Abstract:
This relates to a multi-part attachment device for attaching a device to a stiffening element and to an outer skin of a vehicle. The multi-part attachment device comprises a base body having an angular profile for attaching the attachment device to the stiffening element and to the outer skin of the vehicle. Furthermore, the multi-part attachment device comprises an upper part with a lug, wherein the upper part is attached to the base body. This also relates to a method for attaching a device to a stiffening element and to an outer skin of a vehicle as well as to an aircraft with a multi-part attachment device.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
       [0001]    This application claims priority to German Patent Application No. 10 2014 116 638.8, filed 13 Nov. 2014, which is incorporated herein by reference in its entirety. 
       TECHNICAL FIELD 
       [0002]    This relates to the fastening of components or devices in a vehicle. This relates to a multipart fastening device for fastening a device to a reinforcing element and to the outer skin of a vehicle. This further relates to a method for fastening a device to a reinforcing element and to the outer skin of a vehicle, as well as to an aircraft with a multipart fastening device for fastening a device to a reinforcing element and to the outer skin of a vehicle. 
       BACKGROUND 
       [0003]    Transport items or devices in airplanes are normally secured against slippage during airplane operation. Such fastening devices are often secured to frame structures or reinforcing elements, such as ribs or stringers. The transport objects or devices can be fastened to the fuselage structure of the airplane by means of these fastening devices. Because such a fastening device can be exposed to high loads, in particular during flight or various flying maneuvers, it may be fabricated out of a resistant material that meets the weight requirements. This may be important, in particular, in vehicles or aircraft. For example, such fastening devices are manufactured using blanks that were milled into a specific shape in the production process. Depending on the material, this process can be expensive and time-intensive. 
         [0004]    DE 10 2011 114 098 A1 shows a fastening device for fastening components to a fastening structure of a transport means. The fastening device exhibits a clamping device for introduction into an opening in the fastening structure, and an actuating device joined with the clamping device. 
         [0005]    DE 10 2011 085 450 A1 describes a linking arrangement for linking a component to a base part, wherein the connecting arrangement exhibits a fixing device for fixing the component and a connecting device for load transfer. 
       SUMMARY 
       [0006]    This relates to a multipart fastening device for fastening a device to a reinforcing element and to the outer skin of a vehicle. The multipart fastening device that is also referred to below simply as fastening device, exhibits a base body in the form of an angled profile for fastening the fastening device to the reinforcing element and to the outer skin of the vehicle. The multipart fastening device further exhibits a top element with an eyelet, wherein the top element is fastened to the base body. Thus, the top element may not be in direct contact with the outer skin of the vehicle. 
         [0007]    Such a multipart fastening device may make it possible to reduce the material outlay while manufacturing a fastening device. Instead of fabricating the fastening device out of a block or blank, for example via milling, manufacturing the multipart fastening device may make it possible to use base profiles adjusted to the respective parts of the fastening device in the production process already, for example an L-profile, to have the latter yield the final shape of the individual parts of the fastening device. This means that an already angled profile, e.g., an L-profile, can be used in manufacturing the base body, so as to mill the final shape of the base body out of the L-profile. For example, one cross section of the base body exhibits an angled profile that can differ from a cross section of an L-profile. As opposed to the L-profile, the angle between the two flanges or legs of the angled profile can differ from 90 degrees. For example, the top element with the eyelet can be fabricated in a separate production process, also via milling or forming. After the base body and top element have been fabricated, these two parts can be joined together and fastened to the reinforcing element and outer skin of the vehicle. Putting together these two parts, i.e., the base body and top element, makes it possible to significantly reduce the material used in manufacturing the fastening device by comparison to a method in which the fastening device along with the base body and top element are fabricated out of a single blank or block. In other words, the base body as well as the top element according to the embodiment are separately fabricated, wherein the production process utilizes blanks that are already basically similar to the final shape of the base body and top element already before the two parts are made. As a result, potentially less material must be removed during a milling process to obtain the final shape of the base body or top element. This will be explained in even greater detail in the description to the figures. Let it be noted that additional manufacturing methods other than milling are also possible. For example, forming processes may be used. 
