• 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:
    STRUCTURAL SET OF AN AIRCRAFT, AND METHODS TO ASSEMBLE A STRUCTURE AND AIRCRAFT. A structural assembly of an aircraft that includes a structural element constructed of a composite material that includes a matrix material and plurality of fibers positioned to extend through the matrix material, wherein at least a portion of the plurality of fibers it is accessible from a surface of the structural element. A fastener attaches the structural element to a structural component. A metal structure comprising gallium is positioned in contact with a surface of the fastener. The metal structure extends from the surface of the fastener and contacts at least a portion of at least a portion of the plurality of fibers. A method for assembling a structure is also included.
    公开号:BR102015031874B1
    申请号:R102015031874-0
    申请日:2015-12-18
    公开日:2020-10-27
    发明作者:Adam Franklin Gross
    申请人:The Boeing Company；
    IPC主号:
    专利说明:

    FIELD
    [001] This invention relates to an interstitial filler positioned between structural components of a structure, and more particularly, to an interstitial filler that provides electrical conductivity between the structural components of an aircraft. FUNDAMENTALS
    [002] Structures and particularly aircraft are designed to resist lightning strikes and to maintain their structural integrity. Traditional aircraft construction, for example, included metal structural elements that are attached together with metal fasteners. The fasteners were electrically grounded to the metallic structural elements, with the metallic fasteners being in contact with the metallic structural elements. This arrangement provided the electrical conductivity between the fastener and the structural element, thus not electrically isolating the fastener from the structural elements. The insulation of the fastener would, on the contrary, provide an unwanted electrostatic force between the fastener and the structural element in the event of a lightning strike in the aircraft.
    [003] More recently, aircraft are being built from structural components made of a composite material. The composite material comprises a matrix material, often a resin, and a fiber material, such as carbon fiber. The resin is generally not so electrically conductive, in contrast to the fiber material. This composite material is often carbon fiber reinforced plastic (“CFRP”). The structural elements of CFRP are attached together with fasteners, such as metal pins. A pin used to fix a structural element constructed of CFRP may not necessarily be electrically grounded to the structural element of CFRP. Rough surfaces of the dowel and the rough surfaces of the structural element can create interstices between the surface of the metal dowel and that of the electrically conductive fiber. This condition can lead to the formation of electrostatic force between the fastener and the constructed structural element of CFRP.
    [004] Currently, in an attempt to prevent the formation of an electrostatic force between the fastener and the structural element, the fasteners or dowels are coated with a sealing material, electrically insulating, before they are attached to the structural element constructed of CFRP. Thus, at the time of a lightning strike in the aircraft, the insulation of the fastener in relation to the structural element prevents an unwanted electrostatic formation between the fastener and the structural element.
    [005] However, coating the fasteners with the sealant and then fixing them to the structural element requires a large amount of attention, time and expense, compared to the traditional retention of metallic structural elements with metal fasteners. The seal must completely cover the surface of the fastener; otherwise, at the time of a lightning strike on the aircraft, current could move from the fibers of the structural element to the fastener through an opening or gap in the seal. Current that passes through such an opening will load the fastener and create an unbalanced load between the fastener and the CFRP fiber. This condition can create unwanted electrostatic forces between the pin and the CFRP fibers. Additionally, care must be taken when fixing the fastener, so that the seal is not removed in the process. In addition, once the fastener is installed, careful inspection needs to be done so that no opening through the seal has been created during the fastener fastening process. Thus, careful steps must be taken in the fixer liner, fixing the fixer and inspecting the fixer in the fixing process. These steps contribute to the cost of assembling the aircraft.
    [006] Other attempts to prevent the unwanted formation of electrostatic force between the CFRP material of the structural element and the fastener or metallic pin have been made. These attempts were not possible. For example, the use of a metallic weld could not be employed. Although the weld would provide electrical conductivity and structural integrity between the pin and the CFRP material, the integrity of the CFRP material would be structurally compromised at a temperature greater than two hundred and fifty-four Fahrenheit (254 ° F) - 123.3 ° C, which is below the melting temperature of many welds. Alternatively, a conductive adhesive could be employed between the pin and the CFRP material. However, the adhesive has a more resistive conductivity than a metallic bond. This resistivity could result in a charge formation between the two pin surfaces and the CFRP material and result in an unwanted electrostatic discharge.
