AU2004313609B2 - High impact strength, elastic, composite, fibre, metal laminate - Google Patents

Description

P.\OPER\DH\252767p sopal.doc-16/06/05 Keceiveci 1/ June Luu2) HIGH STRENGTH, IMPACT RESISTANT, ELASTIC COMPOSITE LAMINATES Field of the Invention The present invention relates to high impact resistant composite laminate structures. 5 Background of the Invention It is known to utilise physical characteristics of fibre composites to enhance impact resistant properties of, for example, a laminate structure. However, the elastic properties of continuous and unidirectional fibrous composites are highly anisotropic and depend of fibre orientation with respect to the applied stress. The axial tensile 10 strength of a unidirectional lamina is typically controlled by the fibre ultimate strain. The transversal tensile strength of a unidirectional lamina is mainly controlled by the matrix ultimate strain. The strength of a fibre reinforced structure is at least an order of magnitude greater in the longitudinal direction than in the transversal/perpendicular direction to the fibre main axis. 15 Object of the Invention The present invention seeks to provide a new laminate which utilises a composite structure. Summary of the Invention In accordance with the invention, there is provided a high-strength, impact resistant, 20 elastic, fibre composite laminate including at least two inner fibre plies and at least one dissipating element between the inner plies, wherein said at least one dissipating element dissipates and redirects a load applied to the laminate to tensile loading of at least one of said inner plies directed along its longitudinal axis. In another aspect, there is provided a nanostructure including at least two inner fibre 25 plies and at least one dissipating element between the inner plies, wherein said at least sopal.OC.cimLhuon Received 17 June 2005 -2 one dissipating element dissipates and redirects a load applied to the laminate to tensile loading of at least one of said inner plies directed along its longitudinal axis. Preferably, the laminate includes a pair of outer layers and a polymer matrix between each of the plies and the outer layers. 5 In comparison with known structural materials the laminate offers a unique combination of mechanical strength, especially during extreme dynamic loading (impact), with significant weight reduction in comparison with similar samples made from steel or aluminium. Brief Description of the Drawings 10 The invention is described by way of non-limiting example only, with reference to the drawings, in which: Figure 1 is a fragmentary cross-sectional view of a laminate with tubes as dissipating elements. Figure 2 is a fragmentary cross-sectional view of a laminate with corrugated sheet as 15 dissipating elements. Figure 3 is a fragmentary cross-sectional view of a laminate with ornamesh/rigidised form as dissipating elements. Figure 4 is a graph showing the relationship between samples weight and respective impact energy absorbed. 20 Figure 5 is a graph showing weight comparison between samples. Detailed Description of a Preferred Embodiment A laminate structure formed in accordance with the invention represents a new approach in damage tolerant material design philosophy with optional first and second outer face layer for forming an outer face (4), at least two inner plies (2), a dissipating 25 element (1) and usually (dominantly) polymer matrix (3).

P:\OPER\DHMl2527670,sopal.doc-16/06/05 Received 17 June 2005 -3 The dissipating elements may be various metal, non-metal, natural and non-natural structures in a form of, but not limited to: expanded metal, ornamesh, rigidised metal, corrugated sheet, tubular shape, spherical shape, other geometric shapes, ribbed, textured, woven mesh (plain, twill square, holander, micron), and any other similar 5 geometric forms, or other structures having the function of dissipation and redirection of local active outer loading (perpendircular/transversal or impact) applied to at least one of the faces, to tensile loading, of at least one of said inner reinforced plies directed along its longitudinal axis. The outer plies (2) are constructed from a variety of dry or pre-impregnated (prepregs) 10 reinforcement materials such as but not limited to: Glass, Aramid, Carbon, Quartz, Borron, Basalt, Polyurethane, natural, non-natural, and any other single or hybrid fibres, in combination with variety of any known thermosetting and thermoplastic matrixes (3) such, but not limited to: Vinylester, Epoxy, Phenolic, Polypropylene Nylon, Polyester, Amino, Bismaleimides, Polyether, Silicones, Cyanatesters, 15 Polybutadhine, Polyetheramide, Polyimides, fire retardant, corrosion resistant, any sort of adhesives, coatings, pigments, sealants, catalysts, accelerators, diluents, etc. The optional outer face layers (4) may be made from a variety of any metallic, non metallic natural or non-natural materials. The above described laminate structure represents a singular variation of material 20 creation, and there is possibility to apply plurality of plies as described above in any possible direction and combination. Figure 1 illustrates basic principles of internal force-impact energy dissipation and redirection of local active loading (impact) [F] applied to at least one of the two outer faces of the new structure, to longitudinal (tensile) reaction [Fi] in fibre reinforcement 25 plies in a single structure. These forces are forming force equilibrium as shown on Figure 1 show an example of the laminate structure (7) where the Aluminium tubes (1) are used as dissipating elements.

