• 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:
    joint for composite wings The present invention relates to a wing joint including a tee cord and a joint plate, for connecting an onboard wing panel assembly and an outboard wing panel assembly. wing panel assemblies include a stiffening spar bonded or cured together with a wing shell. the reinforcing stringer screen and cover can be trimmed to expose a noodle and base flange. the noodle and base flange face the bottom of the t-string, and the wing casing faces the junction plate. exposed noodles may not be embedded in the trimmed reinforcing stringer base flange. the bottom of the t-string may include a groove to accommodate a non-inlaid noodle so that a gap does not exist between the t-string and the base flange. alternatively, shims can be used to offset a non-inlaid noodle, or the base flange and screen can include sacrificial layers, allowing the base flange and screen to be trimmed to be embedded with the noodle.
    公开号:BR102013029090B1
    申请号:R102013029090-4
    申请日:2013-11-12
    公开日:2022-01-18
    发明作者:Chun-Liang Lin；Ryan M. Mahn；Karl B. Lee
    申请人:The Boeing Company；
    IPC主号:
    专利说明:

    BACKGROUND DESCRIPTION FIELD
    [0001] The configurations described in this specification refer to a joint for composite wings. The gasket may be a gasket on the underbody side of an aircraft. DESCRIPTION OF RELATED TECHNIQUE
    [0002] Bolted body side joints can be used to attach wings to an aircraft fuselage. A design of a body-side joint 200, currently used for connecting a wing to a fuselage, is shown in Figure 12. The joint 200 includes a double positive cord 210, which includes a vertical portion 211, an upper aboard portion. 212, a lower outboard portion 213, an upper outboard portion 214, and a lower outboard portion 215. An onboard wing panel assembly 220 is connected to the onboard side of the double positive cord 210, and an assembly of Outboard wing panel 230 is connected to the outboard side of the double positive rope 210.
    [0003] The onboard wing panel assembly 220 includes a stiffening spar 260, connected to an onboard wing shell 240, and the outboard wing panel assembly 230 includes a stiffening spar 260, connected to to an outboard wing casing 250. Reinforcement spar 260 includes a base flange 261 at the bottom of rib spar 260 and a cover 263 located on top with a fabric 262 connecting cover 263 to the base flange 261. The base flange 261 of the stiffener spar 260 is connected to the on-board wing casing 240. The base flange 261 can be attached to the on-board wing casing 240.
    [0004] The cover 263 is connected to the upper edge portion of the double positive chord 210 by a number of fasteners 281. A portion of the fabric 262 and the base flange 261 of the reinforcing stringer 260 is trimmed so that the base flange 261 of the reinforcing stringer 260 does not overlap the lower edge portion 213 of the double positive cord 210. A radial filler plate 291 is positioned above the base flange 261. Fasteners 290 connect the radial filler plate 291 to the base flange 261 and to the on-board wing housing 240, which attach the on-board wing housing 240 and the base flange 261, to form a slot retaining mechanism. Only the onboard wing shell 240 of the onboard wing panel assembly 220 is positioned below the lower edge portion 213 of the double positive lanyard 210. The onboard wing shell 240 is positioned between the lower edge portion 213 of the lanyard double positive 210 and a junction plate 270. Fasteners 280 connect the junction plate 270, securing the onboard wing housing 240 to the gasket 200.
    [0005] Outboard wing panel assembly 230 is constructed in the same manner as onboard wing panel assembly 220. Fasteners 281 are used to connect cover 263 of stiffener 260 to upper outboard portion 214 of the double positive rope 210. Fasteners 280 connect the outboard wing housing 250 to the junction plate 270 and the lower outboard portion 215 of the double positive rope 210. The connection of a portion of a wing panel assembly to a first part of a joint and the connection of a second part of a wing panel assembly to a second part of the joint can result in different forces being applied to different parts of the assembly.
    [0006] In view of the above, there is a need in the technique for a body-side joint that secures both parts of a wing panel assembly with a retention configuration having a single interface. SUMMARY
    [0007] It may be beneficial to provide a joint that secures both parts of a wing panel assembly with a retention configuration having a single interface.
    [0008] A configuration is a wing joint comprising a tee string, a joint plate, an onboard wing panel assembly and an outboard wing panel assembly. The T-string includes an onboard part, an outboard part and a vertical part. The junction plate has an onboard part and an offboard part. The wing joint includes at least one onboard stiffening spar connected, such as being attached, to the onboard wing shell to form an onboard wing panel assembly and at least one attached outboard stiffening spar. , such as being attached, to the outboard wing shell to form an outboard wing panel assembly. A part of the onboard wing panel assembly is positioned between the onboard part of the tee cord and the onboard part of the junction plate. A portion of the outboard wing panel assembly is positioned between the outboard portion of the T-string of the junction plate. A first plurality of fasteners connect the on-board portion of the T-cord with the on-board portion of the splice plate, to secure the on-board wing panel assembly to the T-cord and splice plate. A second plurality of fasteners connect the outboard portion of the tee cord with the outboard portion of the splice plate.