    [007] A soft metallic insert could also be used and positioned between the two surfaces of the pin and the CFRP material. However, this can improve the electrical conductivity between the two surfaces, but it creates a weak structural point between the two surfaces and is limited in its ability to conform to the two surfaces. Alternatively, welding of the bolt to the CFRP structural component is not possible, where a surface, that of the CFRP structural component, is not metallic.
    [008] There is a need for an inexpensive and reliable interstitial filler that will conform to the rough surfaces of the fastener or pin and the constructed structural element of CFRP. The interstitial filler will need to provide electrical conductivity between the fastener or pin and the fibers of the CFRP material to ground the fastener to the structural element constructed of CFRP material. SUMMARY
    [009] An example of an aircraft structural assembly includes a structural element constructed of a composite material that includes a matrix material and a plurality of fibers positioned to extend through the matrix material, wherein at least a portion of the plurality of fibers is accessible from a surface of the structural element. A fastener attaches the structural element to a structural component. A metal structure comprising gallium is positioned in contact with a surface of the fastener. The metal structure extends from the surface of the fastener and contacts at least a portion of at least a portion of the plurality of fibers.
    [0010] An example of a method for assembling a structure that includes the step of providing a structural element constructed of a composite material that includes a matrix material and plurality of fibers positioned to extend through the matrix material in which at least , a portion of the plurality of fibers is accessible from a surface of the structural member. Another step includes mixing a liquid metal alloy comprising gallium with at least one of a solid metal or solid metal alloy to form a slurry. The method further includes the step of applying the slip to a surface of a fastener and to at least a portion of the at least portion of the plurality of fibers. Another step in the method includes attaching the structural element with the fastener to a structural component, where the slurry is positioned in contact with the surface of the fastener and interconnects the surface of the fastener with at least a portion of at least a portion of the plurality of fibers.
    [0011] The characteristics, functions, and advantages that have been discussed can be obtained independently in several modalities or can be combined in still other modalities, other details of which can be seen with reference to the following description and the following drawings. BRIEF SUMMARY OF THE DRAWINGS Figure 1 is a side elevation view of an aircraft; Figure 2 is a schematic cut-out view, for example, of a selected portion of the aircraft in Figure 1, in which a cross section is shown of a fastener connecting structural elements constructed of a composite material to a structural component with a metallic interstitial filler. , positioned in contact with, and interconnecting, a surface of the fastener with fibers of the composite material of the structural elements; Figure 3 is a Table 1 showing sample compositions of interstitial fillers comprising gallium based alloys of liquid metal combined with a pure solid metal or with a solid metal alloy; Figure 4 is a graph showing free corrosion rates for selective samples of metallic interstitial fillers from Table 1 of figure 3; Figure 5 is a graph showing galvanic corrosion rates for selective samples of metallic interstitial fillers from Table 1 of figure 3; and Figure 6 is a Table 2 showing rates of free and galvanic corrosion, together with relative, free galvanic corrosion rates, for selective samples of metallic interstitial fillers from Table 1 together with copper foil and 6061 aluminum alloy. .
    [0012] Although several modalities have been described above, this description is not intended to be limited to them. Variations can be made to the described modalities, which are still within the scope of the attached claims. DETAILED DESCRIPTION
    [0013] As discussed earlier, it is important to build structures that resist damage when struck by lightning. An example of such assembled structures includes an aircraft. It is desired that the formation of electrostatic force is not created between metal fasteners and structural elements of the aircraft, mounted, at the time of a lightning strike. With the aircraft now being selectively assembled with composite materials, grounding a metal fastener with conductive fibers from the composite material of a structural element is necessary.
    [0014] With reference to figure 1, an example of an assembled structure, aircraft 10, is shown. Aircraft 10 includes several sections for its assembly. These sections, in this example, include a fuselage 12 and wings 14 that extend from opposite sides of the fuselage 12. Fuselage 12 also includes a nose section 16 and an opposite tail section 18. Each of these sections of the aircraft 10 it can be selectively built with structural elements made of composite materials.
    [0015] With reference to figure 2, an example fixation of the structural element 20 is shown for an assembly of a selective section of the aircraft 10. The structural element 20 is constructed of a composite material, which includes a matrix material 22 and a plurality of fibers 24 positioned to extend through the matrix material 22.
