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    • 专利摘要:
    sub-laminated module, laminated composite structure and method of making them the present invention relates to several configured sub-laminated modules (5.15), comprising at least a first fold (2a, 12a) and a second fold (2b, 12b ), the first fold (2a, 12a) comprising fibers that extend in first orientation (7a, 13), the second fold comprising fibers that extend in a second orientation (7b, 14). the second orientation (7b, 14) is compensated in relation to the first orientation (7a, 13), whose deviation defines an acute angle (19) between the two orientations. the acute angle (19) is less than 90º and in at least one modality, the acute angle (19) is approximately 25º. in certain modalities, the acute angle (19) defines an unbalanced structure of the sub-laminated module (5,15). in certain embodiments, the first and second folds (2a, 12a, 2b, 12b) can be additionally joined in relation to one another in an uncrimped configuration. laminated composite structures (10,110) formed from various types of sublaminated modules (5,15) are also provided, at least some of which can be homogenized. Various methods of fabricating sublaminated modules (5.15) and laminated composite structures (10.110) are also provided.
    公开号:BR112013017815B1
    申请号:R112013017815-9
    申请日:2011-10-12
    公开日:2020-05-12
    发明作者:Stephen W. Tsai；Cognet Michel；Sanial Philippe
    申请人:Compagnie Chomarat；The Board Of Trustees Of The Leland Stanford Junior University；
    IPC主号:
    专利说明:

    Invention Patent Descriptive Report for LAMINATED COMPOSITE STRUCTURES AND METHODS FOR MANUFACTURING AND USING THE SAME.
    BACKGROUND
    Field of the Invention
    The present invention generally relates to laminated composite structures, in particular those containing angular fold orientations to obtain desirable improved physical properties, together with methods of making and using such structures.
    Description of the Related Art
    Conventional laminated composite structures are generally designed to mimic the strength characteristics of conventional metal-based laminated materials and as such are limited to configurations that have folds that are symmetrical and balanced. Such conventional structures when so limited and containing at least three fold folds formed from black carbon fibers, are commonly referred to in the art as black aluminum due to their combined carbon composition and characteristics that simulate the metal.
    Symmetrical laminates involve a reflective or mirror image equivalence of the fold orientation close to its median plane, while balanced laminates involve an equal number of folds positively (+) and negatively (-) oriented throughout. Such restrictions have traditionally remained unchallenged due to problems as conventional laminated composite structures will deform after cooling from the curing temperature or increased residual stress when the operating temperature changes.
    Symmetrical laminates have traditionally been formed by stacking multiple folds of several unidirectional folds and fabric in such a way that the laminated composite displays a mirror image of itself close to a mid-plane of the structure. Such lamination processes are generally time-consuming and labor-intensive as well as error-prone, requiring the necessary precision in ordering the respective
    2/34 composite bras and can result in an unnecessary number of folds, which can contribute to a process with waste and excessive costs. Additional symmetrical laminates have historically proven complications when trying to taper the outer surface of a structure, due at least in part to the desire to maintain symmetry throughout, even when folds of folds detach to form the tapered object. In addition, depending on the individual symmetrical folds or in pairs with substantially the same orientation, they are highlighted to form the tapered object, the stacking sequence of the laminate and, therefore, the strength characteristics of the material, are changed.
    Balanced laminates, like the symmetrical ones described above, have traditionally been formed by stacking multiple folds of several unidirectional folds in a plurality of precise orientations with relatively large angles between them. For example, each off-axis bend, such as a + 45 ° bend, is typically combined and mirrored by a -45 ° bend. Additionally, it has been a common practice guidelines have four folds incorporating angles of -45 °, 0 o, + 45 ° and 90 °. Alternatively, three - ply orientations are also common, such as the settings of 0, ± 45 °. It was critical when the number of positive (+) and negative (-) oriented folds remained the same.
    Balanced and symmetrical laminates of this nature have historically created difficulties when trying to minimize the thickness of the laminate, requiring increasingly thin folds as the only option. Tapering complexities also existed in these structures, given that the detachment of particular folds or groups of these should not disturb the desired symmetry or balance. Additionally, balanced laminates are orthotropic, where the deflection and rotation that result from the bending and deformation moments are not coupled. This structural response is analogous to that of isotropic materials such as metal.
    Although not routine in the art, coupled bending and deformation moments can provide desirable deformation characteristics, in particular, allowing inventors to confidently predict
    3/34 forces folding from deformation and causing the two to work against each other, leading to a reduced degree of deflection and / or rotation not possible with orthotropic and isotropic materials. This can be advantageous for long, thin structures, such as wind turbine blades, helicopter rotor blades, airplane wings and tails and the like, where tip deflection can be reduced in one direction by using this folding-coupling deformation of an unbalanced laminate, but it can also provide advantages in several other applications.
    Conventional laminated composite structures historically exhibit static and fatigue characteristics that can allow the formation of a certain degree of micro-cracks in the structure that exist before the final break of the structure. This is due, at least in part, to the differential stress between the first fold break (FPF) and the last fold break (LPF), as is commonly known and referred to in the art and as will be described in further detail below. In many applications, such microcracking is tolerable, making laminate composite structures suitable, at least in that respect. Certain applications, however, cannot tolerate microcracking, requiring alternatively planned structures that minimize the differential stress between FPF and LPF. Of course, with at least the previously described symmetry and balance restrictions, conventional laminated composite structures with four or more bend angles are generally not suitable for such applications.
    Consequently, there is a need to provide laminated structures and methods of manufacturing and using them, which minimize the various deficiencies and limitations mentioned above of balanced and symmetrical laminated structures, minimize micro-cracks and expand the first fold crack envelope, all without sacrificing physical properties.
    BRIEF SUMMARY
    Briefly, several embodiments of the present invention address the above needs and obtain other advantages by providing laminated structures that comprise angular fold orientations.
    4/34 in an innovative way to obtain the desired improved physical properties and facilitate the manufacturing processes.
    In accordance with the purposes of the various modalities as described here, a sub-laminated module is provided for use in forming a laminated composite. The sub-laminated module comprises: a first fold comprising fibers that extend in a first orientation; a second fold comprising fibers extending in a second orientation, the second orientation being offset in relation to the first orientation; and an acute angle defined by the relative compensation between the first orientation and the second orientation, the acute angle being less than 90 ° and which defines an unbalanced structure of the sub-laminated module, in which the first fold and the second fold are secured one in relation to the other in a non-crimped configuration.
    In accordance with the purposes of the various modalities as described here, another sub-laminated module is provided for use in forming a laminated composite. The sub-laminated module comprises: a first fold comprising fibers extending in a first orientation, the fibers of the first fold comprising a plurality of distributed fiber cables lying adjacent to each other; a second fold comprising fibers extending in a second orientation, the fibers of the second fold comprising a plurality of distributed fiber cables lying adjacent to each other; and an acute angle defined by the relative compensation between the first and the second orientations, the acute angle being less than 90 ° and which defines an uncompensated structure of the sublaminated fold.
    In accordance with the purposes of the various embodiments as described here, a laminated composite structure is provided. The laminated composite structure comprises a plurality of sublaminated modules. Each sub-laminated module comprises: a first fold comprising fibers that extend in a first orientation; a second fold comprising fibers extending in a second orientation; and an acute angle defined by the relative compensation between the first and the
    5/34 second orientations, the acute angle being less than 90 ° and which defines a non-compensated structure of the sub-laminated module, in which the first fold and the second fold are attached to each other in an uncrimped configuration.
