MXPA00011128A

MXPA00011128A - Products and method of core crush prevention

Info

Publication number: MXPA00011128A
Application number: MXPA/A/2000/011128A
Authority: MX
Inventors: Scott D Lucas; Robin K Maskell
Original assignee: Cytec Technology Corp; Scott D Lucas; Robin K Maskell
Priority date: 1998-05-22
Filing date: 2000-11-13
Publication date: 2001-09-07

Abstract

Stiffness-treated honeycomb sandwich structures which exhibit reduced core crush and/or reduced void content are provided. Additionally, stiffness-treated prepreg plies which exhibit increased frictional resistance when disposed on other prepreg plies are also provided. Further, associated starting materials and methods are provided.

Description

PRODUCTS AND NUCLEUS CRUSH PREVENTION METHOD BACKGROUND OF THE INVENTION. The invention relates generally to the field of laminated structures and more particularly to methods for making honeycomb interleaving structures and associated products with decreased values of core crush and / or reduced void content. Additionally, the invention relates to starting materials used to assemble these honeycomb interleaving structures. Co-curated honeycomb interleaving structures comprising a honeycomb core and at least one prepreg (i.e., a fabric impregnated with a resin system) placed on each surface of the honeycomb core are used throughout the aerospace industry In order to provide high mechanical strength at low densities. A major problem with honeycomb interleaving structures is the tendency of the honeycomb core to crush during the autoclaving process in manufacturing. This problem is commonly referred to as "core crushing".

Ref. 124718 The crushing of the core during the production of the structures (for example, airplane structures) returns to the useless structure and increases the production costs due to the direct costs of labor, delays and material. It is known that core crushing occurs due to the differential movement during the autoclaving process between the prepreg layers comprising the honeycomb interleaving structure. This differential movement is believed in the industry that possibly occurs late in the autoclave cycle when the viscosity of the resin system is still minimal. Thus, the known methods used to reduce core crushing during the autoclave process have focused on the prevention of differential movement by either mechanical / physical means (i.e. using tie-downs to prevent the pre-impregnated layers from moving. differential) or by a chemical means that focuses on the resin system (i.e., using a quick reaction resin system to allow for an increase in the viscosity of the resin system), or have focused on other parameters of the process autoclave (for example, the resin system used, such as the vacuum levels used for the organization and storage or the internal pressure of post-processing and in situ). See, in general, D.J. Renn, T. Tulleau, J.C. Seferis, R.N. Curran and K.J. Ahn, "Composite Honeycomb Core Crush in Relation to Internal Pressure Measurement," Journal of Advanced Materials, October 1995, p. 31-40 ("The resin system was shown to be the most important parameter in determining core crush"). However, a known mechanical / physical means of core crush reduction can increase production costs due to an increase in labor costs. Additionally, a chemical means known to reduce core crushing that focuses on the resin system or other parameters of the autoclave process has sometimes failed to provide a satisfactory reduction of core crush in known honeycomb interleaving structures. An additional problem associated with honeycomb sandwich structures made by conventional methods is their tendency, in some cases, to break down over time due to the presence of a high content of voids and / or delaminations within and between the pre-impregnated layers of the Honeycomb intercalation structures. This problem is commonly referred to as a "high void content". The high content of holes in the pre-impregnated layers can facilitate the entry of moisture accumulation in the hollows of the pre-impregnated layers. When subjected to elevated temperatures (eg, autoclave conditions), this moisture increases the pressure within the voids in the pre-impregnated layers and extends the size of the voids in the cured structure, resulting. Additionally, the high content of voids in the cured structure provides a route for moisture to enter and accumulate in the core of the structure, thereby adding weight to the structure. The high content of gaps thus tends to shorten the life of the structure and / or increase the unwanted properties (for example, weight) of the structure, and increases production costs due to direct labor costs, delays and material. A known cause of the high void content is the insufficient consolidation of the components of the honeycomb intercalation structure during the autoclave process. The consolidation is known to occur optimally at high pressure (i.e. approximately 7.03 kg / cm2 (100 PSI)) during the high temperature autoclave cycle. The consolidation of the components of a known honeycomb interleaving structure generally occurs at relatively low pressures (i.e., less than about 3.16 kg / cm 2 (45 PSI)) due to high pressures (i.e., greater than about 3.16 kg / cm2 (45 PSI) and up to approximately 5.97 kg / cm2 (85 PSI)) which will intensify the consolidation, will inadvertently cause core crushing in known honeycomb intercalation structures. Thus, the known methods used to reduce the void content have generally focused on resin modifications and prepreg processing techniques to reduce the moisture content and trapped air within the prepreg. These known methods can increase the production costs of honeycomb interleaving structures due to the need to process each honeycomb interleaving structure through at least two autoclave cycles. Additionally, the low consolidation pressure used in these known methods may fail to sufficiently advance consolidation of the pre-impregnated layers with the honeycomb core. As discussed above, the known prepreg layers may have their restricted differential movement to reduce core crush in the honeycomb sandwich structures produced therefrom. Known methods of restricting this differential motion have focused on a mechanical / physical restraint means (ie, using tie-down, or a chemical restriction means that focuses on certain parameters of the autoclave process (eg, resin system). used, vacuum levels used for organization and storage, internal pressure post-processing and in situ) as discussed above, however, as discussed above, these mechanical and chemical restraints can increase production costs due to an increase in labor costs and / or may fail at all times to provide a satisfactory reduction of core crush in known honeycomb interleaving structures The known fabric components of prepreg layers generally consist of fibers that are They have been glued or prepared and / or given or finished. The sizing of the fabric facilitates the weaving of the fibers in a fabric. The fabric finish improves certain known properties of the fabric (e.g., moisture resistance) and certain mechanical properties of the prepreg formed from the finished fabric (for example, tensile strength, resistance to understanding and adhesive characteristics to the honeycomb core in the honeycomb structure). The properties generally associated with the known tissue components of the prepreg are as follows. The commercially available carbon fiber-based fabrics are generally prepared but not finished, with sizing concentrations of 0.5% to 1.5% +/- 0.1% (by weight) depending on the type of weft used and / or the type of final use contemplated and / or the type of sizing used. In contrast, commercially available fiberglass-based fabrics are sizing and then finished. However, the starch based apprehension is substantially removed by baking after weaving the fabric and before the application of the finish. These fiberglass-based fabrics can have finish concentrations of 0.08% to 0.21% +/- 0.018% (by weight) depending on the type of weft used and / or the type of final use contemplated and / or the type of finish used. . For example, commercially available fiberglass-based fabrics made using a proprietary 8-frame raster and patented commercially available finishes from Ciar k-Schwebel ™ (Anderson, SC) (ie, CS 724) or Burlington Glass Fabrics ™ (Alta Vista, VA) (ie, BGF 644, BGF 508, BGF 508A) is believed to have a finish concentration of 0.10% +/- 0.02%. Known (finished) fiber-based fabric components based on a fabric having a weft pattern of 8 linings and a fiber areal weight of 293 +/- 10 g / cm2 generally have a stiffness value of ASTM of less than 3.0 pounds per foot (Ib. Ft). An exception to this general rule is a fiberglass-based fabric finished with F-69 (HexcelMR Corporation, Casa Grande, AZ), which applicants have measured that has an ASTM stiffness value of approximately 9.25 pounds per foot, based on the tests carried out on a sample of a fabric finished with F-69, based on fiberglass, with a frame of 8 garrisons having a fiber areal weight of 2.93 +/- 10 g / m2. Known (sizing) carbon fiber-based fabric components based on a fabric having a flat web and a fiber areal weight of 193 +/- 7 g / m2 generally have an ASTM stiffness value of no more than 3.3 pounds per foot (Ib x ft). The processing associated with the known tissue components of the prepreg layer in general are as follows. Known fiberglass-based tissue components are generally finished by the application of the finish, followed by heat treatment at a temperature in the range of 148.8 ° C (300 ° F) to 176.6 ° C (350 ° C). F). Accordingly, there is a need for new and improved honeycomb interleaving structures exhibiting reduced core crush. Additionally, there is a need for new and improved honeycomb interleaving structures that exhibit reduced void content. Additionally, there is a need for new and better pre-impregnated layers having a restricted differential movement (eg during manufacturing). In addition, there is a need for new and better starting materials for honeycomb sandwich structures exhibiting reduced core crush, honeycomb sandwich structures exhibiting reduced void content, and prepreg layers whose differential movement is restricted to .

BRIEF DESCRIPTION OF THE INVENTION According to the invention, it has been discovered that the ASTM stiffness value of the weave component of the prepregs and the honeycomb structures can influence the differential movement of the prepregs, the value of crushing of core and the content of hollows of honeycomb interleaving structures. Certain ways have been developed to alter the ASTM stiffness value of this tissue component. Therefore, under one aspect of the invention, rigidly treated fabrics comprising a plurality of fibers and polymeric material placed in at least some of the fibers have been developed, wherein the fabric treated in stiffness exhibits an ASTM stiffness value greater than ASTM stiffness value of an untreated fabric. The magnitude of this increase in the stiffness value of ASTM for fabrics treated in stiffness can be defined in terms of percentage (for example, not less than 7%) in absolute terms (for example, not less than 3.4 pounds per foot). In a further aspect of the invention, methods have also been developed for making rigid treated fabrics having an ASTM stiffness value greater than the ASTM stiffness value of an untreated fabric, methods comprising obtaining a fabric comprising a plurality of fibers and polymeric material and / or precursors of polymeric material placed in at least some of the fibers, and treating the fabric under conditions sufficient to produce an ASTM stiffness value of the treated fabric with stiffness greater than the stiffness value of ASTM of an untreated fabric. These conditions include without limitation heat treatment, ultraviolet treatment, and free radical mechanisms and other methods for treating the precursors to advance the formation of the polymeric material and / or chemical bonding of the precursors and / or polymeric materials to the fibers. The heat treatment is presented at treatment temperatures for rigidity improvement and / or during a residence time for the improvement of rigidity, and / or for a temperature-time product of rigidity improvement, and / or in the presence of precursors at a precursor concentration for improving rigidity, and / or in the presence of a heated gas circulation velocity for the improvement of rigidity. Alternatively, the thermal treatment may be presented at lower temperatures while substantially all of the thermal energy generated at lower temperatures is transferred to the materials to be treated in rigidity. In a further aspect of the invention, rigidly treated fabrics having an ASTM stiffness value greater than the stiffness value of ASTM and an untreated fabric made by the above methods have also been developed. In another aspect of the invention, raw materials of the stiffness treated fabric comprising the woven raw material, precursors of the polymeric material placed in at least some of the woven raw material in a precursor concentration of stiffness enhancement have also been developed. and optionally polymeric materials placed in at least some of the fabric raw material. The concentration of the stiffness improving precursor can be measured in terms of an increase in weight percentage or percent concentration (w / w) with respect to precursor concentrations that do not produce increased ASTM stiffness values for the known treatment conditions. In another aspect of the invention, methods have been developed for making raw materials from stiffness treated fabric, which comprises obtaining the raw material from fabric and placing in at least some of the raw material of tissue, 1) precursors of the polymeric material in a precursor concentration of rigidity improvement, and 2) optionally, a polymeric material. Additionally, methods have also been developed for making the raw materials of stiffly treated fabric comprising obtaining the raw material of fabric comprising the precursors of the polymeric material and / or the precursors of the polymeric material placed in at least some of the raw material of fabric, and treating the fabric raw material under selected conditions to return to an ASTM stiffness value of a woven fabric treated in stiffness made from the raw material of fabric treated in stiffness greater than the ASTM stiffness value of an untreated fabric . For example, the treatment may be selected from the group consisting of heat treatment, ultraviolet treatment and free radical mechanisms. In a further aspect of the invention, it has been found that the increased ASTM stiffness value of the invention, of the rigidly treated fabrics made by the treatment process described herein results from one or more of the following optionally present properties. of the fabrics of the invention and / or in tissue raw materials of the fabric of the invention. First, during the treatment a portion of the polymeric material in the tissue or fabric raw materials can be chemically bound to the fibers and / or the fabric raw materials and the advanced numbers of precursors of the polymeric material can develop during the treatment. Second, a portion of the polymeric material can be chemically bound to the fibers and / or the fabric raw materials and can coat the fibers and / or the fabric raw materials to increase the average thickness thereof when compared to the corresponding fibers and / or the raw materials of tissue from an untreated fabric. Third, during the treatment certain components of the fibers (for example yarns or tow and filaments) may have the polymeric material placed on their capillary surface at an average thickness greater than the average thickness of the polymeric material placed on the non-capillary surface thereof. components. In a further aspect of the invention, pretreated layers treated in stiffness comprising a stiff treated fabric and a resin system have been developed. In another aspect of the invention, methods have been developed for making preimpregnated layers treated in stiffness by obtaining a stiff treated fabric and a resin system, and depositing the resin system on the treated fabric in stiffness. In a further aspect of the invention, it has been discovered that the use of the treated fabric in rigidity in the construction of the pre-impregnated layers treated in rigidity allows a greater resistance to friction between a pre-impregnated layer treated in rigidity and any other layer (treated in rigidity or untreated) that the resistance will friction between two untreated pre-impregnated layers. The magnitude of this resistance to friction between a pre-impregnated layer treated in stiffness and any other layer (treated in stiffness or untreated) can be defined as an absolute value (eg 13.62 kg (30) to 90.8 kg (200 pounds) or as a percentage increase with respect to the frictional resistance between two untreated pre-impregnated layers (eg 10% to 600%) In a further aspect of the invention, precursors of honeycomb interleaving structures treated in rigidity have been developed comprising a honeycomb core having a first surface and a pre-impregnated layer treated in stiffness placed on the first surface, wherein the pre-impregnated layer treated in rigidity comprises a resin system and a rigidly treated fabric of the invention. precursors of honeycomb interleaving structures treated in rigidity may additionally comprise at least one additional prepreg layer placed in the first surface, wherein each of the additional prepreg layers may comprise an independently selected resin system and a fabric treated in stiffness, selected, independently or untreated fabric. At least one of the additional prepreg layers and the preimpregnated layer treated in stiffness may optionally extend beyond the first surface of the honeycomb core for lamination during the future processing to convert the precursor to a honeycomb intercalation product. In another aspect of the invention, honeycomb interleaving structures treated in stiffness comprising a honeycomb core having a first surface and a second surface, a first prepreg coated on and extending beyond the first surface have been developed. of a second prepreg positioned on and extending beyond the second surface, wherein a portion of the first prepreg layer extending beyond the first surface contacts a portion of the second prepreg layer that extends further beyond the second surface to form an edge band. Optionally, the additional pre-impregnated layers can be placed on the first surface and / or the second surface "and / or the edge band The first prepreg comprises a resin system and a stiff treated fabric of the invention, the second prepreg layer and each of the optional additional prepreg layers each comprising a resin system independently selected and a tissue independently selected from the fabrics treated in stiffness of the invention or untreated fabrics Optionally, the first prepreg has a high resin content In a further aspect of the invention, methods have been developed for precursors of honeycomb interleaving structures treated in rigidity comprising obtaining an assembled honeycomb interleaving precursor comprising a honeycomb core having a first surface and a first prepreg positioned on the first surface, wherein the first prepreg comprises a resin system and a tissue selected from the treated tissues in stiffness of the invention and treating the assembled honeycomb intercalation precursor under sufficient autoclave conditions to consolidate the assembled honeycomb intercalation precursor. In a further aspect of the invention, methods have been developed for developing a honeycomb interleaving structure treated in rigidity comprising obtaining an assembled honeycomb interleaving comprising a honeycomb core having a first surface and a second surface, a first pre-impregnated layer positioned on and extending beyond the first surface, a second pre-impregnated layer positioned and extending beyond the second surface, wherein a first portion of the first prepreg layer extending beyond the first surface makes contact with a second portion of the second prepreg layer that is beyond the second surface to form an edge band. Optionally, the additional pre-impregnated layers can be placed on the first surface and / or the second surface and / or the edge band. The first prepreg layer comprises a resin system and a fabric selected from the stiff treated fabrics of the invention and the second prepreg layer and each of the optional additional prepreg layers each comprise an independently selected resin system and a tissue treated in independently selected stiffness or an untreated tissue. The assembled honeycomb intercalation is treated under sufficient autoclave conditions to consolidate the assembled honeycomb intercalation. The use of at least one prepreg treated in rigidity in the construction of a honeycomb interleaving structure treated in rigidity enhances certain desirable properties of the honeycomb interleaving structure treated in rigidity. For example, the core crushing value of a honeycomb interleaving structure treated in stiffness is less than a second core crushing value of an untreated honeycomb interleaving structure wherein each prepreg layer of the same is a prepreg layer. not treated. The core crush value of a honeycomb interleaving structure treated in stiffness can be defined as the percentage of the area of the honeycomb interleaving structure exhibiting crushing of a core (eg 0% to 5%) depending on the conditions of selected treatments. For example, the autoclave conditions used to treat an assembled honeycomb interleaving can be selected to produce a core crush value of not more than 3% in the honeycomb interleaving structure treated in stiffness when using a pressure therein ( in the range of about 3.16 kg / cm2 (45 PSI) to 5.97 kg / cm2 (85 PSI)). The pressure in this range is greater than the pressure under which it is believed that an untreated honeycomb core will be consolidated without resulting in a core crush value of more than 3% (i.e., less than 3.16 kg / cm2 (45 PSI)). Due to this increased pressure during consolidation under autoclave conditions, the void content of the honeycomb interleaving structure treated in stiffness is less than that of an untreated honeycomb interleaving structure. The invention has the following advantages. The invention provides honeycomb interleaving structures that are treated in stiffness to exhibit reduced core crush and / or reduced void content, thereby improving the strength, operating weight and / or life of the structures. Additionally, the pre-impregnated layers of the invention, which are treated in rigidity to increase their resistance to friction, have restricted differential movement against other pre-impregnated layers, a feature that reduces the wear caused by peeling during manufacture. The fabrics of the invention are starting materials treated in rigidity for the production of honeycomb interleaving structures exhibiting reduced core crush and reduced void content, and for the preparation of pre-impregnated layers with increased frictional resistance against other pre-impregnated layers. .

BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 illustrates a core sample of machine-drawn honeycomb to form a core crush discriminating panel. Figures 2A and 2B schematically illustrate a core crush panel storage; Figure 2A is a cross-sectional view illustrating a general storage of a pre-laminated structure, and Figure 2B is a top view of the structure. Figure 3 schematically illustrates a packing procedure for the tissue-based honeycomb interleaving structures prior to autoclaving. Figure 4A is a graph illustrating an autoclave cycle for a core crush-discriminating panel of the fiberglass-based honeycomb interleaving structure of the sample, Figure 4B is a graph illustrating an autoclave cycle for a crushing panel for core crushing the structure of I honeycomb interlayer based on sample carbon fiber. Figure 5 illustrates a sample core crush discriminating panel that exhibits a degree of core crushing after the autoclave. Figure 6 schematically illustrates the structure of a typical finishing species for glass fibers, a silane coupling agent. Figure 7 illustrates the chemistry that underlies the formation of chemical bonds between the precursors of the silane coupling agent and the surface of the fiber via hydrolysis and condensation. Figure 8 schematically illustrates the chemistry that underlies the silane coupling agent precursors that form chemical bonds with the surface of the fiber and / or other silane coupling agents (ie, to form the polymeric material) via condensation. Figure 9 schematically illustrates the accumulation of the precursors and / or the polymeric coupling agent in the capillary species between the filaments, which accumulation is caused by thermal treatment. Figure 10 is a graph illustrating the frictional force exhibited between two prepreg layers based on two heat-treated fabrics (ie, Sample 3) of Example 1 at 51.6 ° C (125 ° F). "Figure 11 is a graph illustrating the frictional force exhibited between two prepreg layers based on two heat-treated fabrics (ie, Sample 2) of Example 5 at 79.4 ° C. (175 ° F). Figure 12 is a graph illustrating the frictional force exhibited between two prepreg layers based on two heat-treated fabrics (ie, Sample 1) of Example 5 at 51.6 ° C (125 ° F).

DETAILED DESCRIPTION OF THE PREFERRED MODALITIES According to the invention, rigidly treated fabrics are provided comprising a plurality of fibers, polymeric material placed in at least some of the fibers, and optionally, precursors of polymeric material placed in at least some of the fibers. fibers, wherein the fabrics treated in rigidity exhibit an ASTM stiffness value greater than the ASTM stiffness value of an untreated fabric. The fibers used according to the invention include glass fibers, carbon fibers, aramid fibers, Kevlar ™ fibers, and quartz fibers, each of these fibers can be of variable length and of variable width. The fibers used according to the invention may each comprise a bundle of filaments of varying length and variable width. In this way, the glass beasts can comprise threads, each of the threads comprising a bunch of filament of variable length and variable width. Additionally, the carbon fibers can comprise tows, each of the tops comprises a bunch of filament of variable length and variable width. Additionally the aramid fibers, Kevlar ™ fibers and quartz fibers may each comprise substituent components (including yarns and / or tow and / or filaments and / or the other substituents) of variable length and variable width. The polymeric material useful in the practice of the invention includes derivatives of the precursors of a polymeric material. These derivatives are of the general chemical formula (precursor) n minus the particular leaving groups required for the formation of the applicable derivative of the precursor, wherein n > 2. These derivatives include any of the following species: oligomers, glycidyl ethers, glycidyl amines, ethoxylated species, cross-linked species. { for example, addition products (including without limitation etherification) and condensation products} , species extended in the chain. { for example, addition products (including without limitation etherification) and condensation products} , species bound to hydrogen, species bound to ionic components, reaction species of free radicals and for glass fibers, oxanos and siloxanes and for carbon fibers, species elaborated by basic healing mechanisms (for example, basic reaction products of Lewis, reaction products of inorganic bases, reaction products of primary and / or secondary amines and / or amide reaction products) acid curing mechanism (eg, Lewis acid reaction products, phenol reaction products , reaction products of organic acids and / or reaction products of anhydrides) and olefin reaction products. Finally, these derivatives can be thermoplastic and / or elastomeric materials.

Sufficient conditions to allow the formation of these derivatives of the precursors of the polymeric material are those that advance the polymerization of the precursors of the polymeric material to each other, and include temperature, pressure and other reaction conditions (e.g., pH, presence of amines in variable concentrations, presence of electron withdrawing groups, presence of high energy photons, etc.) that promote the formation of oligomers, formation of glycidyl ether, formation of glycidyl amines, formation of ethoxylated species, formation of species cross-linked, addition reactions (including without limitation etherification), condensation reactions, formation of extended species in the chain, formation of hydrogen-bound species, formation of ionic species, and formation of free radical reaction species. For glass fibers, these conditions include those that promote the formation of oxanos and / or formation of siloxanes. See, for example, Figures 7 and 8. For carbon fibers, these conditions include those that promote basic healing mechanism, (for example, Lewis base reaction products, reaction products of inorganic bases, reaction products. of primary and / or secondary amines, reaction products of amides), acid curing mechanisms (for example, reaction products of Lewis acids, reaction products of phenols, reaction products of organic acids and / or reaction products of anhydrides) and / or olefin reaction mechanisms. These derivatives may have optional, additional properties. For example, most known derivatives associated with the "sizing" of carbon fibers may optionally have an epoxy molecular weight (EEW) of more than m, where m is selected from any variable in the range between about 260 grams equivalent to approximately 5500 grams equivalents, where "epoxy equivalent weight" means the weight (in grams) of the polymeric material that contains 1 gram equivalent of epoxy functionality. It is contemplated within the scope of the invention that these derivatives can be polymerized from precursors at any time up to the time in which a structure incorporating the improved fabric in rigidity has been formed and consolidated, including before or after depositing in the less any of the fibers of the precursors, before or after wetting of the fibers coated with precursor with resin, and before or at the time of consolidation of the fibers impregnated with resin, coated with precursor under autoclave conditions. Preferably, the derivatives are polymerized from the precursors before moistening the tissue in which the precursors can be deposited with an appropriate resin. The precursors of the polymeric material useful in the practice of the invention include chemical agents associated by a particular fiber, chemical agents that are used by those skilled in the art to facilitate the weaving of fibers into a fabric and / or to improve the ability of processing and / or mechanical properties of the fibers, and / or to prevent adsorption of moisture from the fibers. The formation of derivatives (eg, polymerization) based on this chemical agent can be presented by any means known to those skilled in the art, including without limitation a thermal catalyst and / or ultraviolet light and / or free radicals. Although some polymerization and / or formation of derivatives of the chemical agent may have occurred, the polymerization of the chemical agents is not generally taken to term. In addition, the chemical agent, in the non-polymerized form, can have reactive end and / or side groups that allow the chemical agent (i) to polymerize and / or form derivatives with itself, and / or (ii) chemically bind to its associated fibers. In this way, the precursors of a polymeric material associated with the glass fibers are generally known as "finished". The finishes associated with glass fibers may have the general chemical structure of: A3-Si-RB where each A is independently selected from hydrogen, - (CH2) n (where n may vary from 1 to 4), or a hydrolysable function that can comprise any of the following chemical species: -OH, -OCH3, -OCH2CH3 >; -OCH2CH2OCH3, -CH3, -OCH3, -OCH2CH2OH, and -0 (0) CCH3, Si is silicon, R is an alkyl linking group, and may be absent or may comprise any of the following chemical species: ~ (CH2) n (where n can vary from 1 to 7), (NH (CH2) n) a (where a can vary from 1 to 3, and where n can vary from 1 to 4), and S4 (CH2CH2CH2) 2 and B is an organofunctional group, and can comprise any of the following chemical species: -CH3, CH2 = C (CH3) C (0) 0-, (CH2 = CH2) -Ph-CH2- [where Ph is a phenyl ring, and (CH2 = CH2) - Ph- is styrene], CH2-CHCH20-, CH2 = CH, Cl (CH2) n- [where n can vary from 1 to 3], -SH, -NH2, -NH2 (CH2CH2NH) n [where n can vary from 1 to 3], N = C = 0, -NH- (CH2) n-Si-A3 [where n can vary from 1 to 3], NH-C (0) -NH2, -NH-Ph (where Ph is a ring of faith) 0 (See, for example, Figure 6). Alternatively, the finishes associated with glass fibers may comprise the following species: N- (2-aminoethyl) -3-aminopropyltrimethoxysilane, 3-methacryloxypropyltrimethoxysilane, N- (2- (vinylbenzylamino) -ethyl) -3-aminopropyl- trimethoxy silane, 3-glycidoxypropyltrimethoxysilane, vinyltriacetoxysilane, octyltriethoxysilane, methyltriethoxysilane, methytrimethoxysilane, tris- (3- (trimethoxysilyl) propyl) -isocyanurate, vinyltriethoxysilane, vinyltrimethoxysilane, vinyltris- (2-methoxyethoxy) -silane, vinylmethi Idimetoxy si tin, gamma, methacryloxypropyltrimethoxysilane, beta- (3,4-epoxycyclohexyl) et iltrimethoxysilane, gamma-glycidoxypropyltrimethoxysilane, gamma-mereaptopropyl trimethoxy silane, bis- (3- [triethoxysilyl] -propyl) -tetrasulfane, gamma-aminopropyl t-rethoxysilane, aminoalkyl silicone [of the General Formula (H2NCH2CH2CH2SiO? .5) "- (where n may vary from 1 to 3)], gamma-aminopropyltrimethoxysilane, N-bet a- (aminoet il) -gamma, aminopropi ltrimethoxysilane, triamino-functional silane, bis- (gamma-trimethoxysilylpropyl) amine, N-phenyl-gamma-aminopropyltrimethoxysilane, polyazamide-silane (50% in methanol), N-beta- (aminoethyl) -gamma-ami opropylmethi Idimetoxy si tin, gamma -ureidopropyltrialkoxysilane (50% in methanol), gamma-ureidopropyltrimethoxysilane, and gamma-isocyanatopropyltriethoxysilane. Optionally, the finishes associated with glass fibers may comprise chloroalkyl species, in general, with 3-chloropropyl t-rimethoxysilane as an example of these optional finishes. Additionally, the finishes associated with glass fibers may comprise species commercially available from Dow corning ™ (Midland, MI) under the following designations: Z-6020, Z-6030, Z-6032, Z-6040, Z-6075, and optionally Z-6076. Additionally, the finishes associated with glass fibers may comprise the following species commercially available from OSI Specialties (Danbury, CT) under the following designations: A-137, A-162, A-163, A-1230, Y-11597, RC -1, A-151, A-171, A-172, A-2171, A-174, A-186, A-187, A-189, RC-2, A-1289, A-1100, A-1101 , A-1102, A-1106, A-1108, A-1110, A-1120, A-1126, A-1128, A-1130, A-1170, Y-9669, Y-11343, A-1387, A -2120, A-1160, Y-11542 and A-1310. Additional commercially available finishes associated with glass fibers are described in the following publications, the entire contents of each of which is incorporated herein by reference: "A Guide to Dow Corning Silane Coupling Agents," From No. 23- 012C-90 (Available from -Dow CorningMR (Midland, MI)); "Coupling Agents for Textile Applications", From No. 25-343-92 (Available from Dow Corning ™ (Midland, MI)); OSI Specialties, "Organofunctional Silanes", From No. SC-1294 (12-91-15M) (Available from OSI Special ties ™ (Danbury, CT)); OSI Specialties, "Silquest ™ Silanes-Products and Applications", From No. 10-009-20, 6-0499, 10-96-5M (Available form OSI SpecialitiesMR (Danbury, CT)). Additionally, the precursors of a polymeric material associated with carbon fibers are known as "sizing." The sizing associated with carbon fibers is based on bisphenol A, which has the general chemical structure of: Rs N O / \ -CM. CM. CH * 1 Optionally, the presto can characterize polyurethane components derived from toluene-di (isocyanate) (TDl) TDl that have the general chemical structure of: Additionally, the presto can partially polymerize and / or have derivatives (as defined above). ) of the same formed, and may optionally have an epoxy equivalent weight (EEW) of any selected value in the range of from about 260 grams equivalent to about 5500 grams equivalents, where "epoxy equivalent weight" means the weight (in grams) of the polymeric material that contains an equivalent gram of epoxy functionality. Those skilled in the art will be able to identify, in light of the teachings of the invention, additional species of finishes, sizes and precursors suitable for use with the known glass fibers and carbon fibers in the practice of the invention and these finishes Further embodiments are contemplated within the scope of the invention and are hereby incorporated by reference.