         [0008]    The multipart fastening device is fastened to a partial piece of the outer skin of the vehicle, as well as to a reinforcing element of the vehicle. The reinforcing element can exhibit a ribbed shape, and be connected with the outer skin of the vehicle or fastened thereto. For example, the reinforcing element and/or outer skin of the vehicle can be made out of a fiber composite or a multilayer composite. In particular carbon fiber-reinforced plastic (CFK) is used for this purpose. However, the reinforcing element and/or the outer skin of the vehicle can also be fabricated out of other materials, for example metal alloys. At any rate, the fastening device is aligned in such a way inside the vehicle when in a fastened state as to be simultaneously fastened to the reinforcing element and outer skin of the vehicle. The device can here be fastened to the outer skin and reinforcing element by means of a fastener. The reinforcing element can also exhibit a profiled cross section. 
         [0009]    For example, the reinforcing element exhibits an S-shaped profile cross section. The profile cross section is here the cross section of the profile aligned transverse to a longitudinal direction of the profile. The longitudinal direction of an often bar-shaped profile thus runs perpendicular to the profile cross section. The base body exhibits an angled profile in its cross section. This means that the cross section of the base body exhibits two partial areas that are aligned at a specific angle relative to each other. These areas are referred to below as flanges. The top element can be positively and/or non-positively joined with the base body. For example, the top element is fastened to the base body by means of a fastener, so that the base body and top element contact each other by way of at least one, but preferably two, contact surfaces. The eyelet of the top element is ring-shaped. The eyelet exhibits an opening, in which a connecting element of the device to be fastened can be mounted. For example, such a device is a container or an electrical device, which is secured against slippage inside of the vehicle. In particular, the fastening device can be used to fasten a vacuum generator for wastewater tanks of the vehicle. To this end, the vacuum generator is fastened by means of a strut in the eyelet of the top element of the fastening device. The vehicle can be an aircraft, rail vehicle, or road vehicle. In particular, however, the vehicle is an airplane. 
         [0010]    In an embodiment, the base body is fastened to the reinforcing element and to the outer skin of the vehicle by means of a rivet joint. 
         [0011]    It may be possible for the base body to be joined with the reinforcing element via a first contact surface, and with the outer skin of the vehicle via a second contact surface. As many rivets as desired can be provided for fastening the base body to the reinforcing element. However, six rivet joints are preferably provided for fastening the base body to the reinforcing element. As many rivets as desired can also be provided for fastening the base body to the outer skin of the vehicle. However, six rivet joints are here preferably also provided for fastening the base body to the outer skin of the vehicle. The rivet joints can here be arranged side by side along a line in relation to the base body, wherein the line can be aligned perpendicular to the longitudinal axis of the vehicle with the fastening device in the fastened state. However, other joining processes can also be used as an alternative to a rivet joint, such as welding processes or soldering processes for fastening the base body to the reinforcing element or for fastening the base body to the outer skin of the vehicle. 
         [0012]    In another embodiment, the top element is fastened to the base body and, if necessary, also to the outer skin by means of a rivet joint. 
         [0013]    The top element may be fastened to the base body in such a way as not to produce any direct contact between the top element and outer skin of the vehicle. Likewise, the top element can be fastened to the base body in such a way that the top piece is not in direct contact with the reinforcing element. In other words, the top element can only be joined with the outer skin or reinforcing element via the base body. The top element can here be fastened to the base body by means of as many rivet joints as desired. However, four rivet joints or six rivet joints are preferably provided for fastening the top element to the base body. The rivet joints or the rivets that join the top element with the base body, i.e., fasten it to the base body, can penetrate through the base body, so that the rivets that fasten the top element to the base body simultaneously also fasten the entire fastening device, which encompasses the top element and base body, to the outer skin or reinforcing element. 
         [0014]    In another embodiment, the reinforcing structure is selected from the group comprised of ribs, stringers and frame structure. 
