• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    LONGARINE AND MULTIPLE SUPPORT WING COATING The present invention relates to an apparatus and processes providing the construction of wing sections having multiple support wing spars. According to one aspect of the description provided in this specification, an aircraft wing can be constructed by applying one or more layers of composite material to several wing mandrels. Wing chucks, when placed together, generate the shape of the wing. After the layers of composite material have been applied to each individual mandrel, the mandrels are brought into contact with each other. Then, the mandrels are compressed using the wing surface tooling, applied to the various wing mandrels. The composite material is then cured. After curing, the surface tooling and wing chucks are removed, resulting in a wing having multiple multi-support wing stringers and a metallic coating.
    公开号:BR102013030239B1
    申请号:R102013030239-2
    申请日:2013-11-25
    公开日:2020-06-30
    发明作者:John H. Moselage, Iii
    申请人:The Boeing Company；
    IPC主号:
    专利说明:

    [0001] [001] The construction of specific conventional aircraft wings varies from manufacturer to manufacturer, but has several manufacturing processes in common. One or more wing spars, which extend the entire length of the wing, are placed and secured in a wing construction template. One or more ribs are attached to the wing stringers to provide more support for the wing. After fixing the ribs on the wing members, a series of wing reinforcement members are attached to the wing members, providing additional structural support, as well as providing support for the metallic wing lining. After the installation of one or more other items, such as fuel tanks, electronic components, etc., if necessary, the metallic wing of the aircraft wing, reinforced with reinforcement stringers, is attached to the wing and ribs. The metallic wing coating can be fastened using various processes, including, but not limited to, the use of rivets or other fasteners. Then, other aircraft wing components are attached to the wing assembly, such as wing flaps, ailerons attached to a rear wing, as well as front and rear wing control surfaces.
    [0002] [002] Conventional techniques for building wings can use a relatively significant number of parts and can be a laborious, time-intensive process. The number of parts can increase the weight of the wing, as well as the complexity of the construction of the wing.
    [0003] [003] In view of the above, there remains a need in the technique for a wing construction technique that uses fewer parts and is less intense in time. SUMMARY
    [0004] [004] It should be considered that this summary is provided to introduce a selection of concepts, in a simplified form, which are further described below in the detailed description. This summary is not intended to be used to limit the scope of the claimed object.
    [0005] [005] The apparatus and the processes provide wing supports with multiple supports and a metallic coating, using one or more forming mandrels. According to an aspect of the invention provided in the present specification, an aircraft wing can be constructed by applying one or more layers of composite material to a plurality of forming mandrels. Wing chucks, when placed together, generate the shape of the wing. After the layers of composite material are applied to each individual mandrel, the mandrels are brought into contact with each other. More material can be added to form all or part of the metallic wing coating or the top and / or bottom part of the multi-support wing stringers. Then, the mandrels are compressed using a wing surface tooling applied to the plurality of wing mandrels. In some instances, during compression of the mandrels, the composite material can be tensioned to straighten the fibers in the composite material. The composite material is then cured. After curing, the wing surface tooling and mandrels are removed, resulting in a wing having multiple support wing stringers and metallic coatings. If necessary, one or more ribs are installed inside the multi-support wing stringer to provide additional support.
    [0006] [006] According to another aspect, a wing may comprise a plurality of multi-support wing stringers for attaching the wing to an aircraft's fuselage. The wing may have an upper surface, a lower surface and a plurality of wing segments. The multi-support wing stringers, the upper wing surface and the lower wing surface can be cured together, or composite layers bonded together formed of substantially continuous fibers.
    [0007] [007] According to yet another aspect, a system for forming an aircraft wing may include a plurality of mandrels, formed according to the upper, lower, front and rear surfaces of the aircraft wing. The system may also include a compression apparatus, to compress together the plurality of mandrels, to cure the layers of composite material in the mandrels. The system may also include a tension block, to maintain tension in the composite material.
    [0008] [008] The aspects, functions and advantages, which have been discussed, can be obtained independently in a plurality of configurations of the present invention, or can be combined in more other configurations, whose additional details can be seen with reference to the description presented below and drawings. BRIEF DESCRIPTION OF THE DRAWINGS
    [0009] [009] Figure 1 is a perspective view from the top of an exemplary mandrel, which can be used to form multiple support wing stringers, according to the plurality of configurations presented in this specification.
    [0010] [0010] Figure 2 is a perspective view from the top of an exemplary mandrel, which can be used to form a wing, illustrating the application of a skewed layer wound in filament on the mandrel, according to the plurality of configurations presented in the present descriptive report.