Those skilled in the art will also be able to identify, in light of the teachings of the invention, additional species of finishes, sizing and precursors associated with aramid, Kevlar ™, and quartz fibers that can be used in the practice of the invention and these Additional finishes are contemplated within the scope of the invention and are incorporated herein by reference herein. As used herein, " stiffness value" is the stiffness value of a fabric (in pounds or kilograms) as determined by the circular bending process. The circular bending procedure was developed by the American Society for testing and materials (). This circular bending procedure is published in the annual standards book (1996), under the fixed designation D 4032 (published first or revised to the l1994), and under the title "Standard Test Method of Stiffness of Fabric by the Circular Bend Procedure". All portions of the annual book of standards pertinent to this circular bending procedure are hereby incorporated herein by reference.

As used herein, "untreated fabric" means a fabric, which optionally has the same types of fiber, weft and / or precursors of polymeric material as the fiber, weft and / or precursors of the polymeric material of the rigidly treated fabric. with which it is compared. An untreated fabric is a fabric that can comprise fabric raw materials and optionally precursors of polymeric material, wherein the fabric and the raw materials of fabric have not been treated under conditions that advance the polymerization and / or formation of derivatives of the precursors of the polymeric materials to the extent necessary to reduce core crushing to less than 5%, or preferably less than 3%, or more preferably less than 0.1%. These conditions include without limitation (a) treatment with ultraviolet, (b) catalytic treatment with free radicals, (c) dermal treatment, either (i) at treatment temperatures for rigidity improvement, and / or (ii) for a time of residence to the improvement of rigidity, and / or (iii) for a time-temperature product of rigidity improvement, and / or (iv) in the presence of the precursor placed in the fabric and / or the fabric raw material at a precursor concentration of rigidity improvement, and / or (v) in the presence of a heated gas circulation speed of rigidity improvement, and / or (vi) any combination of (i), (ii), ( iii), (iv), and / or (v), and / or (d) any combination of (a), (b) and / or (c). Treatment methods contemplated for use in the invention include ultraviolet treatment (ie, use of high energy photons to promote the polymerization of precursors, free radical treatment mechanisms (ie, use of peroxides to promote polymerization). of precursors) heat treatment and all other methods known to those skilled in the art for advancing the polymerization and / or formation of precursors derivatives of polymeric materials As used herein, "heat treatment" means the treatment of a woven (after weaving), fabric comprising a plurality of woven raw materials and polymeric material and / or precursors of polymeric material placed in the woven raw materials, or the treatment of woven raw materials in which the material polymeric and / or precursors of polymeric material are placed (before weaving) at any temperature in the range of about 100 ° C at the temperature at which the precursors and / or the polymeric material placed in the fabric will begin to degrade (for example up to and exceeding 537. 7 ° C (1000 ° F) for some precursors and / or polymeric materials. Any method known to those skilled in the art can be used to apply heat to the tissue and / or tissue raw materials, including without limitation furnaces, heated fabric or machinery for the production of woven raw material or plates. As used herein, "woven raw materials" means a plurality of fibers and / or yarns (or tow) and / or filaments, each of which may optionally be woven and / or brought into contact to form a woven fabric. gone . The percentage by which (i) the stiffness value of ASTM of the fabric treated in stiffness is greater than (ii) the stiffness value of ASTM of the untreated fabric is determined by taking the difference between the value -in (i) and the value in (ü), divided by the value in (ii), and multiplied by 100%. With respect to fabrics based on fiber and fabrics based on carbon fibers, this percentage is less than 7 •%. and preferably it is not less than 45%. Optionally, with respect to fabrics based on fiberglass, this percentage is not greater than 350% (Table 1). Optionally, with respect to the fabrics based on carbon fiber, this percentage is not higher than 500% (Table 2). The stiffness value of ASTM may vary depending on the type of fiber used in the manufacture of the fabric and / or the conditions under which the fabric is treated. With respect to fabrics based on carbon fibers, the ASTM stiffness value of a fabric treated in stiffness according to the invention is not less than about 3.4 pounds per foot, generally in the range of about 3.1 pounds per foot to 12.0 pounds per foot. For example, the stiffness value of ASTM is preferably within the range that has as a terminal point under any value from about 3.1 to about 6.0 pounds per foot (Ib x ft), and as a higher terminal point any value greater than the point low terminal and from approximately 4.5 pounds per foot to approximately 12.0 pounds per foot. With respect to glass fiber-based fabrics, the stiffness value of ASTM in general is in the range of about 3.0 pounds per foot about 8.1 pounds per foot. Example ranges for the high ASTM stiffness value include a range of about 3.4 pounds per foot to about 7.0 pounds per foot, a preferred range of about 4.0 pounds per foot to about 6.5 pounds per foot, with a currently preferred range of approximately 4.5 pounds per foot at approximately 6.0 pounds per foot. Optionally, the fabric of the invention can have a fiber areal weight of stiffness restriction. As used herein, "fiber areal weight" means the weight in grams / (meter) 2 (g / m2) of the fabric, which fabric is finished in the case of fabrics based on glass fibers and is prepared in the case of fabrics based on carbon fibers. The fiber areal area of a fabric can affect the ASTM stiffness value of this fabric, which may additionally depend on the stretch style used to make the fabric. As used herein, "stiffness restriction fiber areal weight" means a fiber areal weight preferably less than q, where q is a value selected from the range of between about 99 g / m2 and 2000 g / m2 . For fabrics made using the style of 8 weft linings, it is currently preferred that it be a value selected from the range of about 500 g / m2 and 900 g / m2. Fabrics with different weft styles may have different values q, as is easily recognized and identified by those skilled in the art. Additionally, the presently present properties can improve the desirable property of a high ASTM stiffness value for the stiff treated fabric of the invention when compared to untreated fabrics. For example, a portion of the polymeric material placed in the fibers of the fabric treated in the stiffness of the invention can be chemically bound to the fibers and may optionally consist of an essential form of advanced n-mers of precursors of the polymeric material.

As used herein, "chemically linked" means a covalent, ionic or hydrogen bond between two chemical moieties (e.g., between two precursors, between two polymeric materials, and / or between a polymeric material and a precursor) or between a chemical portion (for example, a precursor for a polymeric material) and a fiber. Sufficient conditions to allow a portion of the precursors a portion of the polymeric material to be chemically bound to the fibers during processing include temperature, pressure and other reaction conditions (eg, pH, presence of amines in varying concentrations, presence of removal of electrons, presence of high energy buttons, etc.), sufficient to allow the formation of oligomers, formation of glycidyl ethers, formation of glycidyl amines, formation of ethoxylated species, formation of cross-linked species, addition reactions (including without limitation to etherification), condensation reactions, formation of chain extended species, formation of hydrogen-bound species, formation of ionic species, formation of reaction species of free radicals and for glass fibers, formation of hexanes and formation of siloxanes and for carbon fibers, formation of species that use mecca basic healing units (eg, Lewis base reaction products, reaction products of inorganic bases, reaction products of primary and / or secondary amines, and / or reaction products of amides), acid curing mechanisms ( for example, reaction products of Lewis acids, reaction products of phenols, reaction products of organic acids, reaction products of anhydrides), and / or reaction mechanism of olefins. See, for example, Figure 7. As used herein, "advanced numbers of precursors (of the polymeric material)" means a polymeric material of the general formula (precursor) n minus the particular leaving groups required for the formation of the Applicable derivative of the precursor, wherein n is the number of numbers in the polymeric material and n has a value preferably not less than z, where z is a value within the range of between about 3 and about 100. Preferably, the polymerization proceeds to termination under the treatment in the method of the invention. As used herein, "average n-value" means the value of n, on average, determined as follows. Due to the generally low concentration of the polymeric material, the average value of n for any particular polymeric material can be determined by forming a thin film consisting essentially of a film of less than 1 mm thickness of the precursors of the polymeric material upon removal. substantially all the volatile compounds of a thin layer of solution containing the precursors, thin layers that are placed on an inert substrate, treat the thin film formed in this way and under heat treatment conditions, the temperature and residence time identical to those used to treat tissue whose average N-value needs to be determined, using known titration and measurement techniques to isolate the polymeric material formed in this way and to derive the average weight of this polymeric material, and divide the molecular-weight value of the polymeric material isolated in this way by the value of the pe average molecular weight of the precursor in it to obtain a value for n. Optionally, for short carbon fibers, the value of n can be determined by unwinding a predetermined length of prepared carbon fiber, sizing the predetermined length, substantially removing all precursors and polymeric materials from the sizing of the predetermined length when subjected to reflux the predetermined length for an appropriate time in an appropriate solvent, remove the majority of the solvent and the remainder of the predetermined length of the refluxing solvent to form an oily residue, remove substantially all of the solvent from the oily residue under elevated temperature (e.g. ° C) and reduced pressure (for example, 'substantially less than 1.03 kg / cm2 (14.7 PSI)), and using known potentiometric titration techniques to determine the value of n. As a further example of the optionally present properties that improve the desirable property of a high ASTM stiffness value for the fabric of the invention when comparing untreated fabrics, a portion of polymeric material placed on the fibers of the fabric of the invention it can be chemically bound to the fibers and can coat the fibers to increase the average thickness thereof when compared to the corresponding fibers of an untreated fabric. Optionally, a subset of the fibers of the fabrics of the invention may comprise yarns (or tow) and / or filaments having a capillary surface and a non-capillary surface, with the polymeric material placed on the capillary surface of substantially all of the yarns ( or tow) and / or filaments of the subset which are generally thicker on average than the polymeric material placed on the non-capillary surface of the same yarns (or tow) and / or filaments. The average thickness of the coating of the polymeric material in the fabric raw materials can be affected by one or more of the following factors. The nature of the organofunctional groups in the polymeric material and / or the precursors thereof, the availability of water, the pH, the age of the solution of the polymeric material and / or the solution of precursors thereof as in the date, the solution Applicable is used to coat the raw materials of fabric, the topology of the surface of the raw materials of fabric and / or the presence or absence of certain catalysts. As used herein, "average thickness", when used in the context of the coated fiber (or constituents thereof), can be determined by the average of a plurality of measurements of the thickness of the coated fiber (or, as applicable, constituents of the same. "Measurements are taken at different points on the full length of the fiber (or, as applicable, constituents thereof) Alternatively," average thickness "of the coating of a surface capillary or a non-capillary surface of the coated yarns (or tow) and / or filaments and can be determined by the plurality of measurements of the thickness of the coating on the capillary surface and the coating on the non-capillary surface of the coated yarns (or tow) and / or filaments, measurements taken at different time points on the full length of the same yarns (or tow) and / or filaments The thickness of the fibers (or yarns or towing thereof) can be measure when using an automated electronic micrometer. Alternatively, the thickness of the fibers (or as applicable, yarns, tow or filaments thereof) can be measured using methods known to those skilled in the art. See, for example, S. Sterman, H.B. Bradley, SPI 16th Annual Technology Conference (Reinforced Plastics) (1961); G. Vogel, SPI 22nd Annual Technology Conference (Reinforced Plastics) (1967). For example, these measurements can be taken by preparing sections of electron transmission photomicrographs from the applicable sample of yarn (or tow) and / or filament comprising a polymeric material via known methods (eg, the "replica" method). "for glass fibers), and determine the measurement of the thickness of the fabric raw material and optionally the thickness of both the coating on the capillary surfaces and the coating on the non-capillary surfaces each for the threads (or tow) and / or filaments in the outer covering of the associated bundle. The thickness in relation to the carbon fibers can be measured using methods well known to those skilled in the art (e.g. scanning electron microscopy).

As used herein, "increase in average thickness" means the increase in percentage of (i) the thickness of the coated fiber and / or yarn (or tow) and / or filament having an increased ASTM stiffness value. , when compared to (ii) the thickness of a coated fiber and / or yarn (or tow) and / or filament of a fabric that does not have an increased ASTM stiffness value. This percentage increase is determined by taking the difference between the value in (i) and the value in (ii) in the preceding statement, and divide this difference by the value (i). This increase in percentage is preferably within the range which has as a terminal point under any value between about 5% and about 10% and as a higher terminal point any value greater than the low terminal point and between about 8% and about 20% . The example ranges for the increased value include a range of 7% to 18%, a preferred range of 8% to 16%, with a currently preferred range of 10% to 14%.