Received 17 June 2005 -4 Figures 2 and 3 show another two examples (single structure) where applied various metal structures (expanded metal, ornamesh, rigidised forms, corrugated sheets), as the dissipated elements (1), can redirect outer active force/impact energy [F] to the face of the structure, to the tensile force/reaction [Fi] in the longitudinal axis of 5 reinforcement plies (2). Figure 3 show very high consistency of impact energy absorbed by Strength, Impact Resistant, Elastic Composite Laminate samples. Figure 4 show significant specific weight reduction of Novel High Strength, Impact Resistant, Elastic Composite Laminate materials in comparison with steel and 10 aluminium. To further expand on the above, to achieve internal active force/impact energy dissipation and redirection in the laminate (Figure 1) various metallic and non metallic structures may be used as dissipating elements including but not limited to: expanded metal, ornamesh, rigidised forms, corrugated sheets, tubular shapes, 15 spherical shapes, weave mesh (plain, twill, square, Hollander, micron) metallic or non-metallic foams, foam like structures and any other similar forms (2), and include but are not limited to one or more elements selected from the following metallic, non metallic, natural and non-natural material groups including but not limited to: aluminium alloys, steel alloys, zinc alloys, titanium alloys, copper alloys, magnesium 20 alloys, nickel alloys, brass alloys, carpenter, gold, silver, platinum, hastelloy, haynes alloy, inconel, molybden alloy, palladium, bronze, tantalum, monel, tungsten, borron, beryllium, zintec, matrix composites, thermoplastics, thermosets, plastics, foams, wood, rubber, paper, ceramics, leather, balsa, cedar, liquids and gases (vacuum) as a single components or compositions. 25 As a result of loading redirection/dissipation, there are now tensile-reactive forces/loadings in at least one of reinforcement plies directed along its longitudinal axes and, based on mechanical properties of fibre reinforcement materials where the tensile strength of reinforcement materials is at least an order of magnitude higher than transversal strength, the result is the significantly higher strength, especially Keceivea Vi June zouLJ -5 impact resistant, novel laminate structure.[MC1] In comparison with already known/existing composite structures whose major disadvantage is brittleness, the laminate can offer high impact resistance with exceptionally high levels of elastic/plastic deformability and high percentage of elastic recovery after plastic 5 deformation. With application of this invention, the impact resistance of the laminate does not depend mainly on the matrix's (3) properties; it is now mainly dependable on the fibre reinforcement's mechanical properties. Specific, desirable properties of new composite structures include: 10 . redirection and dissipation of outer transversal/perpendicular loading/impact to tensile loading along longitudinal axis in reinforcement inner plies, - high impact strength, . high energy-absorbing ability, . high elastic/plastic deformability under impact, 15 . high percentage of elastic recovery during plastic deformation, . low density, - high tensile strength in all directions, - high fatigue resistance and durability, . simple and cost-effective machining and fabricating. 20 Production of a suitable laminate can include all known processes in composite manufacturing such as, but not limited to: hand lay-up, wet lay-up, spray-up, bag moulding, pressure/vacuum bag moulding, match moulding, press moulding, infusion, open moulding, closed moulding, sequentical moulding, continuous moulding, resin transfer moulding, autoclave moulding. 25 The laminate structure is made from cost-effective and standard materials readily available and exhibits significant proven improved mechanical properties in comparison with all existing composite laminates.

