• 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:
    The invention relates to a method for manufacturing a hybrid laminated wing body (1), in which a laminar flow of the wing body is to be obtained by shaping and boundary extraction, the hybrid laminated wing body (1) by placing a perforated outer skin (2) on an internal supporting structure. (3) while forming a plurality of separate extraction chambers (6) are manufactured in such a way that the extraction chambers (6) on the one hand are in functional communication with the perforated outer skin (2) for extraction of the boundary layer and on the other hand with i the inner support structure (3) provided choke openings (8) for connection to an extraction system (9), characterized in that the inner support structure (3) is made of a fiber composite material with the following steps: - providing flat, non-draped fiber semi-finished products ( 110) of the fiber composite material, - insertion of displacement bodies (100, 210) in the fiber semi-finished products (110) p at the places where the choke openings (8) are later to be provided in the internal support structure (3), by displacing the fibers of the respective fiber semi-finished products (110) without destruction, - draping the fiber semi-finished products (110) on a molding tool surface (310) of a mold ) with the displacing bodies (100, 210) inserted in the fiber semi-finished products (110), - curing a matrix material of the fibrous composite material which embeds the fibers of the fibrous semi-finished products (110), while the displacing bodies (100, 210) inserted in the fiber semi-finished products (110) remain in fiber fibers (110), and - removing the displacement bodies (100, 210) after curing the matrix material to form the choke openings (8) in the support structure
    公开号:DK201900108A1
    申请号:DKP201900108
    申请日:2019-01-28
    公开日:2020-10-07
    发明作者:Forssbohm Tobias
    申请人:Deutsch Zentr Luft & Raumfahrt；
    IPC主号:
    专利说明:

    The invention relates to a method for manufacturing a hybrid laminated wing body, in which a laminar flow of the wing body is to be obtained by shaping and boundary layer extraction.
    Under the ever-increasing cost pressure, aircraft manufacturers are striving to make the operation of their aircraft cheaper by appropriate measures.
    A significant main focus in this connection lies in a significant weight reduction of the total weight of commercial aircraft as well as a reduction of air resistance during the flight.
    With consistent use of fiber composite materials also for critical resp. load-bearing structures, the aspect of weight reduction and consequently fuel saving can be addressed.
    In addition, to reduce air resistance, it has been found that during flight it is advantageous if a laminar boundary layer is maintained on the outer surface of the blade body, in particular the buoyancy-producing wing body, as long as possible, since turbulent flow rates in particular lead to a significant increase in air resistance and consequently to increased fuel consumption.
    Air currents that hit an aerodynamic profile body tend in principle to have a laminar boundary layer flow.
    Admittedly, with a suitable design, for example with protruding rivets or edges in the aerodynamic profile surface, it can quickly lead to the general laminar boundary layer turning into a turbulent boundary layer and thus increasing the air resistance.
    Consequently, it is important for the maintenance of a laminar boundary flow that the design favors the maintenance of a laminar flow and, as far as possible, prevents wrapping into a turbulent boundary flow.
    In addition, it has been found that by extracting the boundary layer by means of an extraction system provided in the wing body and a microperforated aerodynamic surface, the longest possible laminar flow can be obtained at the aerodynamic profile body, which further lowers the air resistance and consequently all in everything saves fuel.
    A long-lasting laminar-
    , DK 2019 00108 A1 flow means in this connection that the flow path along the profile surface is as long as possible and at best reaches from the front edge to the rear edge of the aerodynamic profile body.
    Aerodynamic profile bodies resp. wing bodies which, due to their design as well as by means of a boundary layer extraction, must maintain as long a laminar flow as possible, are also referred to as hybrid laminarized wing bodies resp. profile bodies and is at least currently known in the experimental stage under the name HLFC technology. In this connection, such a wing body has a structure in which a perforated outer skin, for example of an erosion-resistant material, such as metal or aluminum, is applied to a support structure which, due to its shape together with the perforated outer skin applied thereto, forms individual extraction chambers under the perforated outer skin so as to be able to extract the air flow at the outer skin in the boundary layer area. The individual extraction chambers formed each have one or more choke openings, with which the extraction chamber in question then communicates in connection with an extraction system for generating a negative pressure. The extraction chambers can be produced, for example, by the support structure on the side facing the perforated outer skin having a corrugated structure resp. shape so that upon application of the perforated outer skin due to the wave structure, chambers arise between the support structure and the perforated outer skin.
