties to the SMC, either during the processing or molding steps or in the finished parts, and can be incorporated in the SMCs of the present invention. h one aspect of the invention, inner section 4 and outer section 8 contain at least one layer of such ORMM materials. One layer is sufficient to form the respective inner or outer section and provide the desired structural characteristics for structural member 2. Additional layers can be added to improve the strength, stiffhess, or other physical characteristics of structural member 2. It is possible to use a single layer with fibers having complementary orientations. It is preferred, however, to use a plurality of layers with complementary orientations to balance intrinsic stresses in the layers that make up the sections that result when, as described below, the B-stage materials are fully cured. To be complementary, the fibers in successive layers should be symmetric and balanced (e.g., by having the fibers offset from the sheet axis by equal and opposite amounts from one layer to another) as shown in Figure 2. The fibers can also be oriented to meet the design parameters of the component into which they are being incorporated, e.g., to optimize the structural strength against the expected load. The fibers could be oriented at any suitable angle, including at angles ranging from about 0 to about 90 degrees, including in ±15, ±30, ±45, ±60, and ±75 degrees, or as otherwise known in the art. See, for example, U.S. Patent Nos. Re. 35,081 and 5,061,583, the disclosures of which are incorporated herein by reference. The configuration of inner portion 4 and outer portion 8 can vary within structural member 2. For example, the materials used for the composite, the fiber orientation, and the curvature, thickness, shape and other characteristics of the inner and/or outer portions (4, 8) can differ along the length and width of structural member 2. See, for example, U.S. Patent No. 5,718,212, the disclosure of which is incorporated by reference. Intermediate portion 6 of the structural member 2 of the present invention has any structure which spaces and/or supports inner portion 4 and outer portion 8, as well as enhances the structural properties of those two portions when placed therebetween. Further, intermediate section 6 can be made of any suitable material which separates, supports, stabilizes, couples and attaches inner portion 4 with respect to outer portion 8. Interposing intermediate section 6 between inner section 4 and outer section 8 improves the structural properties according to well- known principles of engineering mechanics and mechanical engineering of structural member 2 over the properties of a member comprising only appropriately shaped inner section 4 and outer section 8 bonded together. Preferably, as illustrated in Figure 1, the intermediate portion is substantially contiguous with the outer surface of inner section 4 and the inner surface of outer section 8, e.g., the intermediate section 6 contacts the inner section 4 and/or the outer section 8 at discrete points over most — if not all — of their surfaces. In one aspect of the present invention, intermediate portion 6 has a ribbed structure (RS), or a structure where any single member (rib) of that structure extends continuously from a location proximate the inner (or outer) portion to a location proximate the outer (or inner) portion, hi another aspect of the invention, the RS is a structure where any rib connects at one end to a location proximate the at least one layer of the inner (or outer) portion and the other ends abuts or connects to another rib. Examples of RSs include corrugated materials, posts, curvilinear materials, honeycomb cores, and the like. These structures, as well as other RSs, are illustrated in Figure 3. A RS is advantageous because, for the additional weight added, the structural properties of the structural member are often substantially increased. The RSs contain both "ribs" and a large volume of voids. The "ribs" of the RS enhance the structural properties of the structural member while the voids are provided to minimize the weight of the RS. The respective amounts of ribs and voids present in the RSs used in the present invention depend on the configuration of the RS selected, e.g., which of those illustrated in Figure 3 is selected. Preferably, the amount of voids should be maximized and the amount of ribs minimized, thereby giving the minimum weight for the maximum strength, provided the necessary (or desired) structural properties of the RS or the structural member is obtained. The RSs employed in the present invention can be incorporated into the structural member in any suitable manner. In one aspect of the invention, the RS can be incorporated as a standalone "rib" extending from the at least one layer of the inner portion to the at least one layer of the outer portion, such as the configurations illustrated in Figure 3. hi another aspect of the invention, the rib can be connected to a supporting sheet(s) or another rib(s) where the sheet(s) or other rib(s) itself is connected to the at least one layer of the inner or outer portion. If desired, additional materials can be incorporated into the ribbed structure. Examples of additional materials that can be incorporated into the RS include be filled with materials other than air, such as resins, foams, insulating materials, or NVH (noise, vibration, or harshness) damping materials, and/or the like. The RS need not be uniform in the structural member. In one aspect of the embodiment, the type of ribs in the RS can vary from location to location. Further, multiples types of RSs can be combined in the at least one layer of the intermediate portion. In another aspect of the invention, the periodicity and/or thickness of the ribs can be changed in different areas of the at least one layer of the intermediate portion, hi another aspect of the invention, the strength and other physical properties of the ribs can change from one location to another. The ribs of the RS can be made of any suitable material which exhibits the desired structural properties. Suitable materials include any material