         [0015]    For example, this can be a rib or stringer inside of an airplane fuselage. The reinforcing element can exhibit a profiled cross section. However, such a fastening device can also be fastened to other structural components of the vehicle or airplane. For example, such structural components can be support structures arranged inside the fuselage of the vehicle or airplane and/or fastened to the outer skin of the vehicle or airplane. 
         [0016]    In another embodiment, the angled profile exhibits a first plate-shaped partial area and a second plate-shaped partial area. The two plate-shaped partial areas can be inclined relative to each other at an obtuse angle. 
         [0017]    Plate-shaped here means that the lateral expansions of the partial area of the base body exceed its thickness. For example, the first plate-shaped partial area exhibits a surface that forms the contact surface with the reinforcing element when the base body is fastened to the reinforcing element. Similarly to the above, the second plate-shaped partial area can exhibit a surface that is in contact with the outer skin of the vehicle when the base body is fastened to the outer skin. The second plate-shaped partial area can here also exhibit a curved contour, thereby giving rise to a shell-shaped partial area of the base body at this location, which is in contact with the outer skin of the vehicle. The shell-shaped partial area of the base body can thus emulate the contour or progression of a fuselage section. This means that the second shell-shaped partial area is curved, so that the latter runs along the inner contour of the outer skin of the vehicle or airplane. The surface of the second plate-shaped or second shell-shaped partial area can be provided with a bulge, which engages into a recess of the outer skin or establishes a positive contact with the latter when the base body is fastened to the outer skin by means of rivet joints. If the base body is fastened to the reinforcing element, the first plate-shaped partial area can be aligned essentially perpendicular to the longitudinal direction of the vehicle or airplane. For example, this is the case when the first plate-shaped partial area is fastened to a rib of an airplane by means of rivet joints. 
         [0018]    In another embodiment, the angle between the two plate-shaped partial areas measures between 90° and 110°. 
         [0019]    The first plate-shaped partial area can exhibit a transition to the second plate-shaped or shell-shaped partial area with an inner radius. The radius can be incorporated by the process used in manufacturing the base body, for example milling. The angled profile of the base body allows the latter to be fastened to both the reinforcing element and outer skin of the vehicle when in a fastened state. 
         [0020]    In another embodiment, the base body consists of a first material, and the top element consists of a second material that differs from the first material. 
         [0021]    For example, the first material or material of the base body is a titanium alloy. For example, such an alloy is the Ti6Al-4V titanium alloy. Using an aluminum alloy for the top element makes it possible to save on weight, wherein a sufficient stability for fastening the device to the reinforcing element or outer skin can also be achieved. However, let it be noted that any other alloys or materials desired can be used for the top element or base body. The base body and top element can be fabricated out of different materials, since the fastening device consists of multiple parts, and is not made out of a single blank. 
         [0022]    Another aspect of the embodiment indicates a method for fastening a device to a reinforcing element and to the outer skin of a vehicle. In one step of the method, a base body with an angled profile is fabricated out of a blank having an L-shaped profile. For example, the base body is milled out of the blank. In another step of the method, a multipart fastening device is fastened to the reinforcing element and outer skin of the vehicle by way of the base body. This means that the fastening device encompasses the base body with which the fastening device is fastened to the reinforcing element and outer skin of the vehicle. In another step of the method, a top element with an eyelet is fastened to the base body. The eyelet here exhibits an opening, whose axis comes to lie essentially perpendicular to a longitudinal axis of the vehicle if the fastening device is fastened to the reinforcing element and outer skin. Rivet joints can be used to fasten the multipart fastening device to the reinforcing element and outer skin of the vehicle and/or to fasten the top element to the base body. 
         [0023]    In an embodiment, the fastening device is fastened to the reinforcing element and outer skin of the vehicle while fastening the top element to the base body. This makes it possible to fasten the top element to both the base body and the reinforcing element or outer skin within a single assembly step. For example, those rivet joints that join the top element with the base body are simultaneously also used to join the base body with the reinforcing element or outer skin of the vehicle. To this end, the rivets of the rivet joints of the top element can penetrate the base body and protrude into the reinforcing element or outer skin of the vehicle. 