    [0011] [0011] Figure 3 is a perspective view from the top of an exemplary mandrel, which can be used to form a wing, illustrating the application of a unitary layer to the mandrel, according to the plurality of configurations presented in this specification.
    [0012] [0012] Figure 4 is a perspective view from the top of an exemplary mandrel, which can be used to form a wing, illustrating a final arrangement of the mandrel, according to the plurality of configurations presented in this specification.
    [0013] [0013] Figure 5 is a perspective view from the top of a plurality of exemplary mandrels, which can be used to form a wing, according to the plurality of configurations presented in this specification.
    [0014] [0014] Figure 6 is a perspective view from the top of a plurality of exemplary mandrels, which are brought into contact with each other, according to the plurality of configurations presented in this specification.
    [0015] [0015] Figure 7 is a perspective view from the top of a wing surface tool, before compression, according to the plurality of configurations presented in this specification.
    [0016] [0016] Figure 8 is a perspective view from the top of a wing surface tool, during compression, according to the plurality of configurations presented in this specification.
    [0017] [0017] Figure 9 is a perspective view from the top of a wing surface tool being removed, after curing, according to the plurality of configurations presented in this specification.
    [0018] [0018] Figure 10 is a perspective view from the top of a wing having multi-support wing stringers and metallic coating, after removal of the wing surface tool and chucks, according to the plurality of configurations presented in the present descriptive report.
    [0019] [0019] Figure 11 is a perspective view from the top of a wing having multi-support wing stringers and metallic coating, after removing the wing surface tool and the mandrels, further illustrating the installation of a vertical rib, of according to the plurality of configurations presented in this specification.
    [0020] [0020] Figure 12 is a perspective view from the top of a fuselage section with two wings, having multiple support wing stringers, according to the plurality of configurations presented in this specification.
    [0021] [0021] Figure 13 is an illustrative routine for the manufacture of multi-support wing stringers, according to the plurality of configurations presented in this specification. DETAILED DESCRIPTION
    [0022] [0022] The detailed description presented below provides wings having multiple support wing stringers. As discussed briefly above, the wings of conventional aircraft are typically built using a plurality of components, including one or more stringers, ribs and wing reinforcement stringers, each performing individual functions. After the wing is built, it is typically attached to a wing support in the aircraft's fuselage. In a conventional aircraft, the wing support is a structural component, reinforced in the aircraft's fuselage, to which the wings are attached. Building conventional aircraft wings can be an expensive and time-intensive process. Furthermore, if the wing is constructed using certain materials, including polymer, or especially composite materials, the multiple wing sections reduce the availability of relatively long lengths of an entire material, reducing the mechanical strength of the polymers and / or composite materials. For example, when using carbon fiber reinforced thermoplastic materials, if the surface contains multiple breaks in the fibers, the benefit of using the composite can be reduced, as additional structures or reinforcement material may need to be used to compensate for the loss structural rigidity.
    [0023] [0023] By using the concepts described in this specification, an aircraft wing can be built using a series of forming mandrels, which, when placed together, produce the shape of the wing. Composite materials, or other suitable materials, can be applied to the forming mandrel, and then compressed and cured to form a wing, having multi-support wing stringers. In other configurations, one or more layers of composite materials can be fully or partially cured before applying the layers to one or more parts of the forming mandrel. In this configuration, one or more layers, partially or fully cured, of composite material can be bonded together with other layers, partially or fully cured, of composite materials. It should also be considered that the concepts described in this specification, relating to an aircraft wing, can also be used in other aircraft components, such as a vertical or horizontal stabilizer, without departing from the scope of this description and the claims associated companies.
    [0024] [0024] In the detailed description presented below, references are made to the attached drawings, which form a part of it, and which are shown by way of illustration, specific configurations or examples. With reference then to the drawings, in which the similar numbers represent similar elements throughout the plurality of figures, the manufacture of wings, having multiple support wing stringers, will be described. It should be considered that a multi-support wing stringer construction, according to the plurality of embodiments described in this specification, may have one or more struts and one or more metallic coatings, the present invention of which is not limited to any number of stringers and metallic coatings.