known in the art to provide such a function, including materials having individual cells like beads, corrugated materials, thermoplastic molded materials, honeycomb materials, woods (balsas), and foams such as rigid expanded plastic foams, polymer foams, metal components, flexible metal (i.e., aluminum) foams, or any combination of these materials. See, for example, U.S. Patent Nos. 5,344,038, 4,573,707, 5,562,981, 4,128,963, 4,968,545, and 5,894,045, the disclosures of which are incorporated herein by reference. A preferred intermediate portion 6 may be formed using honeycomb materials (also known as honeycomb cores). These materials usually comprise a thin sheet (or sheets) of material, such as paper or aluminum foil, which is formed into a variety of random or geometric cellular configurations. See U.S. Patent No. 5,876,654, the disclosure of which is incorporated herein by reference. Honeycomb cores, which have a geometric cellular configuration, are known to have structural properties or characteristics that are superior to most foam or solid cores with a comparable density. Honeycomb cores can be made of various shapes and types of materials such as aluminum, aramid materials such as Korex ® , nylon materials such as Nomex ® , plastic, reinforced phenols, carbons, and fiberglass, or a combination thereof. Preferably, honeycombs made of Nomex ® are employed as the material for intermediate portion 6. The material and configuration (width, length, and geometric shape) of the cells can be optimized to provide the desired support and/or stabilization to the inner and outer portions. For example, the cell size can range from about 1/8 to about 3/4 inches, and is preferably about 3/16 inches. The cells of the honeycomb cores can be filled with materials other than air, such as resins, foams, insulating materials, or NVH (noise, vibration, or harshness) damping materials, and/or the like. The type of material used, the thickness, the cell configuration, and "fill-in" material for intermediate portion 6 can vary along the length of structural member 2. The structural member of the present invention may, if desired, have additional layers or portions on the outside of outer portion 8. hi one example, a layer of metal, insulation, another composite material, or honeycomb core material may be placed over outer portion 8. Numerous additional portions or layers, including similar or different composite materials, could be added in a similar manner, hi addition, at least one structural component, such as a bracket, coupler, cap, or the like could be located on the end(s) of structural member 2. The structural member of the present invention may have any substantially non-flat contour or configuration. Figure 4 illustrates several such configurations. The structural members illustrated in Figure 4 differ from the structural member illustrated in Figure 1 in that the cross-section of the tube is not substantially circular. The structural members of the present invention also contain a vibration damping or reducing mechanism. With structural members of the present invention, it may be required to damp out oscillations caused by varying mechanical loads, either axial loads, bending and shear loads, or torsional loads. The vibration damping mechanism would aid in damping out such oscillations. Any suitable vibration damping or reducing mechanism can be employed in the present invention. In one aspect of the invention, a damping layer can be incorporated into the structural member. Thus, as depicted in Fig.12, at least one damping layer 12 can be included in the structural members of the present invention. When included, the at least one damping layer 12 can be incorporated into any part or portion of structural member 2. For example, the at least one damping layer 12 can be adjacent to (when there is only a single layer) or in (when there is a plurality of layers) inner portion 4 and/or outer portion 8. hi another example, the material of the damping layer could be incorporated into or intermixed with the intermediate portion 8. The configuration, material, thickness, and number of layers comprising at least one damping layer 12 are selected for the desired damping ability. The damping layer 12 can have any configuration in the structural member which accomplishes the function(s) discussed above. In one aspect of the invention, the damping layer 12 can be a continuous or substantially continuous layer(s) as illustrated in Figure 12. hi another aspect of the invention, the damping "layer" is not continuous, e.g., it may be substantially contiguous at discrete points with inner and/or outer portion as illustrated in Figure 13. Another example of the non-continuous damping "layer" is illustrated in Figures 14 and 15, where structural member 2 may have sections with a damping material and sections without a damping material. Additional examples of the patterns in non-continuous "layers" are illustrated in Figure 16, which can be configured to dampen the expected vibrations. The thickness of the damping layer can be selected to provide the desired damping effect. To that end, multiple layers can be provided at the same or different locations to give the desired thickness. In a preferred aspect of the invention when the damping layer is substantially continuous, the thickness of the damping layer(s) can range from about 0.002 inch (0.05 mm) to about 0.125 inch (3.175 mm). The damping layer can be made of any suitable material which provides the vibration damping function. Numerous materials offer an efficient means of dissipating or damping the energy associated with such oscillations, such as viscoelastic materials. Examples of viscoelastic materials include any of those known in the art, including rubbers such as butyl rubber or natural rubber, plastics such as polyvinyl chloride (PVC), adhesives of various polymers materials including epoxy-based materials, silicones, or polyurethane. See, for example, U.S. Patent Nos. 5,342,465, 5,250,132, 5,419,416, and 5,655,976, the disclosures of which are incorporated herein by reference. Preferably, 3M™ VHB™ Tape is used as the damping layer(s) in the present