         [0024]    Another aspect indicates an aircraft with a multipart fastening device for fastening a device to a reinforcing element and the outer skin of a vehicle, wherein the multipart fastening device exhibits the features described above. 
         [0025]    For example, the fastening device is joined or fastened to a fuselage shell or outer skin of the aircraft, and with a reinforcing element, e.g., a rib or stringer, of the aircraft. 
         [0026]    In addition, other objects, desirable features and characteristics will become apparent from the subsequent summary and detailed description, and the appended claims, taken in conjunction with the accompanying drawings and this background. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0027]    The various embodiments will hereinafter be described in conjunction with the following drawing figures, wherein like numerals denote like elements, and: 
           [0028]      FIG. 1  shows a one-part fastening device for fastening a device to a reinforcing element and to the outer skin of a vehicle according to an exemplary embodiment. 
           [0029]      FIG. 2  shows a cross sectional view of an L-profile as well as of a base body of a fastening device for fastening a device to a reinforcing element and to the outer skin of a vehicle according to an exemplary embodiment. 
           [0030]      FIG. 3  shows a multipart fastening device for fastening a device to a reinforcing element and to the outer skin of a vehicle according to an exemplary embodiment. 
           [0031]      FIG. 4  shows a multipart fastening device for fastening a device to a reinforcing element and to the outer skin of a vehicle according to another exemplary embodiment. 
           [0032]      FIG. 5  shows a flowchart for a method for fastening a device to a reinforcing element and to the outer skin of a vehicle according to an exemplary embodiment. 
       
    
    
     DETAILED DESCRIPTION 
       [0033]    The following detailed description is merely exemplary in nature and is not intended to limit the disclosed embodiments or the application and uses thereof. Furthermore, there is no intention to be bound by any theory presented in the preceding background detailed description. 
         [0034]      FIG. 1  shows a one-part fastening device  10 , which was made out of a block or blank via milling. The one-part fastening device  10  exhibits a first plate-shaped partial area  19  as well as a second plate-shaped partial area  18 . The second plate-shaped partial area can also be a shell-shaped partial area  18 , whose contour is adjusted to the shape of the outer skin  13  of an airplane fuselage. For example, the shell-shaped partial area  18  of the one-part fastening device  10  is curved or bent along a transverse direction  16 . The one-part fastening device  10  exhibits an eyelet  14 , wherein the eyelet  14  is designed in the form of a passage opening in the transverse direction  16 . As a consequence, the transverse direction  16  can essentially be parallel to a drilling axis of the eyelet  14 . In the state depicted on  FIG. 1 , the fastening device  10  is made to contact the outer skin  13  of the vehicle or airplane by means of a contact surface or surface of the shell-shaped element  18 . The fastening device  10  is further joined with the outer skin  13  of the airplane by way of rivet joints  17 . The fastening device  10  is here fastened to the outer skin  13  of the airplane by a total of six rivets  17 . The first plate-shaped partial area  19  as well as the shell-shaped partial area  18  are angled relative to each other. For example, both areas are arranged at an obtuse angle relative to each other. Further provided is a web, which joins the two angled areas together, and is provided with the eyelet  14 . In terms of the transverse direction  16 , this web, and hence the eyelet  14 , is centrally secured to the fastening device  10 . The transverse direction  16  is here essentially perpendicular to the flight direction of the airplane or to a longitudinal axis  29  of the airplane. The first plate-shaped partial area  19  extends essentially parallel to a vertical direction  28 , which is perpendicularly aligned relative to the transverse direction  16  and longitudinal direction  29 . As a consequence, the vertical direction  28  is essentially parallel to a contact surface between the first plate-shaped partial area  19  and a reinforcing element  12  of the