    [0025] [0025] Returning to Figure 1, a perspective view from the top of a mandrel, which can be used to form a wing, is illustrated. The forming (or wing) mandrel 100 may have an upper surface layer 102, which is formed according to an upper surface layer of an aircraft wing (shown by way of example in Figure 12). The forming (or wing) mandrel 100 may also have a lower surface layer 104, which is formed according to an lower surface layer of an aircraft wing. The top surface layer 102 and the bottom surface layer 104 can be formed so that when one or more layers of composite material, such as carbon fiber reinforced thermoplastic material, are applied to the mandrel 100, the resulting shape is that of a aircraft wing. Furthermore, the top surface layer 102 and the bottom surface layer 104 can be formed so that there are little or no folds or breaks in the composite material, providing greater rigidity of the composite material. The forming (or wing) mandrel 100 may also have a front surface layer and a rear surface layer, in contact with one or more of a plurality of mandrels.
    [0026] [0026] As will be described in more detail below, when forming a structure using composite materials, it is typically preferable to avoid not only unnecessary folds or breaks in the material, but also to keep the straightness of the fibers extending into one or more parts of the material. In typical composite materials, it may be preferable to have straight fibers in the composite material matrix. It should be considered that the present invention is not limited to the use of straight fibers in a composite matrix. A plurality of configurations of the present invention can be implemented in the construction of wings having matrices composed using straight or curved fibers, or combinations thereof.
    [0027] [0027] If it is desired or necessary to straighten the fibers in a composite fiber matrix, before curing, mandrel 100 may also have tension blocks 106 and 108. Stress blocks 106 and 108 can be used separately or together each other to "pull" the fibers from a composite matrix, thereby providing a matrix of straightened fibers. In some configurations, fibers in a composite matrix (described in more detail below) can be attached to one or both of the tension blocks 106 and 108, or can be formed around the tension blocks 106 and 108. The tension blocks 106 and 108 can be configured to extend outwardly from mandrel 100, at various pressures to provide tension in the fibers in the fiber matrix.
    [0028] [0028] A configuration of the fiber matrix construction, as discussed briefly above, and the formation of a wing having multiple support struts are then described in relation to Figures 2 -12. In Figure 2, a first layer of skewed layer wound in filament 200 (illustrated in a pattern hatched on the surface of the mandrel) is rolled or applied to mandrel 100. If necessary or desired, the skewed layer wound in filament 200 may have tension applied in it, by using tension block 106 and / or tension block 108, to help straighten the fibers in the skewed layer wound in filament 200.
    [0029] [0029] After the skewed layer wound in filament 200 is applied to mandrel 100, a unitary layer is applied, as shown in Figure 3. Unitary layer 300 is applied to mandrel 100 and can be tightened using the tension block 106 and / or tension block 108. It is to be understood that the present invention is not limited to any specific configuration of skewed layer or unitary layer. For example, one or more layers of a skewed layer can be added before adding a unitary layer. In the same way, one or more layers of unitary layer can be added between applications of the one or more skewed layers.
    [0030] [0030] It should also be understood that the present invention is not limited to any number of layers of any type of layer, as a plurality of combinations can be used to obtain structural or cost targets. For example, and not by way of limitation, it may be desirable or necessary to add sufficient layers of curled skew layer and / or unitary layer to obtain a desired structural thickness or wing stiffness. In addition, it should be understood that the present invention is not limited to a layer having a single type of layer, as some configurations may use a combination of skewed and single layers within the same layer. A plurality of combinations can be used according to the plurality of configurations, without departing from the scope of this description and the associated claims.
    [0031] [0031] Figure 4 illustrates a complete composite matrix 400 in mandrel 100. The composite matrix 400 can be formed using a plurality of layering and application techniques, such as, by way of example, the process described above in relation to Figures 2 and 3.
    [0032] [0032] Figure 5 is a perspective view from the top of a series of mandrels, having composite matrices formed entirely applied to them. The chuck device 500 has individual chucks 500a - d. Mandrels 500a - d have a composite matrix 502 arranged in them, having individual composite matrices 502a - d. The composite matrix 502 can be formed of one or more layers, a plurality of layer combinations, and can be, in whole or in part, not cured at that point. As illustrated in Figure 5, the general shape of an aircraft wing can be seen when viewing the mandrel device 500.
    [0033] [0033] According to a plurality of configurations, after the composite die 502 is applied to the mandrel device 500, the mandrels 500a - d are brought into contact with each other, as shown in Figure 6. The individual mandrels (illustrated by means of example as mandrels 500a - d in Figure 5) are brought into contact with each other to form a multi-support wing stringer arrangement, having the composite matrix 502, which is formed of multiple composite matrices (illustrated by way of example as the composite matrices 502a -d in Figure 5).