    In accordance with the purposes of the various embodiments as described here, a laminated composite structure is provided. The laminated composite structure comprises a plurality of sublaminated modules. Each sub-laminated module comprises: a first fold comprising fibers extending in a first orientation, the fibers of the first fold comprising a plurality of distributed fiber cables lying adjacent to each other; a second fold comprising fibers extending in a second orientation, the fibers of the second fold comprising a plurality of distributed fiber cables lying adjacent to each other; and an acute angle defined by the relative compensation between the first and the second orientations, the acute angle being less than 90 ° and which defines an uncompensated structure of the sublaminated fold.
    In accordance with the purposes of the various modalities as described here, a method of manufacturing a sub-laminated module for use in forming a laminated composite is provided. The method comprises the steps of: placing a first fold in a first orientation; positioning a second fold in a second orientation, the second orientation being offset in relation to the first orientation, such that an acute angle less than 90 ° is defined; stacking the second fold adjacent the first fold such that a non-compensated structure is formed, and sewing the first fold and the second fold relative to each other in a substantially uncrimped configuration.
    In accordance with the purposes of the various modalities as described here, another method of fabricating a sub-laminated module is provided for use in forming a laminated composite. The method comprises the steps of: distributing a first fiber cable comprising a plurality of fibers to form a first fold of folds; distri
    6/34 include a second fiber cable comprising a plurality of fibers to form a second fold of folds; positioning the plurality of fibers of the first cable in a first orientation; positioning the plurality of fibers of the first cable in a second orientation, the first and second orientations defining an acute angle between them, the acute angle being less than 90 ° and defining a non-compensated structure of the sublaminate fold; stack the first fold and the second fold adjacent to each other; and sewing the first fold and the second fold relative to each other in an uncrimped configuration.
    In accordance with the purposes of the various modalities as described here, a method of fabricating a laminated composite structure is provided. The method comprises the steps of: forming a plurality of sublaminated modules, each module comprising: a first fold comprising fibers extending in a first orientation; a second fold comprising fibers extending in a second orientation; and an acute angle defined by the relative compensation between the first orientation and the second orientation, the acute angle being less than 90 ° and defining an uncompensated structure of the sub-laminated module; stacking a plurality of sublaminated folds adjacent to each other; fixing the respective folds of the plurality of sublaminated folds in relation to each other in a substantially uncrimped configuration; and sequentially depositing the respectively fixed plurality of sublaminated folds to form the laminated composite structure.
    In accordance with the purposes of the various modalities as described here, another sub-laminated module is provided for use in forming a laminated composite. The sub-laminated module comprises: a first fold comprising fibers that extend in a first orientation; a second fold comprising fibers extending in a second orientation, the second orientation being offset in relation to the first orientation; and an acute angle defined by the relative compensation between the first orientation and the second orientation, the acute angle being
    7/34 less than 30 °, where the first fold and the second fold are fixed relative to each other in an uncrimped configuration.
    BRIEF DESCRIPTION OF THE VARIOUS VIEWS OF THE DRAWINGS
    Having described several modalities of the invention in general terms, reference will now be made to the attached drawings, which are not necessarily drawn to scale and in which:
    Figure 1 illustrates a symmetrical laminated structure according to the prior art;
    Figure 2 illustrates an asymmetric laminated structure, not compensated 10 according to various modalities;
    Figure 3 illustrates an exemplary formation of the laminated structure of Figure 2 from at least two sublaminated modules 15.
    Figure 4 illustrates the degree of homogenization obtainable by the laminated structures configured similarly to those in Figure 2;
    Figure 5 is a graph showing a reduced degree of distortion between laminate 1 in Figure 1 and laminate structure 10 in Figure 2;
    Figure 6A illustrates an unbalanced laminate according to the various modalities that encounters a bending and torsional force;
    Figure 6B is a graph showing a variety of flexion-torsion coupling values with respect to an unbalanced angle of at least one fold of the asymmetric laminated structure of Figure 1;
    Figure 7 is a graph that illustrates an unbalanced panel in an exemplary cantilever that could result in minimum deflection values, even zero, with various proportions of combined flexion and torsion movements applied;
    Figure 8 is a pair of graphs illustrating an exemplary microcrack zone in a symmetrical laminated structure according to the prior art, together with a microcrack-free zone in the asymmetrical laminated structure, not compensated 10 of Figure 2 according to various modalities of invention;
    Figure 9 illustrates a process of sewing a fold of non-crimped fabric of the asymmetric sublaminated structure according to various patterns; and
    Figure 10 illustrates a machine modified to manufacture the asymmetric laminated structure of Figure 1.
    DETAILED DESCRIPTION OF VARIOUS MODALITIES
    Various embodiments of the present invention will now be described more fully below with reference to the accompanying figures, in which some, but not all of the embodiments of the invention are shown. In fact, the modalities of the invention can be practiced in several different ways and should not be considered as limited to the modalities described herein. In particular, these modalities are provided in such a way that this description will satisfy the applicable legal requirements. The expression or is used here in the alternative and linking sense, unless otherwise indicated. Like numbers refer to like elements.
    Overview
    In general, various embodiments of the present invention dispense with one or more of the traditionally accepted restrictions that govern the laminate structure and the methods for making them. Such restrictions, as will be shown, generally compromise the integrity and benefits of composite materials, while also making prediction of laminate strength extremely difficult, at best. Typical restrictions include, but are not limited to: symmetry, balance, fold number, relatively large angles between folds and the ten percent (10%) rule, as will be described later below.
    Generally, symmetry requires that the folded composition of a laminated structure looks exactly the same when inverted or turned around the axis of the laminated structure's median plane. In this way, the symmetrical laminated structures appear as a reflection or mirror image of themselves in relation to their axis of the median plane. Balance, although at least tangentially related to symmetry, additionally requires that for any number of individual fold orientations within the laminated structure, the orientations must always occur in positively (+) and negatively (-) oriented fold pairs.
    9/34
    In other words, for balance to exist, the number of positively oriented folds must always remain equal to the number of negatively oriented folds.
    In addition, the need for balance within the laminated structures, although desirable in the prior art, is valid only for a uniquely predefined set of reference axes; not for any other axes (for example, it is not constant). However, balanced laminated structures can remain beneficial for certain applications, such as those that will experience a fully reversible load (for example, aircraft fuselages, because, for example, an aircraft must also be able to turn left and right). right), wishing to have uniform deflection and / or rotation in at least two opposite directions. In fact, since balance is inherently necessary for the fully reversible torsional moment and shear load, the bend orientations can be manipulated and thus selected in a way that meets the particular design criteria in this regard. However, in other various applications, one may only want to minimize deflection and / or rotation in a particular direction so as not to eliminate other potentially desirable characteristics (eg lift force and the like). In such characteristic applications, non-compensated laminated structures may be preferable.
    The restriction on the number of folds arose as a result of the problems described above with symmetry and balance, since obtaining both requires a greater number of folds than could be used otherwise. Consider, for example, where four fold orientations are used when building a laminated composite structure, at least four fold folds can be chosen to maintain balance, while at least eight fold folds may be required to achieve symmetry . In conjunction with such restrictions on the number of folds, conventional laminated structures are further limited by a ten percent (10%) rule. As such is commonly defined and referred to in the art, this rule requires that each bend orientation must buy
    10/34 address at least ten percent of the total laminated structure. As a non-limiting example, a laminated structure [0 ° / ± 45 ° / 90 °] so limited may comprise twenty (20) folds, sixteen (16) of which are oriented at ± 45 °. For such a laminated structure to comply with the 10% rule, precisely two of the remaining four folds must be oriented at 0 °, with the two that still remain oriented at 90 °. Therefore, such a laminate would be 10% to 0, 80% to ± 45 ° and 10% at 90 °. As can be seen, the 10% rule alone significantly impacts the minimum thickness or caliber of such laminated structures, along with their minimum number of folds necessary to achieve balance and / or symmetry. Such a minimum caliber can be dictated not only by the anticipated need for load-hauling, but also by considerations of handling, effective stiffness or other non-structural requirements, which may be suitable for a particular application.