    [0016] In this example shown in figure 2, the structural element 20 is located on top of another structural element 26, which is also constructed of the composite material including a matrix material 28 and a plurality of fibers 30 which are also positioned to extend through matrix material 28. Both structural element 20 and other structural element 26 are attached to structural component 32. Structural component 32 is another structural item in an aircraft section assembly 10. Structural component 32 can be constructed of a composite material, metal or similar. In this example, structural component 32 is a portion of a metal frame positioned within a selected section of the aircraft 10.
    [0017] The plurality of fibers 24 and 30, in this example, are constructed of electrically conductive material, such as carbon. The matrix material 22 and 28, in this example, is constructed from one of a thermoplastic resin, such as polypropylene, polyethylene and nylon, or thermosetting resin, such as an epoxy.
    [0018] The structural element 20 and the other structural element 26 are fastened or fixed to structural component 32 with the fastener 34. The fastener 34 is a fastening item, which can fasten two or more items together, such as a pin, screw, pin or similar. In this example, fastener 34 is a pin, which includes head 36, threaded shaft 38 (threads not shown) and threaded nut 40 (threads not shown). The fastener or pin 34 is constructed of metal, such as carbon steel, titanium alloy or similar.
    [0019] In this example, a through hole 42 is positioned through structural component 32. The through hole in this example has been preformed in structural component 32. Through hole 42 can also be positioned through structural component 32 by drilling through structural member 32. Through hole 44 and undercut section 54 of structural element 20 and through hole 46 of another structural element 26 were formed by drilling through structural element 20 and the other structural element 26 in this example. When drilling through the composite material of the structural element 20 and the other structural element 26, the rough surface 48 of the structural element 20 and the rough surface 50 of the other structural element 26 are formed. In addition, the rough surface 52 is formed in the recess section 54 of the structural element 20.
    [0020] The plurality of fibers 24, which extend through the matrix material 22 of the structural element 20 is schematically represented in figure 2. In this example, the plurality of fibers 24 extend through the matrix material 22 and the fibers are positioned through the entire structural element 20, extending in the direction of length, direction of width and stratified in the direction of thickness of structural element 20. The plurality of fibers 24 in figure 2 is schematically shown extending in a direction of length and stratified in thickness direction of the structural element 20, without showing the plurality of fibers 24 extending in the width direction within the matrix 22.
    [0021] With the formation of a discrete through hole 44 and the recess section 54 through structural element 20, the through hole 44 and the recess section 54 engage at least a portion 25 of the total plurality of fibers 24, which are positioned across the entire structural element 20. In figure 2, at least a portion 25 of the plurality of fibers 24 of structural element 20 is shown schematically, positioned on, and along the rough surface 48 of through hole 44 , and on, and along the rough surface 52 of the recess section 54. The portion 25 of the plurality of fibers 24 is also positioned around through hole 44 and the recess section 54, but is not shown. At least a portion 25 of the plurality of fibers 24 in Figure 2 is shown schematically extending to the rough surface 48 in the through hole 44 and to the rough surface 52 in the undercut section 54. However, with the through hole 44 and the recess section 54 formed, in this example, by drilling through the structural element 20, the ends of at least a portion 25 of the plurality of fibers 24 positioned in the through hole 44 and in the recess section 54 can extend from being flush with, or recessed from, the rough surface 48 and the rough surface 52. Regardless of the position of one end of a fiber of at least a portion 25 of the plurality of fibers 24 with respect to the rough surfaces 48 and 52, the ends will be accessible from the rough surface 48 in the through hole 44 and from the rough surface 52 of the recess section 54.
    [0022] The other structural element 26 with the plurality of fibers 30 is similarly configured and schematically presented as described above for the structural element 20 with the plurality of fibers 24. The plurality of fibers 30 is schematically shown to extend through the material of matrix 28 and the fibers are positioned through the entire other structural element 26, extending in the length direction, width direction and stratified in the thickness direction of the other structural element 26 as the plurality of fibers 24 has been configured within the structural element 20 and schematically shown. The plurality of fibers 30, in this example, is shown extending in one length direction and stratified in the thickness direction of the other structural element 26, without showing the plurality of fibers 24 extending in the width direction within the matrix 28.