    [0034] [0034] To cure, partially or entirely, and form the multi-support wing stringer configuration, according to the plurality of configurations of the present invention, a curing system can be used. As discussed above, one or more layers of composite material can be fully or partially cured prior to use in a forming mandrel. In this configuration, the partially or fully cured composite layers can be bonded together with other partially or fully cured composite layers, using one or more layers of adhesive, to fix the layers of composite material within a composite matrix. An example of a system for forming multiple support wing stringers is shown in Figure 7. After the individual mandrels forming the mandrel apparatus 500 are brought into contact with each other, thus forming the composite matrix 502 of a series of matrices individual composites, a series of surface tools can be applied to the plurality of surfaces of the mandrel device 500. It should be considered that additional material can be added by the stringer surface, after the mandrels, which form the mandrel device 500, have been in contact with each other. The additional material can be used to form the metallic lining of the wing, reinforce the mandrel already in place, or provide a plurality of aerodynamic or physical properties, for example.
    [0035] [0035] A plurality of processes for adding the curled skew layer and the additional single layer are known to those skilled in the art, to which the plurality of configurations, described in this specification, are not dependent on any particular mandrel application process. In one configuration, a curable upper wing metallic coating, a curable lower wing metallic coating, a curable front wing edge and a curable rear wing edge can be applied (or arranged) after the additional layers have been added to the matrix. compound 502, before applying surface tools to the composite matrix 502.
    [0036] [0036] The compression apparatus 504 has a front metal coating surface tool 506, a lower metal coating surface tool 508, a rear metal coating surface tool 510 and a top metal coating surface tool 512. It should also be considered that not all materials added are "curable" materials, as a non-curable material can be added to the composite matrix 502. The surface tools 506, 508, 510 and 512 are compressed individually or collectively, thereby applying mode, pressure on the respective surfaces of the mandrel device 500, to help form and cure the composite die 502. In some configurations, the heating element 514 can be applied to one or more of the surface tools 506 - 512. The combination of pressure and heat can cure, fully or partially, the composite matrix 502 in a desired period of time, or can provide structural rigidity additional. The heating element 514 can use a plurality of means of applying heat to the composite matrix 502, including steam and electric current. Figure 8 illustrates the compression apparatus 504 in a compressed state, with the chuck apparatus 500 shown outside the compression apparatus 504.
    [0037] [0037] Once the composite matrix 502 is cured to a desired level, the compression device 504 is removed, illustrated in more detail in Figure 9. The surface tools 506, 508, 510 and 512 of the compression device 504 are removed from the surface of the then cured composite die 502, and the individual mandrels of the mandrel apparatus 500 are extracted from the composite die 502. The resulting structure is illustrated in Figure 10. It should be noted that the present invention is not limited to the entire composite die cured 502, as it may be desired or necessary, in some configurations, to remove the curing mechanisms (for example, the compression apparatus 504 or the heating element 514), before the composite matrix 502 is fully cured. Various degrees of cure can be used according to the plurality of configurations of the present invention, without departing from the scope of this description and the associated claims.
    [0038] [0038] Figure 10 is a perspective illustration from the top, showing a composite matrix 502 with a multi-support wing stringer. By using composite materials formed on mandrels in contact with each other, the composite matrix 502 has the stringers 600a - e in it, which extend internally to the composite matrix 502 along the X - Y axis, thus forming the stringers multi-support wing. By using a mandrel device, such as the mandrel device 500 of Figure 7, it can be noted that the composite die 502 can be formed having fibers disposed therein, which can be straightened and not cut (or indefinitely finished) . After curing, the composite matrix 502 can be considered a contiguous, singular structure. If it is desirable or necessary to further reinforce the composite matrix 502, one or more ribs (or segments of ribs) can be installed in the composite matrix 502, an example of which is shown by rib 700 in Figure 11.
    [0039] [0039] Furthermore, using the concepts described in this specification, a wing, formed according to the plurality of configurations described in this specification, can be attached to a fuselage section of an aircraft, without the need for a support conventional wing. Exemplary techniques are described in the copending patent application (13/685024) entitled: Vertically Integrated Stringers ", filed on November 26, 2012. Figure 12 illustrates one of these configurations, in which a wing, formed according to the techniques described in this specification, it is attached to a fuselage, without the use of a traditional wing support. It should be considered that the concepts, presented in this specification, can also be used to form a wing, according to the techniques described in this specification, to be attached to a traditional wing support.
