DE102006026538A1 - Adhesive arrangement for gluing two structure components in air- or spacecraft, comprises first structure component, which consists of first material and has first adhesive surface, and a second structure component - Google Patents

Abstract

The adhesive arrangement for gluing two structure components in air- or spacecraft, comprises first structure component (2), which consists of first material and has first adhesive surface (3), a second structure component (8), which consists of second material and has second adhesive surface (9), and a glue joint between first- and second adhesive surface. The glue joint comprises fiber and/or woven fiber structures. The fiber length is 10 mm and the fiber diameter is 0.001-0.3 mm. A coating is applied on the first- and second adhesive surface. The adhesive arrangement for gluing two structure components in air- or spacecraft, comprises first structure component (2), which consists of first material and has first adhesive surface (3), a second structure component (8), which consists of second material and has second adhesive surface (9), and a glue joint between first- and second adhesive surface. The glue joint comprises fiber and/or woven fiber structures. The fiber length is 10 mm and the fiber diameter is 0.001-0.3 mm. A coating is applied on the first- and second adhesive surface. The first structure component is formed as stringer for forming a reinforcement means, as Doppler or crack-stopper for preventing cracking or crack growth. The coating has thickness of 0.2 mu m. The first structure component and/or the second structure component are formed as structure components of a lightweight construction structure of an aircraft. The glue joint has a thickness of 0.01-0.3 mm. An independent claim is included for a method for the production of gluing two structure components in air- or spacecraft.

Description

The The invention relates to a bonding arrangement for bonding two structural elements and a method for bonding two structural elements, in particular in the aerospace sector.

lightweight structures in aircraft typically include thin-walled structural elements, such as about sheets, an outer skin, Stringer, frames, ribs and the like of aluminum materials, which are connected by riveting. In areas special loads, such as in the field of door, window or Hatch cutouts, in the area of the wing and tail roots, or in the area from door or hatch corners, it is common additional Structural elements in the form of stiffeners, Dopplers, crack stoppers and the like made of high-strength materials such as titanium or titanium alloys. Titanium materials, such as pure titanium and titanium alloys, have very good mechanical properties as well as a high fatigue strength on. Crack-stopper and Doppler made of titanium materials allow it to reinforce the hull structure which reduces the level of mechanical stresses and the Lifespan of the hull structure is increased.

Crack-stopper, Also known as crack stopper, as well as Doppler titanium material are becoming major at the moment used in two areas of the aircraft structure.

To the one is crack stopper made of titanium material in the area of the frames riveted to the longitudinal seams. The main task of the crack stopper is to spread the resulting Cracks in the area of the longitudinal seam to prevent. This is done by preventing the crack growth under the tear stopper or by the crack deflection of the longitudinal seam in an area where this crack is quickly detectable. Especially with larger cracks, such as after damage to the hull structure during the Departure, the crack stopper prevent the spread of the crack in the next Section and thereby minimize the consequences of unpredictable damage.

To the others are Doppler made of titanium material in the area of passenger door and cargo hatch corners Riveted in the fuselage. The main task of Doppler is to the crack formation of the door and To prevent hatch corners. This is done by reducing the mechanical stresses in the door and Lukeneck area and by preventing the crack growth under the Doppler.

A Riveting represents a proven and Connection method used in aircraft construction for several decades for connecting individual structural elements to structural components, for example the connection of stringer and clips with outer skin, as well as to connect of components to an aircraft structure, such as the connection from individual shells to a fuselage section, the connection of Fuselage sections to a hull, the connection of wings with Hull and the like. A riveting of crack stoppers and Dopplers made of titanium with structural elements made of aluminum materials has sufficient mechanical strength. The use of surface protection agents leads to a permanent resistance against Corrosion.

To the disadvantages of riveted structural elements are in addition long processing times also reduced fatigue properties. In the area the rivet holes arise stress concentrations and as a result of material fatigue microcracks. For example, the number of rivets used is estimated in the field of Doppler on the door and Hatch corners over 10,000. This results in a deterioration of the fatigue properties, which currently only with an increase the thickness of individual structural elements can be solved. These activities to lead however, to increase the weight of the aircraft structure as well the associated disadvantages. In addition, procedures are for Connection of individual structural elements to structural components of a Aircraft structure known to exist without rivet holes. These include adhesive and welding process for the Connection of individual skin sheets as well as for the connection of skin sheets with stiffening elements.