% • As used herein, "capillary surface" means the portion of the surface of a first strand, tow or filament, as applicable, of a fiber, which portion is defined by the set of all the points in the fiber. surface of the first thread, tow or filament, as applicable, which are crossed by a straight radial line that crosses both the center of the first thread, tow or filament, as applicable, as some point in the second thread, tow or filament, as applicable, which is part of the same fiber as the first thread, tow or filament, as applicable. As used herein, "non-capillary surface" means that the portion of the surface of a yarn, tow or filament, as applicable, that a fiber that is not the capillary surface of this yarn, tow or filament, as is applicable . The tissues contemplated for use in accordance with the invention are made using methods well known to those skilled in the art, methods including without limitation and without considering any particular order (order that is easily derivable to those skilled in the art, with the order of the steps that is optionally interchangeable), one or more of the following steps: (i) processing or obtaining the fiber, and / or (ii) in the case of fiberglass (and other fibers whose sizing can not be polymerize to increase the stiffness value of ASTM from the fabric made thereon), deposit in the fiber an appropriate size (eg, starch based solution for glass fibers) and / or bake this appropriate size after weaving and / or (iii) deposition in the fiber of precursors of a polymeric material and / or a polymeric material and / or (iv) treatment of the precursors of the polymeric material and / or the polymeric material under co sufficient to promote the polymerization of the precursors with each other and to promote that the polymeric material and the precursors become chemically bound to the fibers. Fibers prepared in this way can be woven under (a) any weft style known to those skilled in the art, including without limitation those weft styles commonly known by the designation of planar weft, raid foot weft, weft pattern of 5 garrisons, raster plot of 8 garrisons, basket plot, 2 by 2 basket plot, log plot, cross plot, 2/2 crossover, 2/1 crossover, no loop pattern, flat plot ± 45, raster plot of 8 garrisons + 45, razo pie razo ± 45 and / or raster plot of 12 garrisons and / or (b) under any fiber arial weight, or otherwise joined to elaborate the fiber. According to the invention, there are further provided methods for making a treated fabric with stiffness having an ASTM stiffness value greater than the ASTM stiffness value of an untreated fabric, which method comprises obtaining a fabric comprising a plurality of woven fabrics. fibers and a polymeric material and / or precursors of a polymeric material placed on the fibers, wherein a portion of the polymeric material and / or the precursors chemically bind to the fibers and treat the fabric under conditions sufficient to produce a fabric treated in rigidity which has an ASTM stiffness value greater than the ASTM stiffness value of a corresponding untreated fabric. Preferably, the ASTM stiffness of the fabric treated in stiffness is not less than 3.4 pounds per foot. Optionally, the portions of the polymeric material and / or the precursors are chemically bound to the fibers and / or other precursors and / or to the polymeric material wherein the derivatives are formed in this way. As examples of these conditions sufficient to produce an ASTM stiffness value of the treated fabric in stiffness greater than the ASTM stiffness value of an untreated fabric, conditions may include without limitation heat treatment, ultraviolet treatment (e.g. of high-energy buttons to promote polymerization of precursors) and treatment with free radicals (for example, use of peroxides to promote the polymerization of precursors). For example, when the treatment method is heat treatment, a rigidity improvement temperature may be employed. As used herein, "treatment temperature and rigidity improvement" means a temperature within the range which has as a terminal point under any value from about 121 ° C (250 ° F) to about 232.2 ° C (450 °) F) and as an upper terminal point any value greater than the low terminal point and from approximately 232.2 ° C (450 ° F) to approximately 371.1 ° C (700 ° F). The ranges of the example for the increased value include the intervals of 232.2 ° C (250 ° F) to 315.5 ° C (600 ° F) and 176.6 ° C (350 ° F) to 260 ° C (500 ° F) with the intervals currently preferred from 176.6 ° C (350 ° F) to 235 ° C (455 ° F) (CS724, BGF644) and 148.8 ° C (300 ° F) to 176.6 ° C (350 ° F) (BGF508A). As a further example of these conditions sufficient to produce an ASTM stiffness value of the treated fabric in stiffness greater than the ASTM stiffness value of an untreated fabric, the fabric can be thermally treated for a residence time of rigidity improvement. during the weaving of the fabric. As used herein, "residence time" means the amount of time the fabric is subjected to the heat treatment. The residence time in general is an inverse function of the linear velocity of the fiber and / or the process line for the faorication of the fabric, and a function of the number of heating sources for the thermal treatment (for example, furnace) as length of the manufacturing process line and the length of each of these heat sources. For example, the residence time of an elaborate fabric in a manufacturing process line that has a linear velocity of 10 yards / minute, with 2 ovens along the line, and a length for each of 10 yards, will be 2 minutes [ie 10 yards / furnace (length of each heating source) X 2 furnaces (number of heating sources) X 1 minutes / 10 yards (linear) = 2 minutes (residence time)]. As used herein, "residence time in rigidity improvement" is generally a residence time within the range which has as a terminal point under any value between about 0.4 minutes and about 720 minutes and as a terminal point higher any value greater than the low terminal point and between approximately 1.2 minutes and approximately 1440 minutes. The example ranges for the increased value include a range of 0.4 to 10 minutes, a preferred range of 0.8 minutes to 5 minutes, with a currently preferred range of 1.2 minutes to 2.5 minutes. As a further example of these conditions sufficient to produce an ASTM stiffness value of the treated fabric in stiffness greater than the ASTM stiffness value of an untreated fabric, the fabric can be heat treated for the time-temperature and improvement product. of rigidity. As used herein, "time-temperature product" means the product of the residence time of the temperature of the heat treatment. In this way, a fabric that is heat treated at 204.4 ° C (400 ° F) for a residence time of 2 minutes will have a time-temperature product of 800 min-° F. As used in this, "temperature-time product of rigidity improvement" is generally a temperature-time product within the range that has as a terminal point under any value between about 200 min-° F and about 1080 min-° F, and as an upper terminal point any value greater than the low terminal point and between approximately 480 min- ° F and 1,008,000 min- ° F. The example ranges for the increased value include the range of 350 min- ° F to 6000 min- ° F, a preferred range of 440 min- ° F to 2500 min- ° F, with a currently preferred range of 544 min- ° F F at 728 min- ° F. As a further example of the conditions sufficient to produce an ASTM stiffness value of the treated fabric in stiffness greater than the ASTM stiffness value of an untreated fabric, the fabric can be heat treated after weaving for a period of time. of rigidity improvement treatment. As used herein, "stiffness improvement treatment time" is generally a time within the range that has as a terminal point under any value between about 2 min and about 30 min, and as a higher terminal point any higher value that the terminal point low and between approximately 30 min and approximately 1440 min.Example intervals for carbon fiber-based fabrics include the value of 2 min to 30 min and preferred ranges of 10 min to 20 min (at varying temperatures). between approximately 204.4 ° C (400 ° F) and 273.8 ° C (525 ° F)), and a range of 60 min to 90 min (approximately 176.6 ° C (350 ° F)) As an additional example of the conditions sufficient to produce an ASTM stiffness value of the treated fabric in stiffness greater than the ASTM stiffness value of an untreated fabric, the fabric can be heat treated in the presence of the precursor at a concentration of improving precursor. stiffness As used herein, "precursor concentration" means the concentration of the precursor placed in the fibers and / or the fabric raw material. This concentration can vary substantially depending on the type of precursor employed, as well as the type of weft in the fabric made from the raw materials of fabric. This concentration can be measured on a percentage basis by weight, a percentage that can be determined when calculating the difference 'between (i) the weight of the fibers after the fibers are coated with the precursors, and (ii) the weight of the uncoated fibers (as determined by weighing a sample of the coated fibers after removal of the coating). by burning the precursors via methods known to those skilled in the art "for example, (loss in the icnition" or LOI method]), and dividing that difference by the value (i). One skilled in the art can contemplate Alternative Means for Calculating the Precursor Concentration As used herein, "stiffness enhancement precursor concentration" is any precursor concentration that is different from (e.g., greater than or less than, those concentrations in the ranges employed. ordinarily and that, depending on the end-use application for which the fabric made from the non-conditioned fabric will be used, it serves to improve (or alternatively, to lower entrances of the precursor, so as not to reduce) the ASTM stiffness value of the fabric. In this way, for end-use applications of glass fiber fabric, where most end-use applications are more interested in increasing rigidity than weight reduction, a precursor concentration of rigidity improvement will be a concentration preferably within the range which has as the terminal point under any value between about 0.13% and about 0.30% and as the upper terminal point greater than the low terminal point and between about 0.17% and about 1.0%. The exemplary ranges for the stiffness enhancement precursor concentration in a fabric having a 8-gield weft with a commercially available finish from Clark-Schwebel ™ (Anderson, SC) includes a range of 0.13% to 0.17 and a range preferred from 0.14% to 0.16% (see Table 1, samples based on type of finishes CS 724). The exemplary ranges for the stiffness enhancement precursor concentration in a fabric having a weft of 8 trim with a commercially available finish from Burlington Glass Fabrics ™ (Alta Vista, VA) includes a range of 0.11% to 0.20% and a preferred range of 0.13% to 0.15%. (See Table 1 samples based on finished type BGF 508A). Alternatively, for end-use applications of carbon fiber fabric, where most end-use applications are more interested in the definition of weight, a strength precursor concentration of stiffness will be a concentration preferably within the range of it has as a terminal point under any value between about 0.05% and about 0.95% and as a terminal point higher than any value greater than the low terminal point and between about 0.10% and about 1.58%. An exemplary range for the stiffness enhancing precursor concentration is about 0.05% to about 0.49%, with a preferred range of about 0.01% to about 0.39%. With respect to the stiffness enhancement striker concentrations that are commercially available, an exemplary range for stiffness improving precursor concentration is about 1.08% to particularly 1.3 percent with a preferred range of about 1.08% to about 1.17% As a further example of sufficient conditions to produce an ASTM stiffness value of the treated fabric in stiffness greater than the ASTM stiffness value of an untreated fabric, the fabric can be heat treated in the presence of a gas velocity heated t rigidity improvement. As used herein, "heated air recirculation rate" means the rate of recirculation and / or filtration of the ambient gas (e.g., air) that is within the volume of the heating source (s) ( for example, oven (s)) used for the thermal treatment of the fabric. This speed is important because the ambient gas surrounding the fabric, when heated by the heating source, can act as a carrier to more efficiently add thermal energy to the fabric. The heated stiffness improving air flow rates contemplated for use in this invention include those circulation speeds that heat the fabric more efficiently (e.g., faster) than those circulation speeds practiced by those skilled in the art during the known processing of comparable fabrics. According to the invention, a stiff treated fabric having an ASTM stiffness value greater than the ASTM stiffness value of an untreated fabric made by a method comprising obtaining a fabric comprising a plurality of fibers is additionally provided. and polymeric material and / or precursors of polymeric material placed in at least some of the fibers, and treating the fabric under conditions sufficient to produce an ASTM stiffness value of the treated fabric in stiffness greater than the ASTM stiffness value of a untreated tissue. Optionally, (e) the fabric treated in rigidity has a stiffness value of ASTM but not less than about 3.4 pounds per foot, and / or (ii) a portion of the polymeric material comprises n-mers. of the precursor, and / or (iii) the polymeric material reviews a portion of the fiber to increase the average thickness of the coated fibers compared to the average thickness of an equal number of corresponding fibers of an untreated fabric. According to the invention, multiple woven raw materials treated in stiffness are additionally provided for a fabric having the desired properties of an ASTM stiffness value greater than that of an untreated fabric, for example an ASTM stiffness value of no less than 3.4 pounds per foot. Examples of these stiff-treated woven raw materials of the invention include stiff-treated woven raw material comprising woven raw material, precursors of polymeric material placed in at least some of the woven raw material in a precursor concentration of stiffness improvement and optionally polymeric material placed in at least some of the fabric raw material.