    [0023] With the formation of a discrete through hole 46 through the structural element 26, the through hole 46 engages at least the portion 47 of the total plurality of fibers 30, which are positioned through the entire other structural element 26. At least a portion 47 of the plurality of fibers 30 of structural member 26 is shown schematically positioned at, and along the rough surface 50 of through hole 46. The at least portion 47 of the plurality of fibers 30 is also positioned around through hole 46, but is not shown. At least a portion 47 of the plurality of fibers 30 is shown schematically extending to the rough surface 50 in the through hole 46. However, with the through hole 46 formed, in this example, by drilling through structural element 26, the ends at least a portion 47 of the plurality of fibers 30 positioned in the through hole 46 may extend from being flush with, or lowered from, the rough surface 50. Regardless of the position of an end of a fiber at least at least a portion 47 of the plurality of fibers 30 with respect to the rough surface 50, the ends will be accessible from the rough surface 50 in the through hole 46.
    [0024] In the formation of the recessed portion 54 and the through hole 44 of the structural element 20 and in the formation of the through hole 46 of the other structural element 26, these openings are dimensioned to be slightly larger than the fastener 34, to allow the fastener 34 extends through structural member 20 and the other structural member 26. For the same reason, the through hole 42 of structural member 32 is similarly slightly larger than the dimension of the fastener 34. An interstice 55 is formed between the head 36 and the threaded shaft 38, on the one hand, and the rough surfaces 48, 50 and 52 of the structural element 20, recessed portion 54 of the structural element 20 and the other structural element 26, on the other hand. The interstice 55 is also formed between the structural component 32 and the fastener or pin 34, as seen in figure 2.
    [0025] A metal frame 56 is positioned inside, and conforms to the interstice 55. Metal is a solid material that is typically malleable, fuse, and ductile, with good electrical and thermal conductivity. Metal structure 56 is in contact with surface 57 of fastener 34, which includes surface 58 of head 36 and surface 60 of threaded shaft 38. Metal structure 56 extends through interstice 55 from surfaces 58 and 60 and contacts at least a portion of at least a portion 25 of the plurality of fibers 24 associated with structural element 20 and undercut section 54 of structural element 20. This configuration of metal structure 56 establishes an electrical connection with the fibers and fixator 34, thus grounding fixator 34. Similarly, metal frame 56 contacts surface 57 of fixator 34, which includes surface 60 and extends through interstice 55 and contacts at least a portion of at least at least a portion 47 of the plurality of fibers 30 associated with the other structural element 26. Likewise, this configuration of the metal structure 56 establishes an electrical connection with the fibers and the fastener 34, thereby grounding the fastener 34. Also, in this example, metal frame 56 contacts surface 57 of fastener 34, which includes surface 60 and extends through interstice 55 and contacts surface 62 of structural component 32 in through hole 42. This configuration of metal structure 56 also establishes the electrical connection between the fastener 34 and the structural component 32.
    [0026] Metal structure 56, as described above, extends from the metal surfaces, described above, of fastener 34, through interstice 55 to the above described, at least a portion of at least a portion 25 and 47 of the plurality of fibers 24 and 30, respectively, and for structural component 32. The metal structure 56 extends in a range between twenty-five micrometers (25 pm) and one millimeter (1 mm) in making these connections electrical. As metal structure 56 extends through interstice 55, it contacts and conforms to rough surfaces 48, 50 and 52. As will be described below, metal structure 56 is applied as a slurry or pasty consistency to the above surfaces fastener 34 and rough surfaces 48, 50 and 52 and surface 62. In applying the metal structure to rough surfaces 48, 50 and 52, at least a portion of at least a portion 25 and 47 of the plurality of fibers 24 and 30, respectively, come into contact with metal structure 56. When fixing structural element 20 and the other structural element 26 to structural component 32 with fixer 34, the pasty consistency of metal structure 56 is positioned within, and occupies the interstice 55, and provides a continuous electrical connection between the fastener 34 and the fibers described above of the composite material. The metal frame also provides an electrical connection between fastener 34 and structural component 32.