    In a variety of applications, and in particular for highly loaded structural applications, where the weight, thickness and integrity of laminated structures are invariably critical design factors, conventional limitations such as those identified and described above often prove to be costly. In response, various embodiments of the present invention dispense with one or more of these limitations, comprising asymmetric and non-compensated structural characteristics that can result in a degree of flexion-torsion coupling, at least with respect to individual sub-laminate modules, as will be defined later. below. Flexo-torsion coupling provides a reliable and predictive mechanism for controlling the deflection exhibited by the structure in response to combined bending and torsional forces.
    Due to their asymmetrical and non-compensated nature mentioned above, different modalities result in improved homogenization with less folds, often critical when aimed at minimizing weight and thickness without sacrificing structural integrity. The improved homogenization, as will be described in further details below, facilitates the convenient calculation of the combined effect of structure resistance
    11/34 laminated and keeps the material properties constant when tapered. In these and several other modalities, the number of fold orientations is minimized within the laminated structure by eliminating conventional provisions such as four-fold angles and the ten percent rule (10%). As a result, these and other modalities provide a faster, more efficient and less prone to laminate formation error, often using sub-laminate modules, which in turn improve the design and stacking processes for tapered structures.
    Such sublaminated modules, as will be described in further detail below, generally comprise a predefined set or group of individual fold folds that have multiple fold orientations. The sublaminated modules can be supplied in dry form, or alternatively in pre-impregnated form, as will be described later below. Each sub-laminated module, while involving multiple single-fold orientations, is treated as an isolated unit for the purpose of joining finished laminate product. In this way, as will be described later in detail below, the sublaminated modules function as basic building blocks for joining finished laminated products. The sublaminate modules can comprise any of a desired variety of fold folds, as long as they contain multiple fold orientations. However, it is desirable to minimize the number of folds of folds within the respective sub-laminate modules, as will be described in further details below.
    Various embodiments of the present invention can also comprise unbalanced structural characteristics. In these and other modalities, which may or may not incorporate certain characteristics as described above, the selection of particular fold angle orientations assists in structural rigidity and strength. The predictability of such parameters is improved, since at least some modalities select the bend orientation in which the deformations resulting from the combined moments of flexion and torsion imposed are controllable, a characteristic not
    12/34 present in balanced structures (for example, orthotropic and / or isotropic).
    Each of these characteristics, together with their respective benefits, will be described in more detail below, with reference to the representative figures, when necessary.
    Asymmetric Structural Features
    Returning initially to Figure 1, a symmetrical laminated structure 1 according to the prior art is illustrated. As can be better understood from this figure, the symmetrical laminated structure 1 is generally constructed with at least a four-fold orientation, which incorporate -45 °, 0 °, + 45 ° and 90 ° orientations. The four-fold orientation of the illustrated structure 1 is accomplished by the relative orientations of the sequential folds 2a, 2b, 2c and 2d. This sequence of folds, at least in the illustrated example, is repeated three times above and below the middle plane 6, as will be described in more detail below. Alternatively, three folds orientations are also common and usually dispensed with directions at 90 ° favor a configuration oriented at 0, + 45 °, -45 °. Remarkably contradictory, such configurations always maintain balance with an equal number of positively (+) and negative (-) oriented folds and this remains a common industrial practice. Such configurations maintain symmetry by stacking the folds of folds 2a, 2b, 2c and 2d in two groups of fold orientations 7a, 7b, each centered close to the axis of the middle plane 6 of the formed structure 1. Thus, when fully formed , the folds of folds appear as mirror images of each other, in relation to the axis of the median plane 6, thus maintaining symmetry, as previously described. For certain applications, the sublaminated modules 5, of the type previously described here, can be incorporated within the symmetrical laminated structure 1, each generally including at least four folds, i.e. 2a, 2b, 2c and 2d. Of course, it should be understood that prior art configurations (not shown) often include sublaminated modules that have eight (8) to ten (10) or more folds
    13/34 of folds, according to what is necessary to obtain not only balance, but also symmetry. Such restrictions, as can be expected, generally result in relatively thick laminated structures with an unnecessarily thick thickness to support the load.
    Turning now to Figure 2, an asymmetric laminated structure, unbalanced 10 according to various modalities is shown. As can be better understood from that figure, the laminated structure 10 may, in certain embodiments, comprise a plurality of first fold folds 12a, a plurality of second fold folds 12b, a first orientation 13 (see also Figure 3) and a second orientation 14 (see also Figure 3). The plurality of first fold folds 12a is, according to certain embodiments, separated by the respective fold folds of the second fold fold 12b. Each of the plurality of second fold folds 12b is indicated in Figure 1 without any marks, in order to distinguish them from the diagonally oriented marks on each of the plurality of the first fold folds 12a.
    Each of the plurality of the first folds 12a of Figure 2 can, according to various embodiments, be oriented in the first orientation 13 (see also Figure 3) with respect to each of the plurality of second folds 12b. Each of the plurality of second fold folds 12b, in turn, oriented in the second orientation 14, as will be described in more detail below with reference to at least Figure 3. Thus, the angle of the fold 19 (see Figure 3 ) can be formed between the respective orientations of the first and second folds of folds, such that the angle of the folds corresponds to an angular change between them. At least in the illustrated modalities, the angle of the fold 19 is 25 °, while in other modalities, the angle of the fold 19 can be in the range between about 10 ° to 40 °, which may be desirable for a particular application . In other modalities, the range can be between 15 ° to 30 °, depending on the desired result of the flexion-torsion coupling, as will be described in more detail below. The coupling component
    14/34 to shear of the flex-torsion coupling generally reaches a maximum value around a bend angle of 30 °. In other embodiments, it should be understood that the bend angle 19 can be any of a variety of acute angles (for example, less than 90 °), as will be described in more detail below with respect to various unbalanced structural characteristics of the laminated structure 10. Additionally, according to various modalities, the angle of the fold 19 can be a continuous variable, meaning that the values of the angles of the fold are not limited to being values of discrete integers.
    The laminated structure 10, like the laminated structures 1 of the prior art, may comprise, according to various modalities, an axis of the median plane 16. In certain embodiments, as illustrated at least in Figure 2, the first and second folds of stacked folds 12a, 12b do not need to be symmetrical close to the axis of the median plane 16. In other words, as noted previously, the plurality of first folds 12a are separated, each by their respective ones from the plurality of second folds 12b, while across the entire laminated structure 10. In contrast, as best understood from the comparison of Figures 1 and 2, at least two of the plurality of folds of folds 2d are positioned directly adjacent to each other (for example, not separated by any one of the folds of remaining folds 2a, 2b and / or 2c). In this way, the first and second stacked fold folds 12, 12b are generally configured according to various modalities in an asymmetric configuration.
    Returning to Figure 2, the laminated structure 10 according to various modalities can be stacked in a single orientation 17. In comparison with the heterogeneous laminated structure 1 of the prior art of at least Figure 1, in which the folds of folds must be stacked in two orientations 7a, 7b such that it remains centered close to the middle plane axis 6, the folds 12a, 12b of the laminated structure 10 can be stacked in sequential order with no relation to their orientation or their relative positioning on the axis of the median plane 16. In certain
    15/34 modalities, as will be described in more detail below, although the folds of folds may not be sequentially individually stacked, sub-laminate modules (see Figure 2 and later description of this), each comprising two or more folds of folds they are sequentially stacked themselves. Since individual sub-laminate modules can be stacked sequentially in this context, such a configuration provides a significant cost advantage when compared to the laborious and time-consuming process required by the symmetrical configuration of the prior art and creates a homogenized structure. The ability to stack folds sequentially (or sub-laminate modules, as described below below) also minimizes the risk of errors when positioning the folds themselves, while also greatly facilitating the tapering and detachment procedures of the fold, as will also be further described below.
