• 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:
    TUBULAR COMPOUND ANCHOR HAVING INTERNAL REINFORCEMENT AND METHOD FOR MANUFACTURING THE SAME. The present invention relates to a strut (20) which comprises a substantially hollow composite tube (22). A fitting (24) at each end of the tube adapts the strut for attachment to a structure. The tube is reinforced by at least a pair of opposite reinforcements. A method of creating the anchor is also revealed.
    公开号:BR112014010465B1
    申请号:R112014010465-4
    申请日:2012-10-05
    公开日:2020-11-17
    发明作者:Samuel R. Stewart
    申请人:The Boeing Company；
    IPC主号:
    专利说明:

    BACKGROUND INFORMATION 1. Field:
    [001] The present disclosure relates, in general, to composite column structures and deals more particularly with an internally reinforced tubular strut to maximize the ratio of strength to strut weight. 2. Precedents:
    [002] Column structures formed from compounds are used in a variety of applications because of their favorable strength to weight ratio. For example, composite tubular struts can be used in the aerospace industry as a support or reinforcement to transfer loads in any direction along the longitudinal geometric axis of the strut, thereby placing the strut under compression or tension. Fittings at the ends of the strut provide additional strength at the strut attachment points on a frame.
    [003] Composite struts are known in which end fittings, often made of metal, are attached to a tubular composite body by connections rather than by fasteners. The tubular bodies have a substantially constant cross section and a relatively thick wall, in order to meet design load criteria. Fittings can be attached to the ends of the tubular body by double-step joints that can result in greater than desired peeling forces being applied to the inner and outer layers of the tube wall. The manufacture of these types of composite struts is both laborious and long because of the need for precise manual layering of the layers, as well as the need for two autoclave curing cycles to separately cure the inner and outer layers of the joint.
    [004] Thus, there is a need for a tubular composite strut that can be manufactured more quickly and using less specialized labor hours. There is also a need for a composite strut as described above that has an improved strength to weight ratio. SUMMARY
    [005] The revealed modalities feature a tubular composite strut and related manufacturing method that optimize the strut's structural strength ratio through the use of a suitable cross-section tube configuration using internal reinforcements cured together with the tube body, as well as the ability to adjust the thickness of the outer layer. The strut is manufactured using an internal mandrel that allows the arrangement of internal reinforcements designed to result in an ideal moment of inertia value and to maximize the performance of the strut. The internal mandrel allows the use of an automatic fiber placement machine to arrange the layers of the tubular body and reinforcements, which can reduce the need for an autoclave curing cycle to achieve the desired compaction. The tube body is joined in the end fittings using a stepped joint with a single side connection. The internal reinforcements can be positioned and designed to resist bending forces depending on the loading plane of the fixture, thus allowing a reduction in the thickness of the pipe body wall.
    [006] According to a disclosed embodiment, a strut is presented comprising a laminated composite tubular body having a substantial hollow interior. At least one pair of reinforcements extends longitudinally through the interior of and is attached to opposite sides of the tubular body. The tube body includes end fittings adapted to attach the strut to a frame. The fittings include an opening having a central geometric axis and adapted to receive an elongated pin connecting the fitting to the structure. Each end of the reinforcements is substantially symmetrical around a plane that extends perpendicular to the geometric axis of the pin. Each of the inserts includes a pair of the plurality of external steps and the tubular body includes groups of layers respectively overlapping and joined on the steps. The strut also comprises a single shear joint between each of the fittings and a corresponding end of the tubular body. Each reinforcement is a laminated compound cured together with the tubular body.
    [007] According to another modality, a strut is presented to transfer the loads in compression or tension. The strut comprises an elongated tubular body having a wall formed of multiple laminated composite layers and end fittings adapted to secure the tubular body to a structure using a pin. The strut also comprises a single joined shear joint between each of the fittings and the tubular body and composite reinforcements within the tubular body attached to the wall to reinforce the body. Each of the end fittings transfers the loads to the tubular body around the longitudinal geometric axis of the corresponding pin. The composite reinforcements include at least a first pair of opposing reinforcements aligned along a geometric axis substantially perpendicular to the geometric axes of the pin.
    [008] According to yet another modality, a method is presented to constitute a strut, comprising making an elongated mandrel, including forming cavities in the mandrel along its length. The method also includes placing a slot at each end of the mandrel, locating composite reinforcement devices in the mandrel cavities and forming a tubular composite body by arranging the composite layers in the mandrel overlapping the reinforcement devices and the inserts. The method also involves curing the tubular body and reinforcements together and removing the mandrel. The formation of the mandrel includes forming an axis at each end of the mandrel and the placement of the grooves in the mandrel is performed by placing the grooves in the axes. Reinforcements can be formed out of line and placed in the mandrel as a complete part arrangement. The location of the reinforcement devices in the mandrel cavities includes arranging and forming the reinforcements and placing the reinforcement devices formed in the cavities. The formation of the tubular body can be carried out using an automatic fiber laying machine to lay and compact strips of the composite tape on the surface of the mandrel. The location of the reinforcement devices in the mandrel cavities may include using an automatic fiber laying machine to seat and compact the strips of composite tape within the cavities. The formation of the tubular composite body may include forming a single shear joint between the tubular body and each of the fittings. Removing the mandrel may include dissolving the mandrel with a liquid. The method may further comprise inserting reinforcement mandrels into the reinforcement devices and removing the reinforcement mandrels after the tubular body and reinforcements have been cured together.