airplane. For example, such a reinforcing element  12  is a rib or stringer of the airplane. In the state depicted on  FIG. 1 , the fastening device  10  is not joined or fastened to reinforcing element  12  for reasons of clarity. In a fastened state, however, the fastening device  10  is in contact both with the outer skin  13  of the airplane and the reinforcing element  12  of the airplane, and here fastened by means of rivet joints  17  to the outer skin  13  and reinforcing element  12 . For example, six rivets  17  are also provided for the first plate-shaped partial area  19 , and fasten the fastening device  10  to the reinforcing element  12 . The contact surface between the first partial area  19  and the reinforcing element  12  is here a flat surface, for example. This flat surface is stretched by the transverse direction  16  and by the vertical direction  28 , for example. The shell-shaped partial area  18  of the fastening device  10  exhibits a bulge  15  or projection, for example, which engages into a recess in the outer skin  13  when the fastening device  10  is fastened to the reinforcing element  12  as well as to the outer skin  13  of the airplane. For example, in the fastened state, this bulge  15  projects into the outer skin  13  of the airplane, essentially parallel to the vertical direction  28 . The bulge  15  is centrally arranged on the fastening device  10  in relation to the transverse axis  16 , and is located in the area of the web and/or eyelet  14  of the fastening device  10 . The diameter of the eyelet  14 , which is circular in shape, measures between 15 and 20 mm. The diameter of the eyelet preferably measures between 16 and 17 mm. The eyelet  14  is designed as a hole drilled through the web in the transverse direction. 
         [0035]      FIG. 2  shows a blank  20  or block from which a base body of a multipart fastening device is fabricated. For example, the blank  20  is a profile with an L-shaped cross section, from which a base body  21  of a multipart fastening device is fabricated. For example, the base body  21  of the multipart fastening device is milled out of the L-shaped profile. The base body  21  is shown with a dashed line on  FIG. 2 . The L-profile exhibits a first expansion  27   a  in the vertical direction  28 , wherein the first expansion  27   a  can simultaneously also be the maximum expansion of the base body  21  in the vertical direction  28 . For example, the first expansion  27   a  measures 90.5 mm. The L-profile exhibits a second expansion  27   b,  also in the vertical direction. For example, this second expansion  27   b  measures 15.5 mm. In the longitudinal direction  29 , the L-profile exhibits a third expansion  27   c,  for example measuring 43 mm. A fourth expansion  27   d,  also in the longitudinal direction  29 , measures 9.5 mm. The first expansion  27   a  and third expansion  27   c  are here each length measures of flanges or legs of the L-profile. The second expansion  27   b  as well as the fourth expansion  27   d  here each represent thickness measures of the two flanges or legs of the L-profile. The maximum expansion of the base body  21  in the longitudinal direction  29  can be described by the third expansion  27   c . As depicted on  FIG. 2 , the base body  21  fabricated out of the L-profile exhibits a similar cross sectional contour as the L-profile. As a result, the material removed while milling, i.e., while manufacturing the base body  21  out of the L-profile, can be significantly reduced. The base body  21  exhibits an angled profile similar to the L-profile. However, instead of a right angle, an obtuse angle  26  is provided for the L-profile between a first plate-shaped partial area  23  and a second plate-shaped partial area  24  after manufacture. However, this can also be an acute or right angle. For example, the obtuse angle  26  measures between 90° and 110°. In addition, a radius  25  is provided in the area of the transition between the first plate-shaped partial area  21  and the second plate-shaped partial area  24 . The second plate-shaped partial area  24  can be a shell-shaped element, which is curved in the transverse direction  16  of the base body  21 , i.e., in the viewing direction on  FIG. 2 , and thus adjusted to the outer skin  13  of the airplane fuselage. However, this curvature is not visible on  FIG. 2 , since only a cross section of the L-profile or base body  21  of the multipart fastening device is shown. 