- . ~ Received 17 June 2005 -6 With respect to orientation, these internal dissipating elements may be arranged as, but not limited to, unidirectional, cross-ply, symmetric, balanced and quasi-isotropic. As components in the manufacturing of a diverse variety of laminates it is possible to use any known single or hybrid dry or preimpregnated (prepregs) reinforcement fibres 5 that are made from one or more materials selected from the groups consisting of, but not limited to: Glass (E, S, S-2, T, E-CR), Aramid, Carbon/Graphite, Quartz, Ceramic, PBO, Basalt, Boron, Polyethylene, Natural and hybrid fibre reinforcements (2) as, but not limited to: Quadriaxial, Unidirectional, Double-bias, Biaxial, Triaxial, Plain woven, Woven rovings, Braided, Yam, 3 Weave rovings, Chopped strands, Mats, 10 simultaneous stitches with use of any known matrixes (3) but not limited to: Vinylester, Epoxy, Phenolic, Polypropylene Nylon, Polyester, Amino, Bismaleimides, Polyether, Silicones, Cyanatesters, Polybutadhine, Polyetheramide, Polyimides, fire retardant, corrosion resistant, any sort of adhesives, coatings, pigments, sealants, catalysts, accelerators, diluents, etc. 15 With respect to orientation, reinforcement plies may be arranged in a number of ways, including: unidirectional, cross-ply, symmetric, balanced, quasi-isotropic and hybrid laminates. Optional outer face layers (4), whether for protective or decorative purpose, may be one of the metallic, non-metallic, natural and non-natural materials including, but not 20 limited to: aluminium alloys, steel alloys, zinc alloys, titanium alloys, copper alloys, magnesium alloys, nickel alloys, brass alloys, carpenter, gold, silver, platinum, hastelloy, haynes alloy, inconel, molybden alloy, palladium, bronze, tantalum, monel, tungsten, borron, beryllium, zintec, matrix composites, thermoplastics, thermosets, plastics, foams, wood, rubber, paper, ceramics, leather, balsa, cedar. 25 The laminate as their integral components may include structures based on a variety of metallic, non -metallic, natural and non-natural materials such as, but not limited to: aluminium alloys, steel alloys, zinc alloys, titanium alloys, copper alloys, magnesium alloys, nickel alloys, brass alloys, carpenter, gold, silver, platinum, hastelloy, haynes alloy, inconel, molybden alloy, palladium, bronze, tantalum, monel, P:OPER\DH\I252767p sopal.doc-16/06/05 04/001004 Received 17 June 2005 -7 tungsten, borron, beryllium, zintec, matrix composites, thermoplastics, thermosets, plastics, foams, wood, rubber, paper, ceramics, leather, balsa, cedar, liquids and gases (vacuum) as a single components or compositions. Nanostructures may be formed as described above, with substitution of expensive 5 materials such as boron, with materials mentioned, to reduce current high prices and make them widely available to industry, but they are not limited only to these components. As the second stage of fabricating parts/structures with the laminates, it is possible to use most of technologies used in metal and plastics forming processes such as, but not 10 limited to: moulding and stamping, as well as technologies used in cold deformation forming processes such as, but not limited to: blanking, punching, flanging, embossing, bending and drawing. Primary and secondary structures designed, created and manufactured on the basis of the laminate material design philosophy, can be used in the: 15 . aviation industry (civil and military), . space industry (civil and military), . train and rail industry (civil and military), . maritime industry (civil and military), . automotive industry (civil and military), 20 . all sorts of building industry (civil and military), * protective industry/ballistic (civil and military), - construction industry, decoration, machinery, furniture and municipal engineering, road-side safety barriers, and similar, - multiple general applications, 25 . materials developed through nanotechnology. EXAMPLES For example, measured and calculated average properties of laminate sample made from two outer layers of E-Glass quadriaxial woven fibre 1200 gr/m2, one PAOPER\DHMI2527670 sopal.doc-16/06105 Received 17 June 2005 -8 internal/dissipation element: Aluminium Ornamesh Type R, and Vinylester resin DERAKANE 411-350, are: - Tensile Strength a> 1000 MPa, - Density p = 2247 kg / m3, 5 - Peak Impact Force F = 184.3 kN (without penetration), - Impact Energy Absorbed EA = 3985 J (without penetration), - Deflection 41 mm, - Young's modulus of elasticity E = 33 GPa, - Poison's ratio v = 0.33. 10 Density of some High Strength, Impact Resistant, Elastic Composite Laminate design solutions may be significantly reduced to 1600 kg / m3. Table 1. Comparison of selected mechanical properties of materials now in use in the automotive and aviation industries with some of the laminates of the invention. Specific Materials Thickn Specific Weight per Absorbed Absorbed Deformati Peak Force Tensile ess Weight 1m2 Impact Impact on [mm] [kN] Strength [mm] [kg/m3] [kg/m2] Energy Energy/We [MPa] [J ight [J/kg) Aluminium 1.5 2750 4.13 0 0 perforated - 485 Steel 0.8 7850 6.28 0 0 perforated - 655 Steel 1.5 7850 11.78 4272 1453 69 133.4 655 Honey.Comp. 4.3 1220 5.25 - - perforated - Glare-5 2.0 2590 5.18 150 - perforated 10.3 NHSIRECL 1 2.9 2247 6.51 3985 1510 41 184.3 >1000 NHSIRECL 2 5.0 1934 9.67 3778 1108 13 153.9 >1000 NHSIRECL 6 15.2 1304 19.82 3919 688 29 176.0 >1000 DYN 1 - - - 3727 - perforated 91.7 DYN 5 - - - 4100 - perforated 69.9 15 Legend: - Data for Glare-5, "Application of Fibre-Metal Laminates", Polymer Composites, August 2000, [Absorbed Impact Energy (maximum) before Perforation], - Data for DYN 1, and DYN 5 (Structures based on Kevlar reinforcements), form 20 "Impact Testing in Formula One", A. N. Mellor, (Absorbed Impact Energy within displacement of 100 mm) Transport Research Laboratory, Crowthorne, England, ("ICRASH 2002" International Conference, February 2002, Melbourne), - NHSIRECL - Composite Laminates of the invention.