The optional types of precursor ranges of associated rigidity, optional stiffness and fabric raw material enhancement include (i) the woven raw material which are glass fibers and / or glass threads and / or glass filaments and the stiffness improving precursor concentration which is in the range of 0.25% to 1.0% and / or (ii) the woven raw material which are glass fibers and / or glass threads and / or glass filaments, woven optionally in an 8-frame pattern to form a fabric, the precursors of the polymeric material having either the commercially available finishing formula known as CS 724 finish and the concentration of the stiffness improving precursor which is in the range of 0.13. % to 0.17% or of the formula of a commercially available finish known as BGF 508A finish, and the concentration of the stiffness improving precursor that is in the range of 0.11% to 0.20% and / or (iii) the woven raw material which are carbon fibers and / or carbon yarns and / or carbon filaments and the strength precursor concentration of stiffness which are in the range of 0.10% to 0.39 Optional, additional modes of the raw material of tissue include the following. A portion of the precursors can be chemically linked to a subset of at least some of the tissue raw material. Alternatively, the polymeric material may be present and placed in at least some of the tissue raw material, and a first portion of the precursors and / or the polymeric material chemically bound to the other precursors and / or the polymeric material, thus forming derivatives. Additionally, some of the derivatives and / or polymeric material may comprise advanced n-mers of precursors of the polymeric material, where the advanced n-mers may have an average n-value of not less than 3. The additional examples of raw materials of Rigid treated fabric of the invention include a carbon fiber tow comprising a plurality of filaments and a polymeric material and / or precursors of the polymeric material placed in a portion of the filaments and / or in the tow, wherein a portion of the polymeric material and / or the precursors are chemically bonded to the filaments, tow that has been treated with a treatment selected from the group consisting of heat treatment, ultraviolet light treatment and treatment with free radicals under conditions wherein a stiffness value of ASTM of a woven treated in elaborate stiffness of the tow is greater than the stiffness value of ASTM of a corresponding untreated fabric. According to the invention, methods are further provided for making a raw material of fabric treated in rigidity. This method comprises obtaining raw material from fabric and placing in at least some of the raw material of fabric, 1) precursors of polymeric material in a concentration of stiffness improving precursor and 2) optionally, a polymeric material. An additional method comprises obtaining tissue raw material comprising precursors of polymeric material and / or precursors of polymeric material placed in at least some of the tissue raw material, and treating the raw material of tissue with a treatment selected from the group that consists of thermal treatment, ultraviolet treatment and free radical treatment under selected conditions to produce a woven treated in rigidity made from the raw material of fabric treated in stiffness that has a stiffness value of ASTM that is greater than the stiffness value of ASTM of a non-treated fabric. Examples of fabric raw materials suitable for use in practice in the invention are carbon fibers and / or carbon tows and / or carbon filaments. A portion of the precursors can be chemically linked to a subset of at least some of the tissue raw material. Alternatively, the polymeric material can be present and placed in the fibers, and a first portion of the precursors and / or the polymeric material can be chemically bound to a second portion of the precursors and / or the polymeric material, thereby forming derivatives. Additionally, some of the derivatives and / or the polymeric material may comprise advanced n-mers of precursors of the polymeric material, wherein the advanced n-mers may have an average n-value of not less than 3. According to the invention, pretreated layers treated in stiffness are provided comprising a stiff treated fabric and a resin system placed in a portion of the stiff treated fabric. As used herein, "prepreg" means a fabric impregnated with resin comprising a fabric, fabric comprising 1) a plurality of fibers, 2) a resin system placed in or wetting the fibers, and 3) optionally, a polymeric material and / or precursors of the polymeric material. Resin systems contemplated for use as part of a prepreg include, but are not limited to, thermosetting resins (including, without limitation, epoxy-based resins, polyester resins, phenolic resins, vinyl-ester resins, polysiloxane resins, ester resins, cyanate, bismaleimide resins and thermosetting polyimide resins) and thermoplastic resins (including, without limitation, polyaralkylene ether resins, polyimide resins, poly (phenylsulfide) resins, polybenzimidazole resins, polysulfone resins and liquid crystalline resins. the resin system is not completely cured until after the prepreg has been assembled into a desired structure, e.g. laminated structure, honeycomb interleaving structure), although partial healing (e.g., cure in stage B) prior to this time can improve the processability of the prepreg layer. As used herein, "rigidly treated tissue" means a tissue selected from the group consisting of any of the fabrics treated in rigidity of the invention identified above, tissues made according to any of the methods of the invention identified with Priority for manufacturing fabrics treated in rigidity, fabrics made from any of the raw materials of fabric treated in rigidity of the invention, identified above and fabrics made from any of the raw materials of fabric made according to any of the methods of the invention identified above for making raw materials from fabric treated in rigidity. Optionally, the pre-impregnated layer treated in rigidity, when placed in a second prepreg layer comprising a resin system and a fabric treated in stiffness or in an untreated fabric, exhibits a frictional resistance to movement between the pre-impregnated layer treated in stiffness and the second pre-impregnated layer or untreated fabric greater than the resistance to friction between two untreated pre-impregnated layers placed one on the other, wherein each of the two untreated pre-impregnated layers comprises the resin system and an untreated fabric. The "resistance to friction between two preimpregnated layers" can be measured by any known method, but preferably by a method publicly presented and / or published in 1996 in an article by the authors M. Wilhelm, C.J. Martin and J.C. Seferis and titled "Frictional Resistance of Thermoset Prepregs and ist Influence on Honeycomb Composite Processing" (hereinafter the "Boeing-Wilhelm Method") the complete contents of the article are incorporated herein by reference. This resistance to friction can be measured at any temperature up to the temperature at which the resin curing a is activated. The frictional resistance between two pre-impregnated layers wherein at least one prepreg layer comprises a resin system and a fabric selected from the rigidly treated fabrics can be defined in terms of absolute percent increase. In this way, this value can be in the range that has as the low point any value in the range from approximately 13.62 kilograms (30 pounds) to approximately 79.45 kilograms (125 pounds) and as the high point any value greater than the low point, value that it is in the range of about 22.7 kilograms (50 pounds) to about 79.45 kilograms (175 pounds), as measured using the Boeing-Wilhelm method. Example ranges include 22.7 kilograms (50 pounds) plus 79.45 kilograms (175 pounds), with a preferred range of 79.45 kilograms (75 pounds) to 79.45 kilograms (175 pounds), with a currently preferred interval of 56.75 kilograms (125 pounds) at 68.1 kilograms (150 pounds), for example from about 13.62 kilograms (30 pounds) to about 22.7 kilograms (50 pounds), as measured using the Boeing-Wilhelm method. Alternatively, this value can be any value at less than an increase of 25% with respect to the value of the frictional resistance of two prepreg layers where both prepreg layers comprise untreated fabric. Optionally, this percentage value can be auctioned at approximately 700%. As used herein, "pretreated untreated layer" means a prepreg layer that optionally has the same type of fabric and / or resin system as the fabric and / or resin system of the prepreg layer treated in stiffness with which It compares. An untreated preimpregnated layer is a prepreg layer comprising an untreated fabric and a resin system placed in a portion of the untreated fabric. According to the invention, methods are provided for making a pre-impregnated layer treated in stiffness which comprises obtaining a treated fabric in stiffness and a resin system, and placing the resin system in the treated tissue in rigidity. Optionally, the pre-impregnated layer treated in stiffness made according to these methods, when a second prepreg layer comprising a resin system and a tissue selected from the group consisting of stiff-treated fabrics and untreated fabrics is placed, exhibits a friction resistance between the pre-impregnated layer treated in rigidity and the second pre-impregnated layer greater than the frictional resistance between two untreated pre-impregnated layers placed one on the other, wherein each of the two untreated pre-impregnated layers comprises the resin system and an untreated fabric. According to the invention, precursors of honeycomb interleaving structure treated in rigidity are provided comprising a honeycomb core having a first surface, and a preimpregnated layer treated in stiffness placed on the first surface, wherein the prepreg layer treated in Stiffness comprises a resin system and a tissue selected from fabrics treated in rigidity. Optionally, the honeycomb interleaving structure precursors treated in stiffness (i) may additionally comprise at least one additional prepreg layer placed on the first surface, wherein each of the. Additional prepreg layers comprise an independently selected resin system and a tissue selected independently from the group consisting of rigidly treated fabrics and untreated tissues and / or (ii) may additionally require that at least one prepreg selected from the group consisting of additional prepreg layers and the preimpregnated layer treated in stiffness may extend beyond the first surface of the honeycomb core. According to the invention, honeycomb interleaving structures treated in stiffness comprising a honeycomb core having a first surface and a second surface, a first prepreg positioned on and extending beyond the first surface, are provided. second pre-impregnated layer placed and extending beyond the second surface, wherein a first portion of the prepreg layer extending beyond the first surface contacts a second portion of the second prepreg layer extending beyond the second surface to form an edge band and optionally, pre-impregnated layers. additional layers placed on the first surface and / or the second surface and / or the edge band, wherein the first prepreg layer comprises a resin system and a fabric selected from the stiffly treated fabrics, and wherein the second prepreg layer each of the additional, optional prepreg layers comprise a resin system independently selected from a fabric independently selected from the group consisting of stiff-treated fabrics and untreated fabrics. Optionally, the first preimpregnated layer of the honeycomb intercalation treated in stiffness can have a high resin content. The honeycomb interleaving structures contemplated for use in the invention include interleaving structures comprising (i) a honeycomb core having two surfaces, and (ii) at least two prepreg layers, with at least one of the prepregs laid in place. and / or attached to each of the two surfaces of the honeycomb core. Optionally, an adhesive film can be placed between the honeycomb core and any pre-impregnated layer that makes contact. with the surface of the honeycomb core and comprising carbon fibers. More information on honeycomb intercalation structures can be derived from the article by the authors A. Marshall and entitled "Market and Product Trends in the World Markert for Core Materials", article that was presented at the seminar on intercalation structures of honeycomb in June 1996, the complete contents of this article are hereby incorporated herein by reference. The honeycomb cores contemplated for use in the invention include for example, a core which may comprise (i) about 25% to 75% (by weight) of. Core component selected from the group consisting of aromatic polyamide (aramid) polymer fiber (commonly known as Nomex ™ paper), glass stones, asbestos fibers, Kraft paper fibers, Kevlar ™ fibers, carbon fibers, thermoplastic film and foam (including without limitation polyurethane-based foams, polyimide-based foams and polyvinylchloride-based foams), core component that can be optionally processed to form a plurality of nodes in the core component, and (ii) optionally about 25 % to 75% (by weight) of an epoxy adhesive and / or a phenolic resin coating placed on the core bearing. Alternatively, the core may comprise (i) about 30% to 90% (by weight) the core component selected from the group consisting of aluminum sheets, stainless steel sheets, titanium sheets, copper sheets , lead sheets and inconel sheets, core component that can be processed to form a plurality of nodes in the core component, and (ii) eptionally about 10% to 70% (by weight) of an epoxy adhesive and / or a coating of a phenolic resin placed in the core component. The epoxy adhesive and / or the phenolic resin coating (i) act to join the nodes together and / or (ii) serve as a moisture barrier, and / or (iii) serve as a fire retardant. The nodes form the walls of the honeycomb cell, cells that can have the following example forms. Hexagonal cell (which may be optionally overextended, underextended or reinforced via the optional presence of a flat bisector through the hexagon) and formed cells known as flexible core cells, double flexible core cells, variable cell, iso-core cell, and micro-cell. Additional forms of the honeycomb core cell (for example, polygons, ellipses circles, shapes honeycomb interleaving wherein each prepreg layer constituting the same is an untreated prepreg layer. Optionally, a honeycomb interleaving structure treated in stiffness according to the invention may have less void content compared to an untreated honeycomb interleaving structure. Optionally, a honeycomb interleaving structure treated in stiffness according to the invention may have less "void content" compared to an untreated honeycomb intercalation structure As used herein, "void content" means microscopic voids. and macroscopic, or delaminations, between fibers, threads (or tow) and / or filaments, voids or delaminations that may occur between fibers, yarns (or tow) and / or filaments of different pre-impregnated layers (known as "delaminations / voids"). between layers ") and / or between fibers, yarns (or tow) and / or filaments of the same prepreg (known as" delaminations and / or interlayer voids "). The void content is measured using numerous methods known to those skilled in the art, including without limitation the common method. known and / or practiced as the method of "optical fiber area measurement", under the method of measuring optical fiber area, a plurality of cross sections of the honeycomb interleaving structure portions are obtained; the cross section having the visually apparent void content, the higher is selected from the plurality by visual inspection, and the cross section (s) are scanned by a photomicroscope, with the resulting scan being subjected to the analysis based on a computer program for determining the void content, the resin content and the fiber content of the cross section based on a percentage of the area of this content with respect to the total cross-sectional area scanned In accordance with the invention, methods for making a honeycomb interleaving structure precursor treated in stiffness comprising obtaining an integer precursor are provided. assembly of assembled honeycomb comprising a honeycomb core having a first surface, and a first prepreg positioned on the first surface, wherein the first prepreg comprises a resin system and the tissue selected from fabrics treated in the stiffness and treating the assembled honeycomb intercalation precursor under sufficient autoclave conditions to consolidate the honeycomb intercalation precursor, assembled. The honeycomb interleaving structures contemplated for use in accordance with the invention are made using methods well known to those skilled in the art, methods that include, without limitation and with respect to any particular order (order that can be easily identified by those skilled in the art) the following optional steps: prepare or obtain a fabric, fabric that is optionally a stiff treated fabric, impregnate at least one sheet of fabric with a resin system to form a prepreg, make a honeycomb core having at least two surfaces, placing and / or attaching a sheet to a surface of the honeycomb core to form a honeycomb core-fabric bilayer and / or to the second surface of the honeycomb core-tissue bilayer to form an intercalation of tissue-honeycomb-core, pack the honeycomb core-tissue bilayer and / or the intercalation of the honeycomb core-tissue, promote the excess air from the bag via vacuum and / or cure the honeycomb core-tissue bilayer or co-cure the tissue-core interlayer of honeycomb-tissue under increased pressure (generally not to exceed 3.6 kg / cmz (45 PSI ) to prevent further crushing of the honeycomb core) and optionally increased temperature, conditions. See, for example, Figures 1 to 4. According to the invention, methods are provided for making a honeycomb interleaving structure treated in stiffness comprising obtaining an assembled honeycomb interleaving comprising a honeycomb core having a first surface and a second surface, a first prepreg coated layer and extending further beyond the first surface, a second preimpregnated layer placed on and extending beyond the second surface, wherein a first portion of the prepreg layer extends beyond the second surface to form an edge band. Optionally, the structures can be reinforced by additional pre-impregnated layers placed on the first surface and / or the second surface and / or the edge band. The first prepreg layer comprises a resin system and a fabric selected from stiff treated fabrics of the invention, and the second prepreg layer and each of the optional additional prepreg layers each comprise an independently selected resin system and a tissue treated in stiffness or untreated tissue. The assembled honeycomb interleaving is treated under conditions sufficient to consolidate between assembled honeycomb interleaving, for example under autoclave conditions. As used herein, "autoclave conditions" include conditions of temperature and / or pressure sufficient to advance the healing of the resin system (s) placed in the prepregs and / or the core. of honeycomb, and / or advancing the consolidation of the assembled honeycomb interleaving. Optionally, the honeycomb interleaving structure treated in stiffness has a first core crushing value less than a second core crushing value of an untreated honeycomb interleaving structure. Additionally, the autoclave conditions may optionally comprise sufficient pressure to cause a first core crush value of not more than 3% in the honeycomb interleaving structure treated in stiffness and the second core crush value of more than 3% in a honeycomb intercalation structure not treated. As used herein, a stiffness improving pressure is sufficient to consolidate a "honeycomb core-tissue" bilayer into a consolidated bilayer and / or to consolidate a "honeycomb-tissue core" interleaving into an intercalation, honeycomb structure. Due to the higher stiffness value of ASTM of the treated fabric in stiffness compared to the untreated fabric, the honeycomb core bilayers and the intercalations using rigidly treated fabrics are able to withstand higher pressures during the autoclave cycle before that the core crush is present. Due to this high pressure, a greater consolidation of (and therefore less void content in) the bilayers and intercalations using at least one tissue treated in rigidity can be achieved. The value of the "pressure" can be indicated in terms of absolute or percentage increase. In this way, this value can be a pressure in the range that has as a low point any value in the range of between approximately 3.16 kg / cm2 (45 PSI) and approximately 4.22 kg / cm2 (60 PSI) and as a high point any value greater than the low point, value that is in the range from approximately 2.51 kg / cm2 50 PSI) approximately 5.97 kg / cpJ (85 PSI) Example ranges include 3.51 kg / cm2 (50 PSI) at 5.93 kg / cm2 (85 PSI), with a preferred range of 3.86 kg / cm2 (55 PSI) to 5.62 kg / cm2 (80 PSI), with a currently preferred range of 4.57 kg / cm2 (65 PSI) to 4.92 kg / cm2 (70 PSI) ). Alternatively, this value can not be less than an increase of p percent with respect to the value of the maximum usable pressure to consolidate an interleaving of "untreated tissue-untreated honeycomb core" into an intercalation structure of honeycomb without substantial crushing of the core (eg approximately 3.16 kg / cm2 (45 PSI)), where p is selected from any value between 10 and 150. Optionally, the value of p is not greater than about 200. The invention will now be described in greater detail with reference to the following non-limiting examples. All references cited herein are hereby incorporated by reference. Those skilled in the art, when guided by the teachings of this specification, may discover during the term of this patent other embodiments of this invention that fall within the scope of the appended claims.

