• 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:

    公开号:FR3017668A1
    申请号:FR1551401
    申请日:2015-02-19
    公开日:2015-08-21
    发明作者:olaf Steffen；Christian Uckert
    申请人:Deutsches Zentrum fuer Luft und Raumfahrt eV；
    IPC主号:
    专利说明:

    [0001] The invention relates to a method for assembling a fairing body component to one or more parts, to form a flow surface of the body component. fairing, along which the flow can be made in a laminar regime. The invention also relates to an assembly arrangement for this purpose.
    [0002] Because of their advantageous property, high strength and rigidity in at least one direction for a relatively low specific weight, fiber reinforced composite materials are now essential in the aeronautical and aerospace field. But fiber reinforced composite materials are also increasingly used in the automotive field. This can reduce the weight of aircraft and land vehicles while maintaining the same stability, which usually results in a proportional fuel economy. Another goal sought in particular in the field of aeronautics is the reduction of the resistance due to friction, which occurs in particular at the bearing surfaces producing the lift of an aircraft. Its share in total resistance due to friction can reach up to 34%. Thanks to the development of laminar wing technology, this share can however be considerably reduced, by obtaining the maintenance of the flow of the boundary layer at the flow surfaces of the airfoil. It is thus possible to reduce the coefficient of friction of the wall up to 1/10 of the value of a boundary layer in a turbulent regime, which would allow significant savings in the fuel consumption of the aircraft.
    [0003] In this regard, a problem is posed by the high aerodynamic requirements relating to the seal areas of the pieces forming the flow surface. In order for the boundary layer flow to change from a laminar to a turbulent regime, disturbances in the geometry of the flow surface must be kept as low as possible. Tolerance values of up to 0.5 mm must be observed, depending on the location of use. In particular, the height differences between installed parts in the direction of flow, as well as three-dimensional disturbances, such as rivet heads or bolts, most often cause the boundary layer flow of a laminar flow to change. a turbulent regime, so that in particular the conventional concepts for the attachment of fairing body components are no longer sufficient for this technology. Particular attention should be paid in particular to the joint area of the wing envelope and the leading edge of the wing. In conventional construction mode, the outer flow surfaces are most often superimposed and directly riveted to each other, or directly riveted to a doubler, the rivet heads being generally arranged directly in the surface. flow next to a directly visible seam area.
    [0004] Even if a fiber-reinforced composite material is used to make a fairing body component, the rivets or screws used for fastening the fairing body component to a connecting member must pass through the flow surface, which opposes the maintenance of a boundary layer flow in laminar regime. Thus, according to WO 2013/000447 A1, an assembly arrangement is known for the aerodynamically smooth assembly of two profile elements, as well as a method for this purpose, according to which the two pieces have for assembly by rivets an assembly area located below the level of the flow surface. After assembling the two section elements by riveting, the assembly area is smoothed by applying a filler mass, so as to achieve an aerodynamically smooth connection between the two profile elements. This certainly allows to meet the conditions of a flow in laminar regime. However, the geometry to be filled by the filling mass above the rivet heads is complex, so that the accuracy of the filling operation itself is subject to stringent requirements. In addition, such a technique can be used only for parts assembled to each other, such as the leading edge of the wing and the load-bearing wing in the example of use, which have a surface junction long enough. Individual rivets of reinforcing members on the inner side of the fairing body component, or glue discharge rivets, can not be judiciously treated with this technology.