    In addition to contributing to the cost advantages, the laminated structure 10 according to various modalities can additionally comprise a plurality of sublaminated modules 15, as previously defined and described here. Each of the sublaminated modules 15, as described at least in Figure 2, can generally comprise at least a first fold fold 12a and a second fold fold 12b, each having a different orientation generally, as described here in another place. In certain embodiments, the sub-laminate modules 15 form the basic building blocks for forming the laminated structure 10 and are thus generally treated as single units during the manufacturing process. In other words, like the building blocks, sublaminated modules 15 according to various modalities can be pre-assembled, which allows them to be directly stacked on top of each other through a deposition process on an axis (one- axis layup) that can substantially minimize reconfigurations.
    In at least those modalities that comprise the sublaminated modules 15 as described in Figure 2, the deposition process
    16/34 on one axis can be up to seven (7) times faster than the conventional four-axis deposition employed with the prior art of laminated structures 1, although it should be understood that varying degrees of improved efficiency can be achieved, as can be desired for a particular application. Alternative modalities, as will be described in more detail below, may involve the rotation (for example, inversion or folding) of all other sublaminated modules 15 to form a balanced laminate (for example, a [0 ° / ± fold angle 19 configuration] / 0 °), which reaches a fully reversible torsion moment or full load (for example, which has magnitudes from -1 to +1), as may be desirable for a particular application. In this way, the basic building block, that is, each sub-laminate module 15 can be used according to certain modalities not only to form unbalanced laminated structures as shown in Figure 2, but also balanced laminated structures, both through a process deposition on an axis. In additional modes, when the angle of the fold 19 is 45 °, as in the sub-laminated module [0/45], the sub-laminated module 5 can be inverted or folded in the [-45/90] configuration. By stacking these two sublaminates (one rotated and the other not) according to various modalities, an almost isotropic laminated structure of [0 ° / ± 45 ° / 90 °] can be obtained. Such a configuration can be formed, according to certain modalities, through a deposition in two axes since at least one of the sublaminated modules is rotated by 90 degrees. It should be understood, however, that in any of these and still other modalities, such deposition processes generally achieve relatively comparable and desirable efficiencies, at least in part avoiding off-axis accumulations (for example, accumulations with angle + bend orientations) 19 or angle - fold 19).
    With particular reference to Figure 3, the formation, according to various modalities, of an exemplary laminated structure 10 of at least two sublaminated modules 15, is illustrated. Top left of Figure 3, a first module 15, comprising a single first
    17/34 fold fold 12a and a single second fold fold 12b are illustrated. A machine 1000, as generally understood from at least Figure 10, to have the direction of the machine 17, can be aligned with a global axis of the sub-laminated module 15. In certain embodiments, the direction of the machine 17 can be along the 0 axis corresponding to an axis of bending at least one ply (e.g., the second fold folds 12b of Figure 3), which further enhances the cost and efficiency benefits of such modules 15. such machine direction 17 will typically result in a machine setting of [0/25] for those modes that have a 19 ° bend angle of 25 °. It should be understood, however, that in other embodiments, the direction of the machine 17 does not need to be oriented along the 0 o axis, as may be desirable for a particular application. As a non-limiting example, machine direction 17 can be configured along the 60 ° axis, resulting in a machine configuration of [60/85] for those modes that have a 25 ° bend angle. Most notably, it should be understood that the difference between the configuration angles, regardless of their respective values, will substantially correlate, according to various modalities, to the desired bend angle 19.
    As can also be understood from Figure 3, the first module 15 can be combined with a second module 15, which also comprises a first and second single folds 12a, 12b. The resulting laminated structure 10 can thus be formed, according to certain modalities, by sequentially stacking the respective modules 15, each having at least one common axis aligned with the direction of the run 17. Although at least the illustrated modules 15 comprise two folds distinct from folds, in other embodiments, it can be envisaged that the modules may comprise two or more folds of each respective fold fold 12a, 12b. However, it should be understood that the thickness of the modules 15 should be minimized in general and those that comprise the two distinct folds of folds 12a, 12b provide the highest degree of flexibility and efficiency throughout the process
    18/34 deposition (eg stacking), as will be described in detail below.
    Various embodiments of the sublaminated modules 15 can, as previously discussed, be pre-formed (e.g., sewn) and comprise at least one first and second fold fold 12a, 12b. As will be understood later from at least Figure 3, an additional advantage of such modules 15 is their ability to be rotated (for example, inverted and / or bent) close to at least their common axis aligned with the direction of the race 17 ( as illustrated, the shaft 12b of the second fold folds that is, in a non - limiting example, the 0 axis). Thus, for those modalities that seek to maintain balance, as will be described in more detail below, the sublaminated modules 15 can be inverted, or alternatively, simply folded in relation to this axis, such that the axes of the respective first folds of folds 12a are oriented positively (+) and negatively (-), respectively. As a non-limiting example in which the first folds of folds 12a are oriented at an angle of 25 °, folding or rotating a sublaminate sheet over itself can ultimately result in a laminated structure formed 10 with a [0 / + 25 ° / -25 °] configuration, as may be desirable for a particular application.
    It should be understood that in certain of these modalities that have rotated modules, any fold fold sewing within the modules (as will be described later) can occur before any invention or folding of a sheet, with any necessary stitching of the two rotated modules occurring afterwards . It is clear that it should be understood that certain modalities may not need balance, in which case only positively (+) oriented folds 12a (or alternatively, only negatively oriented (-)) folds can be used. As such, the rotation (e.g., inversion or folding) of the sublaminated modules 15 may, at least in these modalities, be unnecessary or even undesirable. Subsequently, in other modalities, it may be desirable for a majority of sub-laminate modules 15 to remain
    19/34 unbalanced, while the global laminated structure formed in this way is, as a whole, balanced by the rotation (for example, inversion or folding) of a certain percentage of the modules, as previously described here.
    It should be noted that according to various modalities comprising the sublaminated modules 15, the benefits of the accumulation described above (for example, stacking) apply similarly when trying to create tapered surfaces in a fold structure 10, formed in the final analysis. With reference to Figure 1, it can be seen that the creation of a tapered surface on the laminated structure 1 of the prior art, which has its multiple fold folds, multiple fold orientations and symmetry in the middle plane, are not only time consuming and laborious, but also extremely prone to error. In particular, if an upper fold fold is reduced, a lower fold fold will also need to be reduced to maintain symmetry; but if nothing reduces it may result in an unbalanced structure. Additionally, not reducing anything else can inherently alter the structural composition of the laminated structure 1, potentially impacting the resistance characteristics associated with it. As such, folds of additional folds will need to be reduced, often limiting the length and degree of taper obtainable.
    Additional considerations were also necessary when tapering conventional structures, particularly with respect to the relative order in which the respective folds are reduced, along with the distance that must be maintained between successive reduced folds. In contrast, the tapered surfaces can be formed in certain modalities of the laminated structure 10 by releasing successive sublaminated modules 15, individually or in multiples, as may be desirable for a particular application. Being homogenized, as will be described later below, the reduced sub-laminated module 15 can be located on the outside, the tool side or inside the laminate, without considering symmetry, For those structures that have at least sixteen (16)
    20/34 sublaminated modules 15 (as described later below), each module can be reduced in steps of 0.125 mm, with a total distance between successive reductions being 1.0 mm. Tapered reductions in these and other modalities can be linear, non-linear, uni or two-dimensional and / or squared, each of which at least partly contributes to a reduction in the degree of fold waste found conventionally otherwise with fold reductions oriented at an angle.