    [0009] The outboard stiffening spar and the onboard wing joint stiffening spar may each include a base flange, at least one screen and at least one noodle. The outboard stiffener stringer and the onboard stiffener stringer can be blade stiffener stringers. The outboard stiffening stringer and the onboard stiffening stringer may be I stiffening stringers. The I stiffening stringers may include a cap. The onboard gusset and the outboard gusset can both be trimmed to expose at least one noodle. The onboard wing panel assembly may comprise a part of an onboard wing shell, a part of a base flange of an onboard reinforcing spar, and a part of at least one exposed noodle. The outboard wing panel assembly may comprise a part of an outboard wing shell, a part of an outboard stiffening spar and a part of at least one exposed noodle.
    [00010] The tee string of the joint may include a first groove in the onboard portion to accommodate at least one exposed noodle from an onboard reinforcing spar, and a second slot in the outboard portion to accommodate at least one noodle exposed part of an outboard reinforcement spar. The joint may include a first shim, positioned between the base flange of an onboard stiffening spar and the onboard portion of the T-string, and a second shim, positioned between the base flange of the outboard stiffening spar and the overboard portion of the T-string. The first and second shims may be positioned adjacent to at least one exposed noodle. The gasket may be a gasket on the lower body side for a composite wing assembly.
    [00011] The onboard portion of the T-string may include at least one cut, and the outboard portion of the T-string may also include at least one cut. A part of the fabric of the onboard reinforcement spar may extend to the cut in the onboard part of the T-string, and a part of the fabric of the outboard reinforcement spar may extend to the cut in the outboard part of the rope. The onboard and outboard portions of the T-string may include at least three longitudinal rows of fasteners securing the wing panel assemblies to the T-string and splice plate. Cuts in the onboard and outboard portions of the T-string may extend between the fasteners in at least one row of the fasteners. Cuts in the onboard and outboard portions of the tee rope may extend between the fasteners on at least two rows of the fasteners. The T-string and the joint joint plate can be comprised of titanium or aluminium.
    [00012] A configuration is a process of forming a winged joint. The method comprises forming an onboard wing panel assembly and forming an outboard wing panel assembly. The onboard wing panel assembly comprises at least one onboard stiffening spar connected to an onboard wing shell, the stiffening spar including a base flange, at least one screen and at least one noodle. The outboard wing panel assembly comprises at least one outboard stiffener spar connected to an outboard wing shell, the stiffener stringer including a base flange, at least one screen and at least one noodle. The process includes cutting the fabric of the onboard stiffener to expose at least one noodle and cutting the outboard stiffener spar to expose at least one macaroni. The method includes positioning a part of the onboard wing panel assembly between an onboard part of the T-cord and an on-board part of the joint plate, and securing the on-board wing panel assembly to the T-cord. and on the junction plate with a plurality of fasteners. The onboard wing panel assembly part includes an onboard wing shell part, an onboard reinforcing spar base flange part, and at least one exposed noodle. The method includes positioning a part of the onboard wing panel assembly between an outboard part of a tee cord and an outboard part of a junction plate, and securing the outboard wing panel assembly edge on the T-string and on the splice plate with a plurality of fasteners. The outboard wing panel assembly part includes an outboard wing shell part, an outboard stiffening spar base flange part, and at least one exposed noodle.
    [00013] The method may include providing a groove in the onboard portion of the T-string to accommodate at least one exposed noodle of the on-board reinforcement spar, and providing a groove in the outboard portion of the T-string to accommodate at least least one noodle exposed from the outboard reinforcement spar. The method may include providing at least one first wedge positioned between the onboard wing panel assembly and the onboard portion of the T-cord, and providing at least a second wedge positioned between the onboard wing panel assembly and the overboard portion of the T-string. The shims may be positioned adjacent to at least one exposed noodle.
    [00014] The reinforcing stringers or the process may be composite materials, comprised of a plurality of layers. The process may include adding additional sacrificial layers to the reinforcing spars prior to forming the wing panel assemblies, the sacrificial layers allowing at least a portion of them to be removed to provide an exposed noodle to be embedded without reducing the load-bearing capacity of the wing panel assemblies. Forming an onboard wing panel assembly may comprise curing the onboard wing shell and the onboard stiffening spar together, and forming an outboard wing panel assembly may comprise curing the shell together. outboard wing and outboard stiffening spar. Forming an onboard wing panel assembly may further comprise connecting the onboard wing shell and the outboard wing panel assembly together, and forming an outboard wing panel assembly may further comprise the joint connection of the outboard wing casing and the outboard stiffening spar.
    [00015] One configuration is a wing joint, comprising a first retainer plate, a second retainer plate and a wing panel assembly. A part of the wing panel assembly is secured between the first retainer plate and the second retainer plate. The reinforcing spar of the wing panel assembly has been trimmed to expose a noodle, which is part of the portion of the wing panel assembly secured between the first retainer plate and the second retainer plate. BRIEF DESCRIPTION OF THE DRAWINGS
    [00016] FIG. 1 shows a joint configuration for a composite wing.
    [00017] FIG. 2 shows a partial cross-section of a reinforcing spar attached to a wing shell to form a wing panel assembly to be used with a joint configuration for a composite wing,
    [00018] FIG. 3 shows a schematic representation showing the potential forces in a joint configuration for a composite wing.