    [0005] Also, the object of the present invention is to provide an improved method of assembly, as well as a corresponding assembly arrangement, which makes it possible to satisfy the laminar regime criteria for a fairing body component made of reinforced composite material. of fibers, irrespective of the bonding geometries in complementarity-shaped bonding assemblies, whether riveted or screwed. According to the invention this object is achieved by the method for assembling a fairing body component to one or more parts, to form a flow surface of the body component, fairing along which the flow can be made. in laminar mode, characterized by the following steps: a) providing a structural member carrying the fairing body component, made of a fiber reinforced composite material, b) inserting assembly elements into the element of carrying structure of the fairing body component, passing the assembly members through the carrier structure member, c) assembling the supporting structure member of the fairing body component with said at least one piece by means of assembly members passing through the carrier structure member, and d) arranging and bonding a fairing surface member comprising a composite material fiber-reinforced, on the carrier structure element assembled with said at least one piece, to form the flow surface along which the flow can be in laminar flow, so that the connecting elements passing through the carrier structure member are covered, at the flow surface, by the fairing surface member having been attached by gluing. According to the invention this object is achieved by the assembly arrangement for assembling a fairing body component to one or more parts, to form a flow surface of the fairing body component, the along which flow may be in laminar flow, characterized in that the fairing body component has a load-bearing structural member of a fiber-reinforced composite material and a fairing surface member having a fiber-reinforced composite material , an arrangement in which one or more connecting elements are inserted into the carrier structure member and pass through the carrier structure member, said at least one component is assembled to the carrier structure member of the fairing body component at means of the connecting elements passing through the supporting structure element, which arrangement, to form the flow surface along the lacquer When the flow can be made in a laminar regime, the fairing surface element is arranged and bonded to the supporting structure element assembled with the at least one piece, so that at the level of the flow surface the joining members passing through the carrier structure member are covered by the fairing surface member having been attached by gluing. For the purposes of the present invention, the term "fairing body" means the elements which, by their use, are subjected to the flow of a fluid on an outer flow surface. Such a fairing body may for example be a wing body of an aircraft, denomination fairing body designating in the sense of the present invention, the elements of a flying object which are arranged to project from the fuselage of the flying object, and which are subject to the flow of layers of air, when the flying object is used in the manner provided. The term "fairing body component" means at least parts of the fairing body from which the fairing bodies are assembled, at least in part. Thus, the nose of a fairing body may for example be a fairing body component. The leading edge of a load-bearing wing or empennage may also be a fairing body component or at least a part thereof. In accordance with the invention, there is now provided a method for assembling a fairing body component to one or more pieces to form a flow surface of the fairing body component, around which the flow can flow. to do in laminar regime. A part to be assembled to the fairing body component may for example be another fairing body body component, a profile element, a connecting element or a connection element for assembling a plurality of fairing body components such as for example rib soles, or for example reinforcing elements, stiffening elements and / or connecting elements located inside, ie arranged in a space located inside the fairing body.
    [0006] According to the invention, there is here proposed a two-step manufacturing method, according to which on the one hand the parts are first arranged on a supporting structure member of the fairing body component, passing connecting members through the carrier structure member, then arranging a fairing surface member on the carrier structure member, thereby covering the connecting members on the carrier structure member and thereby providing the the fairing body component assembly.
    [0007] According to the invention, it is thus proposed to first provide a structural member carrying a fairing body component, the carrier structure member being made of a fiber reinforced composite material. The carrier structure element can for example also be obtained by manufacturing the carrier structure element of a fiber reinforced composite material. For the purposes of the present invention, a fiber-reinforced composite material is a material having a plastic material provided with reinforcing fibers. Such materials may for example be glass fiber reinforced plastics or carbon fiber reinforced plastics.
    [0008] In the bearing structure component of the fairing body component, the manufacture and curing of which is complete, assembly elements are now inserted by passing the assembly elements through the carrier structure element. Such connecting elements may for example be rivets or screws. As a general rule, holes are firstly made in the carrier structure element, into which the assembly elements are then inserted. The connecting elements are here arranged in the carrier structure so as to extend, as a rule, towards the interior space formed by the fairing body, so as to accommodate the part to be connected and assembled. Advantageously, the connecting members are introduced through the carrier structure member from the side directed towards the flow surface, toward the side of the load bearing member, which is directed to the space. inside the fairing body. The connecting elements are most often visible on the side of the supporting structure element, which is directed towards the flow surface. After introduction of the assembly members into the carrier structure member, the supporting structure member of the fairing body component is connected to and assembled with the at least one piece by means of the connecting members passing through the carrier structure, for example in the form of an assembly connection by rivets or screws. Then, a fairing surface member is arranged and bonded to the carrier structure member, such that the connecting members traversing the structural member are covered at the flow surface, by the fairing surface element attached by gluing. The fairing surface element itself also has a fiber reinforced composite material.