    [0027] A method for assembling a structure, such as, in this example, the aircraft 10, includes providing structural element 20. In this example, the other structural element 26 is additionally provided. The structural element 20 as well as the other structural element 26 are constructed of a composite material, which includes, as described above, a matrix material 22 for the structural element 20 and the matrix material 28 for the other structural element 26. A plurality of fibers 24 extends through the matrix material 22 of the structural element 20 and the plurality of fibers 30 extends through the matrix material 28. At least the portion 25 of the plurality of fibers 24, as described above, is accessible from the rough surfaces 48 and 52 associated with structural element 20 and at least a portion 47 of the plurality of fibers 30, as described above, is accessible from the rough surface 50 associated with structural element 26. With structural element 20, the other structural element 26, structural component 32 and fastener 34 available for assembly, mixing a liquid metal alloy containing gallium with at least one of a solid and free metal solid metal, can be driven. In this example, a Wig-L-Bug dental amalgamator is employed. This mixture forms a slurry.
    [0028] The slurry or pasty mixture is applied to surface 57, including surfaces 58 and 60 of fastener 34 and on at least a portion of at least a portion 25 and 47 of the plurality of fibers 24 and 30, respectively, by applying the pasty material to the rough surfaces 48, 50 and 52. The pasty material is also applied to the surface 62 of the structural component 32. With the pasty material of the metal structure 56 properly applied, the fixation of the structural element 20, together with, in this embodiment, the other structural element 26, to the structural component 32, with the fastener 34, can proceed as described above. With the fixation of the fastener or pin 34, the interstice 55 becomes occupied and filled with the pasty consistency of the metal structure 56 and conforms to the shape of the interstice 55. As will be described below, the pasty material, over a period of time, hardens and solidifies. The metal frame 56 provides the necessary electrical connection between the fastener 34 and the fibers and the structural component 32 and grounds the fastener 34.
    [0029] Metal structure 56, which contains a gallium alloy, is initially in a liquid state at approximately room temperature, and is then mixed with a metal powder or film to form a fluid paste, in which an epithelial bond formed, in which gallium in the liquid metal alloy diffuses into a solid metal, such as a pure metal or metal alloy. The initial mixture forms a slurry or pasty mixture which becomes an alloy with a higher melting temperature. Over time, the slurry or pasty consistency cures to form a solid.
    [0030] With reference to figure 3, Table 1 is shown, which includes samples of compositions for metal structure 56. As can be seen in Table 1, gallium alloys are formed by combining gallium with one or both of tin and Indian. These metal alloys are initially in a liquid state, approximately at room temperature, below thirty degrees Celsius (30 ° C). The gallium-containing liquid metal alloy is then mixed with a solid metal or solid metal alloy. The solid metal or solid metal alloy to be mixed with the liquid metal alloy is either in a powder or film state. The particle size or film thickness dimension is between fifty nanometers (50 nm) and one hundred micrometers (100 pm). As can be seen in Table 1 of figure 3, the solid metal mixed with the healthy gallium alloy is either pure nickel, pure copper or pure silver. A solid metal alloy, bronze, can selectively be used to mix with the liquid gallium metal alloy. Table 1 shows the elemental weight ratio of material of the chemical components to be mixed to create each sample of the metal structure 56.
    [0031] By mixing the gallium alloy with the solid metal or solid metal alloy, the resulting slurry or pasty consistency provides the user with the ability to properly apply the material to conform to the rough surfaces of the fastener and the composite material. Once when the fixation is completed using the fixative 34, the metal material or structure 56 cures to a solid state. The assembled structure, or, in this example, aircraft 10, can then be used for the flight.
    [0032] An additional mechanical reinforcement phase can be added to the slurry from mixing the liquid gallium metal alloy with a solid metal or solid metal alloy. This mechanical phase will provide improved shear strength for the cured solidified alloy. This mechanical phase material can selectively include one of a pure cobalt, pure tungsten, pure molybdenum or pure titanium or a titanium alloy, such as AMS 4911, or stainless steel, such as 302 or 316.
    [0033] With reference now to figure 4, the graph shows results of free corrosion testing of five selected samples of metal structure 56, which appear in Table 1 of figure 3. Corrosion resistance is important for metal structure 56 , which will be exposed to varying environmental conditions in the outdoor environment. The evaluation of the test criteria uses a commercial, three-electrode corrosion test cell. In addition to the tested samples, which comprised the working electrode, the cell contained a platinum mesh counter electrode and a silver wire reference electrode. The electrolyte (the corrosive environment) was sodium chloride solution (NaCl) at three percent by weight (3.0% by weight), exposed to laboratory air, that is, containing dissolved oxygen. Using the fixture in the cell, a surface area of one square centimeter (1 cm x 1 cm) of each sample was exposed to the electrolyte. Standard linear polarization measurements were performed around the corrosion potential (open circuit) using potential sweeps from - 10 mV to +10 MV. The data was adapted to straight lines to obtain polarization resistance (Rp, Ohms). Relative corrosion rates were expressed using the reverse polarization resistance. As can be seen in the graph, the test in at least one case, extended for eighty hours.