EXAMPLES Figure 1 illustrates a core sample 10 of machined honeycomb to form a core crush discriminating panel. As shown herein, the core generally has a length "L", a width "W", a chamfer "C" placed around them, a tape direction indicated by an "RD" arrow, and a size of cell In the present examples, the honeycomb core sample 10 is a Nomex ™ core of 1.3 kilograms (3 pounds) having a length L = 30.48 cm (12 inches), a width W = 20.32 'cm (8 inches), and a chamfer C = 20 degrees, a tape direction RD that runs substantially in the direction of the width of the sample and substantially perpendicular to the direction of the length of the sample, and a cell size of 0.95"cm (3/8) However, those skilled in the art will readily be able to select the dimensions, topology and appropriate additional properties sufficient to achieve the desired objects and advantages of the present invention Figures 2A and 2B schematically illustrate a crush panel storage of core: Figure 2A is a cross-sectional view illustrating a general storage of a pre-laminated structure, and Figure 2B is a top view of the structure. s, the core crush panel includes a Nomex ™ core honeycomb sample of 1.36 kg (3 pounds), as described with reference in Figure 1. As shown in Figure 2A, in a cross-sectional view (taken along the W width of the panel), 9 different preimpregnated layers (schematically illustrated as generally horizontal lines) can be seen. Four of these are "full coverage" pre-impregnated layers, two placed on the upper surface of the honeycomb core 10 and two placed on the bottom surface of the honeycomb core 10, with one of each of the upper and bottom layers being it is oriented to +/- 45 °, and the other of each of the upper and bottom layers is oriented to -0 / 90 °. Two of the pre-impregnated layers are "double" pre-impregnated layers with one placed on top of the honeycomb core, and the other placed on the bottom surface of the honeycomb core 10, and with orientation of both layers being -0 / 90 °. The remaining three pre-impregnated layers are "picture frame" layers, with three placed around the edge band E of the honeycomb interleaving structure (i.e., that part of the structure where the pre-impregnated layers contact each other directly. , and with orientation of the three prepreg layers which is -0 / 90 ° As shown in Figure 2B, in the view at the top, the honeycomb core interleaving structure generally has a length "1" , a width "w" and an edge band E formed around the perimeter of the honeycomb core 10. In the present examples, the honeycomb core honeycomb interleaving structure has a length of 1 = 40.64 cm (16 inches) and a width w = 12 cm The honeycomb interleaving structure thus formed can be used as a core crush discriminating panel Figure 3 illustrates schematically a packing procedure for interleaving structures honeycomb based on tissue before the autoclave process. As shown in Figure 3, the packaging process generally includes a honeycomb core sample 10, at least two prepregs (e.g., fabrics treated with a resin system) 12, 13 effectively placed on the bottom and top surface of the honeycomb core sample to form a honeycomb interleaving structure, a * tool 16, a release film 18, a vent 20, a vacuum bag 22 and a vacuum bag belt 24. The tool 16 is preferably aluminum, and the surface of the tool 16 is preferably prepared with free sides, as is known in the art. A tissue-based honeycomb interleaving structure having this storage can be thermally treated in an autoclave to provide co-healing of the honeycomb core sample in prepregs, as is known in the art. Fig. 4A is a graph illustrating an autoclave cycle for a core crush-discriminating panel of the glass fiber-based honeycomb interleaving structure, demonstrates (see later examples), and Figure 4B is a graph illustrating an autoclave cycle for a honeycomb interleaving structure core crush-discriminating panel based on sample carbon fiber (see later examples). With reference to Figure 4A, in the present examples with respect to glass fiber-based fabrics, the following cure cycle values were used: maximum heating rate = 1.65 ° C (3 ° F) / minute, peak temperature = 126.6 ° C (260 ° F) +/- 5.5 ° C (10 ° F), retention time = 90 minutes +/- 5 minutes, maximum cooling fall rate = 2.75 ° C (5 ° F) / minute, minimum vacuum to vacuum bag = 55.88 cm (22 inches Hg) and autoclave pressure = 3.16 kg / cm2 (45 PSI) +/- 0.35 kg / cm2 (5 psi) (deflated when the pressure is 1.4 kg / cm2 (20 PSI).) With reference to Figure 4B, in the present examples with respect to carbon fiber-based fabrics, the following cure cycle values were used: Maximum heating rate = 1.65 ° C (3 ° F) / minute, peak temperature = 66.6 ° C (350 ° F) +/- 5.5 ° C (10 ° F), holding time = 120 minutes +/- 5 minutes, falling speed maximum cooling = 2.75 ° C (5 ° F) / minute, towards a minimum vacuum bag = 55.11 cm (22 inches Hg), and autoclave pressure = 3.16 kg / cm2 (45 PSI) +/- 0.35 kg / cm2 (5 PSI) (deflated when the pressure is 1.40 kg / cm2 (20 PSI)). in the technique they will be able to easily determine both the operable ranges and the optimal values of the heating rates, peak temperatures, retention time, cooling drop speeds, vacuum and autoclave pressures based on the selected core and prepreg materials. Figure 5 illustrates a core crush-discriminating panel and demonstrates that it exhibits a degree of core crushing after the autoclave. As shown herein, for each side, the panel of the core crush discriminating panel demonstrates autoclaved each Q "Li" indicates the original length of a respective panel side and "X" (located between the respective panels of the panels). opposite arrows) indicates the offset amount of the center of the panel side from its original location.

Example 1.- Fabric and stiffness A fabric based on glass fiber was prepared and processed as follows. Commercially available glass fibers were prepared by a starch-based solution and woven into multiple samples using a raster pattern of 8 linings (style 778 °, fiber areal weight of 293 +/- 10 g / m2). The starch-based sizing was baked from each of the samples. Each of the samples was given an identification designation (ie GL-XXX, where XXX is a value ranging from 011 to 999). - See Table 1. Each of the samples was treated with one of three different commercially available finishes (for example, precursors of the type known as CS 724, available from Clark-Schwebel ™, BGF 644 or BGF 508A, both available from Burlington Glass Fabrics ™) at varying precursor concentration levels. See Table 1. Each of the different woven fiberglass fabric samples was thermally treated at varying temperatures for varying residence times and variable time-temperature products. See Table 1 TABLE 1 Type ID Faith Value of% efe Terrife- Velocity Sample rate Finished crushing rigidity Tura fe of line resicten- PSM (IOI) treats (yards / cia per foot) core minutes) (minutes ) (° F) 222 GL-010! CS724 5.9 0 0.17 450 25 / 1.2 GL-011 CS724 4.5 0 0.14 450 25 1.2 GL-012 CS724 2.8 20 0.10 350 40 0.8 GL-014 CS724 2.2 35 0.10 350 40 0.8 GL-015 BGF644 6.3 0 0.16 500 20 1.6 GL-019 BGF644 6.0 0 0.16 525 20 1.6 G -030 BGF644 3.4 5 0.16 375 • 30 1.1 G -031 BGF644 4.6 0 0.16 450 40 0.8 GL-04I CS724 8.0 0 0.17 450 25 1.2 GL-042 CS724 5.9 0 0.14 450 25 1.2 GL-042a CS724 6.6 0 0.14 450 (1.2) 25 (1.2) 1.2 350 (1440) 0 (1440) + 1440 GL-047 BGF644 4.0 '3 0.17 425 20 1.6 GL-048 BGF644 3.0 15 0.17 350 20 1.6 GL-051 CS724 2.4 23 0.10 350 40 0.8 GL-052 CS724 2.5 21 0.10 350 40 0.8 G -053 CS724 2.7 18 0.10 350 40 0.8 G -054 CS724 1.9 25 0.10 350 40 0.8 GL-055 CS724 8.1 0 0.16 600 20 1.6 GL-242 BGF508A 5 0 0.12 350 20 1.6 GL-243 BGF508A 5.3 0 0.15 350 20 1.6 GL-245 BGF508A 5.9 0 0.13 350 20 1.6 GL-279 BGF508A 2.7 26 0.09 350 20 1.6 GL-280 BGF508A 5.9 0 0.13 350 20 1.6 GL-281 BGF508A 5.7 0 0.13 350 20 1.6 G -283 BGF508A 4.1 17 0.12 350 20 1.6 GL-285 BGF508A 5.7 0 0.14 350 20 1.6 GL-234 BGF508A 6.1 tbd 0.18 250 20 1.6 G -233 BGF508A 6.4 tbd 0.24 300 20 1.6 GL-235 BGF508A 5.7 tbd 0.15 325 20 1.6 GL-229 BGF508A 5.8 tbd 0.14 375 20 1.6 Tissue based on carbon fibers was prepared and processed as follows. Commercially available rolls of the fabric based on carbon fibers, borrowed, woven using a flat web (flat weft style 322; fiber areal weight of 193 +/- 27 g / m2), were procured. Each of the tissue rolls was treated with one of the two different commercially available sizes [e.g., precursors of the type known as UC309, available from Union Carbide (Danbury, CT) and processed by Amoco (Greenville, SC) or Toray (Japan) (Precursor of Toray may have a different commercial identification although the precursor of Toray has the same chemical structure as UC309), or of the type known as EP03, available from Toho (Japan) and processed by Toho (Palo Alto, CA )] at variable precursor concentration levels. See Table 2. Each of the rolls was given an identification designation (ie, GR-XXX, where XXX is a value that varies from 001 to 999). Each of the first four rolls was then further divided into two samples, a "control" sample ie, a sample in Table 2 that has an identification but was not marked with an "a" suffix and a sample of "treated" (ie, the sample in Table 2 that has the same identification designation as the "control" sample, and was also marked with a "a" suffix). See Table 2. Each of the "control" samples was an untreated tissue. Each of the "treated" samples is an untreated fabric that was subjected to heat treatment at a treatment temperature ° F) for one treatment time (minute). Each of the remaining rolls / samples is an untreated fabric that was subjected to heat treatment at a treatment temperature ° F during a treatment time (minute), as indicated. See Table 2 (NA means not applicable). With reference to the data set forth in Table 2, those skilled in the art will readily appreciate that improved ASTM values- and reduced core crush values can be achieved by the present invention either by treating the carbon fibers prior to weaving. or when treating a fabric based on carbon fiber after weaving. Those skilled in the art will also appreciate that the temperature range for the heat treatment of a carbon fiber or a carbon fiber-based fabric has an upper limit that is specific to the size. The upper limit may be a temperature at which the sizing begins to degrade during the heat treatment, such that, despite the% finish (LOI), the carbon fiber treated or woven based carbon fiber can not exhibit a value of improved ASTM or core crush value. The thermal treatment above this limit can be evidenced by a characteristic burning odor during the thermal treatment.

TABLE 2 ID.% Value of% efe% efe Tepperature Sample rate sizing rigidity of crushing pressure ASTM treatment (li shing of treatment (minutes) per foot) core (° F)! GR-001 UC309 2.2 16! 1.2 NA +0 GR-OOla UC309 3.1 0 1.2 350F 1440 GR-002 EP03 2.4 37 1.4 NA +0 GR-002a EP03 12.0 0 1.4 350F 1440 GR-003 UC309 2.1 7 1.1 NA • +0 GR-003a UC309 3.7 0 1.1 350F 1440 GR-004 UC309 3.3 43 1.1 NA +0 GR-004a UC309 6.4 0 1.1 350F 1440 GR-005 C309 3.5 25 1.1 NA +0 GR-006 UC309 4.8 8 1.1 350F 30 GR-007 UC309 5.2 1.1 350F 60 GR-008 UC309 5.6 1.1 350F 90 GR-009 UC309 5.4 1.1 350F 120 GR-010 UC309 5.6 1.1 350F 180 GR-011 UC309 5.6 1.1 350F 240 GR-012 UC309 6.1 0 1.1 350F 360 GR-014 UC309 5.4 0 1.1 500F 10 GR-015 UC309 5.2 1.1 500F 20 GR-016 UC309 4.3 1.1 600F 10 GR-017 UC309 4.1 1.1 600F 20 GR-018 UC309 4.0 1.1 500F 2 GR-019 UC309 4.3 5 1.1 500F 4 Table 2 (continued) Type ID efe Value of% efe% efe Tarperature Tiarpo of our sizing stiffness efe crushed spressefe treatment ñSTM (pounds efe to treatment (rr? Inutc > s) per foot ) core (° F) GR-020 UC309 4.5 1.1 500F 6 GR-021 UC309 4.9 1.1 500F 8 GR-022 UC309 5.4 1.1 500F 15 GR-023 UC309 5.3 1.1 500F • 30 GR-024 UC309 3.1 1.1 GR-025 UC309 2.4 .1.1 GR-026 UC309 3.4 30 1.1 NA +0 GR-027 UC309 4.8 1.1 525F 2 GR-028 UC309 5.0 1.1 525F 4 GR-029 UC309 4.9 1.1 525F 6 GR-030 UC309 4.7 1.1 525F 8 GR-031 UC309 5.0 0 1.1 525F 10 GR-032 UC309 5.2 1.1 350F 1440 GR-033 UC309 4.7 1.1 350F 360 GR-034 UC309 4.5 1.1 450F 10 GR-035 UC309 4.0 1.1 500F 10 The ASTM stiffness value of, or stiffness of, each sample of the glass fiber fabric and the carbon fiber fabric was determined by the circular bending growth developed by the American Society for Testing and Materials (ASTM).

The ASTM stiffness values derived by this test are summarized in Table 1 and Table 2. As seen in Table 1 and Table 2, the numerous fabrics with increased ASTM stiffness values differ for a fabric genus that has a value of ASTM stiffness increased, as contemplated by the invention.

Example 2.- Start Materials Start materials were prepared based on glass fiber and processed as follows: commercially available glass fibers were prepared with a starch-based solution and woven into multiple samples using a raster frame of 8 linings (style 7781, fiber areal weight of 293 +/- 10 g / m2). The starch-based sizing was baked from each of the samples. Each of the samples was given an identification designation (ie, GL-XXX, where XXX is a value that varies from 001 to 999). See Table 1. The samples identified as GL-010 (0.17%), GL-011 (0.14%), GL-041 (0.17%, GL-042 (0.14% and GL-055 (0.16%), together with GL- 015 (0.16%), GL-019 (0.16%), GL-030 (0.16%), GL-031 (0.16%), GL-047 (0.17%) and GL-048 (0.17%) were given levels of precursor concentration of stiffness improvement (0.14% - 0.17%, as indicated in the parentheses) of the particular finish, compared to the finishing concentrations commercially practiced for the particular finish (eg CS 724 or BGF 644, as applicable) ), it was estimated that it is 0.10% +/- 0.02%, similarly the samples identified as GL-243 (0.15%), GL-245 (0.13%), GL-229 (0.14%), GL-280 ( 0.13%), GL-281 (0.13%) and GL-285 (0.14%) were given levels of precursor concentration of stiffness improvement (0.13% -0.15%, as indicated in the parentheses) of the particular finish, in Comparison to finishing at commercially finished finishing concentrations for part finishing cular (for example, BGF 508A, as applicable), which is estimated to be 0.10% +/- 0.02 %) • As seen in Table 1, from the ASTM stiffness test performed on the thermally treated fabric formed from these starting materials, the stiffness values for the glass fiber-based fabrics of samples varied. from 3.0 to 8.1, which are within the increased, defined ASTM stiffness value ranges contemplated by the invention.