    [0009] The fairing body component is thus, according to the invention, subdivided into two functional elements, namely on the one hand the carrier structure element to which said part is assembled using the assembly elements, and the fairing surface element, which covers the connecting element passing through the supporting structure and simultaneously forming the flow surface in a laminar regime. The two elements, both the fairing surface element and the load-bearing body component of the fairing body component, here have at least one fiber-reinforced composite material, so that the present invention makes it possible to manufacture fairing body, especially in the aeronautical field, in a fiber-reinforced composite material, and at the same time to assemble them to parts and to arrange them on the fairing body so as to satisfy the criteria of a flow in a laminar regime of such a fairing body component.
    [0010] The inventors have found that such an assembly process would reliably cover the assembly elements by means of a layer of fiber-reinforced composite material, so as to meet the criteria of a laminar flow. . In particular, it is possible to significantly reduce the undulations and the three-dimensional perturbations at the level of the flow surface. At the same time, substantial stiffening and connecting elements can be provided, thereby reinforcing the fairing body component, or assembling the fairing body component to other fairing body components by means of structural elements. profile. The fairing surface element can here be configured to completely cover the carrier structure element and / or is of a single-stage surface configuration. According to an advantageous embodiment, a load-bearing surface element which contains a de-icing system is bonded to and bonded to the supporting structure element. This provides the advantage that in addition to providing such a de-icing system, it is also possible with the functional layer of the de-icing system to cover the assembly elements at the same time in order to produce a surface of the de-icing system. flow in laminar flow. According to an advantageous development, the deicing system of the fairing surface element is manufactured by arranging an electrically conductive fiber reinforced composite material between an electrically insulating material. Thus, it has proved advantageous to arrange an electrically conductive fiber reinforced composite material, for example a carbon fiber reinforced plastic (CFK), between two layers of glass fiber reinforced plastic material as a material. insulating. In this case, a conventional manufacturing technology for fiber-reinforced composite materials makes it possible to arrange the deicing system on the carrier structure element. According to another advantageous embodiment, in addition or alternatively, the fairing surface element is manufactured by arranging a steel sheet as an outer flow surface. For this purpose, a sheet of steel is provided on the fiber-reinforced composite material used for the fairing surface element to thereby provide protection against erosion.
    [0011] The fairing surface element is adhered to the supporting structure element by means of a suitable glue or a suitable adhesive layer, the adhesive layer or glue of the adhesive layer providing by its hardening, bonding the fairing surface element to the carrier structure member. As regards the adhesive or the adhesive layer, there are, for example, suitable elastomeric bonding agents. But it is also possible to consider other adhesives or adhesives. Apart from bonding the fairing surface element to the supporting structure element by means of an adhesive layer provided between the two elements, the steel sheet can also be glued, as a surface of external flow, on the fiber-reinforced composite material of the fairing surface element, by means of such an adhesive layer. Thus, the steel sheet can for example be glued to the defrosting system of the fairing surface element by means of an adhesive layer.
    [0012] It is thus advantageous to insert and provide an adhesive layer between the carrier structure member and the fairing surface member. According to a choice of two advantageous embodiments, the fairing surface element can be assembled by gluing to the carrier structure element by means of a process known as cobonding or simultaneous bonding or binding or a process known as secondary-bonding or secondary link. In the case of the simultaneous bonding method, the fairing surface member having at least one fiber reinforced composite material in an uncured state, ie non-crosslinked, and an adhesive layer provided between the fairing surface element and the supporting structure element are arranged in common on the carrier structure element. On this occasion it is possible to additionally arrange for example the steel sheet as an erosion layer, on the uncured fiber reinforced composite material of the fairing surface element, a layer of adhesive can also be provided between these two elements. Then, for the manufacture of the fairing surface member, said at least one fiber reinforced composite material of the fairing surface member is cured in a single process step, in common with the adhesive layer for gluing. the fairing surface member on the carrier structure member, and where appropriate, for adhering the steel sheet to the fiber reinforced composite material of the fairing surface member.