From the pamphlets DE 196 39 667 or DE 198 44 035 is a structural component in welded skin stringer construction known. Large-format skin panels are welded by means of laser beam welding as stringer or ribs. Laser beam welding enables a secure linear connection between individual structural elements. A large-scale connection between individual structural elements of aluminum materials and structural elements made of titanium materials is not yet feasible for technical reasons and for reasons of corrosion in aircraft.

From the publication EP 1 393 893 is a structural component in glued skin stringer construction known. Large-format skin panels are connected by gluing with grid-like framework structures. Bonding enables the manufacture of safe and corrosion-resistant, large-area connections between structural elements consisting predominantly of aluminum materials in aircraft construction.

The Bonding of structural elements made of titanium materials, for example with structural elements of aluminum materials is not yet used. The reason for that lies in the considerable expense for the pretreatment of the surfaces of Titanium materials. The known pre-treatment methods for bonding of titanium materials include machining the surfaces Titanium materials with sandblast or abrasives, and are thus for the industrial application in aircraft not applicable. Furthermore results in the bonding of different materials, the problem Each material requires a special, own pretreatment.

Of the Invention is therefore the object of a Klebeanordnung and a method for producing a bond between structural elements to provide, which in particular in aircraft industrial are applicable and which the effort for pretreatment of each other to keep glued structural elements as low as possible.

These The object is achieved by the Adhesive arrangement with the features of claim 1 and by the Method solved with the features of claim 9.

The The idea underlying the present invention is that that a first structural element of a first material, which at least a first adhesive surface and a second structural element made of one of first material different, second material, which at least a second adhesive surface is provided, wherein one of the second material of the second Structure element having coating at least on the first adhesive surface the first structural element is applied. Subsequently, a Adhesive bond between the on the first adhesive surface of the first structural element applied coating and the second Adhesive surface of the second structural element provided to the two structural elements to stick together.

Consequently the present invention over the known approaches the Advantage on that the corresponding surfaces to be bonded the two structural elements before providing the adhesive bond by means pretreated with the same pretreatment processes and materials and can be glued using the same adhesives. Thereby becomes the possibility a secure adhesive connection between structural elements of, for example a titanium alloy and structural elements of, for example, a Aluminum alloy ensures the glued structure in a simple and inexpensive way is advantageous to produce.

In the dependent claims find advantageous embodiments and improvements of specified in claim 1 adhesive arrangement and in the claim 9 specified method.

According to one preferred development, the first structural element has a Titanium material or the like. By coating one out of one Titanium material existing structural element with another, when gluing easier to handle coating material can on elaborate and in aircraft only conditionally applicable pre-treatment measures of the titanium material, such as sandblasting, grinding or the like be waived. The term "titanium material" encompasses this case both pure titanium and titanium alloys.

According to one Another preferred development is the first structural element as a stringer for forming a stiffener, as a Doppler or as crack stopper for preventing cracking or crack propagation, or the like is formed.

To a further preferred embodiment, the coating preferably at least a thickness of about 0.2 microns. For example If the coating consists of an aluminum material, for example an aluminum alloy, depending on of the second structural element to be bonded. Especially in aircraft is usually a structural element, such as a skin sheet, Stringer, frame, a rib or the like made of an aluminum material. By coating, for example, a high-strength material, such as a titanium material, existing first structural element with aluminum or a suitable aluminum alloy may be similar surface materials pretreated with each other and correspondingly advantageous to each other be glued. In this case, the coating, for example by means of a plating process, by means of a vapor deposition method or The like on the first adhesive surface of the first structural element be applied. Preferably, the Beschich device during the Production and / or prior to any rolling of the first structural element on the first adhesive surface applied to the first structural element, so that such rolling process without damage the corresponding rollers expires. The coating can be both single-sided and double-sided on the first structural element are applied, d. H. either only on the surface to be bonded of the first structural element or on the side facing away from the bond Surface.