    [0034] The free corrosion rates that are given by the polarization resistance inverse are shown in this graph in figure 4. The lower values of the polarization resistance inverse in this graph indicate greater corrosion resistance. All of the copper-containing metal alloys had equivalent corrosion rates, regardless of the metal composition when the same liquid metal alloy (Ga / In or Ga / In / Sn) was used. The gallium liquid metal alloy had some effect. The gallium / tin liquid metal alloy was more resistant to corrosion than gallium / indium liquid metals. The difference can be attributed to the fact that tin is more oxidatively stable than indium. As can be noted, silver containing solidified metals was more stable than any material containing indium.
    [0035] With reference to figure 5, this graph shows results of galvanic corrosion test for three selected samples of metal structure 56 from Table 1 of figure 3. The galvanic test is conducted on samples of metal structure 56, a since the metal structure 56 is in constant electrical contact with carbon fiber conductive of the composite material.
    [0036] The test criteria include placing each sample in contact with carbon fiber reinforced plastic (“CFRP”) and using linear polarization measurements performed on combined test sample / CFRP electrodes. This proposal treats the galvanic pair as a single electrode and allows a relative comparison of the rates of free corrosion and galvanic corrosion. The CFRP was prepared by cutting a piece of a square centimeter (1 cm2) from a CFRP panel. One face was scraped to expose the carbon fiber. The edges and back face were sealed with epoxy for 5 minutes, cured overnight at fifty degrees Centigrade (50 ° C). The entire CRFP piece was immersed in the electrolyte adjacent to the test sample. The electrical connection between the test sample and the CFRP was made using a direct connection wire from the test sample to a threaded bar sealed with epoxy, connected to the CFRP. The area for the test sample was 0.785 square centimeter (0.785 cm2) and the CFRP area was two centimeters by two centimeters (2 cm x 2 cm), which is equal to four square centimeters (4 cm2). Thus, the CFRP / metal alloy area ratio was 5: 1.
    [0037] With reference to the graph in figure 5, the initials eighteen hours to twenty-two hours recorded in the graph are the results of a free corrosion test for these three samples. The galvanic test above was then started, which indicated a sharp increase in corrosion rates for each sample in this graph. As time progressed, the corrosion rate of each of the three samples substantially leveled and reached a stable state. Again, the higher position on this graph indicates a higher corrosion rate. As can be seen, gallium / tin with copper alloy and gallium / indium with copper alloy have similar corrosion rates. Gallium / indium and silver alloy had the lowest corrosion rate.
    [0038] With reference to figure 6, Table 2 of corrosion rates of five samples is provided. The first three samples are sample compositions from Table 1 in Figure 3 and are found in the corrosion tests in the graphs shown in Figures 4 and 5. The next sample in Table 2 is copper foil and the final sample is aluminum alloy. 6061. This table shows the free corrosion rate in the first column. The second column shows the galvanic corrosion rate. In the third column, a ratio of the galvanic corrosion rate to the free corrosion rate is shown. Liquid gallium alloy, mixed with solid copper metal samples, have slightly higher galvanic corrosion rates than copper foil and liquid gallium alloy mixed with silver solid metal, but significantly lower corrosion rate than copper alloy. 6061 aluminum.