    [009] In short, according to one aspect of the invention, a strut is provided, including a laminated composite tube having a substantially hollow interior, at least a pair of longitudinal reinforcements attached to the opposite sides of the tube and a fitting at each end of the tube adapted to be attached to a structure.
    [0010] Advantageously, the strut on which the reinforcements are located inside the hollow interior of the tube.
    [0011] Advantageously, the strut in which the fitting includes an opening having a central geometric axis and adapted to receive an elongated pin connecting the fitting to the structure and each reinforcement is substantially symmetrical around a plane perpendicular to the geometric axis of the opening .
    [0012] Advantageously, the strut in which each reinforcement is substantially symmetrical around a plane perpendicular to the geometric axis of the opening.
    [0013] Advantageously, the strut in which each of the fittings includes a plurality of external steps and the tube includes groups of layers respectively overlapping the steps, in which the external steps and overlapping groups of layers form a single shear joint.
    [0014] Advantageously, the anchor still including a second pair of reinforcements within the hollow interior of the tube and attached to the tube.
    [0015] Advantageously, the strut in which the second pair of reinforcements is substantially symmetrical around a plane substantially parallel to the geometric axis of the opening and each reinforcement is trapezoidal in the shape of the cross section.
    [0016] Advantageously, the strut in which each reinforcement is a laminated compound and is cured together with the tube.
    [0017] Advantageously, the strut in which each of the fittings is made of metal and is attached to the tube by a single shear joint.
    [0018] According to another aspect of the invention, a strut for transferring loads in compression or tension, including an elongated tube having a wall formed of multiple laminated composite layers, is provided; a fitting at each end of the tubular body adapted to secure the tube to a structure with a pin, a single shear joint between each of the fittings and the tube and composite reinforcements attached to the tube wall to reinforce the body.
    [0019] Advantageously, the strut on which each of the fittings transfers loads to the tube around the longitudinal geometric axis of the corresponding pin and the composite reinforcements are located inside the tube and include at least a first pair of opposite reinforcements aligned along a geometric axis substantially perpendicular to the geometric axes of the pin.
    [0020] Advantageously, the strut on which the composite reinforcements include a second pair of opposing reinforcements aligned along a geometric axis that extends substantially parallel to the geometric axes of the pin.
    [0021] Advantageously, the strut in which each of the fittings includes an external wall having a plurality of external steps and the tube body includes groups of layers respectively overlapping the external steps and forming a single shear joint.
    [0022] Advantageously, the strut in which each reinforcement is a laminated compound and is cured together with the tube.
    [0023] Advantageously, the strut on which each reinforcement extends substantially along the length between the fittings.
    [0024] In accordance with yet another aspect of the invention, a method of creating a strut is provided, including making an elongated mandrel; place a slot on each end of the mandrel; locate compound reinforcement devices in the mandrel; forming a composite tube by arranging composite layers in the mandrel; cure the tube and reinforcements together and remove the mandrel.
    [0025] Advantageously, the method in which the manufacture of the mandrel includes forming an axis at each end of the mandrel and forming the cavities in the mandrel along its length and the placement of the grooves in the mandrel is performed by placing the grooves in the axes.
    [0026] Advantageously, the method in which the location of the reinforcement devices in the mandrel includes the arrangement and formation of the reinforcements and the placement of the reinforcement devices formed in the mandrel cavities.
    [0027] Advantageously, the method in which the formation of the composite tube is performed using an automatic fiber laying machine to seat and compact strips of composite tape on the surface of the mandrel.
    [0028] Advantageously, the method in which the location of the reinforcement devices in the mandrel cavities includes using an automatic fiber laying machine to seat and compact strips of composite tape within the cavities.
    [0029] Advantageously, the method in which the formation of the composite tube includes forming a single shear joint between the tube and each of the fittings.
    [0030] Advantageously, the method in which removing the mandrel includes dissolving the mandrel with a liquid.
    [0031] Advantageously, the method further includes inserting reinforcement mandrels into the reinforcement devices and removing the reinforcement mandrels after the tube and reinforcements have been cured together.
    [0032] In accordance with a further aspect of the present invention, a method of creating a strut for aircraft applications is presented, including making an elongated mandrel, including forming cavities in the mandrel along its length and forming shafts at each end of the mandrel; manufacture metal end fittings, place sleeves in the metal end fitting respectively on the mandrel axes; arranging and forming a plurality of reinforcements, each having a cross-sectional shape corresponding to the cross-sectional shape of the mandrel cavities; locate the composite reinforcement devices in the mandrel cavities; place reinforcement mandrels on the reinforcement devices; form a composite tube by arranging the composite layers in the mandrel overlapping the reinforcement devices, the fittings and the reinforcement mandrels and cure together the pipe and the reinforcement devices and remove the mandrels by dissolving the mandrels.