Example 3 Honeycomb Interleaving Structure Precursors of the same The honeycomb core that conforms to the specifications of material 8-124, of Boeing, Class IV, Type V, grade 3 were obtained from a commercial source (Hexcel Corporation, Casa Grande, AZ). The honeycomb core was machined to the dimensions shown in Figure 1 and a rectangular panel of a honeycomb interleaving structure was assembled as shown in Figures 2A and 2B, packaged as shown in Figure 3 and shown in FIG. cured as shown in Figures 4A and 4B, for each of the selected sample tissues, as follows. With reference to FIGS. 1, 2A and 2B, the honeycomb intercalation structure comprised (i) a honeycomb core NomexHR, (ii) four prepregs, two placed in and extending beyond the upper surface of the core. honeycomb and two placed in and extending beyond the bottom surface of the honeycomb core, with a portion of the surface of the layers extending beyond the surfaces that contact each other to form an edge band ( iii) three additional pre-impregnated "image box" layers placed only along the edge band, and (iv) two additional "double" prepregs, both placed only at the side edges (e.g., biased side surface that connects the upper surface to the bottom surface) of the honeycomb core and the edge band, all of which prepregs comprised a respective sample fabric selected in accordance with Example 1. For each of the selected sample tissues prepared according to Example 1, a prepreg sheet was prepared by increasing the sample fabric with an appropriate resin system. The prepreg sheet was cut into two pieces, or preimpregnated layers, and placed in a honeycomb core to form a honeycomb panel precursor. Each of the preimpregnated layers was of sufficient dimensions to allow both (i) the covering of all surfaces of the honeycomb core and (ii) the overlap of the two prepregs to form an edge band, all in accordance with the panel dimensions. of honeycomb interleaving structure, core crush discriminator, rectangular, storage of which is illustrated in Figure 2A. The honeycomb panel precursor was stored in an aluminum tool and packaged according to Figure 3. The packed honeycomb panel precursor was subjected to an autoclave cycle, autoclave cycle that was run according to either the Figure 4A (tissue based on fiberglass) or Figure 4B (tissue based on carbon fiber). After the autoclave cycle, the honeycomb interleaving structure panel was formed and was ready for the formation of the crushing value of the core.

EXAMPLE 4 Measurement of Core Crush Rectangular panels, of a honeycomb interleaving structure comprising a NomexMR honeycomb core and two prepreg layers comprising the same fabric were assembled and cured for each of the sample fabrics selected in accordance with Example 3. With reference to Figure 5, for each of the panels of honeycomb interleaving structure prepared in this way, the following measurements were taken for each of the four sides of the panel: • the displacement of the center of the side of the panel. panel from its original position (X), and • the original length of the panel side (LA.) Once measurements were taken for all four sides, the area of the panel section that was crushed was calculated as follows: A = S 2/3 * Xn * Ln, where n varies from 1 to 4 where A is the area of the panel section that was crushed I Xi is the displacement of the center of the i-th interframe structure side n honeycomb from its original position, and Li is the original length of the ith side of honeycomb structure interleaving; y Once the value of A was determined, the percentage of core crushing was calculated according to the following formula:% Core Crushing = 100 7- (96 inches2 - A) / 96 inches2 Crushing percentage results of the core for each of the cores of the honeycomb assembled using the same tissue samples are set forth in Table 1.

Example 5 Measurement of Friction Resistance Between Pre-impregnated Layers The frictional resistance between pre-impregnated layers assembled from the species of the invention was measured as follows. The following three samples based fiberglass-based fabrics prepared according to example 1 were used in the friction resistance measurement test: • Sample 1, which was a woven fabric "control" or untreated woven in a satin weave of 8 linings having fiber areal weight of 293 +/- 10 g / m2 having a finish concentration (commercially available from Clark Schwebel ™ as CS724) of 0.10% and heat treated at 148.8 ° C-176.6 ° C (300-350 ° F) for 1.4 +/- 0.2 minutes; • Sample 2, which was a "treated in stiffness" fabric woven into a satin weave of 8 garments having a fiber areal weight of 293 +/- 10 g / m2, which have a finishing concentration (commercially available) of Clark Schwebel ™ as CS724) of 0.16% and heat treated at 232.2 ° C (450 ° F) for 1.4 +/- 0.2 minutes; • Sample 3, which was a "treated in stiffness" fabric woven in a satin weave of 8 garments having a fiber areal weight of 293 +/- 10 g / m2, which have a finishing concentration (commercially available) from Burlington Glass Fabrics ™ as BGF644) of 0.17% and heat treated at 260 ° C (500 ° F) for 1.2 minutes. For each of the three sample glass fiber-based fabrics, a prepreg sheet was prepared by wetting the sample fabric with an appropriate resin system (e.g., commercially available thermoset epoxy-based resin system available from Cytec Fiberite ( Tempe, AZ), .known as Cytec Fiberite7701). The prepreg sheet was cut into two pieces of equal size, rectangular, or pre-impregnated layers. Each piece of the two piece set was placed on the other piece to form a bilayer, with a portion of each piece that overlaps the other piece at the opposite ends of the bilayer. The resistance to friction between the pieces of the bilayer was measured according to the method to measure the resistance to friction between two preimpregnated layers, a method that was publicly presented and / or published in 1996 in the article by the authors M. Wilhelm , CJ Martín and JC Seferis and entitled "Frictional Resistance of Thermoset Prepreg and its Influence on Honey Composite Processing", the full contents of this article are incorporated herein by reference. See Figure 10-12 To summarize the method, the bilayer was inserted into a friction resistance testing machine comprising two clamps, whose jaws give each other, and a means for adjusting and measuring a tensile force between the clamps. One of the two overlapping edges of the bilayer was placed in each clamp, and the jaws of the clamp were secured against the overlap edge to prevent the detachment of the lap edge within the clamp tongs. Then a force was applied between the clamps, and it was increased slowly until substantial detachment was observed between the two layers of the bilayer. The force at which substantial detachment was observed (e.g., LOAD) was identified as the frictional resistance between the two prepreg layers. The friction resistance test was performed on each of the three samples at each of the two stage temperatures: 51.6 ° C (125 ° F) and 79.4 ° C (175 ° F). The results of the frictional test are shown in Table 3, below.

TABLE 3 LOAD NUMBER (kg TEMPERATURE (° C SAMPLE (Pounds)) (° F)) (platinum) 1 13.82 (30.45) 79.4 (175) 2 70.82 (156.0) 79.4 (175) 3 68.96 (151.9) 79.4 (175) 1 8.79 (19.38) 51.6 (125) 2 60.97 (134.3) 51.6 (125) 3 57.88 (127.5) 51.6 (125) Figures 10 through 12 are graphs illustrating the load versus offset values for samples 2, 3, and 1 at platen temperatures of 51.6 ° C (125 ° F), 79.4 ° C (175 ° F), and 51.6 ° C (125 ° F), respectively, as follows. Figure 10 is a graph illustrating the frictional force exhibited between two prepreg layers based on two thermally treated fabrics (ie, sample 3) of Example 5 at a platen temperature of 51.6 ° C (125 ° F). Each curve in the graph represents the displacement between layers (inches) of these two preimpregnated layers relative to one another as a function of the force (eg, load, measured in pounds) exerted against the prepregs. The point at which the vertical mix mark crosses each curve is the friction resistance for that sample graph. The intercept in x of each curve represents the zero point for the displacement. This curve can explain how the treated fabric stiffness in a prepreg layer can mitigate core crushing. Figure 11 is a graph illustrating the frictional force exhibited "between two prepreg layers based on two heat-treated fabrics (ie, sample 2) of Example 5 at 79.4 ° C (175 ° F) Each curve in the graph represents the displacement between layers (inches) of these two layers pre-impregnated relative to one another as a function of the force (eg, load, measured in pounds) exerted against the pre-impregnated layers.The point at which the vertical mix mark crosses each curve is the friction resistance for that sample graph.The x intercept of each curve represents the zero point for displacement.This curve can explain how the treated tissue stiffness in a prepreg layer can mitigate core crushing. Figure 12 is a graph illustrating the frictional force exhibited between two prepreg layers based on two untreated tissues (ie, sample 1) of Example 5 at 51.6 ° C (125 ° F). curve in the graph represents the displacement between layers (inches) of these two layers preimpregnated relative to each other as a function of the force (eg, load, measured in pounds) exerted against the prepregs. The point at which the vertical mix mark crosses each curve is the friction resistance for that sample graph. The intercept in x of each curve represents the zero point for the displacement. It is noted that in relation to this date, the best method known by the applicant to carry out the present invention is that which is clear from the present description of the invention. Having described the invention as above, the content of the following is claimed as property:

Claims

CLAIMS 1. Use of a stiff treated fabric to produce a honeycomb interleaving structure precursor, wherein the honeycomb interleaving structure precursor includes a honeycomb core, a pre-impregnated layer treated for stiffness and a second prepreg, wherein the pre-impregnated layer treated for stiffness includes the stiff-treated fabric and a resin system, wherein the rigidly treated fabric comprises a plurality of fibers of a polymeric material placed on at least some of the fibers, wherein the fabric treated in rigidity exhibits an ASTM stiffness value greater than the ASTM stiffness value of an untreated fabric, and wherein the pre-impregnated layer treated for stiffness, when placed in a second prepreg layer comprising a resin system and a tissue selected from the group consisting of fabrics treated in stiffness and untreated fabrics, exhibits a resistance to friction between the prepreg treated layer for ri gidity and the second pre-impregnated layer greater than the resistance to friction between two untreated pre-impregnated layers placed one on the other, where each of the untreated pre-impregnated layers comprises the resin system and an untreated fabric.
2. The use of a stiff treated fabric according to claim 1, wherein the fibers of the treated fabric in stiffness and the untreated fabric are glass fibers, and wherein the stiffness value of ASTM of the treated fabric in stiffness it is at least 7% greater than the ASTM stiffness value of the untreated fabric.
3. The use of a stiff treated fabric according to claim 1, wherein the fibers of the treated fabric in stiffness and the untreated fabric are carbon fibers, and wherein the stiffness value of ASTM of the treated fabric in stiffness is at least 45% greater than the ASTM stiffness value of the untreated fabric.
4. The use of a stiff treated fabric according to claim 1, wherein the stiff treated fabric exhibits an ASTM stiffness value of not less than about 3.4 pounds per foot.
5. The use of a stiff treated fabric according to claim 1, wherein the fibers are glass fibers and the stiffness value of ASTM is in the range of about 3.0 pounds per foot to about 8.1 pounds per foot.
6. The use of a stiff treated fabric according to claim 4, wherein the fibers are carbon fibers.
The use of a stiff treated fabric according to claim 4, wherein a portion of the polymeric material is chemically bound to the fibers and consists essentially of advanced n-mers of polymeric material precursors.
8. The use of a fabric treated in stiffness according to claim 7, wherein the advanced n-mers have an average n-value of not less than 3.
9. The use of a fabric treated in rigidity in accordance with the Claim 4, wherein a portion of the polymeric material chemically bonds to the fibers and coats the fibers to increase the average thickness thereof when compared to the corresponding fibers of an untreated fabric.
The use of a stiff treated fabric according to claim 9, wherein the increase in average thickness is in the range of about 8% and about 20%.
The use of a stiff treated fabric according to claim 9, wherein a portion of the portion of the fibers comprises threads or tows having both a first capillary surface and a first non-capillary surface, and the polymeric material placed in the first capillary surface of a first plurality of threads or tows has an average thickness greater than the average thickness of the polymeric material placed on the first non-capillary surface of the threads or tows of the first plurality.
12. The use of a fabric treated in stiffness according to claim 11, wherein a subset of the threads or tows comprises filaments having both a second capillary surface and a second non-capillary surface, and the polymeric material placed on the second capillary surface of a second plurality of the filaments has an average thickness greater than Average thickness of the polymeric material placed on the second non-capillary surface of the filaments of the second plurality.
A method for making a fabric treated in stiffness having an ASTM stiffness value greater than the ASTM stiffness value of an untreated fabric, which method is characterized in that it comprises obtaining a fabric comprising a plurality of fibers and material polymer and / or precursors of polymeric material placed in at least some of the fibers, and treating the fabric under conditions sufficient to produce an ASTM stiffness value of the treated tissue in stiffness greater than the ASTM stiffness value of an untreated fabric .
The method according to claim 13, characterized in that the rigidity treated fabric thus produced exhibits an ASTM stiffness value of not less than about 3.4 pounds per foot.
The method according to claim 14, characterized in that a first portion of the polymeric material and / or the precursors is chemically bound to the fibers.
The method according to claim 15, characterized in that a second portion of the precursors and / or the polymeric material is chemically bound to a third portion of the precursors and / or the polymeric material, and wherein the derivatives are formed in this way.
17. The method according to claim 13, characterized in that the conditions are selected from the group consisting of heat treatment, treatment with ultraviolet light, and treatment with free radicals.
18. The method according to claim 13, characterized in that the polymerization of the polymeric material and / or the precursor of the polymeric material is taken substantially to completion.
19. The method according to claim 17, characterized in that the conditions are thermal treatment of the tissue at a treatment temperature for rigidity improvement.
The method according to claim 19, characterized in that the stiffness improving treatment temperature is in the range of about 121.1 ° C (250 ° F) to about 371.1 ° C (700 ° F).
The method according to claim 19, characterized in that the treatment temperature of improvement d-e stiffness is in the range of about 148.8 ° C (300 ° F) to about 176.6 ° C (350 ° F).
22. The method according to claim 19, characterized in that the stiffness improving treatment temperature is in the range of about 176.6 ° C (350 ° F) to about 232.2 ° C (450 ° F).
23. The method according to claim 17, characterized in that the conditions are thermal treatment of the fabric during a residence time of rigidity improvement.
24. The method according to claim 23, characterized in that the residence time of rigidity improvement is in the range of about 1.0 minutes and about 1440 minutes.
25. The method according to claim 23, characterized in that the residence time of rigidity improvement is in the range of about 1.1 minutes and about 10 minutes.
26. The method according to claim 23, characterized in that the residence time of rigidity improvement is in the range of about 1.2 minutes and about 5.0 minutes. . {
27. The method according to claim 17, characterized in that the conditions of a thermal treatment of the fabric for a time-temperature product of rigidity improvement.
28. The method according to claim 27, characterized in that the stiffness improving time-temperature product is in the range of about 300 minutes-° F to about 600 min-° F.
29. The method according to claim 27, characterized in that the stiffness induction time-temperature product is in the range of about 400 min-F to about 300 min-F.
30. The method according to claim 27, characterized in that the stiffness induction time-temperature product is in the range of about 500 min-F to about 1000 min-F.
31. The method according to claim 17, characterized in that the conditions are thermal treatment of the tissue in the presence of precursor at a precursor concentration of rigidity improvement.
32. The method according to claim 31, characterized in that a portion of the plurality of fibers are glass fibers and the concentration of stiffness improving precursor is in the range of 0.25% to 1.0% by weight.
33. The method according to claim 31, characterized in that a portion of the plurality of fibers are glass fibers and the concentration of stiffness improving precursor is in the range of 0.10% to 0.39% by weight.
34. The method according to claim 17, characterized in that the conditions for a thermal treatment of the fabric in the presence of a heated gas circulation speed of rigidity improvement.
35. A s treated fabric having an ASTM sness value greater than the ASTM sness value of an untreated fabric made by the method comprising obtaining a fabric comprising a plurality of fibers and polymeric material and / or material precursors polymer placed in at least some of the fibers, and treating the fabric under conditions sufficient to produce an ASTM sness value of the treated tissue in sness greater than the ASTM sness value of an untreated fabric.
36. The fabric treated in sness according to claim 35, characterized in that the fabric treated in rigidity has a sness value of ASTM and not less than about 3.4 pounds per foot.
37. The fabric treated in rigidity according to claim 36, characterized in that a portion of the polymeric material comprises advanced n-mers of the precursors.
38. The fabric treated in sness according to claim 37, characterized in that the polymeric material is placed in a portion of the fibers to coat the portion to increase the average thickness of the fibers of the portion compared to the average thickness of a number. equal of corresponding fibers of an untreated fabric.
39. The use of a s-treated woven raw material to produce a honeycomb interleaving structure precursor, wherein the honeycomb interleaving structure precursor includes a honeycomb core, a pre-impregnated layer treated for sness and a second pre-impregnated layer. , and wherein the pre-impregnated layer treated for sness includes a fabric treated in sness that includes the raw material of fabric treated for sness, wherein the raw material of fabric treated for sness comprises tissue raw material, precursors of polymeric material placed in the less some of the woven raw material in a precursor concentration of sness enhancement and optionally, polymeric material placed in at least some of the woven raw material, and wherein the pre-impregnated layer treated for sness, when placed in a second prepreg, which comprises a resin system and a tissue selected from the group consisting of fabrics treated in sness and untreated fabrics, exhibits a frictional resistance between the pre-impregnated layer treated for rigidity and the second pre-impregnated layer greater than the resistance to friction between the two untreated pre-impregnated layers placed one on the other, where each of the Two pretreated untreated layers comprise the resin system and an untreated fabric.
40. The use of a woven treated raw material for sness according to claim 39, wherein the woven raw material is glass fibers and / or glass strands and / or glass filaments and the. The sness improving precursor concentration is in the range of 0.25% to 1.0% by weight.
41. The use of a woven treated raw material for sness according to claim 39, wherein the woven raw material is glass fibers and / or glass strands and / or glass filaments, woven optionally in a style of plot of 8 linings to form a fabric, the precursors and the polymeric material having the formula of a commercially available finish known as CS 724 and the concentration of sness improving precursor are in the range of 0.13% to 0.17%.
42. The use of a woven treated raw material for sness according to claim 39, wherein the woven raw material is carbon fibers and / or carbon tows and / or carbon filaments and the strength precursor concentration of sness is in the range of 0.10% to 0.39%.
43. The use of a woven treated raw material for sness according to claim 39, wherein a portion of the precursors are chemically bound to a subset of at least some of the woven raw material.
44. The use of a treated woven raw material for sness in accordance with claim 39, wherein the polymeric material is present and placed in at least some of the tissue raw material, and wherein at least a first portion of the precursors and / or the polymeric material is chemically bound to a second portion of the precursors and / or the polymeric material and wherein the derivatives are formed in this way.
45. The use of a treated raw material for stiffness. according to claim 44, wherein a third portion of the derivatives and / or the polymeric material comprises advanced n-mers of precursors of the polymeric material.
46. The use of a woven treated raw material for stiffness according to claim 45, wherein advanced n-mers have an average n-value of not less than 3.
47. A method for making a treated raw material for stiffness characterized in that it comprises obtaining woven raw material and placing at least some of the fabric raw material precursors of polymeric material, in a concentration of stiffness improving precursor and optionally, a polymeric material.
48. The method for making a woven treated raw material for stiffness according to claim 47, characterized in that a portion of the precursors is chemically bound to a subset of at least some of the woven raw material.
49. The method for making a woven treated raw material for stiffness according to claim 47, characterized in that the polymeric material is present and placed in the fibers, and wherein a first portion of the precursors and / or the polymeric material is chemically binds a second portion of the precursors and / or the polymeric material, and wherein the derivatives are formed in this way.
50. The method. for making a treated fabric raw material * for stiffness according to claim 49, characterized in that a third portion of the derivatives and / or the polymeric material comprises advanced n-mers of precursors of the polymeric material.
51. The method for making a treated raw material for stiffness according to claim 47, characterized in that the advanced numbers have an average n-value of not less than 3.
52. The method according to claim 47 , characterized in that the polymerization of the derivatives and / or the polymeric material is taken up to full term.
53. A method for making a woven raw material treated for stiffness, characterized in that it comprises obtaining woven raw material comprising precursors of polymeric material and / or precursors of polymeric material placed in at least some of the woven raw material and treating the woven raw material with a treatment selected from the group consisting of heat treatment, ultraviolet light treatment and free radical treatment under conditions wherein a stiffness value of ASTM and a woven treated in stiffness made of the treated woven raw material Rigidity is greater than the ASTM stiffness value of an untreated fabric.
54. The method according to claim 53, characterized in that the woven raw material is carbon fibers and / or coal tows and / or carbon filaments and the treatment is heat treatment.
55. The use of a pre-impregnated layer treated for rigidity to produce a honeycomb interleaving structure precursor including a honeycomb core, the pre-impregnated layer treated for stiffness and a second prepreg, wherein the pre-impregnated layer treated for stiffness comprises a fabric treated in stiffness and a resin system, and wherein the preimpregnated layer treated for stiffness, when placed in a second prepreg layer comprising a resin system and a fabric selected from the group consisting of fabrics treated in stiffness and untreated fabrics, exhibits a frictional resistance between the pre-impregnated layer treated for rigidity and the second pre-impregnated layer greater than the frictional resistance between two untreated pre-impregnated layers placed one on the other, wherein each of the untreated preimpregnated layers comprises the resin system and an untreated fabric.
56. The use of a pre-impregnated layer treated for stiffness according to claim 55, wherein the frictional resistance between the pre-impregnated layer treated for stiffness and the second pre-impregnated layer is between 22.7 kg (50 pounds) and 79.48 kg (175 pounds (Boeing-Wilhelm method) J.
57. The use of a pre-impregnated layer treated for stiffness according to claim 55, wherein the frictional resistance between the pre-impregnated layer treated for stiffness and the second pre-impregnated layer is between 34.0 kg (75 pounds) and 79.45 kg (175-pounds (Boeing-Wilhelm method) J.
58. The use of a pre-impregnated layer treated for stiffness according to claim 55, wherein the resistance to friction between the prepreg layer treated for stiffness and the second prepreg is between 45.4 kg (100 pounds) and '78.1 kg (150 pounds (Boeing-Wilhelm method).] 59. A method for making a pre-impregnated layer treated for rigidity, character bristle because it comprises obtaining a treated tissue in stiffness and a resin system, and placing the resin system in the treated tissue in rigidity. 60. The method according to claim 59, characterized in that the resistance to friction between the pre-impregnated layer treated for stiffness and the second prepreg is between 22.7 kg (50 pounds) and 79.45 kg (175 pounds). 61. The method according to claim 59, characterized in that the resistance to friction between the pre-impregnated layer treated for stiffness and the second prepreg is between 34.0 kg (75 pounds) and 79.45 kg (175 pounds). 62. The method according to claim 5g, characterized in that the resistance to friction between the pre-impregnated layer treated for stiffness and the second prepreg is between 45.4 kg (100 pounds) and 68.1 kg (150 pounds). 63. A honeycomb interleaving structure precursor treated in stiffness characterized in that it comprises a honeycomb core having a first surface and a pre-impregnated layer treated for stiffness placed on the first surface, wherein the pre-impregnated layer treated for stiffness comprises a system of resin and a tissue selected from fabrics treated in rigidity. 6 The honeycomb interleaving structure precursor treated in stiffness according to claim ^ 3 characterized in that it additionally comprises at least one additional prepreg layer placed on the first surface, wherein each of the additional prepreg layers comprises an independently selected resin system and a tissue selected independently from the group consisting of fabrics treated in stiffness and untreated tissues. 65. The honeycomb interleaving structure precursor treated in stiffness according to claim 66, characterized in that at least one prepreg layer selected from the group consisting of the additional pre-impregnated layers and the pre-impregnated layer treated for stiffness extends beyond the first surface of the honeycomb core. 66. A honeycomb interleaving structure treated for stiffness comprising a honeycomb core having a first surface and a second surface, a first prepreg positioned on and extending beyond the first surface, a second prepreg positioned on and extending beyond the second surface, wherein a first portion of the first prepreg extending beyond the first surface contacts a second portion of the second prepreg extending beyond the second surface. to form an edge band and optionally, additional pre-impregnated layers placed on the first surface and / or the second surface and / or the edge band, wherein the first prepreg comprises a resin system and a tissue selected from fabrics treated in rigidity, and wherein the second prepreg layer and each of the optional additional prepreg layers each comprise an independently selected resin system and a fabric independently selected from the group consisting of stiff treated fabrics and untreated fabrics. 67. The honeycomb interleaving structure treated for stiffness according to claim 66, characterized in that the first prepreg has a high resin content. 68. The honeycomb interleaving structure treated for stiffness according to claim ß, characterized in that the first prepreg layer further comprises carbon fibers and wherein the high resin content is greater than about 42%. 69. The honeycomb interleaving structure treated for stiffness according to claim 67 characterized in that the first prepreg layer further comprises glass fibers and wherein the high resin content is greater than about 40%. 70. The honeycomb interleaving structure treated for stiffness according to claim 68, characterized in that the honeycomb interleaving structure treated for stiffness has a first crushing value of the core smaller than a second crushing value of the core of an interleaving structure. of honeycomb not treated. 71. The honeycomb interleaving structure treated for stiffness according to claim 70, characterized in that the first crushing value of the core is in the range of 0% to 5%. 72. The honeycomb interleaving structure treated for stiffness according to claim 70, characterized in that the first crushing value of the core is in the range of 0% to 3%. 73. The honeycomb interleaving structure treated for stiffness according to claim 70, characterized in that the first crushing value of the core is in the range of 0% to 0.1%. 74. The honeycomb interleaving structure treated for stiffness according to claim 70, characterized in that the honeycomb interleaving structure has less void content compared to an untreated honeycomb interleaving structure. 75. A method for making a honeycomb interleaving structure precursor treated in stiffness, characterized in that it comprises obtaining a honeycomb interleaving structure precursor comprising a honeycomb core having a first surface and a first prepreg layer deposited on the honeycomb. first surface, wherein the first prepreg comprises a resin system and a tissue selected from rigidly treated fabrics and treating the assembled honeycomb intercalation precursor under sufficient autoclave conditions to consolidate the assembled honeycomb intercalation precursor. 76. A method for developing a honeycomb interleaving structure treated for stiffness, characterized in that it comprises obtaining an assembled honeycomb interleaving comprising a honeycomb core having a first surface and a second surface, a first prepreg coated layer placed on and being extends beyond the first surface, a second prepreg positioned on and extending beyond the second surface, wherein a first portion of the first prepreg extending beyond the first surface contacts a second portion of the second prepreg layer extending beyond the second surface to form an edge band and optionally additional prepreg layers placed on the first surface and / or the second surface and / or the edge band, wherein the first prepreg layer It comprises a resin system and a tissue selected from fabrics treated in rigidity, and where the second prepreg layer and each of the optional additional prepreg layers each comprises an independently selected resin system and a tissue selected independently from the group consisting of stiff-treated fabrics and untreated fabrics, and treat the assembled honeycomb intercalation under sufficient autoclave conditions to consolidate the assembled honeycomb intercalation. 77. The method according to claim 75 characterized in that the honeycomb interleaving structure treated for stiffness has a first crushing value of the core smaller than a second crushing value of the core of an untreated honeycomb interleaving structure. 78. The method according to claim 77, characterized in that the first core crush value is in the range of 0% to 5%. 79. The method according to claim 77 characterized in that the first core crush value is in the range of 0% to 3%. 80. The method according to claim 77, characterized in that the first crushing value of the core is in the range of 0% to 0.1%. 81. The method according to claim 7 &; , characterized in that the autoclave conditions comprise sufficient pressure to cause a first crushing value of the core of not more than 3% in the honeycomb interleaving structure treated for stiffness and a second crushing value of the core of more than 3% in the structure of untreated honeycomb intercalation. 82. The method according to claim 81, characterized in that the pressure is in the range of between about 3.51 kg / cm2 (50 PSI) and about 5.97 kg / cm2 (85 PSI). 83. The method according to claim 81, characterized in that the pressure is in the range of between about 3.86 kg / cm2 (55 PSI) and about 5.62 kg / cm2 (80 PSI). 84. The method according to claim 81, characterized in that the pressure is in the range between about 4.57 kg / cm2 (65 PSI) and about 4.92 kg / cm2 (70 PSI). 85. The use of a woven treated raw material for stiffness according to claim 39, wherein the woven raw material is carbon fibers and / or carbon yarns and / or carbon filaments and the concentration of breeding precursor of stiffness is in the range of 1.08% to 1.17%.