    If such a support structure for HLFC technology for further weight reduction is to be made of a fiber composite material, the problem arises that the choke openings provided in the support structure must be inserted into the load-bearing fiber composite structure of the support structure by machining methods, which in principle have a detrimental effect on the structure. makes similar demands on industrial production. For machining methods, load-bearing fibers intersect and consequently weaken the structure, which must be compensated with additional material. This eliminates the weight advantage of
    3 DK 2019 00108 A1 use of fiber composite materials, however, partly again. Furthermore, fibrous composite materials are mostly homogeneously constructed and are consequently difficult to machine mechanically, which manifests itself in a lower dimensional accuracy over a plurality of bores. Tool lifetimes are also limited as feed speeds, resulting in a long machining period for insertion of the choke openings. Furthermore, a lubricated machining machining of fiber composite plastic structures has not hitherto been realized industrially, so that as a result of the machining, dust is released which has to be bonded.
    Furthermore, insertion of the choke openings can only take place after the end of the curing reaction and must thus take place on geometrically complex shaped structures, which can sometimes lead to collisions between tools and fiber composite structures.
    DE 10 2013 109 995 A1 discloses a manufacturing method for manufacturing a fiber composite component, in which a kind of mandrel is inserted into the fibrous material before the curing of the matrix material, which does not cut through the fibers but only displaces them so as to produce an opening in the fiber composite component. The mandrel remains until the end of the curing of the matrix material in the fiber composite component and is drilled in connection therewith, the resulting opening in the fiber composite component being coated with an insert or with a bolt, respectively. a rivet to connect the fiber composite component to other components. With the later drilling of the placeholder, however, the necessity of a machining method arises again, which entails the above-mentioned disadvantages of industrial manufacture.
    Accordingly, it is the object of the present invention to provide an improved method of making a hybrid laminated blade body by which such blade bodies can be efficiently manufactured also in an industrial context.
    1 DK 2019 00108 A1 The object is fulfilled according to the invention with the method according to claim 1. Advantageous designs are found in the corresponding subclaims.
    According to claim 1, a method for manufacturing a hybrid laminated wing body is proposed, in which a laminar flow of the wing body is to be obtained at least partially in shaping and boundary layer extraction.
    In this connection, the hybrid laminated wing body is manufactured by placing a perforated outer skin on an internal supporting structure, forming a plurality of separate extraction chambers in such a way that the extraction chambers on one side are in operative communication with the perforated outer skin for extraction. of the boundary layer and on the other hand with choke openings provided in the internal support structure for connection to an extraction system.
    According to the invention, the manufacturing method is now characterized in that the internal support structure is manufactured from a fiber composite material, where the choke openings provided in the internal support structure do not have to be inserted with a machining method.
    In this connection, the fibrous composite material exhibits, firstly, a fibrous material and, secondly, a matrix material as essential constituents, the matrix material embedding the fibrous material and, after curing, forming an integral unit with the fibrous material.
    According to the invention, it is further provided that in order to realize a non-machining method, the choke openings are inserted, first providing flat, non-draped fiber semi-finished products of the fiber composite material.
    In these flat, non-draped fiber semi-finished products, displacement bodies are now inserted at the places where the choke openings are later to be provided in the internal support structure, the displacement of the displacement bodies taking place in such a way that the fibers of the fiber semi-finished products in question are displaced without destruction.
    In connection therewith, the fiber semi-finished products are draped with the inserted displacement bodies on the shaping tool surface of a mold tool, so that the carrier
    DK 2019 00108 The later component shape of the A1 structure is formed. | adjoining it, a matrix material of the fiber composite material is cured, which embeds the fibers of the fiber semi-finished products, for example by tempering and possible pressure action, where the displacement bodies remain in the fiber semi-finished products during the curing process, which may require some time.