         [0036]      FIG. 3  shows a multipart fastening device  30 , which can be fastened to a reinforcing element  12  and to the outer skin  13  of an airplane. In the state depicted on  FIG. 3 , the multipart fastening device  30  is fastened to the outer skin  13  of the airplane, but not to the reinforcing element  12 . However, this only serves to clarify the illustration, so that with the fastening device  30  in the fastened state, it is joined both with the reinforcing element  12  and the outer skin  13 , for example via rivet joints  17 . The multipart fastening device  30  exhibits a base body  21  and a top element  31 . The top element  31  can be fastened to the base body  21  by means of four rivets  17   a . The base body  21  can in turn be fastened to the reinforcing element  12  as well as to the outer skin  13  of the airplane with additional rivets  17 . For example, the reinforcing element is a rib or stringer of the airplane. In the case illustrated here, the reinforcing element  12  is a rib of the airplane. The base body  21  exhibits a first plate-shaped partial area  23  and a shell-shaped partial area  24 , wherein the two areas  23 ,  24  are angled relative to each other. For example, the first plate-shaped partial area  23  and shell-formed partial area  24  are arranged relative to each other at an angle of between 90 and 110°. However, an acute angle or right angle can also be provided. The shell-shaped partial area  24  can be adjusted to the contour or outer skin  13  of the airplane fuselage in one circumferential direction of the latter, thereby resulting in a curvature of the shell-shaped partial area  24  in the circumferential direction of the airplane fuselage. The circumferential direction is here aligned perpendicular to the longitudinal direction  29 . The longitudinal direction  29  is essentially parallel to the longitudinal direction of the airplane fuselage. The plate-shaped partial area  23  at least partially exhibits a thickness of 2.5 mm. The shell-shaped partial area  24  also at least partially exhibits a thickness of 2.5 mm. However, the shell-shaped partial area  24  has a bulge  15  in an area of the base body  21  in which the top element  31  is fastened to the base body  21 . The bulge  15  or projection represents a thickening of the shell-shaped element  24 , which protrudes into the outer skin  13  essentially parallel to the vertical axis  28 . The thickness of the shell-shaped element  24  is greater than 3 mm at this location, for example. The base body  21  can be fabricated out of a titanium alloy, wherein the top element is fabricated out of an aluminum alloy. The top element exhibits a third plate-shaped partial area  33  along with a fourth plate-shaped partial area  32 . The third plate-shaped partial area  33  of the top element  31  is here directly joined with the first plate-shaped partial area  23  of the base body  21  by way of a contact surface. Analogously, the fourth plate-shaped partial area  32  of the top element  31  is directly joined with the base body  21  by way of a contact surface. Two respective rivets  17   a  here penetrate through the third plate-shaped partial area  33  along with the fourth plate-shaped partial area  32  of the top element  31 , and fasten the top element  31  to the base body  21 . The top element  31  exhibits an eyelet  14 , which is circular in shape, and has an opening with a central axis that is essentially parallel to the transverse direction  16 . The eyelet  14  is joined with the plate-shaped partial areas  33 ,  34  of the top element  31  by means of a web  34 . This web  34  extends in a circumferential direction around the eyelet  14 , at least partially around the latter. In the multipart fastening devices  30  shown on  FIG. 3 , a total of  14  rivet joints serve to fasten the multipart fastening device  30  to the reinforcing element  12  and to the outer skin  13  of the airplane. Any number of rivet joints desired can be used, however. The rivets  17   a  fasten the top element  31  to the base body  21  and to the reinforcing element  12 , as well as to the outer skin  13 , so that the rivets  17   a  can respectively penetrate through the base body  21 . The eyelet  14  is used to fasten a device, such as a vacuum generator for wastewater tanks, or some other component to the airplane structure. The diameter of the eyelet  14 , which is circular in shape, measures between 15 and 20 mm. The diameter of the eyelet preferably measures between 16 and 17 mm. The eyelet  14  is designed as a hole drilled through the web in the transverse direction. The fourth plate-shaped partial area  32  of the top element  31  can also be shell-shaped in design, so that the contour of this area  32  of the top element  31  adjusts to the contour of the shell-shaped partial area  24  of the base body  21 . The multipart fastening device  30  makes it possible to save on material during the manufacture of the base body  21  and top element  31 , since the top element  31  and base body  21  can be fabricated in separate production processes. This also enables a cost reduction and a reduction in fabrication time by comparison to manufacturing a one-part fastening device of the kind depicted on  FIG. 1 . 