    [0013] Thus, the fiber reinforced composite material may for example be laminated to the carrier structure member, with a suitable adhesive layer provided between the carrier structure member and the laminating layers of the fiber reinforced composite material. the fairing surface element. Then, a layer of adhesive is reported on the laminating layers of the fiber-reinforced composite material to the extent that it is not already assembled, which may for example be countersunk rivets. are thus inserted into the supporting structure element such that the outer end of the connecting element is at least flat with the surface on which the fairing surface element is to be arranged and adhered. But it is also conceivable that the connecting elements are lower than the joining surface of the supporting structure element on which the fairing surface element must be arranged, so that the connecting elements do not protrude out of said surface, with the risk of disrupting the arrangement and gluing of the fairing surface element. It has been found that in the case of a embedment depth allowing the connecting elements to terminate flat with the junction surface or deeper than the latter, the corrugations could be reduced on the surface of the junction. laminar flow.
    [0014] The invention will be explained in more detail, by way of example, with reference to the appended figures. These show: FIG. 1 a schematic representation of a riveted connection element; Figure 2 a schematic representation of a method of construction of an assembly arrangement according to the invention.
    [0015] Figure 1 shows schematically a fairing body component 1, which has an outer flow surface 2 along which a boundary layer flow in a laminar regime is to be obtained. The fairing body component 1 must here be assembled by means of a riveted form-compliant connection 3 to a part 4 which, in the embodiment of FIG. 1, is a profile element intended for connection. other fairing body components la, so to be able to assemble, for example, a complete fairing body. Said piece 4 is here an element of assembly profile, bent. However, the connecting profile element may also be an integral part of the adjacent fairing body component 1a.
    [0016] The fairing body component 1 comprises, according to the invention, a carrier structure element 5, made of a fiber reinforced composite material, for example a carbon fiber reinforced plastic material. On a junction or assembly face 6 of the carrier structure element 5, there is then arranged a fairing surface element 7, which is adhered to it by means of an adhesive layer provided between the surface element. 7 and the supporting structure element 5. The fairing surface element 7 has on its outer face a laminar flow surface 2.
    [0017] Before arranging and gluing the fairing surface element 7 on the junction face 6 of the supporting structure element 5, the supporting structure element 5 is arranged, using assembly elements. 8, on the piece 4 and is assembled there. In the embodiment of FIG. 1, the assembly element 8 is a countersunk head rivet with a closure ring 9 arranged on the rivet, so as to fix the part 4, by complementarity of shapes, to the 5. The assembly element 8 is arranged at least in plane or smooth manner with the junction face 6 of the carrier structure element 5, and arrives flush with the junction face 6.
    [0018] According to the invention, the fairing surface element 7, which also comprises a fiber-reinforced composite material, is arranged on the junction face 6 of the carrier structure element 5 so that the element assembly 8 is covered by the fairing surface element 7 to form the laminar flow surface. This results in a fairing body component 1 having no protruding or recessed joining elements 8 which could disturb and interrupt the boundary layer flow in a laminar regime. The fairing surface element 7 may be arranged on the junction face 6 of the carrier structure element 5 by the cobonding or simultaneous bonding process, such that the fiber reinforced composite material of the fairing surface 7 is applied in an uncured state, namely non-crosslinked, on the carrier structure element 5, this in common with the adhesive layer between the fairing surface element 7 and the structural element 5. Both the fairing surface member 7 and the adhesive layer used are subsequently cured in a common process step. In a process variant with respect to the previous one, namely the so-called secondary bonding or secondary bonding method, the fairing surface element 7 is first manufactured in a finite manner, in a fiber-reinforced composite material, and is arranged, in the state so manufactured, on the carrier structure member 5 and adhered thereto with a layer of adhesive, the process step of curing the adhesive layer between the fairing surface member 7 and the carrier structure element 5 being effected separately from the manufacture of the fairing surface element 7. In the simultaneous cobonding or simultaneous bonding process, the hardening of the fairing surface element 7 and of the adhesive layer is integrally in one process step.