    [00019] FIG. 4 shows a portion of a stiffening spar, which has been trimmed for use with a one-joint configuration for a composite wing.
    [00020] FIG. 5A shows a top view of a joint configuration for a composite wing.
    [00021] FIG. 5B shows a perspective view of a joint configuration for a composite wing.
    [00022] FIG. 6 shows a T-string configuration that includes a slot to accommodate the exposed non-embedded noodles of a reinforcing stringer.
    [00023] FIG. 7 shows a portion of a trimmed stiffener configuration, for use with a joint configuration for a composite wing, with shims being positioned adjacent an exposed non-embedded noodle of a stiffener spar.
    [00024] FIG. 8 shows an I-reinforcement spar that can be used with the wing joint described.
    [00025] FIG. 9 shows a blade reinforcement spar having sacrificial layers, which may be used with the wing joint described.
    [00026] FIG. 10 is a flowchart of aircraft production and maintenance methodology, according to an advantageous configuration.
    [00027] FIG. 11 is a block diagram of an aircraft in an advantageous configuration.
    [00028] FIG. 12 shows a prior art joint for a composite wing.
    [00029] Although the invention is susceptible to various modifications and alternative forms, specific configurations have been shown, by way of example in the drawings, which will be described in detail in the present specification. However, it should be understood that the invention is not intended to be limited to the particular forms described. Rather, the intent is to cover all modifications, equivalents and alternatives that fall within the scope of the invention as defined by the appended claims. DETAILED DESCRIPTION
    [00030] FIG. 1 shows a configuration of a wing joint 1. The wing joint 1 includes a first retaining plate 10 and a second retaining plate 15 used together to secure an onboard wing panel assembly 20 and an outboard wing panel assembly edge 30. The first retainer plate 10 may be a tee cord, and the second retainer plate may be a junction plate. In the following, the first retaining plate will be referred to as a T-cord 10, and the second retaining plate will be referred to as a junction plate 15. The T-cord 10 includes a vertical part 11, an on-board part 12 and an outboard part 13. The junction plate 15 includes an onboard part 16 and an outboard part 17. The tee cord 10 and the junction plate 15 are used for joint connection to a wing panel assembly onboard 20 and an outboard wing panel assembly 30.
    [00031] The wing-on-board panel assembly 20 is comprised of a wing-on-board shell 40 and a stiffening spar 60. The wing-on-board shell 40 and the stiffening spar 60 may both be comprised of a composite material. , which may be comprised of multiple layers of a material bonded and/or cured together. The material can be comprised of various materials used in forming composite materials. An example of this material is carbon fiber reinforced plastic. Also, the outboard wing panel assembly 30 is comprised of an outboard wing shell 50 and a stiffener spar 60. As discussed above, the outboard wing shell 50 and stiffener spar 60 may be also linked or cured together. The reinforcing stringer 60 used may be various reinforcing stringers, which are used to reinforce the composite parts, such as an I-shaped stringer or a blade stringer.
    [00032] The stiffener spar 60 is bonded to the wing shell 40, 50 to form a wing panel assembly 20, 30. The stiffener spar 60 and the wing shell 40, 50 can be cured together so as to form a bond between the two components. After the wing panel assemblies 20, 30 are formed, the wing panel assemblies 20, 30 can then be connected together with the tee cord 10 and the joint plate 15 to form a wing joint 1. gusset 60 may include a base flange 61 and a fabric 62. If the gusset 60 is an I gusset, as shown in FIG. 8, then the stiffener 60 may include a cover 63. The cap 63 and fabric 62 of the stiffener 60 may be trimmed so that only the base flange 61 of the stiffener 50 protrudes into the wing joint 1 The lid 63 and screen 62 can be trimmed to expose a noodle 64 or a plurality thereof, as discussed below.
    [00033] An end part of the onboard wing panel assembly 20 may be positioned between the onboard part 12 of the T-cord 10 and the onboard part 16 of the joint plate 15. As discussed above, the fabric 62 and the cap 63 can be trimmed so that only the base flange 61 of the stiffener spar 60, which is attached to the on-board wing shell 40, is positioned between the tee cord 10 and the junction plate 15. As discussed below, the reinforcing stringer 60 may also include one or more exposed noodles 64, which is also positioned between the T-cord 10 and the splice plate 15. Several fasteners 80 connect the on-board portion 12 of the T-cord 10 apart onboard 16 of the joint plate 15, securing the onboard wing panel assembly 20 to the wing joint 1. Likewise, the outboard wing panel assembly 30 is connected to the outboard portion 13 of the T-string 10 and to the outboard part 17 of the junction plate 15.
    [00034] FIG. 2 shows a partial cross-section of a wing panel assembly 20 which includes a stiffening spar 60 attached to a wing shell 40. The fabric 62 and cover 63 have been trimmed to expose a noodle 64 on the base flange 61 of the reinforcing stringer 60. The noodles 64 are typically unidirectional fibers, which are used to fill a joint between parts of a reinforcing stringer 60, as shown in FIG. 8. For example, a stiffening I-beam may be comprised of two "c" shaped arms connected together back to back. A void can exist at both the top and bottom junctions where the back of the arms meet. A noodle 64, which can be a unidirectional fiber, can be used to fill the void. The noodles 64 can be comprised of a variety of materials, such as a unidirectional carbon fiber reinforced plastic, a laminated carbon fiber reinforced plastic, or a fiberglass reinforced plastic. As shown in FIG. 2, noodle 64 may not be embedded in base flange 61. If noodle 64 is not embedded in base flange 61, the T-string 10 or reinforcing stringer 60 may be modified to accommodate non-embedded noodle 64, as discussed below.