    Additionally, regardless of the location or the number of reduced sub-laminated modules 15, the structural composition of the laminated structure 10 remains the same throughout the process. For a heterogeneous laminate like the one in Figure 1, as opposed to a homogeneous laminate (as will be described later below) like the one in Figure 2, each fold reduction, for example, removing the outermost 45 ° fold, will change the composition inherent in the global laminated structure. As individual folds are reduced as tapering occurs, the thickness of the laminate and its properties will change. Conventional heterogeneous laminate designs like the one in Figure 1, generally avoid such laminate alteration characteristics by multiple fold fold reduction in precise succession over precise fold lengths, all of which result in less than optimal tapering processes. In contrast, when a laminated structure 10 according to various modalities as illustrated at least in Figure 2 is tapered, each successive fold reduction can occur at any location, with the remaining laminated structure being structurally unchanged. In other words, in at least certain embodiments, the overall structural characteristics of the laminate do not vary over the length of the fold, even without the complex tapering processes conventionally required.
    Returning to Figure 4, with continued reference to Figure 1, an additionally related advantage of asymmetric laminated structures 10 is illustrated, that is, homogenization, which among other things, facilitates the tapering procedures previously described. In particular,
    21/34 the various modalities of laminated and triangulated laminated structures 10, 110 are illustrated in Figure 4 substantially adjacent to laminated structures 1, 210 of the respective prior art. Triangulated laminated structures 110 can be substantially configured as previously described here with respect to laminated structures beaded 10, but with distinction that structures 110 according to various modalities incorporate the previously described folded configuration of module 15 in order to maintain balance, where this may be desirable. However, it should be understood that in other modalities, the triangulated laminated structures 110 can be configured substantially different in part or in whole, when compared with the structures 10.
    Returning to Figure 4, as a non-limiting example, the comparison of structure 110 with respect to structure 1 reveals the improved homogenization of the first when viewed as a whole. In fact, according to certain modalities, the repeated alternation of the folds of folds 12a, 12b addresses complete homogenization. From a practical perspective, complete homogenization means that the structural strength characteristics of the structure, among other properties, can be predicted, manipulated and calculated in relation to the laminated structure as a whole. In contrast, for heterogeneous structures in the prior art, such characteristics had to be treated on a fold-by-fold basis, resulting not only in errors and inefficiencies, but also in the potential impairment of structural integrity, as previously described with regard to tapering procedures. prior art.
    The biangulated modality of Figure 4 addresses complete homogenization with only thirty-two (32) repetitions (for example, 32 folds of individual folds). In those modalities that comprise sublaminated modules 15, homogenization can be achieved with only sixteen (16) modules (notably, still 32 folds of individual folds). It must be understood, however, that other modalities can still be foreseen with any number of repetitions necessary for homogenization, it should be kept relatively thin and cheap in relation to
    22/34 to laminated structures 1 of the prior art. In this regard, it should be understood that various modalities of the present invention, based at least in part on their sublaminated modules and unbalanced biangulated configurations, achieve complete homogenization with much finer laminated structures otherwise available in the prior art due to the least in part to the restrictions previously described.
    As will be described in more detail below in the portion describing non-crimped fabric, folds 12a, 12b, according to various embodiments, can be formed from a variety of materials and in a variety of ways. At least in certain embodiments, however, the folds 12a, 12b can have a thickness that is at least less than the folds of conventional laminated structures 1 (e.g. 2a, 2b, 2c and 2d) although such distinctions in thickness are not specifically illustrated in the various figures. Such thickness of the folds of folds 12a, 12b allows the structure 110 to obtain complete homogeneity with the number of the module and / or the fold fold repetitions, as described above.
    As a non-limiting example and as will be described in detail later below, the folds 12a, 12b can each have a thickness of approximately 0.0625 millimeters, which gives them a weight of approximately 75 g / m 2 . Of course, thinner or thicker and / or heavier or lighter folds 12a, 12b folds can be envisaged in other embodiments, depending on any of a variety of considerations, such as homogeneity, which may be desirable for a particular application.
    Turning to Figure 5, another advantage of asymmetric laminated structures 10, 110 and more particularly in their homogenization, is illustrated. In particular, various modalities of laminated and triangulated laminated structures 10, 110 exhibit a decreased degree of flexible stress (e.g. deformation), largely due to curing over time, than that exhibited by laminated structures 1 of the prior art, such as also illustrated. As an initial antecedent, the laminated structure 1 of the
    23/34 the previous ca is noted as [0 / ± 45 °], which following the previously described restrictions will require bending orientations of 0 o , + 45 ° and -45 ° The triangulated laminated structure 110 is noted as [0 / 25 ° / 0], which similarly maintains a fold balance of + 25 ° and -25 °. The laminated beaded structure 10 is noted as [0/25 °], which results in unbalanced characteristics, as previously described here.
    In certain of these and other embodiments, the degree of flexible stress or deformation in the long run approaches zero when a laminated structure contains a sufficient number of folds of folds. This relationship is later linked to the degree of homogenization, which roughly corresponds to the zero stress or strain approach. As best understood from the leftmost column of Figure 5, the laminated structure 1 of the prior art has been known to exhibit minimal deformation with at least 72 folds having a total thickness of 4.5 millimeters. The triangular laminated structure 100 (middle column of Figure 5) exhibits improved characteristics, reaching minimum deformation with approximately 64 folds of folds that have a total thickness of 4.0 millimeters. In contrast, laminated structure 10, as illustrated in the rightmost column of Figure 5, achieves characteristics comparable to those of the prior art and triangulated laminates, but with only 32 folds of folds (or alternatively, 16 folds of sublaminated modules) and one total thickness of approximately 2.0 mm. Thus, few folding angles and / or finer folds in the sublaminates according to various modalities allow the laminated structure to be homogenized in a total thickness less than previously obtained.
    In addition, considering homogenization, laminated structures 1 of the prior art require more comparable folds, up to 72 folds, to substantially eliminate deformation. Such high fold counts are primarily due to the symmetry, balance and restrictions of the 10 percent rule previously described, requiring such laminates to have sublaminated modules of six or more folds each.
    24/34 one (for example, two or more of each 0 o , + 45 ° and -45 °). As the flexible stress or strain is minimized with the approximately twelve (12) exemplifying sublaminated modules, this results in the 72 individual folds mentioned above. The laminated structure 10 overcomes the deficiencies in this respect by reducing the size of its sublaminated modules 15 to two folds folds (against six), resulting in minimal flexible strain or deformation with a mere 16 sublaminated modules or 32 folds folds. In this way, the laminated structure 10 can, according to various modalities, have an overall thickness less than half that of the conventional laminated structures 1. In at least in the illustrated embodiment, the relative thicknesses are approximately 2.0 millimeters and 4 , 5 mm, although in still other modalities, several relative thicknesses can be predicted. Without such six or more sublaminated modules, such relatively thin thicknesses of the laminated structure are viable in this and yet other modalities, by using a form of unfolded fabric, which is, in certain modalities, itself spread and tuned, for example , by mechanical processes as will be described in more detail below.
    Unbalanced Structural Features
    As can be understood from at least Figure 3, each of the plurality of first folds 12a can be, according to various modalities, oriented in the first direction orientation 13 with respect to each of the second folds 12b , which can be oriented in the second direction orientation 14. In this way, the relative orientations of the first and second folds 12a, 12b define a fold angle19, which can be varied as will be described here to obtain certain desirable structural characteristics. Such manipulation of the fold angle19 can, according to certain modalities, substantially minimize the long-term risks of deflection, rotation and warping of composite materials formed from folds of sub-laminate 110 formed from folds of folds 12a, 12b.