According to another preferred Ausgestal tion, the second structural element comprises an aluminum material, magnesium material, a monolithic or laminated material, a composite material and / or the like. The second structural element is designed in particular as a structural element of a lightweight structure of an aircraft, ie, for example, as a frame, rib or the like.

Further it is conceivable that the material of the second structural element and thus the coating of the first adhesive surface of the first structural element from a hybrid material, in particular a fiber composite metal laminate consists.

A advantageous embodiment of the invention provides that the structural elements as elements of a lightweight structure, preferably an aircraft structure, are formed. The term "structural element" includes in particular also truss structures, manufactured in previous stages of manufacture, For example, multilayer components, stringers, outer skin elements, Exterior skin structures and / or like. At least one structural element can be a sheet metal wherein the term "sheet" is thin-walled, essentially comprises two-dimensional components, both from a monolithic or homogeneous as well as a hybrid, For example, laminated material.

Hybrid Materials can here as laminated materials, such as laminated Aluminum materials, fiber composite metal laminates, for example aluminum-based, fiber-reinforced laminated aluminum materials, carbon fiber reinforced composite materials or like exist. fiber reinforcement can for example, also glass fibers, polyaromatic amide fibers, aluminum oxide fibers, silicon carbide fibers, Basalt fibers, aluminum wires, Titanium wires magnesium wires or the like in addition to the already mentioned carbon fibers. Fiber composite metal laminates are for example as glass fiber Reinforced (GLARE) material or known as Aramite Aluminum Alloy (ARALL).

A particularly advantageous embodiment of the invention also provides before, that the two structural elements to be bonded adhesive arrangement a reinforced by fibers Layer comprising, for example, part of the applied adhesive bond is. The arranged in the adhesive bond between the structural elements Fibers can be aligned unidirectionally. It is also conceivable that which are arranged in the adhesive layer between the structural elements Fibers are bidirectionally or polydirectionally aligned. there can the fibers in a woven structure, such as a grid, a Net or the like may be arranged. The fibers preferably have one minimum length of 10 mm and preferably a diameter between 0.001 mm and 0.3 mm. Before or during the bonding can the fibers in a plastic matrix, for example in an adhesive be involved, as already explained above. After bonding points the adhesive layer of the adhesive bond has a layer thickness of preferably 0.01 mm to 0.3 mm. The fibers can be used, for example, as glass fibers, Carbon fibers, polyaromatic aramid fibers, aluminum oxide fibers, Silicon carbide fibers, basalt fibers or the like and as Aluminum wires, Titanium wires magnesium wires or the like may be formed.

The Invention will be described below with reference to exemplary embodiments with reference explained in more detail on the accompanying figures of the drawing.

From show the figures:

1 a schematic cross-sectional view of an adhesive assembly according to a first preferred embodiment of the present invention;

2 a schematic cross-sectional view of a one-sided with a coating provided first structural element according to a preferred embodiment of the present invention;

3 a schematic cross-sectional view of a coating provided on both sides with a first structural element according to a preferred embodiment of the present invention;

4 a perspective view of a lightweight structure of two bonded together structural elements made of different materials according to a preferred embodiment of the present invention; and

5 a simplified, schematic perspective view in section of the structure of a reinforced adhesive bonding according to a preferred embodiment of the present invention.

In the figures of the drawing, like reference numerals designate the same or functionally identical components, unless stated otherwise is.

1 illustrates an exemplary adhesive arrangement 1 according to an embodiment of the present invention. A first structural element 2 for example, in 4 illustrated lightweight structure 40 consists of a titanium alloy. The structural element 2 is on its surface facing the bond 3 with a coating preferably made as a plating 4 Mistake. The coating material is advantageously selected such that it corresponds to the material of the first structural element 2 to be bonded second structural element 8th corresponds, in this case, for example, as aluminum alloy.

The coating 4 According to the present embodiment, an oxide layer comprises 5 ' which forms the aluminum alloy on its atmosphere exposed surfaces immediately after coating. On the oxide layer 5 ' is part of the pre-treatment measures for the preparation of the adhesive arrangement 1 For example, a suitable primer is applied, which is a primer layer 6 ' forms.