invention. The present invention can be made by any suitable process which provides the structure of structural member 2. Suitable process for making the composite layer(s) include any processes known in the art, such as thermoforming, bladder or resin transfer molding, or inflatable mandrel processes, as described in U.S. Patent Nos. 5,225,016, 5,192,384, 5,569,508, 4,365,952, 5,225,016, 5,624,519, 5,567,499, and 5,851,336, the disclosures of which are incorporated herein by reference. Another suitable process is a vacuum bagging process, such as described in U.S. Patent No. 5,848,767, the disclosure of which is incorporated herein by reference. Other suitable processes are a filament winding process or sheet or tube rolling (also known as roll wrapping). See, for example, U.S. Patent Nos. 5,632,940, 5,437,450, 4,365,952, 5,624,529, 5,755,558, 4,885,865, 5,332,606, 5,540,877, 5,840,347, and 5,914,163, the disclosures of which are incorporated herein by reference. In the filament winding process, filaments of the desired material are dispersed in a matrix of binder material and wound about any suitable substrate, such as a mandrel assembly, with a shape generally corresponding to the desired shape (core region 10) of structural member 2. Any suitable mandrel, including those described in U.S. Patent Nos. 5,795,524, 5,645,668, 5,192,384, 5,780,075, 5,632,940, 5,817,203, and 5,914,163, the disclosures of which are incorporated by reference, can be employed in the present invention. The substrate or mandrel must have sufficient strength, desired shape, and be able to withstand the processing conditions for making the structural member. Suitable mandrels include those made of metals like steel and aluminum, polycarbonate, thermoplastic, or RRMM materials. The mandrels may be solid or hollow. The filaments are wound over the mandrel and are reciprocally displaced relative to the mandrel along the longitudinal or winding axis of the mandrel to build portion 4. Additional portions, structures, or layers, such as additional metal or composite layers, can be added as described above or as known in the art. Preferably, the present invention employs a tube rolling (also known as roll wrapping) process for making the structural member of the present invention. One exemplary tube rolling process is illustrated in Figure 5. The tube rolling process employs discrete sheet(s) of the metal- containing material or sheet(s) (or plies or laminates) of the desired composite material rather than filaments. The sheet(s) is interleaved, wrapped, or rolled over a mandrel assembly such as at least one mandrel 20. If desired, a release film can be applied to the mandrel prior to rolling any materials thereon. When more than one sheet is employed, the sheets can be stacked as illustrated in Figure 2 — rior to or during the rolling process — by hand or by any suitable mechanical apparatus, with the fibers of the composite material oriented in the desired orientation. When a continuous metal sheet is used, there is no need for such a stacking operation. After forming inner portion 4, the material comprising intermediate portion 6 is placed, preferably by wrapping or rolling, on inner portion 4 by any suitable human or mechanical apparatus. The roll wrapping process is then resumed to apply the material of outer portion 8. Further details about roll wrapping processes are described in Engineered Materials Handbook, Volume 1: Composites, ASM hitemational, pp. 569-574 (1987), the disclosure of which is incorporated herein by reference. Additional layers or materials can be added over outer portion 8, if desired, in a similar manner or as known in the art. The layers of the individual portions (inner, intermediate, and outer) can be cut and/or patterned such that when roll wrapped, the ends of individual sheet(s) substantially abut when rolled, thereby forming a butt joint 30. Preferably, the butt joint formed by the ends of any single sheet is staggered from the butt joint formed by the ends of an adjacent sheet, as illustrated in Figure 6. Of course, when a continuous metal sheet is rolled, no butt joint occurs. Inner portion 4 and outer portion 8 may be formed using different methods. For example, inner portion 4 can be formed by filament winding and outer portion 8 by roll wrapping, or vice versa. In this aspect of the invention, inner portion 4 may be fully cured prior to the application of intermediate portion 6. Similarly, inner portion 4 and intermediate portion 6 may be applied and cured together prior to the application of outer portion 8. Other methods known in the art, such as those described above, could also be combined with roll wrapping to make the stractural members by performing discrete steps by different methods. For example, inner portion 4 could be formed using the filament winding process, intermediate portion 6 and outer portion 8 could be formed using the roll wrapping process, and then this intermediate structure could be constrained using a vacuum bagging process. If desired, a bonding agent can be placed between successive layers of portions 4, 6, and/or 8. The bonding agent can be placed on selected areas only, or in a pattern such as in rows and/or columns, or over entire areas of the layer(s)/portion(s). Any suitable agent which helps bond the layers and is compatible with all of the processes employed to make structural member 2 can be employed, including glues, curing agents, adhesive materials, or a combination thereof. See, for example, U.S. Patent No. 5,635,306, the disclosure of which is incorporated herein by reference. The bonding agent can be applied by hand or mechanical apparatus prior to, during, or after the assembly of the respective portion on the substrate. Where portions 4, 6, and 8 are successively layed up in an uncured (e.g. B-stage state), the structure has outer portion 8 overlying intermediate portion 6, which overlies inner portion 4, which overlies the mandrel. If necessary to better bond and connect inner portion 4, intermediate portion 6, and outer portion 8 together, the intermediate structure formed by these portions can be constrained. The intermediate stracture