    [0033] In accordance with a still further aspect of the present invention, an airplane prop is provided for transferring loads in compression or tension, including an elongated tube having a wall formed of multiple laminated composite layers; a fitting at each end of the tube adapted to secure the tubular body to a structure with a pin; a single shear joint between each of the fittings and the pipe body; and composite reinforcements within the pipe body attached to the wall to reinforce the body and where each of the fittings transfers the loads to the pipe body along the longitudinal geometric axis of the corresponding pin, and the composite reinforcements include at least one first pair of opposite reinforcements aligned along a geometric axis substantially perpendicular to the geometric axes of the pin, each reinforcement has a substantially trapezoidal cross-sectional shape, the composite reinforcements also include a second pair of opposite reinforcements aligned along a geometric axis which extends substantially parallel to the geometric axes of the pin, each of the fittings includes an outer wall having a plurality of outer steps and a substantially smooth inner wall, and the tube body includes groups of layers respectively overlapping the outer steps.
    [0034] The characteristics, functions and advantages can be achieved independently in several modalities of the present disclosure or can be combined in still other modalities, in which additional details can be observed with reference to the following description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS
    [0035] The new aspects deemed characteristic of the advantageous modalities are presented in the attached claims. The advantageous modalities, however, as well as a preferred mode of use, additional objectives and their advantages will be better understood by reference to the following detailed description of an advantageous embodiment of the present disclosure when read in conjunction with the accompanying drawings, in which:
    [0036] FIGURE 1 is an illustration of a perspective view of an anchor composed according to the revealed modalities.
    [0037] FIGURE 2 is an illustration of a top view of one of the anchor end fittings shown in FIGURE 1.
    [0038] FIGURE 2A is an illustration of a side view in the direction shown as 2A-2A in FIGURE 2,
    [0039] FIGURE 3 is an illustration of a sectional view taken along line 3-3 in FIGURE 1.
    [0040] FIGURE 4 is an illustration of a sectional view taken along line 4-4 in FIGURE 3.
    [0041] FIGURES 4A to 4C are illustrations similar to FIGURE 4A, but showing alternate modalities of the composite strut, respectively.
    [0042] FIGURE 5 is an illustration of a perspective view of a mandrel used to manufacture the strut shown in FIGURE 1.
    [0043] FIGURE 6 is an illustration of a top view of the mandrel shown in FIGURE 5, with the strut end fittings having been secured to the mandrel axes.
    [0044] FIGURE 7 is an illustration of a sectional view taken along line 7-7 in FIGURE 6.
    [0045] FIGURE 8 is an illustration of a sectional view taken along line 8-8 in FIGURE 7.
    [0046] FIGURE 9 is an illustration of a perspective view of a reinforcement device.
    [0047] FIGURE 10 is an illustration of a cut end view showing the reinforcement shown in FIGURE 9 being placed in one of the mandrel cavities.
    [0048] FIGURE 11 is an illustration similar to FIGURE 10, but showing the reinforcement having been fully installed in the cavity and a mandrel having been installed inside the reinforcement.
    [0049] FIGURE 12 is an illustration similar to FIGURE 10, but showing an alternating modality of the reinforcement being placed in a modified shape of one of the mandrel cavities.
    [0050] FIGURE 13 is an illustration similar to FIGURE 12, but showing the reinforcement having been fully installed in the cavity and a mandrel together with radius fillers having been installed.
    [0051] FIGURE 14 is an illustration similar to FIGURE 13, but showing strips of composite tape being arranged over the mandrel, covering the reinforcement and the reinforcement mandrel.
    [0052] FIGURE 15 is an illustration of a perspective view of an automatic fiber laying machine applying composite tape to the mandrel assembly shown in FIGURE 6.
    [0053] FIGURE 16 is an illustration of a flow diagram of a method of creating an anchor composed according to the revealed modalities.
    [0054] FIGURE 17 is an illustration of an airplane production flow diagram and service methodology.
    [0055] FIGURE 18 is an illustration of an airplane block diagram. DETAILED DESCRIPTION
    [0056] Referring first to FIGURE 1, a columnar structural element in the form of an elongated strut 20 comprises a generally cylindrical tube 22 and a pair of end fittings 24 joined at opposite ends of tube 22. Tube 22 may comprise, but it is not limited to a composite material, such as multiple laminated layers of a fiber-reinforced polymer resin including, but not limited to, carbon fiber-reinforced epoxy. In the illustrated example, the shape of the cross section of the tube body 22 is substantially round, however, other shapes of cross section are possible, such as, without limitation, square, triangular, hexagonal and pentagonal shapes.
    [0057] Each of the end fittings 24 can be, but is not limited to, a metal, such as aluminum or titanium or a compound. End fittings 24 can be manufactured by casting, machining or other common manufacturing techniques. Where end fittings 24 are formed of composite materials, they may include metallic inserts and / or metallic bushings (not shown). Each end fitting includes shackles 26 comprising a pair of separate projections 28 respectively having an opening 30 aligned along a geometry axis 27 to receive a fixing pin 32, without limitation shown as cylindrical, which connects fitting 24 in a structure (not shown). Although shown as a double projection shackle 28, more or less than two projections 28 can be used, depending on the application. The pins 32, together with the end fittings 24, form articulated connections between the prop 20 and the structure (not shown) in which it is attached. Strut 20 can be used, for example, and without limitation, as a support between an aircraft engine (not shown) and the frame (not shown). Depending on the application, the strut 20 can function to transfer axial loads in a bidirectional manner, so that the strut 20 can be tensioned or compressed or both alternately, along its central geometric axis 29. The strut 20 may also experience limited torsional loading.