    [0040] [0040] The composite matrices 800 and 802, which are built according to the plurality of configurations described in this specification, have multiple wing spars, which can be attached to the fuselage section 804. It should be considered that the composite matrices 800 and 802 can be formed in a plurality of shapes and with a plurality of items, wherein the present invention is not limited to any particular configuration. The exemplary wing stringer 806 is identified in Figure 12 for clarity, although it should be understood that the composite matrices 800 and 802 may have additional wing struts. The exemplary wing member 806 may have an elliptical opening 808.
    [0041] [0041] Depending on the angular displacement between the composite matrices 800 and 802 and the fuselage section 804, the elliptical opening 808 may vary in circumference and shape, that is, the foci of the elliptical opening 808 may vary, as well as the radii. For example, on a straight-wing aircraft, in which the stringer 806 can be attached to the fuselage section 804, at an angle of approximately 90 degrees, the elliptical opening 808 can be circular. In another example, such as that illustrated in Figure 12, the stringer 806 can be attached to the fuselage section 804 in an arrow wing profile. In this way, the elliptical opening 808 can be more oval in shape, to provide internal space in the aircraft and be circumferentially attached to the fuselage. One or more circumferential fuselage reinforcement members, such as the reinforcement members described in the copending patent application "Vertically Integrated Stringers" and identified as circumferential reinforcement members 810, can provide additional structural support to the fuselage section 804 The multi-support wing stringers, formed by composite matrices 800 and / or 802, can be attached to one or more beams of an aircraft fuselage, such as the 812 crown beam section. may have one or more types of beams, including, but not limited to, 812 crown beam or keel beam (not shown).
    [0042] [0042] Figure 12 also illustrates the plurality of sections of a wing, which can be formed using the plurality of configurations described in this specification. The composite matrix 802 is illustrated as having a front wing edge 814, a rear wing edge 816, an upper surface layer 818 and a bottom surface layer 820. One or more of the front wing edges 814, rear wing edge 816, top surface layer 818 and bottom surface layer 820 can be curable or bondable, according to the plurality of configurations described in this specification. Furthermore, one or more of the front wing edges 814, rear wing edge 816, top surface layer 818 and bottom surface layer 820 can be formed separately from the others and then attached. In some configurations, the front wing edge 814 and / or the rear wing edge 816 can be formed with the top surface layer 818 and / or the bottom surface layer 820. Thus, in a compression device, such as the device the compression wing 504 of Figure 7, the front wing edge 814 can be a front metallic coating, formed using the front metal coating surface tool 506 of Figure 7, and the rear wing edge 816 can be a metallic coating surface. formed by the use of the 510 metal backing surface tool.
    [0043] [0043] Returning then to Figure 13, an illustrative routine 900, for the construction of multiple support wing stringers, is described in detail. Unless otherwise indicated, it should be considered that more or less operations can be conducted than those shown in the figures and described in this specification. In addition, unless otherwise indicated, these operations may also be conducted in a different order than that described in this specification.
    [0044] [0044] Routine 900 begins at operation 902, in which one or more skewed and / or single layers are applied in a series of forming shafts. In some configurations, the fibers in the skewed and / or single layers can be tightened by using one or more tension blocks in the mandrel. From operation 902, routine 900 continues to operation 904, in which the forming mandrels are brought into contact with each other, to create an arrangement of multi-support wing stringers. In some configurations, the arrangement of multi-support wing stringers comprises a composite matrix, formed of one or more layers of the biased and / or unitary layers. As mentioned above, additional layers can be added at various stages of the forming process.
    [0045] [0045] From operation 904, routine 900 continues to decision 906, in which a determination is made whether additional layers of skewed or single layers are to be added, prior to curing of the composite matrix. In one configuration, it may be desirable to jointly form and cure the multi-support wing stringers and one or more parts of the metallic wing lining. In another configuration, a desired structural thickness or wing stiffness may require additional layers to be added, routine 900 continues to operation 908, in which additional layers are applied at disposal.
    [0046] [0046] If it is determined 906 that no additional layer for the arrangement will be applied 908, or after the additional layers for the arrangement have been applied 908, routine 900 continues to operation 910, in which the surface tooling is applied ( contact) of the plurality of surfaces of the composite matrix. The surface tooling, in some configurations, can serve the plurality of functions. For example, the surface tooling may have one or more surfaces configured to create certain shapes on the surface of the composite die. Surface tooling can also be used to apply pressure and / or heat to a composite matrix, to cure the composite matrix, as well as, in some instances, to provide a reduction in volume of the composite matrix during dispositioning.