    [00035] FIG. 3 is a schematic representation showing the potential forces that can be applied to the wing joint 1. With both the on-board wing housing 40 and the base flange 61 are secured to the tee cord 10 and the junction plate 15 at the same interface, the same pulling force is applied equally to both components, as shown by arrow 85. Further, the pulling forces (arrows 90) in both the T-string 10 and the joint plate 15 are substantially equal and in the same direction, because the two components provide a single interface for capturing the wing panel assembly 20, as compared to the multiple interfaces of the dual positive cord 210 shown in FIG. 12.
    [00036] FIG. 4 shows a part of a stiffening spar 60, which can be connected to the wing joint 1 of the present invention. Reinforcement stringer 60 includes a base flange 61 and screen 62 trimmed to expose a noodle 64. Reinforcement stringer 60 may include a screen extension and cover 65, in which screen 62 interfaces with exposed noodles. 64. As discussed above, the noodle 64 may be comprised of unidirectional fiber and may fill a void between the two interfaces in the reinforcing stringer 60.
    [00037] FIGS. 5A and 5B show a configuration of the T-string 10 that can be used on the wing joint 1. The T-string 10 may include a cut or trimmed detail 14 that allows the fabric 62 of the stiffener 60, such as the The blade of a blade-reinforcement stringer extends between one or more rows of fasteners 80, which connect the T-string 10 to a splice plate 15. The T-string 10 may include multiple rows of fasteners 80. For example, the tee cord 10 may include a first row of fasteners 81, a second row of fasteners 82 and a third row of fasteners 83. Trimmed detail 14 may be designed so that it traverses the first and second rows of fasteners 81, 82, as shown in FIGS. 5A and 5B. The T-string 10 may include various trimmed details 14. The use of the trimmed detail 14 of the T-string 10 may allow the gusset 60 to be more robust by allowing a greater length of the fabric 62 along the gusset 60. The number and orientation of trimmed details 14 is for illustrative purposes only. The configuration, depth and location of the trimmed details 14, as well as the number of lines and configuration of fasteners, can be varied, as will be appreciated by one skilled in the art having the benefit of this disclosure. For example, even the individual length of the trimmed details 14 can be varied within a single T-string 10.
    [00038] FIG. 6 shows a partial cross-section of a T-cord configuration 10, which includes at least one groove 18, on the bottom side of the edge portion 12 of the T-cord 10. The groove 18 may be adapted to accommodate a non-inlaid noodle. 64, present in wing panel assemblies 20, 30. Inserting the non-embedded noodle 64 into the groove 18 may allow the interface between the tee cord 10 and the wing panel assembly 20 to become recessed. The T-string 10 may include several slots 18 in the bottom of both the onboard 12 and the outboard 13 portions, to accommodate several of the exposed noodles 64.
    [00039] FIG. 7 shows a configuration of a trimmed reinforcing stringer 60, which includes shims 67 to accommodate the non-embedded noodles 64. The one or more noodles 67 are located adjacent the non-embedded noodles 64, between the base flange 61 and the string at T 10. Shims 67 fill the gaps between the wing panel assembly 20, 30 and the cord at T 10, due to the noodle 64 being non-inlaid. Shims 67 are shown for illustrative purposes only, as the shape, number and configuration of shims 67 can be varied, as will be appreciated by one skilled in the art having the benefit of this description.
    [00040] FIG. 8 shows a cross-section of an I stiffener 60 attached to a wing shell 40. The I stiffener 60 includes a base flange 61, a screen 62 and a cover 63. For jointed wing panels, the base flange 61 may include a base flange load 66, which is not required for joint cured wing panels. The cap 63 may include a cap filler 68 for both bonded and cured wing panels together. As shown, the noodles 64 fill the gap between the fabric 62 and the cover 63, as well as the gap between the fabric 62 and the base flange 61. As discussed above, the cover 63 and the fabric 62 can be trimmed at one end. of the gusset 60 to expose the noodle 64. The exposed noodle 64 and the base flange 61 can then face the bottom of the T-string 10 when the wing panel assembly 20, the gusset spar 60 attached to the wing housing 40, is attached to the T-string 10 and the junction plate 15, as discussed above.
    [00041] FIG. 9 shows a cross-section of a blade reinforcing stringer 60, which includes layers or strata, referred to herein as sacrificial layers 69, that allow material to be removed from the reinforcing stringer 60 while maintaining the desired structural integrity of the blade. rib 60. As discussed above, the web 62 of the rib 60 is trimmed to expose the noodle 64 and provide an interface between the rib 60 and the T-string 10. Upon exposure of the noodle 64, this 64 may not be embedded in base flange 61. To accommodate potential non-embedded noodles 64, sacrificial layers 69 are added to fabric 62 and base flange 61 of reinforcing stringer 60. Sacrificial layers allow fabric 61 is trimmed to a level 70, which is embedded with exposed noodles 64, while retaining a thickness of reinforcing stringer material 60, which maintains its intended structural integrity.