    Returning for a moment to Figure 2, in this context, should
    25/34 it should be understood that in conventional laminated structures 1, maintaining the balance of positively (+) and negatively (-) oriented folds, that is, an equal number of positive and negative fold angles 19, was considered critical. Such configurations, as commonly known and understood in the art, create orthotropic and / or isotropic structures, each of which exhibits inherently unbound bending and torsion deformations. Laminate structures that have unbound flexion-torsion, although traditionally preferable for their analogous properties with previously used metals (eg aluminum), fail substantially to take advantage of the dynamic relationship that exists between flexion and torsion movements that can be experienced by such structures. The dynamic relationship is often referred to as flexo-torsion coupling in a variety of applications or aeroelastic adaptation in at least aerospace and wind turbine related applications. In any of these and still other embodiments, it should be appreciated that at least the shear coupling component of the flexor-torsion coupling generally reaches a maximum value around a 30 ° bend angle.
    As a non-limiting example of unbound torsion of conventionally balanced laminated structures, consider laminated structure 1 of the type illustrated in at least Figure 1. As can be understood at least in part from Figure 6A, if the structure has been subjected to a bending force (for example, P), the structure will exhibit only a bending behavior. No torsional angles (for example, torsional behavior) can be introduced, although this acts on unbalanced structures to minimize the degree of deflection imposed only by isolated flexion or even combined flexion and torsion, as will be described in more detail below. Likewise, subjecting the laminated structure 1 to a complete torsional force (for example, T), as can be understood at least in part from Figure 6A, will result only in the torsional behavior, due to the non-coupling or absence of flexion-torsion relationship that might otherwise
    26/34 would have weakened or at least partially offset the imposed shear.
    In total contrast to such balanced configurations of conventional laminated structures 1, laminated structure 110 according to various modalities, is intentionally unbalanced in nature in order to take advantage of the aforementioned dynamic relationship between the flexing and twisting movements of the laminated structure. In certain embodiments, it should be understood that, alternatively, at least the sublaminated modules 15 (see Figure 3) are intentionally unbalanced to obtain these benefits, the laminated structure 110 can be balanced, as desirable for a particular application, as previously described here. In at least those unbalanced or balanced embodiments, the laminated structure 110 may incorporate at least one acute angle of the fold 19. In certain embodiments, the acute angle of the fold 19 may be approximately + or - 25 °, while in other embodiments , the angle of the fold 19 can be in the range between about 10 ° to 40 ° or, alternatively, between about 15 ° to 30 °, as may be desirable for a particular application. In at least those unbalanced embodiments, the acute fold angle 19 can be any of a variety of angles between 0 and 90 °, while in at least those balanced modes, acute fold angle is generally less than 45 °.
    Returning to Figures 6A and 6B, the flexo-torsion coupling can be further understood as generally referred to as Z coefficient. The Z coefficient according to various modalities can be defined and measured analytically by the progressive change in a torsion angle in relation to a flexion angle, each of which can be understood from the visualization of the three sequential illustrations of Figure 6A. In fact, as a non-limiting example illustrated at least by the rightmost illustration in Figure 6A, the application of both the bending force P and the torsional force T on the laminated structure 110 may, according to certain modalities, result at a minimum degree of deflection, up to 0 o , depending on the inherent bend angle 19 and the structural material of the structure
    27/34 ra 110, as will be described in more detail below. In any of these cases and in still other embodiments, the shear coupling component of the flexion-torsion coupling generally reaches a maximum value around a bend angle of 30 °.
    With particular reference to Figure 6B, it should be understood that according to certain modalities of the laminated structure 110, such as the angle of the unbalanced fold 19 (for example, as previously described here) approaches a relatively narrow angle of less than or equal to 25 °, the effect of the coupled flexion-torsion Z coefficient can be additionally perceived. In other words, the combined degree of deflection created by both the bending and twisting movements imposed on the structure 110 can be manipulated to substantially neutralize each other (e.g., zeroing), as may be desirable for a particular application. In other embodiments, it should be understood that alternative, still relatively narrow bending angles 19 (for example, the non-limiting examples of 10 ° to 40 ° or 15 ° to 30 °) may be desirable, although they do not completely involve neutralizing forces . However, in certain embodiments, such bending angles 19 can provide advantages by providing a predictable and reliable degree of the desired deflection or rotation, as may be beneficial for a particular application.
    Turning now to Figure 7, for the purposes of a non-limiting example, it can be seen that certain narrow and unbalanced bending angles 19 minimize the degree of deflection 50 experienced by the laminated structure 110 in response to the applied bending and torsional forces. As can be seen, as the bend angle 19 is approximately 25 °, deflection 50 is minimized. The mathematical predictability of such behavior, by pre-selecting bend angles 19 in particular, can prove to be critical in certain applications such as, for example, the manufacture and construction of laminated structures 110 for use in long and thin structural applications, such as wind turbine blades, helicopter rotor folds, aircraft wing surfaces or the like. As a
    28/34 non-limiting example, minimizing deflection can enable the operation of such long, thin folds closer to the towers on which they are erected, saving material costs, increasing speed and contributing to increase the turbine megawatt production. As another non-limiting example, minimizing and / or varying the degree of deflection of the tip 50, may prove to be critical in aerospace and wind turbine-related applications, where the deflection required by an aircraft wing can significantly impact and / or alter the lifting forces, drag forces and / or total loads experienced by the wing. Any of a variety of other applications can exist, including non-limiting examples of rotors or other aerodynamic products.
    Turning now to Figure 8, a pair of complementary graphs illustrates the exemplary microfissure zones 510, 610 in a laminated composite structure 501 (analogous to structure 1), as previously described here) and an unbalanced asymmetric laminated structure 601 (analogous to structures 10, 110, as previously described here). The graphs illustrate the respective failure zones of the first fold (FPF) 525, 625, which, as commonly known and understood in the art, represent the maximum degree of stress imposed on which the first of a plurality of folds within the laminated structure experiences first a failure event (for example, rupture, delamination, etc.). The graphs also illustrate the respective failure zones of the last fold (LPF) 520, 620, which, as commonly known and understood in the art, represent the maximum degree of stress imposed in which the first of a plurality of folds within the laminated structure experiences failure event first.
    As can be seen in Figure 8, the bends of the conventional structure 501 experience a first bend failure (FPF) 525 under a maximum imposed stress δι of approximately 400 MPa, whereas the failure of the last bend (LPF) does not generally occur until an imposed strain δι of approximately 750 MPa is found. As such, conventional structures such as 501 (see also 1 in Figure 1) may encounter an intense degree of micro-cracks in the matrix for the duration of
    29/34 any imposition of force between the failure of the first fold and the failure of the last fold. In contrast, as can be seen with reference to laminated structure 601 (analogous to 10 and 110, as previously described), FPF and LPF occur almost simultaneously, at approximately 1350 MPa. Therefore, not only is the structural integrity and strength of laminated structures such as 601 greatly improved, the reduced differential and in some cases eliminated between FPF and LPF significantly minimizes micro-cracking. This can be seen illustratively in Figure 8 with reference to the difference in the relative areas of zone 510 and zone 610, the latter of which essentially eliminates the possibility of prolonged micro-cracking, thereby improving structural strength. While some designs are tolerant of micro-cracking and do not consider it to be a failure of the laminate composite, other designs believe that no micro-cracking should be tolerated. With the modalities of the present invention, FPF and LPF become almost of equal duration, thus eliminating micro-cracking and making the debate about whether micro-cracking is acceptable controversial.