The second, with the first structural element 2 over the second adhesive surface 9 to be bonded structural element 8th the lightweight structure 40 preferably consists of an aluminum alloy analogous to the coating 4 , On the surface of the second adhesive surface 9 of the second structural element 8th there is also an oxide layer 5 '' , as well as a primer layer applied during the pretreatment 6 '' , Between the primer layers 6 ' and 6 '' there is an adhesive layer 7 from a suitable adhesive, which the two structural elements 2 and 8th firmly together. Adhesive and primer are on the bonding of the aluminum alloys of the coating 4 and the second structural element 8th Voted.

The adhesive arrangement described above by way of example 1 solves the problem of producing a secure and cost effective adhesive bond between structural elements 2 made of titanium materials and structural elements 8th Made of aluminum materials characterized in that prior to bonding at least on the surface facing the bond 3 ie the first adhesive surface 3 a first structural element 2 a coating of a titanium material 4 is applied from aluminum material.

The application of a coating comprising an aluminum material 4 ' . 4 '' on a structural element 2 ' . 2 '' From a titanium material can basically according to a further embodiment according to 2 one-sided, or according to yet another embodiment according to 3 done on both sides. It is essential that the coating 4 ' . 4 '' before the bonding and before the pretreatment of the surfaces to be bonded together, for example, before the application of the primer layers 6 ' . 6 '' , is applied.

The Coating of workpieces, like from sheet metal Structural elements, it can be done by different methods. For example, it is possible that the coating of an aluminum alloy before rolling a sheet of titanium alloy is applied. hereby becomes the rolling process in view of the wear of the rolling rolls improved.

Furthermore allows the coating of structural elements made of titanium materials with aluminum or an aluminum alloy, the application of the same pre-treatment measures to prepare the adhesive bond for the structural elements Titanium materials as well as for the structural elements made of aluminum materials. It is therefore possible for those with the coating provided structural elements of titanium materials in the manufacturing step in which the adhesive bond is produced, same methods, such as surface cleaning, anodization and the like, as well as like substances, such as pretreatment baths, primers, Adhesives and the like to apply or use.

The construction of a lightweight structure 40 made of different structural elements made of different materials is in 4 exemplified. The structural elements are, for example, a Doppler 41 made of a titanium alloy, as well as an outer skin 42 from an aluminum alloy of a passenger plane. The Doppler 41 is on his both the outer skin 42 , as well as the bonding facing surface provided with a coating of an aluminum alloy. The aluminum alloy of the coating and the aluminum alloy of the outer skin 42 are preferably identical. This considerably simplifies the production of the adhesive bond.

An improvement in the properties of the adhesive joint to prevent crack propagation in individual components of the lightweight structure is due to a in 5 exemplified reinforcement of the adhesive layer 53 possible. In 5 was for the sake of clarity on the presentation of in 1 illustrated primer layers 6 ' . 6 '' and oxide layers 5 ' . 5 '' waived.

A structural element 50 Made of a titanium alloy with a coating 51 made of an aluminum alloy. The structural element 50 is at his with the coating 51 provided surface 55 by means of an adhesive layer 53 with a structural element 52 glued from an aluminum alloy. In the adhesive layer 53 are fibers 54 arranged. The fibers 54 are arranged in unidirectional direction parallel to each other. It is also conceivable that the fibers 54 are arranged bi- or polydirectionally, so that they intersect. The fibers can 54 arranged in a fabric structure be. The fibers 54 may be coated on their surface with a wetting agent, or they may be embedded in a plastic matrix.

The Method for producing a bonding arrangement between a first and a second structural element preferably runs as follows from: first a coating is preferably made of the material of the second Structural element or at least one of the material of the second Structural element-containing material on a predetermined surface of the first, with the structural element to be bonded structural element applied. This can especially before or during, but also after the manufacturing process of the first structural element. Then they are together to be bonded surfaces the structural elements pretreated together suitably. The pretreatment is aimed exclusively according to the materials of the adhesive surfaces to be bonded and not according to the materials the structural elements. After pretreatment, the first structural element becomes glued to the second structural element, wherein the coated surface of the first structural element is glued to the second structural element. The bonding is preferably carried out under vacuum in example an autoclave.