    [0058] With reference now to FIGURES 2, 3 and 4, each of the fittings 24 includes a cylindrical section 35 having an outer diameter Di (FIGURE 2) that is substantially equal to the outer diameter D2 (FIGURE 4) of the tube body 22. End fittings 24 also include a stepped section 40 of length L formed by a series of cylindrical steps 42 of progressively smaller diameter. Increasing the length L approximately for the application helps to disperse the “stiffness” associated with the intersection of a metal fitting 24 and the composite tube 22. In other words, increasing the length L of the staggered section 40 disperses the transferred load between end fitting 24 of tube 22 through a larger area. The interior of each socket 24 can be substantially hollow, defined by a smooth longitudinally extending hole 44 having a diameter D3 that extends across the length of the socket 24. In the illustrated embodiment, the diameter D3 of hole 44 is substantially the same as inner diameter D4 of tube 22, in order to maximize the contact area and thus the load transfer capacity between socket 24 and tube 22. However, in other embodiments, the diameter D3 of hole 44 may be different than the inner diameter D4 of the tube 22. As shown in FIGURE 2, the projections 28 are separated into 38 to receive a projection 33 on a structure (not shown) on which the prop must be attached. Although not shown in FIGURE 2, the fixing pin 32 (FIGURE 1) passes through each of the projections 28, 33.
    [0059] The body of the tube 22 comprises a plurality of staggered groups 45 of composite layers 48 which can be formed of tape reinforced with prepreg fiber applied, for example, and without limitation, by an automatic fiber laying machine (AFP) (not shown). However, the use of other types of composite materials, such as, without limitation, metallic and ceramic, and other types of manufacturing techniques may be possible. The staggered layer groups 45 are sequentially arranged on the steps 42 of the end fittings 24, starting with the layer arrangement on the innermost step 42a and ending with the layer arrangement on the outermost step 42b. The groups of stepped layers 45 respectively overlap the steps 42 to form a single stepped shear joint 40 that extends along the length L of the stepped section 40 of the socket 35. In other embodiments, it may be possible to use a skewed joint (not shown) ) between the tube 22 and the socket 24, which comprises multiple chamfers with the same or varied inclinations. The wall 50 of the tube body 22 has a thickness t (FIGURE 4). In the illustrated embodiment, the staggered layer groups 45 form a female tube end at which the male fitting 24 is received, however, in other embodiments, the staggered layer groups 45 can form a male end of the tube 22 and the steps 42 of the socket 24 can be formed in the inner diameter D3 of the hole 44 that receives the male end of the tube 22.
    [0060] With reference now particularly to FIGURES 3 and 4, in one embodiment, the tube 22 can be internally reinforced by two pairs of elongated composite reinforcements 52, 54, respectively. The first pair of reinforcements 52 is located diametrically opposite from each other (FIGURE 4) on the inner surface 47 of the wall of the tube 22 and is generally symmetrically aligned along the geometric axis 25 which extends substantially orthogonal to the geometric axis 27 of the pin 30. The second pair of reinforcements 54 is also located diametrically opposite from each other and generally aligned symmetrically along the geometric axis 27 of pin 30. In the example shown, each of the reinforcements 52, 54 is substantially trapezoidal in the shape of the cross section however, other forms of cross section are possible. Each of the reinforcements 52 has a larger cross-sectional area than the reinforcements 54, in order to provide the tube 22 with greater resistance to curvature around the geometric axes of the pin 27. In one embodiment, one or both of the reinforcements 52, 54 have a cross-sectional shape that is substantially constant over the length of the reinforcement 52, 54. However, in other embodiments, the cross-section of any of the reinforcements 52, 54 can vary in shape or area, both linearly and non-linearly along the length of the reinforcement 52, 54. In some embodiments, the reinforcements 52, 54 can be joined in the tube 22 after the tube 22 is cured.
    [0061] Although the embodiment shown in FIGURES 3 and 4 uses reinforcements 54 located within the surface 47 of tube 22, other reinforcement arrangements are possible. For example, FIGURE 4A illustrates composite reinforcements 52, 54 which are located on the outer surface 53 of the tube 22, while FIGURE 4B illustrates reinforcements 52, 54 which are respectively located on the outer surface 53 and the inner surface 47 of the tube 22. A FIGURE 4C illustrates yet another embodiment, in which the reinforcements 54 located on both the inner and outer surfaces 47, 53 respectively of the tube 22.
    [0062] Attention is now directed to FIGURE 5 which illustrates an internal mandrel 56 that can be used to manufacture the strut 20 previously described. Chuck 56 includes a generally cylindrical body 57 having a generally cylindrical outer chuck surface 58. Chuck body 57 also includes four longitudinal cavities spaced at circumference 62 therein, each having a cross-sectional shape corresponding substantially to the shapes of the section cross section of one of the reinforcements 52, 54. The mandrel 56 further comprises a pair of generally cylindrical shafts 64 at their opposite ends that can be formed integral with the mandrel body 57. Each of the shafts 64 has a diameter 66 corresponding substantially with the inner diameter D3 of hole 44 in the fittings 24 (FIGURE 3). A centrally located hollow hole 68 extends axially through the body 57, the purposes of which will be described in more detail later.