    [00042] With more particular reference to the drawings, embodiments of the invention may be described in the context of an aircraft production and maintenance process 100, as shown in FIG. 10, and of an aircraft 102, as shown in FIG. 11. During pre-production, example process 100 may include specification and design 104 of aircraft 102 and material procurement 106. During production, manufacture of components and subassembly 108 and system integration 110 of aircraft 102 occurs. Thereafter, the aircraft 102 can move on to certification and clearance 112, to be put into use 114. During use 114 by a customer, the aircraft 102 is scheduled for maintenance and use 116 (which may also include modification, reconfiguration, restoration , and so on).
    [00043] All processes of exemplary method 100 may be conducted by a system integrator, a third party and/or an operator (eg, a customer). For purposes of this description, a system integrator may include, without limitation, others from aircraft manufacturers and major system subcontractors; a third party may include, without limitation, other vendors, subcontractors and suppliers; and an operator can be an airline, a leasing company, a military entity, a maintenance organization, and so on.
    [00044] As shown in FIG. 11, aircraft 102 produced by exemplary process 100 may include an aircraft structure 118 with multiple systems 120 and an interior 122. Examples of high-level system 120 include one or more of a propulsion system 124, an electrical system 126, a hydraulic system 128, and an environmental system 130. Various other systems may be included. Although an aerospace example is shown, the principles of the invention can be applied to other industries, such as the automotive industry.
    [00045] The apparatus and process indicated in this specification may be used during one or more of the stages of the production and maintenance process of the aircraft 100. For example, the components or sub-assemblies, corresponding to the production process 108, may be manufactured or manufactured in a manner similar to components or sub-assemblies produced while the aircraft 102 is undergoing maintenance 114. Also, one or more apparatus configurations, process configurations or a combination thereof may be used during production processes 108 and 110, for example, by optimized assembly or cost reduction of an aircraft 102. Similarly, one or more apparatus configurations, process configurations or a combination thereof may be used while the aircraft 102 is undergoing maintenance 114, for example, and without limitation, in use and maintenance 116.
    [00046] Further, the invention comprises the embodiments according to the following clauses:1. A wing joint, comprising: a tee cord having an onboard part, an outboard part and a vertical part; a junction plate having an onboard part and an outboard part; an onboard wing casing; a outboard wing shell; at least one onboard stiffening spar connected to the onboard wing shell to form an onboard wing panel assembly, a part of the onboard wing panel assembly positioned between the onboard part of the tee cord and the onboard part of the splice plate; a first plurality of fasteners connecting the onboard part of the tee cord with the onboard part of the splice plate, for securing the onboard wing panel assembly to the tether at least one outboard stiffener spar connected to the outboard wing shell to form an outboard wing panel assembly, a part of the outboard wing panel assembly positioned between the outboard part of the T-string and the outboard part of the junction plate; and a second plurality of fasteners connecting the outboard portion of the tee cord with the outboard portion of the juncture plate, for securing the outboard wing panel assembly to the tee cord and juncture plate. The wing joint according to clause 1, wherein the joint is a joint on the lower body side for a composite wing assembly.3. The winged joint according to clause 1, wherein the outboard stiffening stringer and the onboard stiffening stringer both comprise a base flange, at least one fabric and at least one noodle. 4. The winged joint according to clause 3, wherein the outboard stiffening stringer and the onboard stiffening stringer are blade stiffening stringers.5. The winged joint according to clause 3, wherein the onboard part of the T-string comprises at least one cut, and the outboard part of the T-cord comprises at least one cut, a part of the reinforcing spar fabric on board extending into the cut in the onboard portion of the T-rope, and a portion of the outboard stiffening stringer fabric extending into the cut in the outboard portion of the T-string. The winged joint according to clause 5, both the first and second plurality of fasteners comprising at least three longitudinal rows of fasteners, the at least one cut in the edge portion extending between the fasteners in at least one row of fasteners, and the at least one cut in the outboard portion extending between the fasteners in at least one row of fasteners.7. The winged joint according to clause 5, both the first and second plurality of fasteners comprising at least three longitudinal rows of fasteners, the at least one cut in the edge portion extending between the fasteners in at least two rows of fasteners, and the at least one cut in the outboard portion extending between the fasteners in at least two rows of fasteners.8. The winged joint according to clause 3, the outboard stiffening stringer and the onboard stiffening stringer being stiffening stringers in I.9. The winged joint according to clause 8, the I-reinforcement stringers further comprising a cap.10. The wing joint in accordance with clause 3, the outboard stiffening stringer and the onboard