can be constrained by applying a suitable compressive force. This can be done using any suitable means including compressive dies or molds, vacuum bagging, or by using a suitable constraining means, e.g., by placing it in a plastic or metal mold, or by applying a suitable shrink-wrap tape(s) 22 or tube made of nylon, silicone, or polypropylene. During the curing process described below, the compressive means (e.g., the shrink-wrap tape or tube) applies suitable compressive force by physical or chemical change so that the materials of structural member 2 contact each other. When the RMM is used in the inner and/or outer portion of the present invention, the compressive force squeezes out excess resin during this curing process. See, for example, U.S. Patent Nos. 5,600,912 and 5,698,055, the disclosures of which are incorporated herein by reference. Moreover, if it is still necessary to better bond and connect the materials in the intermediate structure, they can undergo a suitable chemical reaction. For example, when inner portion 4 and/or outer portion 8 comprise a curable material (e.g., B-stage epoxy prepreg), the intermediate structure can be cured by any suitable means 24, such as an oven curing by applying heat and/or pressure or using an ultraviolet (u.v.) or microwave curing. The necessary heat and/or pressure depend on the size of the mandrel assembly and the materials used in structural member 2. During the curing process, the shrink-wrap tape or tube applies suitable compressive force. When the RMM is used in the inner and/or outer portion of the present invention, the compressive force squeezes out excess resin during this curing process. The above process can be modified for stractural members not having a substantially circular cross-section, including those with outer diameters having at least one flat area or area where the degree of curvature is substantially different from other surfaces of stractural member 2. Examples of such structural members are illustrated in Figure 4. As illustrated in Figure 7, where the outer diameter has at least one relatively flat area, the shrink-wrap material (and accompanying compressive force) applied to the intermediate stracture may not be uniform. Thus, bonding and connecting the materials to one another may not be uniform and, therefore, might impair the integrity of structural member 2. To more uniformly bond and connect such materials, at least one pressure distributor 26 is placed over the relatively flat areas of outer portion 8 prior to applying the shrink-wrap material. The pressure distributors "distribute" the applied compressive force more evenly to such flat areas, allowing a more uniform compressive force to all areas of the intermediate structure. Any suitable shape of pressure distributors which evenly distribute the applied compressive force to the intermediate stracture can be employed in the present invention. Exemplary shapes of the pressure distributors include substantially semicircular shapes (which provide a substantially circular outer surface) and T-shaped distributors where the flat end of the "T" abuts (and matches in size) the flat area of the intermediate stracture and the long-end of the "T" extends outwards. Other shapes and configurations, including single components rather than plural components, could be employed provided they evenly distribute the compressive force over the flat area(s). For the stractural member 2 like the one illustrated in Figure 4, substantially semicircular pressure distributors 26 are depicted in Figure 7. The pressure distributors of the present invention can be made of any suitable material that will maintain its shape when subjected to the compressive force, such as aluminum, steel, and silicone. Preferably, aluminum is employed as the material for the pressure distributor. The shrink-wrap material can be placed under and/or over the pressure distributor(s). The shrink-wrap materials underlying the pressure distributors pressurize the corners, as well as keeping the pressure distributors from sticking to the intermediate structure. The shrink-wrap materials overlying the pressure distributors pressurize the flat areas. The above process can be also be modified for structural members where the inner and outer portion do not have the same shape, such as those depicted in Figure 11. Any suitable process modification which manufactures differently-shaped inner and outer portions can be employed in the present invention. The following two modifications to the above process demonsfrate this concept. Other modifications could be envisioned, even though not demonstrated below. First, the inner portion can have a substantially circular cross-section and the outer portion a non-circular cross-section, hi such an instance, and as shown in Figure 8, the process for making a circular-shaped structural member is followed as described above. To change the shape of the outer portion, a number of pressure distributors are placed over the circular-shaped outer portion prior to the constraining and curing stages. The number of pressure distributors used corresponds to the number of flat sides desired, e.g., four for a square, six for a hexagon, etc... The process as noted above is then continued for the constraining and curing stages. During the constraining and curing process, the circular outer shape is changed to flat sides of the desired polygonal shape by the pressure exerted via the pressure distributors. Second, the inner portion can have a substantially polygonal shape (i.e, square) and the outer portion a substantially circular shape, h this aspect of the invention as depicted in Figure 9, the process for making a square-shaped stractural member is followed as described above. To change the shape of the outer portion, the pressure distributors which are normally placed over the outer portion prior to the constraining and curing stages are omitted. Thus, the square-shaped outer portion is just wrapped with the constraining means. The process as noted above is then continued for the constraining and curing stages. During the constraining and curing process, the outer shape is changed