    After curing of the matrix material and formation of an integrated unit between matrix material and fibrous material, the displacement bodies are removed from the manufactured component, and the respective choke openings are thus formed in the support structure. With such a method according to the invention it becomes possible with HLFC technology of a fiber composite material to produce a support structure for wing bodies, without the necessary throttle openings for the extraction system having to be inserted by means of a machining method. According to the invention, it was recognized in this connection that the displacement bodies can be inserted into the flat, non-draped fiber semi-finished products, and those fiber semi-finished products provided with the displacement body in connection therewith can then be draped on the relevant shaping tool surface, without the inserted displacement bodies the fibers or all in all make the fiber semi-finished product useless. For the process of draping is a very critical process step in the entire manufacturing process, as fibers here are not infrequently displaced resp. changes, and material fractures or stretches do not infrequently occur, which later lead to a structural impact. According to the invention, however, the displacement bodies can remain in the fiber semi-finished products during the draping process without adversely affecting the draping process, so that this has the advantage that the displacement bodies do not have to be inserted later in the already draped fiber semi-finished products and consequently in the complex geometric structure.
    A DK 2019 00108 A1 Furthermore, it was recognized by the inventor that such a choke opening, which was manufactured by means of such a displacement body as described according to the invention, is suitable as a choke opening for extraction of the boundary layer, even if the inner wall of the choke opening was not lined with an insert. In fact, by means of such a displacement body a choke opening can be manufactured so that it corresponds to the specified tolerance values and dimensions, and this dimensional accuracy can be observed over a plurality of these choke openings, namely also when the displacement bodies are inserted into the flat, non-displacement bodies. draped fiber semi-finished products, and the fiber semi-finished products are first draped in connection therewith.
    A further advantage is that with the choke openings produced with the displacement bodies, no fiber ends are exposed. A subsequent edge seal of the choke openings to minimize water uptake of fiber composite components in humid environments can thus be eliminated.
    In this connection, the term "flat" means in particular a fiber semi-finished product which has a flat extent and thereby a relatively small strength or thickness or height. In addition, the term "non-draped" is understood to mean that the fiber semi-finished product has not yet been brought to its final component form, and is preferably still present in a flat, non-deformed state In an advantageous embodiment, one or more fibrous semi-finished products are first formed from the provided non-draped fiber semi-finished products, which are made from several layers of the obtained semi-finished fibrous products. The fibrous packages thus layered are now inserted into the displacement bodies, the fibrous layer packages or the only one fibrous package after the step of preform making and insertion of the displacing bodies then being draped on the molding tool Here it was recognized that such a displacing body in non-draped condition can also be inserted layer of fibrous material without thereby destroying
    ; DK 2019 00108 A1 the fibers, as the boundary conditions ordered at the choke openings can still be complied with.
    In a further advantageous embodiment, several different displacement bodies are provided, each of which has different cross-sectional sizes and / or cross-sectional shapes, a specific opening size and / or opening shape being specified for each choke opening, and a displacement body being selected for a certain place where a chute opening is to be formed, depending on the opening size and / or opening shape specified for the chute opening in question at that location.
    Consequently, different choke openings with different cross-sectional sizes and / or cross-sectional shapes can be inserted over the entire extent of the support structure, whereby the extraction at the aerodynamic surface of the profile body can be affected with respect to the strength. Thus, in principle, larger choke openings are provided in the area of the leading edge, in order to amplify the effect of the extraction here, while the choke openings become smaller in the direction of the trailing edge of the wing body, so as to weaken the extraction force.
    In this connection, it is conceivable that a mandrel which has a conical tip is used as the displacement body, in order to be able to introduce the mandrel into the fibrous material during destruction. However, it is also conceivable for a wire to be used as a displacement body, which may, for example, have different thicknesses.
    In a further advantageous embodiment, at least fibrous semi-finished products are provided as fiber semi-finished products which have not yet been impregnated resp. pre-impregnated with a matrix material, the dried fiber semi-finished products being infused with a matrix material after the draping of the fibrous semi-finished products on the specified tool surface. For this purpose, it is advantageous if the fibrous material draped on the mold tool is sealed vacuum-tight by means of a vacuum build-up DK 2019 00108 A1, and the component in connection therewith is evacuated so as to be able to infuse the matrix material better into the fibrous material. Admittedly, it is also conceivable that pre-impregnated fiber semi-finished products (so-called prepregs) are provided, which in the further manufacturing process do not necessarily have to be infused with a matrix material. It has also proved advantageous if the displacement bodies are coated resp. provided with a release agent or provided with such a release agent so that the displacement bodies can be removed again without destruction from the formed openings without too strong adhesion to the matrix material which hardens. However, it is also conceivable that the displacement bodies consist of a material which generally has the property of having difficulty in entering into an adhesive connection with the matrix material.