    [0047] [0047] From operation 910, routine 900 continues to operation 912, with which the surface tooling is compressed in the composite matrix, to promote the curing process. In some configurations, it may be desirable, in addition to pressure, to apply heat to one or more surface tools, to heat a plurality of surfaces of the composite die. Thus, operation 912 may also include a heating operation.
    [0048] [0048] From operation 912, routine 900 continues to operation 914, in which the composite matrix, in the arrangement of wing supports with multiple supports, is cured. In some other configurations, it may be desirable in operation 912 and / or in operation 914 to apply tension to the layers within the composite matrix, at one or both ends of the composite matrix, to reduce the amount of fiber folds within the composite matrix and increase the straightness of the fibers within the composite matrix. Once curing is complete, routine 900 continues to operation 916, with which surface tooling (and heat) is removed from the composite die. Furthermore, the mandrels are extracted from the composite matrix, forming wing sections having multiple support wing stringers.
    [0049] [0049] Furthermore, the description comprises embodiments, according to the following clauses:
    [0050] [0050] 1. An aircraft wing manufacturing process, comprising:
    [0051] [0051] applying a plurality of skewed layers wound in filament and unitary layers in each of a plurality of separate wing mandrels;
    [0052] [0052] put in contact with each other the plurality of separate wing mandrels, to create an arrangement of wing supports with multiple supports;
    [0053] [0053] put in contact the plurality of wing surface tools with the arrangement of wing struts with multiple supports;
    [0054] [0054] to compress the plurality of wing surface tools, to apply pressure to the provision of multiple support wing stringers; and
    [0055] [0055] curing the arrangement of multiple support wing stringers to form the aircraft wing, having a plurality of multiple support wing stringers.
    [0056] [0056] 2. The process according to clause 1, in which curing the arrangement of multiple support wing spars further comprises applying heat to the provision of multiple support wing spars.
    [0057] [0057] 3. The process according to clause 1, further comprising removing each of the plurality of separate wing mandrels, after curing the arrangement of multiple support wing stringers.
    [0058] [0058] 4. The process according to clause 1, in which applying a plurality of skewed coiled layers and unitary layers comprises adding sufficient layers of curled skewed layers or unitary layers, to obtain a desired structural thickness or wing stiffness .
    [0059] [0059] 5. The process according to clause 1, further comprising arranging a curable metallic upper wing coating and a curable metallic lower wing coating, after applying a plurality of skewed layers wound in filament and unitary layers, wherein curing the arrangement of multi-support wing struts jointly cures the arrangement of multi-support wing struts, the metallic upper wing coating and the metallic lower wing coating.
    [0060] [0060] 6. The process according to clause 1, also comprising installing the plurality of rib segments, after curing the arrangement of wing supports of multiple supports.
    [0061] [0061] 7. The process according to clause 1, also comprising installing a front wing edge or a rear wing edge, after curing the arrangement of multiple support wing spars.
    [0062] [0062] 8. The process according to clause 1, further comprising arranging a curable front wing edge and a curable rear wing edge, after applying the plurality of skewed layers wound in filament and unitary layers, in which to cure the disposition. multi-support wing stringers jointly cure the arrangement of multiple-support wing stringers, the front wing edge and the rear wing edge.
    [0063] [0063] 9. The process according to clause 1, in which compressing the plurality of wing surface tools further comprises applying tension to the plurality of skewed layers wound in filament and unitary layers, to minimize the pleating of a plurality of fibers on them.
    [0064] [0064] 10. A wing, comprising:
    [0065] [0065] a plurality of multi-support wing stringers attached to at least one beam of an aircraft fuselage;
    [0066] [0066] an upper wing surface;
    [0067] [0067] a lower wing surface; and
    [0068] [0068] a plurality of wing segments,
    [0069] [0069] wherein the plurality of multiple support wing stringers, the upper wing surface and the lower wing surface are composite layers, comprising substantially continuous fibers.
    [0070] [0070] 11. Wing according to clause 10, wherein the wing further comprises a plurality of ribs disposed within a plurality of multi-support wing stringers.
    [0071] [0071] 12. Wing according to clause 10, wherein the wing further comprises a front wing edge and a rear wing edge comprising composite layers cured together with a plurality of multiple support wing stringers, the surface of upper wing and the lower wing surface.
    [0072] [0072] 13. Wing according to clause 10, in which at least one of the multi-support wing stringers comprises an elliptical opening.