Received 17 June 2005 -9 Samples (Aluminium, Steel and NHSIRECL) were rigorously tested on a controlled drop weight impact tower with an impactor made from solid steel, weighing 45 kg. The impactor head was formed as sphere of diameter 200 mm. Sample dimensions were 500 x 500 mm. The speed of the impactor at the moment of impact was 55 5 km/h. The comparison between Steel sample thickness 1.5 mm and sample NHSIRECL 1 (Table 1), shows that the level of impact energy absorbed by NHSIRECL 1 is 93% of the impact energy absorbed by the Steel sample with 40% lower deflection. At the same time, the weight reduction between NHSIRECL 1 and Steel 1.5 mm is more 10 than 100%. In comparison with Steel 1.5 mm sample, NHSIRECL 2 shows high level of plastic/elastic deformation, superior deflection reduction with significant weight reduction. Deflection of NHSIRECL 2 is only 20% of deflection recorded by the Steel sample, with 88% of impact energy absorbed of these absorbed by the Steel sample. 15 Use of the laminates of the invention delivers highly controlled and predictable behaviour under load, accompanied by: - manufacturing costs can be significantly minimized since known and established manufacturing processes are used; - manufacturing time can be significantly minimized since known and 20 established manufacturing processes are used and manufacturing simplicity; - materials costs can be significantly minimized since already available, cost effective materials are used, . materials costs can be significantly minimized since reduced number of applied reinforcement plies 25 . significant finished-product weight reduction; . demonstrated increases in mechanical properties through its substitution for heavier (steel and aluminium) and more expensive metals; . expected improved fatigue resistance; . low maintenance and repair costs; l'aurtRDHXl252sopaI.doc-16/0605 Received 17 June 2005 -10 . the possibility of innovative cost-saving solutions to design problems now limited by the necessity to use conventional heavier metal sheeting; . the possibility to manufacture complex sections with reduced number of primary parts in an assembly. 5 The desirable properties of the laminates (high strength, high impact resistance, elasticity/plasticity) give their user a unique opportunity to create structures exhibiting easily replicated, tightly controlled behaviour under a wide range of loads, especially under extreme impact loading. The physical properties of the laminates could be widely varied and precisely tailored 10 to the needs of the particular end use application by combining various sorts of materials in large number of permutations for creating new structures. The result of all above mentioned is an opportunity of global implications for the application and further development of high-tech, high-impact strength, elastic/plastic, cost-effective, lightweight products and components for everyday use in 15 manufacturing, transport, packaging and variety of civil and military industry in general. Although particular preferred embodiments of the invention have been disclosed in detail for illustrative purposes, it will be recognised that variations of permutations and modifications of the disclosed invention, including the use of various 20 materials/components in creating the laminate lie within the scope of the present invention.