to a substantially circular shape by the pressure exerted via the constraining means. When used, the constraining means are then removed from the intermediate stracture. For the plastic or metal mold, the mold is opened and removed. The shrink-wrap tape or tube may have reacted during the curing process to form a thin shell and, if desired, may be removed by hand or by a mechanical apparatus. When used, the pressure distributors are also removed. hi another aspect of the invention, the constraining means can be left on the outer portion either temporarily or permanently. For example, the shrink-wrap tape could be left on the structural member in the form as a thin shell for protection during shipping and then removed later, hi another example, the shrink-wrap tape could be left on the structural member permanently as a protective coating. Through the constraining and curing processes described above, the inner portion and the outer portion are chemically attached and/or or connected to the intermediate portion. Preferably, the materials of the inner and outer portion both chemically bond to the material of the intermediate portion, thus forming a substantially permanent physical bond. Next, the substrate or mandrel may be removed from structural member 2 to form core region 10. The mandrel may be removed by any suitable process, including any known in the art which safely removes the mandrel without adversely impacting structural member 2, such as those disclosed in U.S. Patent No. 5,900,194 and 5,306,371, the disclosures of which are incorporated herein by reference. If desired, core region 10 can be filled by any desired material as known in the art. The mandrel can be either a removable mandrel or an integral mandrel. A removable mandrel is a mandrel that, as described above, is used in the roll wrapping process and then removed to create interior 10. An integral mandrel is a mandrel which becomes part of structural member 2 and is not removed. Thus, the mandrel remains in core region 10 and becomes a part of structural member 2. When using an integral mandrel, the stractural member 2 and the process for making that member are modified from the above description. In this aspect of the present invention, the intermediate portion is provided over the integral mandrel, and then the outer portion is provided over the intermediate portion. The structural member then follows the processing described above, with the exception that the integral mandrel is not removed. Thus, the integral mandrel can serve as the inner portion. If desired, an inner portion could still be included over the integral mandrel, yielding a stractural member with an integral mandrel, an inner portion, an intermediate portion, and an outer portion. The damping layer 12 can be included in the present invention by any suitable method, including those known in the art. In one suitable manner, the desired materials are made in numerous thin layers and sealed between — or abutted adjacent to — layers of stiffer elastic materials, such as between individual layers of inner portion 4 and outer portion 8. Other methods of including a damping layer in materials, especially composite materials, are known in the art. See U.S. Patent Nos. 5,342,465, 5,250,132, 5,419,416, and 5,655,976, the disclosures of which are incorporated herein by reference. If only one layer is employed for inner portion 4 and/or outer portion 8, then the damping layer is created under or over that single layer. When more than one layer is employed for inner portion 4 and/or outer portion 8, the damping layer can be included between the layers comprising the respective inner or outer portion, hi either case, the damping layer is included by selecting the desired material and then placing, preferably by wrapping or rolling, the damping layer under or over the desired layer of the respective inner and/or outer portion, h one aspect of the invention, the damping layer can be incorporated with the material for the inner, intermediate, or outer portion prior to the rolling operation, allowing the damping layer to be wrapped simultaneously with that portion. If necessary, successive layer(s) of the damping material can be used to make the at least one damping layer 12. When the damping layer 12 is a non-continuous layer, the discontinuity is preferably, although not necessarily, formed in the material prior to the roll wrapping operation. The discontinuity can consist of rows or columns of cutouts of any desired shape and size, as exemplified in Figure 17, in the respective material which have been removed by any suitable process known in the art, such as cutting or stamping. Once formed, the structural members of the present invention can be modified or cut for any desired use. For example, the stractural members illustrated in Figures 5 and 7-9 have been cut in half along its length to provide two stractural members. Likewise, the stractural members could be cut along its length to provide any number of members with the desired length(s). Numerous shapes and configurations can be made using by cutting along any dimension of the stractural members, especially when combined with the broadest aspects of the processes of the present invention. A few examples of such shapes and configurations are shown in Figure 10. If desired, at least one stractural component such as a bracket, fastener, coupler, cap, or the like, could be provided on structural member 2, for example, on the ends thereof. Roll wrapping is the preferred method for making the structural members of the present invention. The other methods described above, however, could be combined with roll wrapping to make the stractural members by, in one aspect of the invention, performing discrete steps by different methods. For example, inner portion 4 could be formed using the filament winding process, the intermediate portion 6 and the outer portion 8 could be formed using the roll wrapping process, and then the intermediate stracture could be constrained using the vacuum bagging process. The stractural member of the present invention has numerous uses such as a tie, torsion- bar, tube, beam, column, cylinder