    [0063] Mandrel 56 may be formed from a commercially available material that can be dissolved when subjected to a suitable liquid, such as water, at a later stage in the manufacturing process. In one embodiment, a suitable powder material is mixed with water and poured or injected into a mold (not shown) in order to form aspects of mandrel 56. Following molding, the mandrel is cured, dried using a heat source suitable, such as a convection oven and then sealed, as required. Alternatively, a water soluble mandrel 56 can be manufactured using additive manufacturing processes. In another embodiment, mandrel 56 can be manufactured from a block of material using removable processes with suitable material. In still other embodiments, the mandrel 56 may be formed from a material that is incinerated when raised to a predetermined temperature or it may comprise an inflatable bladder that is emptied and removed from the body of the tube 22 after the manufacturing process is complete. In still other embodiments, mandrel 56 can be disassembled and removed in pieces after tube 22 is cured.
    [0064] Referring now to FIGURES 6 and 7, after the chuck 56 has been manufactured, the end fittings 24 are capped over the axes 64. As can be seen in the embodiment illustrated in FIGURE 7, each of the axes 64 fills with substantially completes the diameter D3 of the hole 44 (FIGURE 3) of the corresponding end fitting 24. In other embodiments, the axis 64 can extend only partially through the length L (FIGURE 3) of the hole 43.
    [0065] With reference now to FIGURES 8 and 9, in one embodiment, reinforcements 50, 52 can be arranged and formed into the form using separate tools (not shown) using conventional disposition and consolidation processes. Then, as shown in FIGURE 10, the formed reinforcement device 50, 52 can be inserted into the corresponding cavities of the mandrel 60, 62. Alternatively, however, automatic equipment, such as an AFP machine, can be used to directly dispose of the reinforcement 52 inside the cavity 62 laying strips (not shown) of fiber-reinforced prepreg tape inside the cavities 60,62 and compacting the strips against the mandrel 56. Referring to FIGURE 11, after the reinforcement devices 50, 52 were placed inside the cavity 62, suitable reinforcement mandrels 84, which may comprise a dissolvable solid material, or inflatable bladders, are placed within the reinforcement 52, in order to maintain the shape of the reinforcement 52 and prevent it from closing during subsequent manufacturing steps.
    [0066] One or more of the reinforcements 50, 52 can include strokes that can improve the structural connection between the reinforcement 50, 52 and the tube 22. For example, with reference to FIGURE 12, the reinforcements 50, 52 can include integrated side flanges 61 which are received respectively within recesses 63 formed on the surface 58 of the mandrel 56, adjacent to the cavities 60,62. As shown in FIGURE 13, when the reinforcements 50, 52 are placed in the mandrel cavities 60, 62, the flanges 61 are substantially flush with the surface of the mandrel 58. A radius filler 65 can be installed between the reinforcement mandrel 84 and flanges 61 to help prevent flanges 61 from closing inward during subsequent stages of compaction and curing. Next, as shown in FIGURE 14, composite layers 48 forming layer groups 45 (FIGURE 3) are arranged over mandrel 56, covering flanges 61 and stepped section 40 (FIGURE 3) of end fittings 24. During this In the disposition process, the reinforcement mandrels 84 support the layers 48 and react to the layer compaction forces applied in those applications where an AFP machine is used to perform the disposition process.
    [0067] FIGURE 15 illustrates the use of an AFP 74 machine to arrange the reinforcements 52, 54 and / or layers 48 that form the wall 50 of the tube 22. The AFP 74 machine can be any of several different suitable types that include a composite tape applicator head 78 controlled by a robot 76. Mandrel 56 and end fittings 24 are supported on a suitable rotating mechanism 70 that rotates 82 mandrel 56 around a central geometry axis 80. Layers 48 may include reinforcement unidirectional fiber having varying fiber orientations according to a predetermined layer plan including, but not limited to, 0, -30, -45, 90, - 60, -45 and -30 degrees or other fiber orientations. As previously mentioned, other types of automatic arrangement processes can be used to arrange the reinforcements 50, 52 and / or the wall layers of the tube 50 including, without limitation, filament winding and fabric arrangement.
    [0068] FIGURE 15 summarizes the general steps of the method previously described for making strut 20. Starting at 86, end fittings 24 are manufactured using suitable casting and molding and / or machining techniques. In 88, mandrel 56 is formed which includes forming or assembling mandrel body 57, cavities 60, 62 and shafts 64. In 90, end fittings 24 are installed on shafts 64 of mandrel 56. In 92, reinforcements 50 52 are arranged and formed using separate tools. Alternatively, reinforcements 50, 52 can be disposed directly into cavities 60, 62 using an AFP machine. In these modalities where the reinforcements 50, 52 are individually arranged and formed in separate tools, they are then placed inside the chuck cavities 60, 62 in step 94. In step 96, reinforcement chucks 84 are installed inside the reinforcement devices 52, 54 along with additional elements, such as noodles or other fillers, as required. In step 98, the layers 48 of the tube wall 50 are arranged over the mandrel body 57, covering the reinforcement devices 50, 52 and the stepped section 40 of the end fittings 24. In 100, a vacuum bag assembly ( not shown) is installed around the anchor device. In 102, the strut device is compacted and cured using an autoclave or other processes that apply heat and pressure to the device. Finally, at 104, mandrels 56, 84 are removed. In the embodiment where chucks 56.84 are formed of a water-soluble material, water can be injected at one end or both ends of the hollow hole 68, resulting in chucks 56, 84 being dissolved and gushed out through the hollow hole 68.