Claims (60)

1. A high strength impact resistant, elastic, composite laminate including: at least two inner fibre plies between the outer layers, and at least one dissipating element between the inner plies, wherein said at least one dissipating element dissipates and redirects a load applied to the laminate to tensile loading of at least one of said inner plies directed along its longitudinal axis.

2. The laminate according to Claim 1, wherein both inner plies are mainly tensilely loaded, said tensile loading being directed along the respective longitudinal axes of said inner plies.

3. The laminate according to Claim 1 or 2, wherein the at least one dissipating element substantially induces an equilibrium between said load and said tensile loading and a component of said load is redirected along a main fibre axis of said at least one inner ply.

4. The laminate according to any preceding Claim, wherein the at least one dissipating element is made from, but are not limited to, one or more of the following materials: metal, metal alloys, thermoplastics, plastics, polymers, foams, metallic foams, wood and rubber.

5. The laminate according to Claim 4, wherein said metal alloys include, but are not limited to: aluminium alloys, steel alloys, zinc alloys, titanium alloys, copper alloys, magnesium alloys, nickel alloys and alloy matrix composites.

6. The laminate according to any preceding Claim, wherein the at least one dissipating element is in the form of, but not limited to: sheet, corrugated sheet, mesh, tubular shape, spherical shape, foam or other foam-like structure.

7. The laminate according to Claim 4 or 5, wherein the at least one dissipating P:\OPER\DHRI2527670 sopal.do- 16/06/05 Received 17 June 2U 5 - 12 element is in the form of an expanded or rigidised metal.

8. The laminate according to any preceding Claim, wherein the at least one dissipating element has, but is not limited to: cross-ply, unidirectional, symmetric, balanced or quasi-isotropic orientation in the laminate.

9. The laminate according to any preceding Claim, wherein there is a plurality of dissipating elements.

10. The laminate according to claim 9, wherein a ply is formed by two or more of said dissipating elements.

11. The laminate according to claim 10, wherein said ply has, but is not limited to: cross-ply, unidirectional, symmetric, balanced or quasi-isotropic orientation in the laminate.

12. The laminate according to any preceding Claim, wherein one or both of said inner plies are reinforcement plies.

13. The laminate according to Claim 12, wherein one or both of said inner plies are made from single reinforcement fibre or hybrid reinforcement fibre.

14. The laminate according to Claim 13, wherein said single reinforcement fibre is made from one of, but not limited to: glass, aramid and carbon/graphite fibres.

15. The laminate according to Claim 13, wherein said hybrid reinforcement fibre is made from two or more of, but not limited to: glass, aramid and carbon/graphite fibres.