and the like and can be used in numerous industries. Primarily, the stractural member can be used whenever a lightweight, strong, cylindrical object is required. The stractural member of the present invention can be used in the automotive, transportation, aerospace, and defense industries in applications such as airplane components, vehicle components such as tracks, trains, shipping containers, defense-related applications, recreational applications such as bikes, sail masts, shafts for golf clubs and racquets, or commercial applications such as bridges and buildings. The following non-limiting examples illustrate the present invention. Example 1 A hollow, cylindrical stractural member with a circular cross-section was made according to following process. A thin coat of a release material (Frekote 700NC or Axel EM606SL/SP) was applied to a cylindrical aluminum mandrel with a 2.4 inch outer circular diameter and a length of 48 inches. Eight B-stage prepreg laminate sheets containing anisotropic graphite fibers in a B-stage epoxy-based resin were cut with measurements of about 9.3 to about 10.7 inches in width and about 48 inches in length. The sheets each have different widths according to their location in the lay-up on the mandrel. It is preferable to have each layer sufficiently wide to form closely- spaced butt joints when the layer is wrapped around the mandrel. Then, two individual sheets of 3M's Scotchdamp Vibration Control Systems VHB viscoelastic damping material were obtained and cut to dimensions of about 10.6 inches by about 48 inches. The first set of laminate sheets or plies (four plies or two pairs) were overlaid in an overlapping manner so the fibers in successive sheets were symmetric and balanced at angles of ±30 degrees from the longitudinal axis of the mandrel and the butt joints of successive layers did not overlap. A single sheet of the damping material was located between the first and second pair of laminate sheets, yielding a first laminate ply with +30 degree orientation, a second laminate ply with -30 degree orientation, a damping material sheet, a third laminate ply with +30 degree orientation, and a fourth laminate ply with -30 degree orientation. The air between the stacked sheets was removed by using a roller or other suitable device. The stacked prepreg sheets were then roll wrapped by hand around the aluminum mandrel with a butt joint to form inner portion 4. Next, intermediate portion 6, comprising a honeycomb of Hexcel Nomex ® core with hexagonal-shaped cells and a thickness of about 0.15 inches, was measured and cut to dimensions of about 8 inches by about 48 inches. This honeycomb core was then roll wrapped by hand on the first set of stacked prepreg sheets (inner portion 4). The second set of laminate sheets or plies (four plies or two pairs) were overlaid in an overlapping manner so the fibers in successive sheets were symmetric and balanced at angles of ±30 degrees from the longitudinal axis of the mandrel and the butt joints of successive layers did not overlap. The second sheet of the damping material was located between the first and second pair of laminate sheets, yielding a first laminate ply with +30 degree orientation, a second laminate ply with -30 degree orientation, a damping material sheet, a third laminate ply with +30 degree orientation, and a fourth laminate ply with -30 degree orientation. The air between the stacked sheets was removed by using a roller or other suitable device. The stacked prepreg sheets were then roll wrapped by hand around the honeycomb core with a butt joint to form outer portion 8. Next, the resulting intermediate, uncured stracture was shrink-wrapped. One layer of polyethylene-based 150 gauge shrink-wrap tape having a width of approximately 1 inch was roll wrapped by a shrink-wrapping machine. Another layer of 200 gauge nylon-based shrink-wrap tape was then roll wrapped by a shrink-wrapping machine. After this wrapping process, the final stracture was subjected to a curing process at about 250 degrees Fahrenheit for about 120 minutes during which the shrink-wrap tapes applied compressive pressure to the intermediate stracture as it was cured. After this curing process, the shell (formed by the shrink-wrap tapes during the curing process) was removed by hand with a knife. The mandrel was then removed from the center of the tube by hand and the tube was cut to the desired length. Example 2 A hollow, cylindrical structural member with a circular cross-section was made according to following process. A thin coat of a release material (Frekote 700NC or Axel EM606SL/SP) was applied to a cylindrical aluminum mandrel with a 2.4 inch outer circular diameter and a length of 48 inches. Four B-stage prepreg laminate sheets containing anisotropic glass fibers in a B-stage epoxy-based resin were cut with measurements of about 9.3 to about 10.7 inches in width and about 48 inches in length. The sheets each have different widths according to their location in the lay-up on the mandrel. It is preferable to have each layer sufficiently wide to form closely- spaced butt joints when the layer is wrapped around the mandrel. Then, two individual sheets of 3M's Scotchdamp Vibration Control Systems VHB viscoelastic damping material were obtained and cut to dimensions of about 10.6 inches by about 48 inches. The first pair of laminate sheets or plies (two plies) was overlaid in an overlapping manner so the fibers in successive sheets were symmetric and balanced at angles of ±45 degrees from the longitudinal axis of the mandrel and the butt joints of successive layers did not overlap. A single sheet of the damping material was located between the first and second laminate sheets, yielding a first laminate ply with + 45 degree orientation, a damping material sheet, and a second laminate ply with -45 degree orientation. The air between the stacked sheets was removed by using a roller or other suitable device. The stacked prepreg sheets sandwiching the damping sheet were then roll wrapped by hand around the aluminum mandrel with a butt joint to form inner portion 4. Next, intermediate portion 6, comprising a honeycomb of Hexcel Nomex ® core with hexagonal-shaped cells and a thickness of about 0.15 inches, was measured and cut to dimensions of about 8 inches by about 48 inches. This honeycomb core was then roll wrapped by hand on the first pair of stacked prepreg sheets (inner portion 4). The second pair of laminate sheets or plies (two plies) was overlaid in an overlapping manner so the fibers in successive sheets were symmetric and balanced at angles of ±45 degrees from the longitudinal axis of the mandrel and the butt joints of successive layers did not overlap. The second sheet of the damping material was located between the first and second laminate sheets, yielding a first laminate ply with +45 degree orientation, a damping material sheet, and a second laminate ply with -45 degree orientation. The air between the stacked sheets was removed by using a roller or other suitable device. The stacked prepreg sheets were then roll wrapped by hand around the honeycomb core with a butt joint to form outer portion 8. Next, the resulting intermediate, uncured stracture was shrink-wrapped. One layer of polyethylene-based 150 gauge shrink-wrap tape having a width of approximately 1 inch was roll wrapped by a shrink-wrapping machine. Another layer of 200 gauge nylon-based shrink-wrap tape was then roll wrapped by a shrink-wrapping machine. After this wrapping process, the final stracture was subjected to a curing process at about 250 degrees Fahrenheit for about 120 minutes during which the shrink-wrap tapes applied compressive pressure to the intermediate stracture as it was cured. After this curing process, the shell (formed by the shrink-wrap tapes during the curing process) was removed by hand with a knife. The mandrel was then removed from the center of the tube by hand and the tube was cut to the desired length. Example 3 A hollow, cylindrical structural member with a circular cross-section was made according to following process. A thin coat of a release material (Frekote 700NC or Axel EM606SL/SP) was applied to a cylindrical aluminum mandrel with a 2.4 inch outer circular diameter and a length of 48 inches. Four B-stage prepreg laminate sheets containing anisotropic Kevlar fibers in a B-stage epoxy-based resin were cut with measurements of about 9.3 to about 10.7 inches in width and about 48 inches in length. The sheets each have different widths according to their location in the lay-up on the mandrel. It is preferable to have each layer sufficiently wide to form closely- spaced butt joints when the layer is wrapped around the mandrel. Then, two individual sheets of 3M's Scotchdamp Vibration Control Systems VHB viscoelastic damping material were obtained and cut to dimensions of about 10.6 inches by about 48 inches. The first pair of laminate sheets or plies (two plies) was overlaid in an overlapping manner so the fibers in successive sheets were symmetric and balanced at angles of ±15 degrees from the longitudinal axis of the mandrel and the butt joints of successive layers did not overlap. A single sheet of the damping material was located between the first and second laminate sheets, yielding a first laminate ply with + 15 degree orientation, a damping material sheet, and a second laminate ply with -15 degree orientation. The air between the stacked sheets was removed by using a roller or other suitable device. The stacked prepreg sheets sandwiching the damping sheet were then roll wrapped by hand around the aluminum mandrel with a butt joint to form inner portion 4. Next, intermediate portion 6, comprising a honeycomb of Hexcel Nomex ® core with hexagonal-shaped cells and a thickness of about 0.20 inches, was measured and cut to dimensions of about 8 inches by about 48 inches. This honeycomb core was then roll wrapped by hand on the first pair of stacked prepreg sheets (inner portion 4). The second pair of laminate sheets or plies (two plies) was overlaid in an overlapping manner so the fibers in successive sheets were symmetric and balanced at angles of ±45 degrees from the longitudinal axis of the mandrel and the butt joints of successive layers did not overlap. The second sheet of the damping material was located between the first and second laminate sheets, yielding a first laminate ply with +15 degree orientation, a damping material sheet, and a second laminate ply with -15 degree orientation. The air between the stacked sheets was removed by using a roller or other suitable device. The stacked prepreg sheets were then roll wrapped by hand around the honeycomb core with a butt joint to form outer portion 8. Next, the resulting intermediate, uncured stracture was shrink-wrapped. One layer of polyethylene-based 150 gauge shrink-wrap tape having a width of approximately 1 inch was roll wrapped by a shrink-wrapping machine. Another layer of 200 gauge nylon-based shrink-wrap tape was then roll wrapped by a shrink-wrapping machine. After this wrapping process, the final stracture was subjected to a curing process at about 250 degrees Fahrenheit for about 120 minutes during which the shrink-wrap tapes applied compressive pressure to the intermediate stracture as it was cured. After this curing process, the shell (formed by the shrink-wrap tapes during the curing process) was removed by hand with a lαiife. The mandrel was then removed from the center of the tube by hand and the tube was cut to the 3.15" length. The structural member was made with a 2.0" inner diameter, and a 2.78" outer diameter. This stracture was then incorporated into a steering column for a particular automobile. The steering column of this automobile was tested for NVH (Noise Vibration and Harshness) by test driving the automobile. About ten engineers participated in the test drive. All ten engineers had the general feeling that there was a significant reduction in vibration when compared to regular composite-based steering column. Having described the preferred embodiments of the present invention, it is understood that the invention defined by the appended claims is not to be limited by particular details set forth in the above description, as many apparent variations thereof are possible without departing from the spirit or scope thereof.