    Non-Olympian Fabric
    According to various modalities, the laminated structure 10 can be constructed primarily from non-crimped fabric (NCF), which is commonly known and understood in the art for providing a plausible balance between cost, handling and performance. NCF is a class of composite materials, which are made with a plurality of unidirectional fold folds, each differently oriented and substantially joined by a transverse seam process, as generally illustrated at least in Figure 9. The transverse seam, as applied generally, it keeps the respective folds together, while allowing minimal degrees of freedom between immediately adjacent folds. In particular contrast to several other commonly known and used fabrics, the NCF cross stitching substantially eliminates crimping of the carbon fabric (for example, making it an uncrimped configuration), which reduces mechanical properties and creates insufficiencies due to
    30/34 to misalignment and the like. Although the cross-stitching process has been described, several alternative processes can be used to join the individual folds in relation to each other. As non-limiting examples, the folds can be joined together using other techniques, such as gluing.
    In various embodiments comprising a cross-stitching process, as previously described, a variety of yarn types can be used, depending on the desired application. In certain embodiments, it may be beneficial to sew the thread with the lightest amount of stitching possible. In these and other embodiments, the yarn may comprise a 33dtex RES yarn with an E5 seam gauge and a 3.4 mm long stitch. In such embodiments, the weight of the seam area is approximately 2.0 g / m 2 . In other embodiments, any of a variety of yarns based on high temperature polyamide or polyimide can be used. In other embodiments, any of a variety of combinations of sewing gauges, yarn materials and the like can be used, as may be desirable for a particular application within the scope of the present invention.
    In various embodiments of the laminated structure 10 that incorporates NCF, the respective unidirectional folds can comprise unidirectional carbon fiber folds and 25 ° folds.> As previously described here, sublaminated modules 15 can be formed with each one, at least some modalities, comprising a single fold of unidirectional carbon fiber and a single fold of + 25 °, thus facilitating a deposition on one axis or alternatively a deposition on two axes folded for normal biaxial loading, each eliminating the need for folds of folds accumulated outside the axis. Other modalities may alternatively be configured with various materials (for example, fiberglass or an electrical conductor such as copper wire) and / or relatively narrow angles or orientation (for example, as commonly known and understood in the art to be analogous), provided that the limitations and parameters as previously described here
    31/34 remain satisfied. As a non-limiting example, in the context of wind turbine folds, laminated structure 10 may, instead of carbon fiber folds, incorporate fiberglass folds, as may be desirable in cost or other considerations, as may be the case. In other embodiments, hybridization may be desirable, leading to a mixture of any of the variety of combinations of carbon fiber, glass fiber and / or periodically spaced electrical conductor (for example, copper wire, as protection from lightning) or still other materials like folds of folds.
    It should be further understood that according to various embodiments, the folds 12a, 12b of the laminated structure 10 can be formed by spreading a strand of carbon fibers or similar strands of any desired material, as is commonly known and understood in the art practice , at least in relation to balanced and symmetrical laminates. At least US Patent Application Pub No. 2006/0093802 describes several yarn dissemination practices and is therefore incorporated by reference in its entirety. The spreading of the threads in this way makes it possible for certain embodiments of the laminated structure 10 to comprise extremely fine fold folds 12a, 12b, each having a thickness of approximately 0.0625 millimeters and a weight of approximately 75 g / m 2 . In these and other embodiments with folds of folds of such thickness, homogeneity, as previously described here, can be obtained with a laminated structure 10 which has a total thickness of approximately 2.0 millimeters. However, it should be understood that any of a variety of thicknesses for each fold fold and, therefore, each laminated structure, can be predicted, provided that it is generally thinner than at least conventional unidirectional fiber, which has a thickness approximately 0.25 mm.
    In additional embodiments, the folds of folds 12a, 12b of the laminated structure 10 formed by whatever material may be additionally of varying thickness, as may be desirable for a
    32/34 application in particular. As a non-limiting example, the respective fold folds in certain embodiments can vary anywhere from approximately 0.02 millimeters to 0.08 millimeters, although in other embodiments, the thickness of the fold can vary up to 0.12 millimeters, as may be desirable for a particular application.
    Exemplary Constructions
    Laminate structures 10 according to various embodiments, as described herein, can be used in a variety of applications. As non-limiting examples, these can include rotating folds (for example, wind turbine, helicopter rotor, etc.), aircraft surfaces such as wings and fuselages and any of a variety of aerospace surfaces. In any of these applications, not only an asymmetric and / or unbalanced configuration may be desirable, as described herein, but further hybridizations of them may be useful. In other words, although orientations of 10 ° to approximately 40 ° (or approximately 15 ° to 25 ° or even any acute angle less than 90 °, as may be the case) have been described, certain modalities may incorporate one or more orientations, depending on a variety of factors such as positioning on the surface.
    As a non-limiting example, a wing-like structure can have top and bottom coatings with an orientation at [0/25 °], with a region superimposed on its front and / or rear edges with an orientation at [0 / ± 25 ° / 0] (which corresponds, for example, to the rotation settings of the sub-laminated module (for example, inverted or folded), previously described here). Such herringbone designs, as commonly referred to, can also be considered horizontal beams in the form of channels or sections with combinations of [0/25 °] on nets and fishbone on the roofs (or vice versa), as can be desirable in a particular application. In addition, for cylindrical structures such as tubes, vases, fuselages, several modalities can comprise a bending orientation of a helical taper configuration, the exact angle of which depends on the material of the bend used and on various conditions of
    33/34 load as described herein.
    Subsequently, it should be understood that the traditional independent contributions of the substructure (for example, folds of folds and / or sublaminated modules) and covering for the respective portions of a stiffened panel (for example, a portion of the surface of the wing or fold) can according to various modalities, be completely replaced by fully coupled anisotropic components (e.g. laminate 10) as described herein. In certain embodiments, the complete laminated structure 10 can be configured such that it is fully coupled and anisotropic, while in other embodiments, the individual components (for example, folds of folds and / or sublaminated modules 15) can each be configured as completely coupled and anisotropic, although the entire rigid panel formed is not. Various combinations and alternatives can be envisaged, as within the scope of the various modalities described here.
    Several options for consolidating laminated structures (for example, folds of folds and / or sublaminated modules) also exist, as they are commonly known and understood in the art. Fabrics within the folds of folds and / or sublaminated modules can be supplied as dry fibers and or pre-impregnated with resin (for example, prepreg). Non-limiting examples of each, as are commonly known and understood in the art, include non-limiting examples of Resin Transfer Molding, Vacuum Resin Transfer Molding, Heated Vacuum Assisted Resin Transfer Molding, Processes outside the Autoclave and Infusion of Resin Film.
    In addition, although several improved tapering procedures have been previously described here, it should be understood that any of a variety of procedures employed, in addition to contributing at least in part to the improved time-based efficiencies, additionally reduce the amount of material needed to the manufacture of several laminated structures that have square edges. As a non-limiting example, consider the laminated structure 1
    34/34 of Figure 1, which contains a plurality of folds, at least some of which are oriented at + 45 ° or -45 °. When conventionally complex tapering procedures are applied, such folds were generally laminated individually, as opposed to the improved sublaminated modules described herein. When so laminated, any fold material that protrudes from the square edge of the conical location would be wasted. According to the lamination procedures employed with laminated structures 110, such as the one illustrated in Figure 2, the detachment of the folds is not from the fold of individual fold, but by the sub-laminated module. And although such modules sublaminated according to certain modalities involve some portions of angled folds (for example, 10 ° to 40 ° or alternatively 25 °), the modules generally comprise relatively narrow angles, which result in a lesser degree of waste when tapering. a laminated structure that has square edges when compared to the degree of waste conventionally produced.