    [0039] Additionally, the invention comprises modalities according to the following clauses: Clause 1: The structural assembly of an aircraft, comprising: a structural element constructed of a composite material comprising a matrix material and a plurality of fibers positioned to extend through the matrix material, wherein at least a portion of the plurality of fibers is accessible from a surface of the structural member; a fastener secures the structural element to a structural component; and a metal structure positioned in contact with a surface of the fastener, wherein the metal structure extends from the surface of the fastener and contacts at least a portion of at least a portion of the plurality of fibers. Clause 2: The structural assembly according to clause 1, in which: the plurality of fibers comprises carbon; the matrix material comprises one of a thermoplastic resin and thermosetting resin; and the fastener is made of metal. Clause 3: The structural set according to clause 1, in which the metal structure comprises an alloy of gallium comprising at least one of indium and tin. Clause 4: The structural assembly according to clause 1, in which the metal structure additionally comprises one of a solid metal and a solid metal alloy. Clause 5: The structural set according to clause 4, in which: the one between the solid metal and the solid metal alloy comprises one between a powder and a film; and a particle size of the powder or a thickness of the film has a dimension in a range between 50 nm and 100 pm. Clause 6: The structural set according to clause 5, in which the solid metal comprises one of pure copper, pure silver, and pure nickel. Clause 7: The structural assembly according to clause 5, in which the solid metal alloy comprises bronze. Clause 8: The structural assembly according to clause 1, wherein the metal structure additionally comprises a mechanical reinforcement phase comprising one of pure cobalt, pure tungsten, pure molybdenum, and pure titanium or an alloy comprising one among an alloy titanium and stainless steel. Clause 9: The structural assembly according to clause 1, in which: the metal structure extends in a range between 25 pm and 1 mm between the surface of the fastener for at least a portion of the portion of the plurality of fibers; and the metal structure is in contact with the surface of the structural element. Clause 10: A method for assembling a structure, comprising the steps of: providing a structural element constructed of a composite material comprising a matrix material and a plurality of fibers positioned to extend through the matrix material, in which at least a portion of the plurality of fibers is accessible from a surface of the structural member; mixing a liquid metal alloy comprising gallium with at least one of a solid metal and solid metal alloy to form a slurry; applying the slurry to a surface of a fastener and to at least a portion of at least a portion of the plurality of fibers; and securing the structural member with the fastener to a structural component in which the slurry is positioned in contact with the surface of the fastener and interconnects the surface of the fastener with at least a portion of at least a portion of the plurality of fibers. Clause 11: The method for assembling a structure according to clause 10, wherein: the plurality of fibers comprises carbon; the matrix material comprises one of a thermoplastic resin and thermosetting resin; the fixer is made of metal; and the gripping step includes placing the slurry in contact with the surface of the structural element. Clause 12: The method for assembling a structure according to clause 10, in which: the liquid metal is an alloy that comprises at least one of indium and tin; and the mixing step includes mixing the liquid metal alloy with at least one of a solid metal and a solid metal alloy. Clause 13: The method for assembling a structure according to clause 12, wherein the one of the solid metal and the solid metal alloy comprises one of a powder and a film. Clause 14: The method for assembling a structure according to clause 13, in which a particle size of the powder or a thickness of the film has a dimension in a range between 50 nm and 100 pm. Clause 15: The method for assembling a structure according to clause 12, in which the solid metal comprises at least one of pure copper, pure silver and pure nickel. Clause 16: The method for assembling a structure according to clause 12, in which the solid metal alloy comprises a bronze alloy. Clause 17: The method for assembling a structure according to clause 10 wherein the mixing step further includes mixing a mechanical reinforcement phase comprising one of pure cobalt, pure tungsten, pure molybdenum and pure titanium or an alloy comprising one of an alloy of titanium and stainless steel. Clause 18: The method for assembling a structure according to clause 10, in which the liquid metal has a melting temperature of less than thirty degrees Centigrade (30 ° C). Clause 19: The method for assembling an aircraft in accordance with clause 10, additionally including the step of allowing the slurry to solidify before the aircraft is put into flight. Clause 20: The method for assembling a structure according to clause 10, in which the structural element and the structural component are parts of an aircraft.
    [0040] Although several modalities have been described above, this description is not intended to be limited to them. Variations can be made to the described modalities that are still within the scope of the attached claims.
    权利要求:
    Claims (14)
    [0001]
    1. Structural assembly (14) of an aircraft (10), characterized by the fact that it comprises: a structural element (20, 26) constructed of a composite material comprising a matrix material (22, 28) and a plurality of fibers ( 24, 30) positioned to extend through the matrix material, wherein at least a portion of the plurality of fibers is accessible from a surface (48, 50, 52) of the structural member; a fastener (34) secures the structural element to a structural component (32); and a metal frame (56) positioned in contact with a surface (38) of the fastener, wherein the metal frame extends from the surface of the fastener and contacts at least a portion (25) of at least a portion of the plurality fiber, where the metal structure (56) comprises a gallium alloy, where the metal structure (56) is obtainable by: mixing a liquid metal alloy comprising gallium with at least one of a solid metal and alloy of solid metal forming a slurry (56); and applying the slurry to a surface (38) of a fastener (34) and to at least a portion (25) of at least a portion of the plurality of fibers.