    [0069] Disclosure modalities can be used, without limitation, in the context of the manufacturing method and service of airplane 106 as shown in FIGURE 15 and an airplane 108 as shown in FIGURE 16. During pre-production, the manufacturing method and airplane service 106 may include specification and design 110 of airplane 108 in FIGURE 16 and procurement of material 112.
    [0070] During production, the manufacture of components and subassembly 114 and integration of system 116 of plane 108 in FIGURE 16 take place. Then, plane 108 in FIGURE 16 can pass certification and delivery 118 in order to be placed in service 120. While in service 120 by a consumer, plane 108 in FIGURE 16 is planned for routine maintenance and service 122 , which may include modification, reconfiguration, renewal and other maintenance or services.
    [0071] Each of the processes of the airplane manufacturing and service method 106 can be performed or performed by a system integrator, a third party and / or an operator. In these examples, the operator can be a consumer. For purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and subcontractors of the main system, a third party may include, without limitation, any number of suppliers, subcontractors and suppliers, and an operator may be a company airline, a rental company, a military entity, a service organization, and so on.
    [0072] With reference now to FIGURE 16, an illustration of an airplane 108 is shown, in which an advantageous modality can be implemented. In this example, airplane 108 is produced by the airplane manufacturing and service method 106 in FIGURE 16 and can include housing 124 with the plurality of systems 126 and inside revealed chuck 128.0 can be used to manufacture various structural components of housing 124, such as like stringers. Examples of systems 126 include one or more of the propulsion system 130, electrical system 132, hydraulic system 134 and environmental system 136. Any number of other systems can be included. Although an example of an airplane is shown, different advantageous modalities can be applied in other industries, such as the automotive and marine industries.
    [0073] Apparatus and methods represented here can be used during at least one of the stages of the airplane manufacturing and service method 106 in FIGURE 15. As used here, the phrase “at least one of”, when used with a list of items , means that different combinations of one or more of the items listed can be used and only one of each item in the list may be required. For example, “at least one of item A, item B and item C” can include, for example, without limitation, item A or item A and item B. This example can also include item A, item B and item C or item B and item C.
    [0074] In an illustrative example, components or subassemblies produced in the manufacture of components and subassembly 114 in FIGURE 15 can be manufactured or manufactured in a similar manner to the components or subassemblies produced while airplane 108 is in service 120 in FIGURE 15. As yet another example, a number of device modalities, method modalities or a combination of them can be used during the production stages, such as manufacturing components and subassemblies 114 and integrating system 116 in FIGURE 15. A number, when referring to items, means one or more items. For example, a number of apparatus modalities is one or more apparatus modalities. A number of apparatus modalities, method modalities or a combination thereof can be used while airplane 108 is in service 120 and / or during maintenance and service 122 in FIGURE 15. The use of a number of different advantageous modalities can substantially accelerate the assembly of and / or reduce the cost of the plane 108.
    [0075] The description of the different advantageous modalities has been presented for purposes of illustration and description and is not intended to be exhaustive or limited to the modalities in the revealed form. Many modifications and variations will be evident to those skilled in the art. In addition, different advantageous modalities can provide different advantages when compared to other advantageous modalities. The selected modality or modalities are chosen and described in order to better explain the principles of the modalities, their practical application and to enable others of knowledge in the art to understand the disclosure for various modalities with various modifications as are appropriate for the particular use considered.
    权利要求:
    Claims (9)
    [0001]
    1. Strut (20), characterized by the fact that it comprises: a laminated composite tube (22) having a substantially hollow interior, a first pair of longitudinal reinforcements (52, 54) attached to opposite sides of the tube (22); a socket (24) at each end of the tube (22) adapted to be attached to a structure, where the socket (24) includes an opening (30) having a central geometric axis (27) and adapted to receive an elongated pin ( 32) connecting the socket (24) in the structure, and in which the first pair of reinforcements (52) is substantially symmetrical around a plane perpendicular to the geometric axis of the opening; wherein the strut (20) further comprises a second pair of longitudinal reinforcements (54) within the hollow interior of the tube and secured to opposite sides of the tube (22), where the second pair of reinforcements (54) is substantially symmetrical around of a plane substantially parallel to the geometric axis (27) of the opening (30) and where each of the reinforcements (52, 54) is trapezoidal in the shape of the cross section.
    [0002]
    2. Anchor, according to claim 1, characterized by the fact that the reinforcements (52,54) are located inside the hollow interior of the tube.
    [0003]
    Anchor according to claim 1 or 2, characterized by the fact that: each of the fittings (24) includes a plurality of external steps; and the tube (22) includes groups of layers respectively overlapping the steps, wherein the external steps and overlapping groups of layers form a single shear joint.