    Conclusion
    Various modifications and other modalities of the invention described herein will come to the minds of those skilled in the technique to which these inventions belong, having the benefit of the teachings presented in the preceding descriptions and attached figures. Therefore, it should be understood that the inventions are not limited to the specific modalities described and that modifications and other modalities are intended to be included within the scope of the appended claims. Although specific expressions are used in this, they are used in a generic and descriptive sense only and not for the purpose of limitation.
    权利要求:
    Claims (10)
    [1]
    1. Sub-laminated module (5, 15) for use in forming a laminated composite (10,110), the sub-laminated module (5, 15) characterized by comprising:
    a primary longitudinal axis;
    a first fold (2a, 12a) comprising fibers extending in a first orientation (7a, 13), the fibers of the first fold (2a, 12a) comprising a plurality of scattered strands lying adjacent to each other in a non-configurable configuration crimped;
    a second fold (2b, 12b) comprising fibers extending in a second orientation (7b, 14), the fibers of the second fold (2b, 12b) comprising a plurality of scattered strands lying adjacent to each other in a non-configurable configuration crimped; and an acute angle (19) defined by the relative compensation between the first and the second orientations, the acute angle (19) being less than 90 ° and defining an unbalanced structure of the sublaminated fold, in which the first orientation and the second orientation they are also oriented in relation to the primary longitudinal axis of the sublaminated module (5, 15), so that an axial displacement of the first orientation in relation to the primary longitudinal axis is different from an axial displacement of the second orientation in relation to the primary longitudinal axis, the the first fold (2a, 12a) and the second fold (2b, 12b) are secured relative to each other by means of a plurality of transverse orientation points configured to define at least partially the uncrimped configuration of the plurality of strands scattered from the first and second folds (2a, 12a, 2b, 12b), and the primary longitudinal axis corresponds to a machine direction (17) in which the sub-laminated module (5, 15) was formed.
    [2]
    2. Sub-laminated module (5, 15), according to claim 1, characterized by the fact that the sub-laminated module (5, 15) is folded in half on itself, in relation to an axis that extends in the second
    Petition 870190108016, of 10/24/2019, p. 4/22
    2/4 orientation (7b, 14), such that:
    the first fold (2a, 12a) forms a first and a fourth fold layer; and the second fold (2b, 12b) forms a second and a third fold layer, the third fold comprising fibers extending in the second orientation (7b, 14) and the fourth fold comprising fibers extending in a third orientation , the third orientation being opposite that of the first orientation (7a, 13) in relation to the second orientation (7b, 14).
    [3]
    3. Laminated composite structure (10,110), the laminated composite structure (10,110) characterized by comprising:
    a plurality of sublaminated modules (5, 15) according to any one of the preceding claims.
    [4]
    4. Laminated composite structure (10,110) according to claim 3, characterized in that the structure comprises at least sixteen sublaminated modules (5, 15) in order to form a homogeneous composite material.
    [5]
    5. Method for making a sub-laminated module (5, 15) for use in forming a laminated composite (10,110), the method being characterized by comprising the steps of:
    spread a set of wires consisting of:
    a first yarn comprising a plurality of fibers to form a first fold (2a, 12a);
    a second yarn comprising a plurality of fibers to form a second fold (2b, 12b);
    positioning the plurality of fibers of the first yarn in a first orientation (7a, 13);
    positioning the plurality of fibers of the second yarn in a second orientation (7b, 14); the first and second orientations defined an acute angle (19) between them, the acute angle (19) being less than 90 ° and defining an unbalanced structure of the sub-laminate fold, in which the first orientation and the second orientation are still oriented in relation to the axis
    Petition 870190108016, of 10/24/2019, p. 5/22
    3/4 primary longitudinal of the sub-laminated module, so that an axial displacement of the first orientation in relation to the primary longitudinal axis is different from an axial displacement of the second orientation in relation to the primary longitudinal axis; the primary longitudinal axis corresponding to a machine direction (17) in which the sub-laminated module is formed by stacking the second fold (2b, 12b) and the first fold (2a, 12a) adjacent to each other;
    sew the first fold (2a, 12a) and the second fold (2b, 12b) in relation to each other in an uncrimped configuration.
    [6]
    6. Method for manufacturing a sub-laminated module (5, 15), according to claim 5, characterized by the fact that during the positioning steps:
    the first orientation (7a, 13) is the direction of the machine; and the acute angle (19) is within a range between 10 ° and 40 °, being 25 °.
    [7]
    7. Method for manufacturing a sub-laminated module (5, 15) according to any one of the preceding claims, characterized in that it comprises the steps of:
    forming a plurality of sublaminated modules (5, 15); stacking the plurality of sublaminated modules (5, 15) adjacent to each other;
    joining the plurality of sub-laminate folds in relation to each other in an uncrimped configuration; and sequentially depositing the respectively joined plurality of sublaminated folds to form the laminated composite structure (10,110).
    [8]
    Method for making a sub-laminated module (5, 15) according to claim 7, characterized in that it comprises, before the stacking step, the plurality of sublaminated modules (5, 15) adjacent to each other, the step of: folding each one of the plurality of sublaminated modules (5, 15) in half over themselves, in relation to an axis that extends in the second orientation (7b, 14), such that:
    Petition 870190108016, of 10/24/2019, p. 6/22
    4/4 the first fold (2a, 12a) forms a first and a fourth fold layer; and the second fold (2b, 12b) forms a second and a third fold layer, wherein the third fold layer comprises fibers extending in the second orientation (7b, 14), the fourth fold layer comprises fibers extending in a third orientation, the third orientation being opposite to that of the first orientation (7a, 13) in relation to the second orientation (7b, 14).
    [9]
    Method for making a sub-laminated module (5, 15) according to claim 7, characterized in that it comprises before the step of stacking each the plurality of sublaminate modules (5, 15) adjacent to each other, the step of turning by at least a first subset of the plurality of sublaminated modules (5, 15) 90 ° with respect to the first orientation (7a, 13).
    [10]
    Method for making a sub-laminated module (5, 15) according to claim 7, characterized in that it further comprises, subsequent to the step of sequentially depositing the respective plurality of sublaminate folds joined together to form the laminated composite structure (10,110), the stage of:
    sequentially depositing one or more of the respectively ordered sublaminated modules (5, 15) so as to form a tapered surface on the laminated composite structure (10,110), in which the sequential deposition of one or more sublaminated modules (5, 15) does not change the material composition of the laminated composite structure (10,110).
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    同族专利:
    公开号 | 公开日
    CN103429422B|2016-08-31|
    ES2680620T3|2018-09-10|
    CA2824216C|2018-01-23|
    EP2663450A1|2013-11-20|
    CA2824216A1|2012-07-19|
    CA2988760A1|2012-07-19|
    US20120177872A1|2012-07-12|
    WO2012096696A1|2012-07-19|
    BR112013017815A2|2016-10-11|
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    US20160159013A1|2016-06-09|
    US10589474B2|2020-03-17|
    US9296174B2|2016-03-29|
    CN103429422A|2013-12-04|
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    法律状态:
    2018-03-27| B25G| Requested change of headquarter approved|Owner name: COMPAGINE CHOMARAT (FR) , THE BOARD OF TRUSTEES OF |
    2018-04-03| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-08-20| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-03-10| B09A| Decision: intention to grant|
    2020-05-12| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 12/10/2011, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US201161432011P| true| 2011-01-12|2011-01-12|
    US61/432,011|2011-01-12|
    PCT/US2011/056035|WO2012096696A1|2011-01-12|2011-10-12|Composite laminated structures and methods for manufacturing and using the same|
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