stiffening stringer both being trimmed to expose the at least one noodle.11. The wing joint according to clause 10, wherein the on-board wing panel assembly comprises a part of the on-board wing shell, a part of the base flange of the on-board stiffening spar, and a part of the at least one exposed noodles of the onboard stiffening spar, and wherein the outboard wing panel assembly comprises an outboard wing shell portion, a portion of the outboard stiffening spar base flange, and a portion of the at least one exposed noodle from the outboard reinforcement spar.12. The wing joint according to clause 11, the tee cord further comprising a first groove in the onboard part for accommodating the at least one exposed noodle of the onboard reinforcement spar, and a second groove in the outboard part for accommodate the at least one exposed noodle from the outboard reinforcement stringer.13. The winged joint according to clause 11, further comprising a first shim and a second shim, the first shim positioned between the base flange of the onboard reinforcing spar and the onboard portion of the T-string, the first shim being adjacent to at least one exposed rib of the onboard stiffener, the second shim positioned between the base flange of the outboard stiffener and the outboard portion of the T-string, the second shim being adjacent to the at least one spar exposed outboard reinforcement spar.14. A method of forming a wing joint, the method comprising: forming an on-board wing panel assembly, the on-board wing panel assembly comprising at least one on-board stiffening spar connected to an on-board wing shell, the at least one onboard stiffening spar comprising a base flange, at least one screen and at least one noodle; forming an outboard wing panel assembly, the outboard wing panel assembly comprising at least one spar outboard rib connected to an outboard wing shell, to at least one outboard rib spar comprising a base flange, at least one ply and at least one noodle; trim to at least one rib spar fabric onboard to expose the at least one noodle; trim the at least one outboard stiffening spar screen to expose the at least one noodle; position a part of the onboard wing panel assembly between an onboard part of a cord the T-shape and an onboard part of a joint plate, the part of the onboard wing panel assembly including a part of the onboard wing shell, a part of the onboard stiffening spar base flange and the at least an exposed noodle of the onboard reinforcing spar; securing the onboard wing panel assembly to the onboard portion of the tee cord and to the onboard portion of the joint plate with a plurality of fasteners; positioning a portion of the onboard panel assembly outboard wing between an outboard part of a T-string and an outboard part of a junction plate, the part of the outboard wing panel assembly including a part of the outboard wing casing, a part of the base flange of the outboard stiffener and the at least one exposed noodle of the outboard stiffener; and securing the outboard wing panel assembly to the outboard portion of the tee cord and to the outboard portion of the junction plate with a plurality of fasteners.15. The method according to clause 14, further comprising: providing a groove in the onboard portion of the tee cord to accommodate the at least one exposed noodle of the onboard reinforcement spar; and provide a groove in the outboard portion of the T-string to accommodate the at least one exposed noodle of the outboard reinforcement spar.16. The method according to clause 14, further comprising: providing at least one first shim positioned between the onboard wing panel assembly and the onboard portion of the T-cord, the first shim being adjacent to at least one exposed noodle the reinforcing stringer on board; and providing at least one second shim, positioned between the outboard wing panel assembly and the outboard portion of the tee cord, the second shim being adjacent to at least one exposed noodle of the outboard stiffening spar.17. The method according to clause 14, wherein forming an on-board wing panel assembly further comprises curing the on-board wing shell and on-board stiffening spar together, and wherein forming an on-board wing panel assembly. on board further comprises the joint curing of the outboard wing casing and the outboard stiffening spar.18. The method according to clause 14, wherein forming an on-board wing panel assembly further comprises joining together the on-board wing shell and the on-board stiffening spar, and wherein forming an on-board wing panel assembly. on board also comprises the joint connection of the outboard wing casing and the outboard reinforcement spar.19. The process according to clause 14, wherein the reinforcing stringers are composite materials comprised of a plurality of layers.20. The method according to clause 19, further comprising: adding sacrificial layers to the onboard stiffening spar and the outboard stiffening spar prior to forming the onboard wing panel assembly and prior to forming the panel assembly of outboard wing, the additional sacrificial layers allowing the removal of the sacrificial layers, to provide the exposed noodles to be embedded without reducing a load-bearing capacity of the onboard and outboard wing panel assemblies.21. A wing joint, comprising: a first retaining plate; a second retaining plate; and a wing panel assembly, the wing panel assembly comprising a stiffening spar connected to a wing housing, a portion of the wing panel assembly being clamped between the first retaining plate and the second retaining plate, in that the reinforcing spar of the wing panel assembly part, clamped between the first retaining plate and the second retaining plate, is trimmed to expose a noodle.