    [0004]
    4. Method of making a strut, characterized by the fact that it comprises: making an elongated mandrel (56), placing a socket (24) on each end of the mandrel (56), locating composite reinforcement devices (50,52) in the mandrel (56), form a composite tube (22) with composite layers on the mandrel (56), cure the tube (22) and reinforcements together and remove the mandrel (56), where the manufacture of the mandrel (56) includes forming an axis at each end of the mandrel (56) and forming the cavities in the mandrel along its length, the cavities having a cross-sectional shape substantially corresponding to the cross-sectional shape of the reinforcements; and wherein the placement of the fittings (24) on the mandrel (56) is carried out by placing the fittings (24) on the shafts.
    [0005]
    5. Method, according to claim 4, characterized by the fact that the location of the reinforcement devices in the mandrel includes: arranging and forming the reinforcements; and placing the reinforcement devices formed in the chuck cavities.
    [0006]
    6. Method according to claim 4 or 5, characterized in that the formation of the composite tube is carried out using an automatic fiber laying machine to lay and compact strips of composite tape on the surface of the mandrel (56).
    [0007]
    Method according to any one of claims 4 to 6, characterized in that the formation of the composite tube (22) includes forming a single shear joint between the tube and each of the fittings (24).
    [0008]
    Method according to any one of claims 4 to 7, characterized in that the removal of the mandrel (56) includes dissolving the mandrel (56) with a liquid.
    [0009]
    Method according to any one of claims 4 to 8, characterized in that it comprises: inserting reinforcement mandrels into the reinforcing devices; and removing the reinforcement chucks after the tube and reinforcements have been cured together.
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    同族专利:
    公开号 | 公开日
    US8904904B2|2014-12-09|
    BR112014010465A2|2017-04-18|
    US20130112309A1|2013-05-09|
    JP2015502504A|2015-01-22|
    EP2773497A1|2014-09-10|
    CA2850628C|2016-05-10|
    ES2770654T3|2020-07-02|
    CN103889692A|2014-06-25|
    EP2773497B1|2019-12-04|
    WO2013066565A1|2013-05-10|
    JP6189312B2|2017-08-30|
    CN103889692B|2016-08-17|
    PT2773497T|2020-03-06|
    CA2850628A1|2013-05-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4014184A|1975-01-27|1977-03-29|Stark Martin H|Propeller shaft liner and inserting apparatus|
    US4275122A|1978-07-17|1981-06-23|Gkn Transmissions Limited|Shaft and universal joint member assembly|
    US4272971A|1979-02-26|1981-06-16|Rockwell International Corporation|Reinforced tubular structure|
    US4469730A|1982-12-30|1984-09-04|The Boeing Company|Composite base structure and end fitting joint and method|
    FR2540430A3|1983-02-07|1984-08-10|Sardou Max|Structure, made of composite materials, which is capable of transmitting compressive and tensile forces|
    US4851065A|1986-01-17|1989-07-25|Tyee Aircraft, Inc.|Construction of hollow, continuously wound filament load-bearing structure|
    FR2604768B1|1986-10-07|1988-12-30|Inst Francais Du Petrole|CONNECTION AND METHOD FOR MANUFACTURING THIS CONNECTION FOR A SHAFT HAVING A REINFORCEMENT REINFORCEMENT|
    GB2215008A|1988-02-17|1989-09-13|Smith Corp A O|Fiber reinforced resin drive shaft having improved resistance to torsional buckling|
    US5439750A|1993-06-15|1995-08-08|General Electric Company|Titanium metal matrix composite inserts for stiffening turbine engine components|
    US5866272A|1996-01-11|1999-02-02|The Boeing Company|Titanium-polymer hybrid laminates|
    JP2000108210A|1998-10-02|2000-04-18|Toyota Autom Loom Works Ltd|Manufacture of frp cylindrical component, and core|
    JP3792515B2|1998-10-19|2006-07-05|美津濃株式会社|Baseball or softball bat|
    US6711783B2|1998-11-12|2004-03-30|Lemole John M.|Anti-pinch knuckle for bidirectional sleeve|
    KR100427223B1|2001-01-18|2004-04-27|임홍섭|Pole and Method for Producing Thereof|
    JP2003001716A|2001-06-21|2003-01-08|Toyota Industries Corp|Method for producing fiber-reinforced plastic pipe|
    JP2004293714A|2003-03-27|2004-10-21|Toyota Industries Corp|Power transmission shaft and its manufacturing method and tool|
    FR2887601B1|2005-06-24|2007-10-05|Snecma Moteurs Sa|MECHANICAL PIECE AND METHOD FOR MANUFACTURING SUCH A PART|
    FR2890591B1|2005-09-12|2012-10-19|Eads|METHOD FOR MANUFACTURING RTM COMPOSITE PIECE AND COMPOSITE PIECE OBTAINED ACCORDING TO SAID METHOD|
    US7452156B2|2006-11-17|2008-11-18|The Boeing Company|Composite structural member and method for making the same|
    US8414724B2|2006-12-02|2013-04-09|The Boeing Company|Composite tube having cobonded end fittings and method of making same|
    DE102007015909A1|2007-04-02|2008-10-09|Mt Aerospace Ag|Process for producing fiber-reinforced hollow bodies|