Claims: CLAIMS 1. A contoured stractural member (2), comprising: a contoured inner layer (4) comprising a metal-containing or composite material; a contoured outer layer (8) comprising a metal-containing or composite material; an intermediate layer (6) having a ribbed stracture connecting the inner layer (4) and the outer layer (8); and vibration damping means. 2. The structural member of claim 1 , wherein the stractural member has a closed configuration. 3. The stractural member of claim 1, the vibration damping means including a damping layer (12). 4. The structural member of claim 3, the damping layer (12) being substantially continuous. 5. The structural member of claim 3, the damping layer (12) being non-continuous. 6. The structural member of claim 3, the damping layer (12) comprising a plurality of damping layers. 7. The structural member of claim 1 , wherein the ribbed structure of the at least one intermediate layer (6) comprises a honeycomb stracture. 8. A contoured structural member (2), comprising: a contoured inner layer (4) comprising a metal-containing material; a contoured outer layer (8) comprising a metal-containing material; an intermediate layer (6) comprising a honeycomb stracture; and vibration damping means. 9. A contoured stractural member (2), comprising: a contoured inner layer (4) comprising a composite material; a contoured outer layer (8) comprising a composite material; an intermediate layer (6) having a ribbed stracture connecting the inner layer (4) and the outer layer (8); and vibration damping means. 10. The structural member of claim 8 or 9, wherein the structural member has a closed configuration. 11. The stractural member of claim 8 or 9, the vibration damping means including a damping layer (12). 12. The structural member of claim 11, the damping layer (12) being substantially continuous. 13. The stractural member of claim 11, the damping layer (12) being non-continuous. 14. The structural member of claim 11, the damping layer (12) comprising a plurality of damping layers. 15. The stractural member of claim 8 or 9, wherein the ribbed stracture of the at least one intermediate layer (6) comprises a honeycomb stracture. 16. A method for making a contoured stractural member (2), comprising: providing an inner layer (4) comprising a metal-containing or composite material; roll wrapping an intermediate layer (6) over the inner layer (4), the intermediate layer (6) having a ribbed stracture; providing an outer layer (8) over the intermediate layer (6), the outer layer (8) comprising a metal-containing or composite material; providing a vibration damping means; and connecting the inner and outer layer (8) to the intermediate layer (6). 17. The method of claim 16, including providing the inner layer (4) by roll wrapping the inner layer (4) over a substrate (20). 18. The method of claim 17, including providing the outer layer (8) by roll wrapping the outer layer (8) over the intermediate layer (6). 19. The method of claim 17, further including removing the substrate (20). 20. The method of claim 16, further including constraining the outer layer (8) when connecting the inner and outer layer (8) to the intermediate layer (6). 21. The method of claim 20, including constraining the outer layer (8) by roll wrapping a shrink-wrap material (22) over the outer layer (8). 22. The method of claim 21, including removing the shrink-wrap material (22) after connecting the inner and outer layer (8) to the intermediate layer (6). 23. The method of claim 16, further including providing at least one pressure distributor (26) over the outer layer (8) prior to connecting the inner (4) and outer layer (8) to the intermediate layer (6). 24. A method for making a contoured structural member (2), comprising: providing an inner layer (4) comprising a composite material; roll wrapping an intermediate layer (6) over the inner layer (4), the intermediate layer (6) having a ribbed structure; providing an outer layer (8) over the intermediate layer (6), the outer layer (8) comprising a composite material; providing a vibration damping means; and connecting the inner (4) and outer layer (8) to the intermediate layer (6). 25. A contoured structural member (2) made by the method comprising: providing an inner layer (4) comprising a metal-containing material; roll wrapping an intermediate layer (6) over the inner layer (4), the intermediate layer (6) having a ribbed stracture; providing an outer layer (8) over the intermediate layer (6), the outer layer (8) comprising a metal-containing material; providing a vibration damping means; and connecting the inner (4) and outer layer (8) to the intermediate layer (6). 26. A contoured structural member (2) made by the method comprising: providing an inner layer (4) comprising a metal-containing or composite material; roll wrapping an intermediate layer (6) over the inner layer (4), the intermediate layer (6) having a ribbed stracture; providing an outer layer (8) over the intermediate layer (6), the outer layer (8) comprising a metal-containing or composite material; providing a vibration damping means; and connecting the inner (4) and outer layer (8) to the intermediate layer (6). 27. A contoured stractural member (2) made by the method comprising: providing an inner layer (4) comprising a composite material; roll wrapping an intermediate layer (6) over the inner layer (4), the intermediate layer (6) having a ribbed structure; providing an outer layer (8) over the intermediate layer (6), the outer layer (8) comprising a composite material; providing a vibration damping means; and connecting the inner (4) and outer layer (8) to the intermediate layer (6). 28. A contoured stractural member (2) made by the method comprising: providing an inner layer (4) comprising a metal-containing material; roll wrapping an intermediate layer (6) over the inner layer (4), the intermediate layer (6) having a ribbed structure; providing an outer layer (8) over the intermediate layer (6), the outer layer (8) comprising a metal-containing material; providing a vibration damping means; and connecting the inner (4) and outer layer (8) to the intermediate layer (6).

Inventors: OBESHAW DALE FRANCIS, OBESHAW, DALE, FRANCIS
Applicants: DELPHI TECH INC, DELPHI TECHNOLOGIES, INC.
Application year: 2001
Main classification: F16C27
IPC codes: B21C37, B29C70, B29D24, B29D31, B32B1, B32B3, B32B15, B32B27, B62D21, B65H75, F16L7, F16L9