16. The laminate according to any one of claims 12 to 15, wherein said reinforcement fibres are formed as, but not limited to: unidirectional woven fibres, PAOPER\DH\l252767 0sopal.do-16/06105 - 13 biaxial woven fibres, triaxial woven fibres, quadriaxial woven fibres, double-bias woven fibres, plain woven fibres or woven rovings.

17. The laminate according to any one of claims 12 to 16, wherein one or both of said inner plies have, but not limited to: cross-ply, unidirectional, symmetric, balanced, quasi-isotropic or hybrid orientation in the laminate.

18. The laminate according to any one of Claims 12 to 17, wherein there is a plurality of inner plies.

19. The laminate of any preceding Claim, wherein the polymer matrix is made from one or, but not limited to more thermosetting or thermoplastic matrix groups.

20. The laminate according to Claim 19, wherein said polymer matrix is made from one or more of the following, but not limited to: vinyl ester resin, epoxy resin, phenolic resin, polypropylene, nylon, fire retardant resin and corrosion resistant resin.

21. The laminate according to Claim 19 or 20, wherein said polymer matrix includes one or more adhesives.

22. The laminate according to any one of Claims 19 to 21, wherein said polymer matrix includes one or more coatings.

23. The laminate according to any one of Claims 19 to 22, wherein said polymer matrix includes one or more pigments.

24. The laminate according to any one of the preceding claims, wherein the laminate includes a pair of outer layers and a polymer matrix between each of the plies and the outer layers.

25. The laminate according to claim 24, wherein said outer layers are made from Amended Sheet P:\OPER\DH\l2527670 sopal.doc-16/06/05 -14 one or more of the following materials, but not limited to: metal, metal alloys, wood, plastics, rubber, paper, thermoplastics, polymers, foams and rubber.

26. The laminate according to Claim 25, wherein said metal alloys include, but are not limited to: aluminium alloys, steel alloys, zinc alloys, titanium alloys, copper alloys, magnesium alloys, nickel alloys, and alloy matrix composites.

27. The laminate according to any preceding Claim, further including at least one additional layer having, but not limited to: honeycomb, hybrid sandwich or foam structure.

28. The laminate according to Claim 27, wherein said additional layer is made from one or more of, but not limited to, the following materials: metal, wood, rubber, plastics, polymers, paper and thermoplastics.

29. The laminate according to any preceding Claim, wherein said laminate absorbs impact energy from but not limited to 3770 to about 4000 J.

30. The laminate according to any preceding Claim, wherein said laminate absorbs and redirects forces from, but not limited 150 to about 190 kN.

31. .The laminate according to any preceding Claim, wherein said laminate has a density range from, but not limited to 1300 to about 2250 kg/m 3 ,

32. The laminate according to any preceding Claim, wherein said inner plies are made from, but not limited to, E-glass quadriaxial woven fibre, said polymer matrix is substantially made from vinyl ester resin and said at least one dissipating element is an aluminium mesh. PAOPER\DH\2527670 sopal.doc-16/0605 - 15

33. A nanostructure including: at least two inner fibre plies between the outer layers, and at least one dissipating element between the inner plies, wherein said at least one dissipating element dissipates and redirects a load applied to the laminate to tensile loading of at least one of said inner plies directed along its longitudinal axis.

34. The nanostructure according to Claim 33, wherein both inner plies are tensilely loaded, said tensile loading being directed along the respective longitudinal axes of said inner plies.

35. The nanostructure according to Claim 33 or 34, wherein the at least one dissipating element substantially includes an equilibrium between said load and said tensile loading and a component of said load is redirected along a main fibre axis of said at least one inner ply.

36. The nanostructure according to any one of Claims 33 to 35, wherein the at least one dissipating element is made from one or more of the following materials, but not limited to: metal, metal alloys, thermoplastics, plastics, polymers, foams, metallic foams, wood and rubber.

37. The nanostructure according to Claim 36, wherein said metal alloys include, but are not limited to: aluminium alloys, steel alloys, zinc alloys, titanium alloys, copper alloys, magnesium alloys, nickel alloys and alloy matrix composites.