The described method is also suitable for the bonding of laminated Materials, such as fiber composite metal laminates, such as about GLARE. It is also conceivable to use the invention in conjunction with composites, in particular carbon fiber composite materials, referred to as composites, use. The pretreatment of the surfaces of the structural elements to be bonded is made by coating the surface to be bonded simplified first structural element of titanium materials, as for both structural elements uniform treatment and bonding methods and materials can be used.

The inventive method, as well as the adhesive arrangement according to the invention enable it, for example in the door and hatch area and riveted in the area of longitudinal seams To replace Doppler made of titanium by bonded titanium Doppler. The possibility a secure bonding allows also the use of glued tear stoppers in longitudinal or in the transverse direction of the fuselage or wing to prevent propagation potential Cracks in the aircraft structure. The possibility of producing a safe, cost-effective and easy to produce adhesive arrangement between structural elements made of aluminum alloy, such as stringers, clips, skin sheet and the like, and structural members of titanium alloys, such as for example Doppler, crack stopper, stiffening elements and the like, has many advantages.

The glued structure exhibits by reducing the number of possible Crack initiation sites better fatigue properties. Such Crack initiation sites are prevalent in conventionally prepared compounds the rivet holes. Thereby Is it possible, the level of permissible stresses in the structural components increase and corresponding to the weight of, for example, an aircraft structure reduce. A further weight reduction results from the saving of rivets that are no longer needed in an adhesive connection.

The Annealing of Dopplers made of titanium or titanium alloys is a very costly process. The rivets used for riveting The Doppler are mostly made of titanium and very expensive. The bonding process provides a cheaper joining process represents.

The Bonding of structural elements made of titanium alloys with structural elements aluminum alloy to a structural component of an aircraft structure, such as a shell can, together with the bonding of structural elements made of aluminum alloys with each other in one step. The time required for the production of the shell is thereby reduced very much, since so far in another, usually in another production hall taking place step of the subsequent riveting of structural elements Titanium alloys with the previously glued structural elements Made of aluminum alloys deleted. About that This also eliminates the transport costs between the production halls.

The Representation in the figures is not to scale. Especially Individual layer thicknesses are greatly exaggerated.

Even though the present invention with reference to preferred embodiments As described above, it is not limited thereto on diverse Modifiable way.

1

adhesive arrangement

2, 2 ', 2' '

structural element made of titanium alloy

3, 3 '

first adhesive surface

4, 4 ', 4' '

coating

5 ', 5' '

oxide

6 ', 6' '

primer layer

7

adhesive layer

8th

structural element made of aluminum alloy

9

second adhesive surface

40

lightweight structure

41

doubler made of titanium alloy

42

shell made of aluminum alloy

50

structural element made of titanium alloy

51

coating made of aluminum alloy

52

structural element made of aluminum alloy

53

layer

54

fiber

55

With Coated surface of the Structure element of titanium alloy

Claims (15)