    [0002]
    2. Structural assembly according to claim 1, characterized by the fact that: the plurality of fibers comprises carbon; the matrix material comprises one of a thermoplastic resin and thermosetting resin; and the fastener is made of metal.
    [0003]
    Structural assembly according to either of claims 1 or 2, characterized in that the gallium alloy of the metal structure comprises at least one of indium and tin.
    [0004]
    Structural assembly according to any of claims 1 to 3, characterized in that the metal structure additionally comprises one of a solid metal and a solid metal alloy.
    [0005]
    5. Structural assembly according to claim 4, characterized by the fact that: the one among the solid metal and the solid metal alloy comprises one among a powder and a film; and a particle size of the powder or a thickness of the film has a dimension in a range between 50 nm and 100 pm.
    [0006]
    6. Structural assembly according to claim 5, characterized by the fact that the solid metal comprises one of pure copper, pure silver, and pure nickel.
    [0007]
    Structural assembly according to either claim 5 or claim 6, characterized in that the solid metal alloy comprises bronze.
    [0008]
    Structural assembly according to any of claims 1 to 4, characterized in that the metal structure additionally comprises a mechanical reinforcement phase comprising one of pure cobalt, pure tungsten, pure molybdenum, and pure titanium or an alloy comprising one from a titanium alloy and a stainless steel.
    [0009]
    Structural assembly according to any of claims 1 to 4 or 8, characterized in that: the metal structure extends in a range between 25 pm and 1 mm between the surface of the fastener for at least a portion of the portion of the plurality of fibers; and the metal structure is in contact with the surface of the structural element.
    [0010]
    10. Method for assembling a structure (10), characterized by the fact that it comprises the steps of: providing a structural element (20, 26) constructed of a composite material comprising a matrix material (22, 28) and a plurality of fibers ( 24, 30) positioned to extend through the matrix material, wherein at least a portion of the plurality of fibers is accessible from a surface (48, 50, 52) of the structural member; mixing a liquid metal alloy comprising gallium with at least one of a solid metal and solid metal alloy forming a slurry (56); applying the slurry to a surface (38) of a fastener (34) and to at least a portion (25) of at least a portion of the plurality of fibers; and securing the structural member with the fastener to a structural component (32), where the slurry is positioned in contact with the surface of the fastener and interconnects the surface of the fastener with at least a portion of the at least a portion of the plurality of fibers, where the structural element and the structural component are parts of an aircraft.
    [0011]
    11. Method for assembling a structure according to claim 10, characterized by the fact that: the plurality of fibers comprises carbon; the matrix material comprises one of a thermoplastic resin and thermosetting resin; the fixer is made of metal; and the gripping step includes placing the slurry in contact with the surface of the structural element.
    [0012]
    A method for assembling a structure according to either of claims 10 or 11, characterized by the fact that: the liquid metal is an alloy comprising at least one of indium and tin; and the mixing step includes mixing the liquid metal alloy with at least one of a solid metal and a solid metal alloy.
    [0013]
    13. Method for assembling a structure according to claim 12, characterized in that the one among the solid metal and the solid metal alloy comprises one among a powder and a film.
    [0014]
    14. Method for assembling an aircraft as defined in any of claims 10 to 12, characterized in that it additionally includes the step of allowing the slurry to solidify before the aircraft is put into flight.
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    同族专利:
    公开号 | 公开日
    CA2913166C|2020-10-27|
    BR102015031874A2|2017-01-24|
    US20160229552A1|2016-08-11|
    EP3053679B1|2019-12-18|
    JP6719218B2|2020-07-08|
    CN105857629A|2016-08-17|
    JP2016175634A|2016-10-06|
    EP3053679A1|2016-08-10|
    CA2913166A1|2016-08-05|
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    法律状态:
    2017-01-24| B03A| Publication of an application: publication of a patent application or of a certificate of addition of invention|
    2018-11-21| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-12-17| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-05-05| B09A| Decision: intention to grant|
    2020-10-27| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 18/12/2015, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/614,656|2015-02-05|
    US14/614,656|US20160229552A1|2015-02-05|2015-02-05|Intermetallic and composite metallic gap filler|
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