    [0019] Figure 2 shows schematically the method of construction of a fairing body component 1 thus manufactured, with a part 4 suitably bonded to this component. The fairing body component 1 has a supporting structure element 5 into which assembly elements 8 have been inserted. This can for example be done by first making bores in the supporting structure element 5, and then by then inserting the assembly elements 8 in said bores. In the embodiment of Figure 2, there is provided an assembly element 8a, which terminates in the plane of the junction face 6 of the carrier structure element. The assembly element 8b placed next to the previous one here has a depth of lowering of for example -0.15 mm, below the junction face 6 of the carrier structure element 5, the outer end of the connecting element is thus embedded in the carrier structure element 5. But it is also possible to envisage a depth of lowering of +0.15 mm, so that the connecting element protrudes out 6. On the junction face 6 of the supporting structure element 5 is arranged an adhesive layer 10 by means of which the fairing surface element 7 is to be glued to the element. 5. The fairing surface element 7 has a de-icing system 11 on which is bonded a sheet of steel 12 as a protection against erosion and an external flow surface 2. The sheet of steel can for example have a thickness of 0.1 25 mm. The adhesive layer 10 may for example have a layer thickness of 0.5 mm. The defrosting system 11 comprises an electrically conductive fiber-reinforced composite material 13 which may for example be CFK 45 ° fabric (carbon fiber reinforced plastic) with a basis weight of 285 g / m 2. The electrically conductive fiber-reinforced composite material 13 is arranged between an electrically insulating material 14, which may, for example, be on both sides in the form of two layers of E-type glass fabric, 45 °, of mass per unit area. of 105 g / m2. The electrically insulating fiber reinforced composite material is here a fiberglass reinforced plastic material. The adhesive layer 10 may for example be constituted by an uncrosslinked elastomer of the EPDM type or by an adhesive film of the Redux319L type. Such an adhesive layer may for example also be provided between the de-icing system 11 and the steel sheet 12. Nomenclature of the markers 1 Component of the fairing body 2 Surface of laminar flow, external 3 Assembly by rivet 4 Part 5 Supporting structure element 6 Joining surface 7 Fairing surface element 8 Connecting element / rivets 9 Closing ring 10 Adhesive layer 11 Defrosting system 12 Steel sheet 13 Electrically conductive fiber-reinforced composite material 14 Composite material reinforced with electrically insulating fibers
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. A method of joining a fairing body component (1) to one or more parts (4) to form a flow surface (2) of the fairing body component (1) along which flow can be made in laminar mode, characterized by the following steps: e) providing a carrier structure member (5) of the fairing body component (1), made of a fiber reinforced composite material, f) inserting elements of assembling (8) in the carrier structure member (5) of the fairing body component (1), passing the connecting members (8) through the supporting structure member (5), g) assembling of the carrier structure member (5) of the fairing body component (1) with said at least one component (4) by means of the connecting elements (8) passing through the carrier structure element (5), and h) arranging and bonding a fairing surface member (7) comprising a material fiber-reinforced mposite on the supporting structure element (5) assembled with said at least one piece (4) to form the flow surface (2) along which the flow can be in a laminar flow, in such a way that the connecting elements (8) passing through the carrier structure element (5) are covered, at the flow surface (2), by the fairing surface element (7) having been attached by gluing.
    [0002]
    Method according to claim 1, characterized in that a fairing surface element (7) is arranged and bonded which contains a de-icing system (11).
    [0003]
    3. Method according to claim 2, characterized in that the defrosting system of the fairing surface element (7) is manufactured by the arrangement of an electrically conductive fiber-reinforced composite material (13) between a material ( 14a, 14b) electrically insulating.
    [0004]
    Method according to one of the preceding claims, characterized in that the fairing surface element (7) is manufactured by arranging a steel sheet (12) as an outer flow surface (2). .
    [0005]
    5. Method according to one of claims 1 to 4, characterized in that the fairing surface element comprising at least one fiber reinforced composite material in an uncured state, is arranged on the carrier structure element, in together with an adhesive layer provided between the fairing surface element and the carrier structure member, and then during a process step said at least one fiber reinforced composite material for the manufacture of the fairing surface is cured in common with the adhesive layer for bonding the fairing surface element to the carrier structure member ,.