    [0073] [0073] 14. Wing according to clause 13, in which an external surface of the elliptical opening is close to an internal surface of the aircraft fuselage.
    [0074] [0074] 15. Wing according to clause 13, in which the foci of the elliptical opening provide an angular displacement between the fuselage and the wing of the aircraft, in which the angular displacement provides a straight wing profile or a wing profile in arrow.
    [0075] [0075] 16. Wing according to clause 10, wherein at least one of a plurality of multiple support wing stringers is attached to at least one of a plurality of multiple support wing stringers of a second wing.
    [0076] [0076] 17. Wing according to clause 10, further comprising a metallic wing coating cured together with a plurality of multi-support wing stringers.
    [0077] [0077] 18. Wing according to clause 10, in which the composite layers, comprising substantially continuous fibers, are composite layers cured or bonded together.
    [0078] [0078] 19. A system for forming an aircraft wing, comprising:
    [0079] [0079] a plurality of mandrels comprising:
    [0080] [0080] an upper surface layer formed according to an upper surface layer of the aircraft wing;
    [0081] [0081] a lower surface layer formed according to an inferior surface layer of the aircraft wing; and
    [0082] [0082] a front surface layer and a rear surface layer in contact with one or more of the plurality of mandrels, wherein the upper surface layers of the plurality of mandrels are formed according to an upper wing surface of the aircraft, and the surface layers inferiors of the plurality of mandrels are formed according to an inferior layer of the wing of the aircraft;
    [0083] [0083] a tension block to maintain tension in one or more layers of composite material, which forms the wing of the aircraft; and
    [0084] [0084] a compression apparatus for mechanically curing one or more layers of composite material, forming the wing of the aircraft, the compression apparatus comprising:
    [0085] [0085] a metal backing surface tool for applying pressure to the rear surface layer of the plurality of mandrels;
    [0086] [0086] a top metallic coating surface tool for applying pressure to the upper surface layer of the plurality of mandrels;
    [0087] [0087] a lower metallic coating surface tool for applying pressure to the lower surface layer of the plurality of mandrels; and
    [0088] [0088] a front metallic surface tool for applying pressure to the front surface layer of the plurality of mandrels.
    [0089] [0089] 20. System according to clause 19, also comprising a heating element, to thermally cure one or more layers of composite material, which forms the wing of the aircraft.
    [0090] [0090] Based on the above, it should be considered that the technologies for the construction of wing sections, having multiple strut wing struts, were presented in this specification. The object described above is provided by way of illustration only and should not be considered as limiting. A plurality of modifications and variations can be made to the object, described in this specification, without following the illustrated and described exemplary configurations and applications, and without departing from the true spirit and scope of the present invention, which is presented in the claims to follow.
    权利要求:
    Claims (14)
    [0001]
    Aircraft wing manufacturing process, comprising: applying layers to each of a plurality of separate wing mandrels (100); placing the plurality of separate wing chucks (100) in contact with each other, to create an array of multi-support wing stringers; placing a plurality of wing surface tools in contact with multiple support wing stringers; compressing the plurality of wing surface tools, to apply pressure to the provision of multiple support wing stringers; and curing the arrangement of multiple support wing spars to form the aircraft wing, having a plurality of multiple support wing spars; characterized by the fact that: the layers comprise a plurality of skewed layers wound in filament (200) and unitary layers (300); and compressing the plurality of wing surface tools further comprises applying tension to the plurality of skewed layers wound in filament (200) and to the unitary layers (300) to minimize the pleating of the plurality of fibers in them.
    [0002]
    Process according to claim 1, characterized by the fact that curing the arrangement of multiple support wing spars further comprises applying heat to the arrangement of multiple support wing spars.
    [0003]
    Process according to any one of the preceding claims, characterized by the fact that it further comprises removing each of the plurality of separate wing mandrels (100), after curing the arrangement of multiple support wing spars.
    [0004]
    Process according to any one of the preceding claims, characterized in that applying the plurality of skewed layers wound in filament (200) and unitary layers (300) comprises adding sufficient layers of curled skewed layers (200) or unitary layers (300 ), to obtain a desired thickness or structural rigidity of the wing.
    [0005]
    Process, according to any of the preceding claims, characterized by the fact that it further comprises: having a curable upper wing metallic coating and a curable lower wing metallic coating, after applying the plurality of skewed layers wound in filament (200) and unitary layers (300), in which the curing of the arrangement of multiple support wing members jointly curing the arrangement of multi-support wing spars, the metallic upper wing coating and the metallic lower wing coating; and installing a plurality of rib segments (700), after curing the arrangement of multiple support wing spars.