    US8123996B2|2008-02-07|2012-02-28|The Boeing Company|Wrinkle control for composite tubes|
    FR2957843B1|2010-03-25|2014-05-16|Epsilon Composite|METHOD FOR PRODUCING A BOND PIECE OF COMPOSITE MATERIAL AND PART OBTAINED|
    US9486965B2|2011-11-03|2016-11-08|The Boeing Company|Composite columnar structure having co-bonded reinforcement and fabrication method|FR2960468B1|2010-05-31|2013-03-29|Commissariat Energie Atomique|ARTICULATED INFLATABLE STRUCTURE AND ROBOTIC ARM COMPRISING SUCH A STRUCTURE|
    DE102011053480A1|2011-06-22|2012-12-27|Mt Aerospace Ag|Component for receiving and / or transmitting mechanical forces and / or moments, a method for its production and its use|
    US10457011B2|2011-11-03|2019-10-29|The Boeing Company|Composite columnar structure having co-bonded reinforcement and fabrication method|
    US10464656B2|2011-11-03|2019-11-05|The Boeing Company|Tubular composite strut having internal stiffening and method for making the same|
    US8973281B1|2012-10-11|2015-03-10|The Boeing Company|Edge distance gauge|
    US9823143B2|2013-10-07|2017-11-21|United Technologies Corporation|Additively grown enhanced impact resistance features for improved structure and joint protection|
    US20160101543A1|2013-12-03|2016-04-14|The Boeing Company|Hybrid Laminate and Molded Composite Structures|
    US11034113B2|2014-01-29|2021-06-15|Sikorsky Aircraft Corporation|Method of assembling a composite spar removable mandrel|
    US20160339661A1|2014-01-29|2016-11-24|Sikorsky Aircraft Corporation|Composite spar removable mandrel|
    WO2015158865A1|2014-04-16|2015-10-22|Hexcel Reinforcements Sas|Method of manufacturing a composite part|
    CN106255584B|2014-04-30|2019-05-03|麦格纳国际公司|It is used to form the device and method of three-dimension object|
    FR3020780B1|2014-05-09|2017-01-13|Airbus Operations Sas|PROCESS FOR MANUFACTURING A COMPOSITE MATERIAL PART FOR AIRCRAFT STRUCTURE BY PULTRUSION AND COCUISSON|
    DE102014222385A1|2014-11-03|2016-05-04|Bayerische Motoren Werke Aktiengesellschaft|Force introduction component and method for producing composite pipe connections with a force introduction component|
    EP3274145A4|2015-03-25|2018-10-31|Sikorsky Aircraft Corporation|Tools and processes for manufacturing parts employing additive manufacturing|
    DE102015215026A1|2015-08-06|2017-02-09|Robert Bosch Gmbh|Mechanical and / or electrical assembly|
    US20170190149A1|2016-01-04|2017-07-06|Caterpillar Inc.|Carbon fiber wrapped structural components for a machine|
    CN105836098A|2016-03-25|2016-08-10|哈尔滨飞机工业集团有限责任公司|Nested type composite material cylinder structure|
    US10272991B2|2016-06-23|2019-04-30|Goodrich Corporation|Metallic composite joint|
    US10563690B2|2016-07-28|2020-02-18|Goodrich Corporation|Thin-skin side stay beams and landing gear assemblies|
    US10746640B2|2017-03-21|2020-08-18|Textron Innovations Inc.|Methods of making a tubular specimen with a predetermined wrinkle defect|
    US10744727B2|2017-03-21|2020-08-18|Textron Innovations Inc.|Methods of making a specimen with a predetermined wrinkle defect|
    DE102017107463B3|2017-04-06|2018-05-09|THK RHYTHM AUTOMOTIVE GmbH|Chassis component and method for its production|
    KR101858723B1|2017-05-23|2018-05-16|주식회사 오즈인더스트리|Lashing Bar and manufacturing method thereof|
    CN108253033A|2017-12-08|2018-07-06|贵州华烽电器有限公司|The stuck pull rod design of anti-operating mechanism|
    US11001369B2|2018-04-02|2021-05-11|Bell Helicopter Textron Inc.|Hybrid light weight rotorcraft hub trunnions|
    DE102018208282A1|2018-05-25|2019-11-28|Zf Friedrichshafen Ag|Suspension handlebar for a motor vehicle|
    EP3597410A1|2018-07-20|2020-01-22|Crompton Technology Group Limited|Composite component and manufacture thereof|
    DE102018213322A1|2018-08-08|2020-02-13|Zf Friedrichshafen Ag|Multi-point link for a chassis of a motor vehicle|
    GB2579217A|2018-11-26|2020-06-17|Lentus Composites Ltd|Gears|
    CN111059137A|2019-11-14|2020-04-24|中国商用飞机有限责任公司北京民用飞机技术研究中心|Connecting structure of composite material rod piece and metal joint and forming method|
    DE102019220541A1|2019-12-23|2021-06-24|Robert Bosch Gmbh|Housing component of a unit|
    法律状态:
    2018-03-27| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2019-10-01| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2020-08-04| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2020-11-17| 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 05/10/2012, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US13/288,491|US8904904B2|2011-11-03|2011-11-03|Tubular composite strut having internal stiffening|
    US13/288,491|2011-11-03|
    PCT/US2012/058994|WO2013066565A1|2011-11-03|2012-10-05|Tubular composite strut having internal stiffening and method for making the same|
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