         [0037]      FIG. 4  presents another example of a multipart fastening device  30 , which is fastened to a reinforcing element  12  as well as to the outer skin  13  of an airplane. As opposed to the multipart fastening device  30  shown on  FIG. 3 , the top element  31  exhibits a third plate-shaped partial area  33 , which in relation to the vertical direction  28  extends at least over half the expansion of the first plate-shaped area  23  of the base body  21  in a vertical direction  28 . The web  34  of the top element  31  here extends perpendicular to the transverse direction  16  along the entire third plate-shaped partial area  33  and the entire fourth plate-shaped partial area  32  of the top element  31 . The web  34  here protrudes perpendicularly out of a surface of the third plate-shaped partial area  33  and the fourth plate-shaped partial area  32 . In the example shown, the top element  31  is further fastened by means of a total of six rivets to the base body  21  and/or to the reinforcing element  12  as well as the outer skin  13  of the airplane. For example, four rivets  17   a  here penetrate through the first plate-shaped partial area  23  of the base body  21  and/or through the third plate-shaped partial area  33  of the top element  31 , and thereby create the attachment to the reinforcing element  12 . By contrast, for example, two rivets  17   a  penetrate through the second plate-shaped or shell-shaped partial area  24  of the base body  21  and/or the fourth plate- or shell-shaped partial area  32  of the top element  31 , and thereby fasten the top element  31  and base body  21  to the outer skin  13 . The web  34  divides the third plate-shaped partial area  33  of the top element  31  into two halves, so that two respective rivets  17   a  are provided on each of the two halves. Viewed in the transverse direction  16 , the web  34  is in the middle of the top element  31  and/or in the middle of the base body  21 . 
         [0038]      FIG. 5  presents a flowchart depicting a method for fastening a device to a reinforcing element  12  and to the outer skin  13  of a vehicle. For example, the device is a vacuum generator of a wastewater tank or some other hydraulic device. For example, the vehicle is an aircraft. In particular, the vehicle is an airplane. In step S 1  of the method, a base body  21  with an angled profile is fabricated out of a blank  20  with an L-shaped profile. In step S 2  of the method, a multipart fastening device  30  is fastened to a reinforcing element  12  and to the outer skin  13  of the vehicle by way of the base body  21 . In a further step S 3 , a top element  31  with an eyelet  14  is fastened to the base body  21 . The method can consist of additional steps. In particular, a further step involves fastening the device by way of a rod-shaped component in the eyelet  14  of the top element  31 . The device can here be hinged in the eyelet  14  via the rod-shaped component. Let it be noted that the base body  21  can be fastened to the reinforcing element  12  and to the outer skin  13  at the same time the top element  31  is fastened to the base body  21 . 
         [0039]    In addition, let it be noted that “encompassing”, “comprising” and “exhibiting” do not preclude any other elements or steps, and that “a” or “an” do not rule out a plurality. Let it further be noted that features or steps described with reference to one of the above exemplary embodiments can also be used in combination with other features or steps in other exemplary embodiments described above. Reference numbers in the claims are not to be construed as limitations. Let it be noted as well that the procedural steps of the described method can be performed in any sequence. Additionally, it is possible to perform several procedural steps simultaneously. 
         [0040]    While at least one exemplary embodiment has been presented in the foregoing detailed description, it should be appreciated that a vast number of variations exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and are not intended to limit the scope, applicability, or configuration of the embodiment in any way. Rather, the foregoing detailed description will provide those skilled in the art with a convenient road map for implementing an exemplary embodiment, it being understood that various changes may be made in the function and arrangement of elements described in an exemplary embodiment without departing from the scope of the embodiment as set forth in the appended claims and their legal equivalents.