    The object is also fulfilled by the use requirement 8 for using a fiber composite component as a support structure in a hybrid laminated wing body, wherein the fiber composite component contains a plurality of choke openings formed by displacement bodies which are displaced by the fibers of the fiber semi-finished products in the places where the choke openings are later to be provided in the internal support structure, and are removed after the curing of a matrix material which embeds the fibers of the fiber semi-finished products.
    The invention is explained in more detail by way of example with the aid of the accompanying figures.
    Here: figure 1 shows a schematic representation of a partial section of a hybrid laminated wing body; Figure 2 is a schematic representation of the insertion of a displacement body into fiber semi-finished products;
    o DK 2019 00108 A1 figure 3 an exemplary schematic representation of the manufacturing method in a sub-aspect. Figure 1 shows in a section a part of a hybrid laminated wing body 1, which has an outer skin 2 and a support structure 3. The support structure 3 has on its side facing the outer skin 2 a corrugated profiling 4, where a cavity 5 is formed between two corrugated mountains, of which can then be formed by placing the outer skin 2 on this corrugated profiling 4 of the support structure 3, the extraction chambers
    6.
    In this connection, the outer skin 2 is designed to be perforated, in particular in the area of the microperforation, and can, for example, have openings of less than 100 μm. With this perforated outer skin 2, by creating a negative pressure in the extraction chambers 6, an extraction of a flowing fluid in the extraction chambers 6 can be achieved, which is indicated schematically by the arrows 7. To produce a negative pressure in the extraction chambers 6, each extraction chamber is in addition communicating with a suction system 9 via a choke opening 8, the extraction system 9 may, for example, be a negative pressure chamber inside the wing leading edge which communicates with the relevant extraction chambers 6 via the choke openings 8. The choke openings 8 may in this connection have different diameters for so as to be able to set the extraction force accordingly.
    With such a wing body 1 it is possible to purposefully suck out the boundary layer by the inflow of the aerodynamic wing body 1 and thus maintain a long-term course of a laminar boundary layer over the cross section of the wing body.
    According to the invention, the support structure 3 with the choke openings 8 in this connection must be made of a fiber composite material, the choke openings 8
    0 DK 2019 00108 A1 just does not have to be produced by means of a machining method, as this would be the case, for example, when drilling. According to the invention, it is now proposed that by means of a displacement body 100, as schematically indicated in Figure 2, the fibers be displaced without destruction by insertion of the displacement body 100 into the fiber semi-finished fabric 110, the displacement body 100 remaining in the fibrous material 110 during the curing of the matrix material. It is schematically indicated that the fibers of the fibrous material 110 are not destroyed in the displacement region 120, but are only deflected from their web, whereby the load-bearing property of the component is still preserved.
    Figure 3 schematically shows the flat fiber layer package 200, which is built up of several layers of fiber semi-finished product 110. In the displacement area 120, at the location of which the respective choke opening is later to be provided, a displacement body 210 is now inserted, which has a flange at the upper end and thus terminates at the level of the upper fibrous layer package 200. On a underside, which is later subsequently brought into contact with a molding tool, the displacement body 210 terminates at the level of the underside of the fibrous layer package. After forming such fiber layer packages as well as inserting the respective displacement bodies 200, the fiber layer package 200 is laid on a molding tool surface 310 of a forming tool 300, as schematically indicated in the lower part of Figure 3. | this compound brings the fiber layer package 200 to its later component form and can now be referred to as component 320. | this connection bends the fiber layer package 200 in particular out of its original fiber plane, also several times, and thus acquires its later component shape
    DK 2019 00108 A1 List of reference numerals 1 hybrid laminated wing body 2 - outer skin 3 - support structure 4 - corrugated profiling 5 - cavity 6 - extraction chambers 7 - extraction 8 - throttle opening 9 extraction system 100 displacement body 110 fiber semi-finished product 120 displacement area 200 fiber layer package tooling tool component
    权利要求:
    Claims (8)
    [1]
    A method of manufacturing a hybrid laminarized blade body (1), wherein by shaping and boundary layer extraction, a laminar flow of the blade body is to be obtained, the hybrid laminarized blade body (1) by placing a perforated outer skin (2) on an internal supporting structure ( 3) while forming a plurality of separate extraction chambers (6) are manufactured in such a way that the extraction chambers (6) on the one hand are in functional connection with the perforated outer skin (2) for extraction of the boundary layer and on the other hand with throttle openings (8) provided in the inner support structure (3) for connection to an extraction system (9), characterized in that the inner support structure (3) is made of a fibrous composite material with the following steps: - providing flat, non- draped fibrous semi-finished products (110) of the fibrous composite material, - insertion of displacement bodies (100, 210) into the fibrous semi-finished products (110) in the present r, where the choke openings (8) are later to be provided in the internal support structure (3), by displacing the fibers of the fiber semi-finished products (110) in question without destruction, - draping the fibrous semi-finished products (110) with those of the fibrous semi-finished products (110) inserted displacement bodies (100, 210) on a molding tool surface (310) of a mold tool, - curing a matrix material of the fiber composite material embedding the fibers of the fiber semi-finished products (110), while the displacing bodies (100) inserted in the fiber semi-finished products (110) in the fiber semi-finished products (110), and - removing the displacement bodies (100, 210) after curing the matrix material to form the choke openings (8) in the support structure (3).