    [0006]
    6. Method according to one of claims 1 to 4, characterized in that the fairing surface element comprising at least one fiber reinforced composite material is manufactured before being arranged on the carrier structure element, by hardening. of said at least one fiber-reinforced composite material, then is arranged on the carrier structure element, in common with an adhesive layer provided between the fairing surface element and the carrier structure element, the the adhesive is then cured to bond the fairing surface member to the carrier structure member.
    [0007]
    7. Method according to one of the preceding claims, characterized in that with respect to the junction surface (6) of the carrier structure element on which is arranged and bonded the fairing surface element, the assembly elements are inserted with a depth of lowering into the supporting structure element, so that the connecting elements are arranged in the plane or below the joining surface.
    [0008]
    8. An assembly arrangement for assembling a fairing body component to one or more parts, to form a flow surface of the fairing body component, along which the flow can be carried out laminar, characterized in that the fairing body component has a load bearing structural member of a fiber reinforced composite material and a fairing surface member having a fiber reinforced composite material, wherein one or more joining members are inserted into the carrier structure member and pass through the carrier structure member, said at least one piece is joined to the supporting structure member of the fairing body component by means of the connecting elements passing through the carrier member. carrier structure, arrangement in which, to form the flow surface along which the flow can be in laminar flow , the fairing surface element is arranged and glued on the supporting structure element assembled with said at least one piece, so that at the flow surface the assembly elements passing through the structural element carrier are covered by the fairing surface element having been attached by gluing.
    [0009]
    9. Assembly arrangement according to claim 8, characterized in that the fairing surface element contains a defrosting system.
    [0010]
    Assembly arrangement according to claim 8 or 9, characterized in that the de-icing system is formed of an electrically conductive fiber reinforced composite material which is arranged between an electrically insulating material.
    [0011]
    Assembly arrangement according to one of claims 8 to 10, characterized in that the fairing surface element comprises a steel sheet as an outer flow surface.
    [0012]
    12. Assembly arrangement according to one of claims 8 to 11, characterized in that relative to the junction surface of the carrier structure element on which is arranged and glued the fairing surface element, the elements assembly members are inserted into the carrier structure member with a lowering depth such that the connecting members are arranged in the plane or below the joining surface. 25
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    同族专利:
    公开号 | 公开日
    DE102014102117B4|2015-10-01|
    FR3017668B1|2019-10-18|
    DE102014102117A1|2015-08-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP3243743A1|2016-05-11|2017-11-15|Airbus Operations Limited|Aircraft joint|US20010048048A1|1999-01-13|2001-12-06|Brian L Riedel|Backside fitting attachment for nacelle acoustic panels|
    FR2905739B1|2006-09-08|2008-11-07|Airbus France Sas|PANEL ASSEMBLY AND METHOD OF MOUNTING PANEL ASSEMBLY|
    GB0805963D0|2008-04-02|2008-05-07|Airbus Uk Ltd|Aircraft structure|
    EP2368699B1|2010-03-22|2018-11-21|Vestas Wind Systems A/S|Method for manufacturing a blade spar for a windturbine|
    DE102011107624A1|2011-06-30|2013-01-03|Eads Deutschland Gmbh|Connecting arrangement for the aerodynamically smooth connection of two profile elements, methods for their production and apparatus for performing the method|GB2571508A|2017-12-13|2019-09-04|Airbus Operations Ltd|Aerofoil structures|
    EP3521162A1|2018-02-02|2019-08-07|AIRBUS HELICOPTERS DEUTSCHLAND GmbH|A shear connection for connecting airframe parts in an aircraft|
    法律状态:
    2016-01-25| PLFP| Fee payment|Year of fee payment: 2 |
    2017-01-18| PLFP| Fee payment|Year of fee payment: 3 |
    2017-12-29| PLSC| Publication of the preliminary search report|Effective date: 20171229 |
    2018-01-18| PLFP| Fee payment|Year of fee payment: 4 |
    2019-01-17| PLFP| Fee payment|Year of fee payment: 5 |
    2020-01-24| PLFP| Fee payment|Year of fee payment: 6 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 7 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102014102117.7A|DE102014102117B4|2014-02-19|2014-02-19|Method and connection arrangement for connecting a flow body component with one or more components|
    DE102014102117.7|2014-02-19|
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