    [00047] While this invention has been described in terms of certain preferred embodiments, other embodiments that are apparent to those skilled in the art, including embodiments that do not provide all of the features and advantages shown in this specification, are also within the scope of this specification. invention. Accordingly, the scope of the present invention is defined only by reference to the appended claims and their equivalents. TABLE OF REFERENCE NUMBERS FOR FIGS. 1 - 121 - wing joint10 - rope at T11 - vertical part of the rope at T12 - onboard part of the rope at T13 - outboard part of the rope at T14 - cutting characteristic on the rope at T15 - junction plate16 - onboard part of junction plate17 - outboard part of junction plate18 - rope grooves in T20 - onboard wing panel assembly30 - outboard wing panel assembly40 - onboard wing casing50 - outboard wing casing60 - reinforcing stringer61 - base flange62 - fabric63 - cover64 - macaroni65 - cover and fabric extension66 - base flange load67 - shim68 - cover load69 - sacrificial plies70 - trim level80 - fastener 81 - first row of fasteners82 - second row of fasteners83 - third row of fasteners85 - pull force on wing panel assembly90 - pull force on tee cord and joint plate200 - prior art wing joint210 - double positive cord211 - vertical part of double positive cord212 - part onboard double positive rope upper edge213 - double positive rope lower edge part214 - double positive rope upper outboard part215 - double positive rope lower outboard part220 - wing panel assembly on board230 - wing panel assembly outboard240 - onboard wing housing250 - outboard wing housing260 - stiffening spar261 - stiffening spar base flange262 - stiffening spar fabric263 - stiffening spar cover270 - joint plate280 - fastener281 - fastener282 - fastener291 - radial filling
    权利要求:
    Claims (15)
    [0001]
    1. Winged joint (1), characterized in that it comprises: a T-string (10) having an onboard part (12), an outboard part (13) and a vertical part (11); joint (15) having an onboard part (16) and an outboard part (17); an onboard wing casing (40); an outboard wing casing (50); at least one reinforcing spar a edge (60) connected to the onboard wing shell (40), to form an onboard wing panel assembly (20), a part of the onboard wing panel assembly (20) positioned between the onboard portion of the lanyard T-rope (12) and the on-board part of the junction plate (16); a first plurality of fasteners (80) connecting the on-board part of the T-string (12) with the on-board part of the junction plate (16) , for attaching the onboard wing panel assembly (20) to the tee cord (10) and juncture plate (15); at least one outboard stiffening spar (60) connected to the outboard wing housing (50), to form a wing panel assembly outboard (30), a portion of the outboard wing panel assembly (30) positioned between the outboard portion of the T-string (13) and the outboard portion of the gusset (17); and a second plurality of fasteners (80) connecting the outboard portion of the T-string (13) with the outboard portion of the junction plate (17), for securing the outboard wing panel assembly (30) to the T-string (10) and the junction plate (15).
    [0002]
    2. Winged joint (1), according to claim 1, characterized in that the joint (1) is a joint on the side of the lower body for a composite wing assembly.
    [0003]
    3. Winged joint (1), according to claim 1 or 2, characterized in that the outboard reinforcement spar (60) and the onboard reinforcement spar (60) are blade reinforcement spars, each one comprising a base flange (61), at least one screen (62) and at least one noodle (64).
    [0004]
    4. Winged joint (1), according to any one of the preceding claims, characterized in that the onboard part of the T-string (12) comprises at least one cut (14), and the outboard part of the T-string (13) comprising at least one cut (14), a portion of a screen (62) of the on-board reinforcing stringer (60) extending into the cut (14) in the on-board part of the T-string (12), and a portion of a screen (62) of the outboard reinforcement stringer (60) extending into the cut (14) in the outboard portion of the T-string (13).
    [0005]
    5. Winged joint (1) according to any one of the preceding claims, characterized in that the first and second plurality of fasteners (80) each comprise at least three longitudinal rows of fasteners (81, 82, 83) , wherein at least one cut (14) in the on-board portion of the T-string (12) extends between the fasteners (80) in at least one row of fasteners (80), and at least one cut (14) in the The T-string (13) extends between the fasteners (80) in at least one row of fasteners (80).
    [0006]
    6. Winged joint (1) according to any one of the preceding claims, characterized in that the first and second plurality of fasteners (80) each comprise at least three longitudinal rows of fasteners (81, 82, 83) , wherein at least one cut (14) in the on-board portion of the T-string (12) extends between the fasteners (80) in at least two rows of fasteners (80), and at least one cut (14) in the The T-string (13) extends between the fasteners (80) in at least two rows of fasteners (80).
    [0007]
    7. Winged joint (1), according to any one of the preceding claims, characterized in that the outboard stiffener (60) and the onboard stiffener (60) are I-shaped stiffener stringers , both having a cover (63).
    [0008]
    8. Winged joint (1) according to any one of the preceding claims, characterized in that both the outboard stiffener (60) and the onboard stiffener (60) comprise at least a noodle (64), both the outboard rib (60) and the onboard rib (60) are trimmed to expose the at least one noodle (64).
    [0009]
    9. Winged joint (1), according to any one of the preceding claims, characterized in that the onboard wing panel assembly (20) comprises a part of the onboard wing casing (40), a part of a base flange (61) of the onboard stiffener (60), and a portion of the at least one exposed noodle (64) of the onboard stiffener (60), and wherein the wing panel assembly is outside (30) comprises a part of the outboard wing casing (50), a part of a base flange (61) of the outboard stiffening spar (60), and a part of the at least one noodle (64) ) of the exposed outboard reinforcement spar (60), wherein the T-string (10) further comprises a first groove (18) in the onboard portion (12) to accommodate the at least one exposed noodle (64) of the onboard stiffener (60), and a second groove (18) in the outboard portion (13), to accommodate the at least one exposed noodle (64) of the outboard stiffener (60), and comp further comprising a first shim (67) and a second shim (67), the first shim (67) positioned between the base flange (61) of the onboard reinforcing stringer (60) and the onboard part of the rope at T (12), the first shim (67) being adjacent to at least one exposed noodle (64) of the onboard reinforcement spar (60), the second shim (67) positioned between the base flange (61) of the outboard stiffener (60) and the outboard portion of the T-string (13), the second shim (67) being adjacent to at least one exposed noodle (64) of the outboard stiffener spar (60).