Adhesive arrangement for bonding two structural elements, in particular an aircraft or spacecraft, comprising: a first structural element ( 2 ; 2 '; 2 ''; 50 ), which consists of a first material and at least a first adhesive surface ( 3 ; 3 '; 55 ) having; a second structural element ( 8th ; 52 ), which consists of a second material differing from the first material and at least one second adhesive surface ( 9 ) having; and an adhesive bond ( 7 ; 53 ) between the first adhesive surface ( 3 ; 3 '; 55 ) of the first structural element ( 2 ; 2 '; 2 ''; 50 ) and the second adhesive surface ( 9 ) of the second structural element ( 8th ; 52 ); characterized in that the first structural element ( 2 ; 2 ' . 2 ''; 50 ) one the second material of the second structural element ( 8th ; 52 ) having coating ( 4 ; 4 '; 4 ''; 51 ) at least on the first adhesive surface ( 3 ; 3 '; 55 ) having. Bonding arrangement according to claim 1, characterized in that the first structural element ( 2 ; 2 '; 2 ''; 50 ) has a high-strength material, in particular a titanium material or the like. Adhesive arrangement according to claim 1 or 2, characterized in that the first structural element ( 2 ; 2 '; 2 ''; 50 ) is formed as a stringer for forming a stiffening agent, as a Doppler or crack stopper for preventing cracking or crack propagation, or the like. Adhesive arrangement according to at least one of the preceding claims, characterized in that the coating ( 4 ; 4 '; 4 ''; 51 ) has at least a thickness of about 0.2 microns. Bonding arrangement according to at least one of the preceding claims, characterized in that the second structural element ( 8th ; 52 ) comprises an aluminum material, magnesium material, a monolithic or laminated material, a composite material and / or the like. Bonding arrangement according to at least one of the preceding claims, characterized in that the first structural element ( 2 ; 2 '; 2 ''; 50 ) and / or the second structural element ( 8th ; 52 ) are formed as structural elements of a lightweight structure of an aircraft. Adhesive arrangement according to at least one of the preceding claims, characterized in that the adhesive bond ( 7 ; 53 ) has a thickness of about 0.01 mm to 0.3 mm. Adhesive arrangement according to at least one of the preceding claims, characterized in that the adhesive bond ( 7 ; 53 ) Fiber and / or fiber-woven structures, wherein the fiber length, for example, at least 10 mm and the fiber diameter in about 0.001 mm to 0.3 mm. Method for producing a bonding of two structural elements, in particular of an aircraft or spacecraft, with the following method steps: - Provision of a first structural element ( 2 ; 2 '; 2 ''; 50 ) of a first material and with at least a first adhesive surface ( 3 ; 3 '; 55 ); Providing a second structural element ( 8th ; 52 ) of a second material differing from the first material and having at least one second adhesive surface ( 9 ); Applying a second material of the second structural element ( 8th ; 52 ) ( 4 ; 4 '; 4 ''; 51 ) at least on the first adhesive surface ( 3 ; 3 '; 55 ) of the first structural element ( 2 ; 2 '; 2 ''; 50 ); and - providing an adhesive bond ( 7 ; 53 ) between the on the first adhesive surface ( 3 ; 3 '; 55 ) of the first structural element ( 2 ; 2 '; 2 ''; 50 ) applied coating ( 4 ; 4 '; 4 ''; 51 ) and the second adhesive surface ( 9 ) of the second structural element ( 8th ; 52 ) for bonding the same with each other. Method according to claim 9, characterized in that the coating ( 4 ; 4 '; 4 ''; 51 ) by means of a plating process on the first adhesive surface ( 3 ; 3 '; 55 ) of the first structural element ( 2 . 2 '; 2 ''; 50 ) is applied. Method according to claim 9, characterized in that the coating ( 4 ; 4 '; 4 ''; 51 ) by means of a vapor deposition on the first adhesive surface ( 3 ; 3 '; 55 ) of the first structural element ( 2 ; 2 '; 2 ''; 50 ) is applied. Method according to at least one of claims 9 to 11, characterized in that the coating ( 4 ; 4 '; 4 ''; 51 ) during manufacture and / or prior to any rolling of the first structural element ( 2 ; 2 '; 2 ''; 50 ) on the first adhesive surface ( 3 ; 3 '; 55 ) of the first structural element ( 2 ; 2 '; 2 ''; 50 ) is applied. Method according to at least one of claims 9 to 12, characterized in that the coating ( 4 ; 4 '; 4 ''; 51 ) to the first structural element ( 2 ; 2 '; 2 ''; 50 ) is applied on one side or on both sides. Method according to at least one of claims 9 to 13, characterized in that the adhesive bond ( 7 ; 53 ) is formed to reinforce the same with integrated fibers and / or fibers woven structures, wherein the fibers preferably before or during the provision of the adhesive bond ( 7 ; 53 ) are involved in this. Method according to at least one of claims 9 to 14, characterized in that the first structural element ( 2 ; 2 '; 2 ''; 50 ) after application of the coating ( 4 ; 4 '; 4 ''; 51 ) and the second structural element ( 8th ; 52 ) for the provision of the adhesive bond ( 7 ; 53 ) by means of the same procedural steps or the same means, for example by means of a uniform surface cleaning, a uniform anodization, a uniform pre-treatment bath, a uniform primer, a uniform adhesive or the like.