38. The nanostructure according to one of Claims 33 to 37, wherein the at least one dissipating element is in the form of a, but not limited to: sheet, corrugated sheet, mesh, tubular shape, spherical shape, foam or foam-like structure.

39. The nanostructure according to Claim 37 or 38, wherein the at least one dissipating element is in the form, but not limited to expanded or rigidised metal. PAOPER\DH252767p sopal.do-16/06/05 Received 17 June 2005 - 16

40. The nanostructure according to any one of Claims 33 to 39, wherein the at least one dissipating element has, but is not limited to: a cross-ply, unidirectional, symmetric, balanced or quasi-isotropic orientation in the nanostructure.

41. The nanostructure according to any one of Claims 33 to 40, wherein there is a plurality of dissipating elements.

42. The nanostructure according to any one of Claims 33 to 41, wherein one or both of said inner plies are reinforcement plies.

43. The nanostructure according to Claim 42, wherein one or both of said inner plies are made from single reinforcement fibre or hybrid reinforcement fibre.

44. The nanostructure according to Claim 43, wherein said single reinforcement fibre is made from one of , but is not limited to: glass, aramid and carbon/graphite fibre.

45. The nanostructure according to Claim 42 or 43, wherein said hybrid reinforcement fibre is made from two or more of, but not limited to: glass, aramid and carbon/graphite fibres.

46. The nanostructure according any one of Claims 42 to 45, wherein said reinforcement fibres are formed as, but not limited to: unidirectional woven fibres, biaxial woven fibres, triaxial woven fibres, quadriaxial woven fibres, double-bias woven fibres, plain woven fibres or woven rovings.

47. The nanostructure according to any one of claims 33 to 46, wherein one or both of said inner plies have, but are not limited to: a cross-ply, unidirectional, symmetric, balanced, quasi-isotropic or hybrid orientation in the nanostructure.

48. The nanostructure of any one of Claims 33 to 47, wherein the polymer matrix P:OPER\DH\l2527670 sopal.do-16/06/05 Received 17 June 2005 - 17 is made from one or more thermosetting and thermoplastic matrix groups.

49. The nanostructure according to Claim 48, wherein said polymer matrix is made from one or more of the following, but not limited to: vinyl ester resin, epoxy resin, phenolic resin, polypropylene, nylon, fire retardant resin and corrosion resistant resin.

50. The nanostructure according to Claim 48 or 49, wherein said polymer matrix includes one or more adhesives.

51. The nanostructure according to any one of Claims 48 to 50, wherein said polymer matrix includes one or more coatings.

52. The nanostructure according to any one of Claims 48 to 51, wherein said polymer matrix includes one or more pigments.

53. The nanostructure according to any one of claims 33 to 52, wherein the laminate includes a pair of outer layers and a polymer matrix between each of the plies and the outer layers.

54. The nanostructure according to claim 53, wherein said outer layers are made from one or more of the following materials, but are not limited to: metal, metal alloys, wood, plastics, rubber, paper, thermoplastics, polymers, foams and rubber.

55. The nanostructure according to Claim 54, wherein said metal alloys include, but are not limited to: aluminium alloys, steel alloys, zinc alloys, titanium alloys, copper alloys, magnesium alloys, nickel alloys, and alloy matrix composites.

56. The nanostructure according to any one of Claims 33 to 55, further including at least one additional layer having, but not limited to: a honeycomb, hybrid sandwich or foam structure. I UAL"1 V UU I I J U11; LUUJ - 18

57. The nanostructure according to Claim 56, wherein said additional layer is made from one or more of the following materials, but not limited to: metal, wood, rubber, plastics, polymers, paper and thermoplastics.

58. The nanostructure according to any one of Claims 33 to 57, wherein said outer layers are made of, but are not limited to: E-glass quadriaxial woven fibre, said polymer matrix is substantially made from vinyl ester resin and said at least one dissipating element is made from aluminium mesh.

59. A laminate substantially as described with reference to the drawings and/or Examples.

60. A nanostructure substantially as described with reference to the drawings and/or Examples.