    [0006]
    Process according to any one of the preceding claims, characterized by the fact that it further comprises installing a front wing edge (814) or a rear wing edge (816), after curing the arrangement of multiple support wing stringers.
    [0007]
    Process according to any one of the preceding claims, characterized by the fact that it further comprises a curable front wing edge (814) and a curable rear wing edge (816), after applying the plurality of skewed layers wound in filament ( 200) and unitary layers (300), where curing the arrangement of multiple support wing spars jointly cures the arrangement of multiple support wing spars, the front wing edge (814) and the rear wing edge (816) .
    [0008]
    Wing, comprising: a plurality of multi-support wing stringers (600) arranged to be attached to at least one beam (812) of an aircraft fuselage; an upper wing surface; a lower wing surface; and a plurality of wing segments; wherein the plurality of multi-support wing stringers are arranged to be in contact with each other, so as to form a multi-support string arrangement, and characterized by the fact that the plurality of multiple support stringers (600), the upper wing surface and the lower wing surface are composite layers, comprising substantially continuous fibers, wherein the fibers of the plurality of multiple support wing stringers ( 600) are under tension.
    [0009]
    Wing, according to claim 8, characterized by the fact that the wing further comprises a plurality of ribs (700) arranged within the plurality of multi-support wing stringers.
    [0010]
    Wing, according to claim 8 or 9, characterized in that the wing further comprises a front wing edge (814) and a rear wing edge (816) comprising composite layers cured together with the plurality of wing spars. multiple supports (600), the upper wing surface and the lower wing surface.
    [0011]
    Wing according to any one of claims 8 to 10, characterized in that at least one multi-support wing stringer (600) of the plurality of multi-support wing struts comprises an elliptical opening (808) substantially in the plane a contact wall of at least one of the multi-support wing stringers; wherein an outer surface of the elliptical opening (808) is close to an inner surface of the aircraft fuselage to which the plurality of multi-support wing stringers (600) are arranged to be fixed; and wherein the foci of the elliptical opening (808) are arranged to provide an angular displacement between the fuselage and the aircraft wing, where the angular displacement provides for a straight wing profile or an arrow wing profile.
    [0012]
    Wing according to any one of claims 8 to 11, characterized in that at least one multi-support wing stringer of the plurality of multi-support wing struts (600) is attached to at least one support wing stringer multiples of the plurality of multiple support wing stringers (600) of a second wing.
    [0013]
    Wing, according to any one of claims 8 to 12, characterized in that it further comprises a cured wing lining together with the plurality of multiple support wing stringers (600).
    [0014]
    Asa according to any one of claims 8 to 13, characterized in that the composite layers, comprising substantially continuous fibers, are cured or bonded composite layers together.
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    同族专利:
    公开号 | 公开日
    CA2831516C|2017-04-18|
    AU2013254936B2|2015-09-03|
    KR20140067900A|2014-06-05|
    EP2789534A1|2014-10-15|
    US9527575B2|2016-12-27|
    KR101786342B1|2017-10-17|
    RU2013152199A|2015-05-27|
    ES2650940T3|2018-01-23|
    CN103832577A|2014-06-04|
    CN103832577B|2017-11-28|
    RU2657645C2|2018-06-14|
    EP2789534B1|2017-09-06|
    KR101737669B1|2017-05-18|
    US20170106968A1|2017-04-20|
    KR20160055764A|2016-05-18|
    JP2014104975A|2014-06-09|
    CA2831516A1|2014-05-26|
    BR102013030239A2|2014-10-29|
    US10737760B2|2020-08-11|
    AU2013254936A1|2014-06-12|
    JP6120086B2|2017-04-26|
    US20140145032A1|2014-05-29|
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    法律状态:
    2014-10-29| B03A| Publication of an application: publication of a patent application or of a certificate of addition of invention|
    2018-03-06| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2018-03-13| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2018-03-20| B06I| Technical and formal requirements: publication cancelled|Free format text: ANULADA A PUBLICACAO CODIGO 6.6.1 NA RPI NO 2462 DE 13/03/2018 POR TER SIDO INDEVIDA. |
    2019-10-08| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-04-07| B09A| Decision: intention to grant|
    2020-06-30| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 25/11/2013, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/685,049|2012-11-26|
    US13/685,049|US9527575B2|2012-11-26|2012-11-26|Multi-box wing spar and skin|
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