    1 DK 2019 00108 A1
    [2]
    A method according to claim 1, characterized in that one or more fibrous layer packages (200) of the provided non-draped fibrous semi-finished products (110) are first formed, wherein the displacement bodies (100, 210) are subsequently inserted into the fibrous layer package or fibrous layer packages (200). ).
    [3]
    Method according to Claim 1 or 2, characterized in that several different displacement bodies (100, 210) are provided, each of which has different cross-sectional sizes and / or cross-sectional shapes, a specific opening size and / or specification being specified for each choke opening (8). or opening shape, and a displacement body (100, 210) is selected for a certain place where a choke opening (8) is to be formed, depending on the opening size and / or opening shape specified for that choke opening (8) at that location.
    [4]
    Method according to one of the preceding claims, characterized in that a mandrel and / or a wire are inserted as the displacement body (100, 210).
    [5]
    Method according to one of the preceding claims, characterized in that dry fiber semi-finished products (110) are provided, the dried fiber semi-finished products being infused with a matrix material after the draping of the fibrous semi-finished products (110) on the shaping tool surface (310).
    [6]
    Method according to claim 5, characterized in that the fiber semi-finished products (110) are closed or sealed vacuum-tight after the draping of the fibrous semi-finished products (110) and before the infusion with the matrix material, and the fiber semi-finished products (110) are subsequently evacuated by means of a vacuum pump.
    [7]
    Method according to one of the preceding claims, characterized in that the displacement bodies (100, 210) are provided or coated with a release agent or provided with such a release agent prior to insertion into the fiber semi-finished products (110).
    4 DK 2019 00108 A1
    [8]
    Use of a fiber composite component as a support structure in a hybrid laminated blade body (1), in which a laminar flow of the blade body is to be obtained by shaping and boundary layer extraction, the fiber composite component containing a plurality of choke openings (8) forming of displacement bodies (100, 210) which, by displacing the fibers of the fiber semi-finished products (110) in question without destruction, are introduced into the fiber semi-finished products (110) at the places where the choke openings (8) are later to be provided in the internal support structure (3). ), and is removed after curing of a matrix material which embeds the fibers of the fiber semi-finished products (110).
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    同族专利:
    公开号 | 公开日
    DE102018102492A1|2019-08-08|
    FR3077523B1|2022-02-25|
    FR3077523A1|2019-08-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE2944371A1|1979-11-02|1981-05-07|Messerschmitt-Bölkow-Blohm GmbH, 8000 München|Hole piercing method for fibre reinforced components - consists of inserting heated spike before hardening and removing after hardening|
    JPS62264896A|1986-05-12|1987-11-17|Terufumi Machida|Manufacture of fiber-reinforced composite material with joining hole|
    EP2687439B1|2012-07-20|2016-12-21|Stichting Nationaal Lucht- en Ruimtevaart Laboratorium|Laminar flow panel|
    DE102013201963A1|2013-02-07|2014-08-07|Bayerische Motoren Werke Aktiengesellschaft|Process for producing a fiber-reinforced plastic component|
    DE102013109995B4|2013-09-11|2016-12-29|Deutsches Zentrum für Luft- und Raumfahrt e.V.|Method for producing a component from a fiber composite material with a hole|
    法律状态:
    2020-10-07| PAT| Application published|Effective date: 20190806 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018102492.4A|DE102018102492A1|2018-02-05|2018-02-05|Process for producing a hybrid laminated wing body|
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