    [0010]
    10. Process of forming a wing joint (1), the process characterized in that it comprises: forming an on-board wing panel assembly (20), the on-board wing panel assembly (20) comprising at least one on-board reinforcement spar (60) connected to an on-board wing shell (40), at least one on-board reinforcement spar (60) comprising a base flange (61), at least one screen (62) and at least one noodle (64); forming an outboard wing panel assembly (30), the outboard wing panel assembly (30) comprising at least one outboard stiffening spar (60) connected to an outboard wing casing (50), at least one outboard stiffening spar (60) comprising a base flange (61), at least one screen (62) and at least one noodle (64); the at least one screen (62) of the onboard stiffener (60) for exposing the at least one noodle (64); trimming the at least one screen (62) of the stiffener spar out of edge (60) for exposing the at least one noodle (64); positioning a part of the on-board wing panel assembly (20) between an on-board part of a T-string (12) and an on-board part of a board joint (16), the part of the onboard wing panel assembly (20) including a part of the onboard wing shell (40), a part of the base flange (61) of the onboard stiffening spar (60) and the at least one exposed noodle (64) of the onboard reinforcement spar (60); attaching the onboard wing panel assembly (20) to the onboard portion of the T-string (12) and to the onboard portion of the plate (16) with a plurality of fasteners (80); positioning a part of the outboard wing panel assembly (30) between an outboard part of a tee cord (13) and an outboard part of a junction plate (17), the part of the outboard wing panel assembly (30) including a part of the outboard wing shell (50), a part of the base flange (61) of the outboard stiffening spar board (60) and the at least one noodle (64) exposed from the outboard stiffener (60); and securing the outboard wing panel assembly (30) on the outboard portion of the tee cord (13) and on the outboard portion of the junction plate (17) with a plurality of fasteners (80).
    [0011]
    11. Process according to claim 10, characterized in that it further comprises: providing a groove (18) in the onboard part of the T-string (12) to accommodate the at least one exposed noodle (64) of the stringer of onboard reinforcement (60); and providing a groove (18) in the outboard portion of the T-string (13) to accommodate the at least one exposed noodle (64) of the outboard reinforcement spar (60).
    [0012]
    12. Process, according to claim 10 or 11, characterized in that it further comprises: providing at least a first shim (67), positioned between the onboard wing panel assembly (20) and the part a edge of the T-string (12), the first shim (67) being adjacent to at least one exposed noodle (64) of the on-board stiffening stringer (60); and provide at least one second shim (67) positioned between the outboard wing panel assembly (30) and the outboard portion of the T-string (13), the second shim (67) being adjacent to at least at least one noodle (64) exposed from the outboard stiffening stringer (60).
    [0013]
    13. Process according to any one of claims 10 to 12, characterized in that forming an on-board wing panel assembly (20) further comprises the joint curing of the on-board wing casing (40) and the on-board spar. onboard stiffener (60), and wherein forming an outboard wing panel assembly (30) further comprises curing the outboard wing shell (50) and outboard stiffener spar (60) together.
    [0014]
    14. Process according to any one of claims 10 to 13, characterized in that forming an on-board wing panel assembly (20) further comprises the joint connection of the on-board wing casing (40) and the onboard stiffener (60), and wherein forming an outboard wing panel assembly (30) further comprises joining together the outboard wing shell (50) and the outboard stiffener spar (60).
    [0015]
    15. Process according to any one of claims 10 to 14, characterized in that it further comprises: adding sacrificial layers (69) to the onboard reinforcement spar (60) and to the outboard reinforcement spar (60) , prior to formation of the onboard wing panel assembly (20) and prior to formation of the outboard wing panel assembly (30), the additional sacrificial layers (69) allowing the removal of the sacrificial layers (69) , to provide the exposed noodle (64) to be recessed without reducing a load-bearing capacity of the onboard and outboard wing panel assemblies (20, 30), wherein the reinforcing stringers (60) are composite materials comprised of several layers.
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    同族专利:
    公开号 | 公开日
    AU2013245438B2|2016-01-21|
    EP2730498A3|2017-11-15|
    KR20140061237A|2014-05-21|
    AU2013245438A1|2014-05-29|
    RU2013150275A|2015-05-20|
    CN103803054A|2014-05-21|
    JP5808379B2|2015-11-10|
    KR101790439B1|2017-10-25|
    US20140131518A1|2014-05-15|
    CN103803054B|2016-06-15|
    KR20160058732A|2016-05-25|
    ES2738790T3|2020-01-27|
    BR102013029090A2|2014-10-21|
    JP2014097786A|2014-05-29|
    EP2730498A2|2014-05-14|
    US9272769B2|2016-03-01|
    RU2654270C2|2018-05-17|
    EP2730498B1|2019-05-01|
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    法律状态:
    2014-10-21| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    2018-11-21| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2020-02-27| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-11-16| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2022-01-18| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 12/11/2013, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/675,809|US9272769B2|2012-11-13|2012-11-13|Joint for composite wings|
    US13/675,809|2012-11-13|
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