Device, in particular connection rod, for bracing a fuselage structure of an aircraft and/or for fastening a component

(54) Title: DEVICE, IN PARTICULAR CONNECTION ROD, TO ENGLISH AN AIRCRAFT FUSELING STRUCTURE AND / OR TO FIX A COMPONENT (30) Unionist Priority: 03/09/2007 of 10 2007 011 621.9, 22/01 / 2007 US 60 / 881,640 (73) Holder (s): Airbus Deutschland Gmbh (72) Inventor (s): Hermann Benthien (74) Attorney (s): Dannemann, Siemsen, Bigler & Ipanema Moreira (86) International Request: pct EP2008050292 de 11/01/2008 (87) International Publication: wo 2008 / 090039de 31/07/2008 (57) Abstract: device, in particular CONNECTION rod, TO ENGLISH A FUSELING STRUCTURE OF AN AIRCRAFT AND / OR TO FIX A COMPONENT. The present invention relates to a device (18, 61), in particular a connecting rod (1, 19) to encompass a fuselage structure (9, 10, 27, 28, 45, 74) and / or components fixing to the fuselage structure (9, 10, 27, 28, 45, 74). In one embodiment, the joints (29, 30, 53) are integrated into the fuselage structure (9, 10, 27, 28, 45) to connect on both sides the connecting rod (1, 19) to the fuselage structure ( 9, 10, 27, 28, 45). As a result of the integration of the joints (29, 30, 53), a reduced number of individual parts is produced in comparison with the previously known modalities, which leads to weight reduction, reduced maintenance and improved reliability against failure. Furthermore, the device (18, 61), according to the invention allows the introduction of forces in the region of the neutral fibers (43, 44) of the fuselage structure (9, 10, 27, 28, 45, 74). An additional device configuration (61) provides only a single-component hinged connection (65) to the fuselage structure (74) via (first) end part (63). The second end part (64) is screwed to the fuselage structure (74). For this purpose, both end parts are provided with a thread at least in sections.

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ΡΙ0806723 -6

Invention Patent Descriptive Report for DEVICE, IN PARTICULAR CONNECTION ROD, TO ENGLISH A

FUSELING STRUCTURE OF AN AIRCRAFT AND / OR TO FIX

A COMPONENT.

The present invention relates to a device, in particular a connecting rod (also known as a Samer rod or a Samer rod), for enclosing an aircraft fuselage structure and / or for attaching a component to the fuselage structure comprising a central part and two end parts that are adjacent to it.

The known modalities of connecting rods generally have a cylindrical and hollow central part joined on both sides by end parts. The diameter of the central part can correspond to the diameter of both end parts. Alternatively, the central part can taper towards the end parts. Screws can be threaded preferably on both sides into the end parts in order to achieve the length adjustment. The connecting rods are used, for example, to attach components to the fuselage structure or to enclose or reinforce it. In order to connect the connecting rod to the aircraft structure, a fastener or a fork support is usually riveted to the structure. The fastener has a hole in which a screw can be fixed to perform the articulated coupling of one of the two screws of the connecting rod. A connecting rod created in this way is adjustable in terms of length and can additionally be pivoted around a geometric axis. An ability to articulate around an additional geometry axis is not possible with this assembly concept.

This mechanical connection of the known connecting rods to the fuselage structure presents, in particular, the disadvantage that a plurality of individual parts are necessary and, in addition, rivet connections must be positioned in the fuselage structure for fixing the fasteners. As a result, the weight, on the one hand, and the manufacturing cost, on the other, of such a reinforcement or retention arrangement by means of a connecting rod increases significantly.

The aim of the invention is to create a device that allows for the merging of the fuselage structure and / or a connection of components to the fuselage structure while, at the same time, reducing the number of individual parts needed, and in which at least one articulation capacity on one side and in addition the option of a charge introduction in the region of neutral fibers is possible.

This objective is achieved by a device with the characteristics of patent claim 1.

As a result of the fact that a joint is arranged in the region of at least one end part, the joint being integrated into the fuselage structure or component and being articulated around at least one geometric axis of rotation, a smaller number of individual parts , and in this way, a reduced weight is produced in comparison with previously known connection concepts, in which, however, the ability to articulate around at least one geometric axis is provided.

In addition, the introduction of force occurs preferably in the region of the neutral fibers of the fuselage structure so that the leverage effect that occurs with the previously known modality of the connecting rod device with fasteners or fork-type supports in the case of the introduction of form is be avoided.

An advantageous configuration provides that the at least one joint is embodied as a cylindrical nut that is hingedly received in a support hole in the fuselage structure to integrally connect the connecting rod device to the fuselage structure.

This results in a particularly simple design structure of the device according to the invention in an aircraft fuselage structure that is sufficient with a minimum number of components and that simultaneously allows for a pivotability around at least one geometric axis in the space.

According to a further development of the invention, it is provided that a through hole is positioned in the fuselage structure with an excessive size in relation to the threaded rods.

As a result, sufficient mobility is guaranteed, that is, in particular, the ability to articulate the threaded rod threaded into the barrel-type door around a geometric axis in space.

According to another further development of the invention, the fuselage structure has a thickening in the region of the support hole.

Thickening is necessary to achieve a seat for the cylindrical nuts that are received in the support hole that can withstand sufficient mechanical loads.

It is additionally provided that, in addition, an inner cylindrical nut is hingedly received in the outer cylindrical nut. This configuration allows the ability of the device according to the invention to articulate around an additional geometric axis in space.

According to an additional advantageous configuration, it is provided that the end parts adjacent to the central part on both sides are respectively supplied with a thread.

As a result, a simplified structure of the device is produced, where the central part and the end parts adjacent to it on both sides are preferably embodied in one piece and solidly like threaded screws. This configuration is particularly suitable for fixing components, in particular vertical supports of a liner structure on the aircraft's fuselage structure. The lining structure is used to suspend material seats on an aircraft for military applications.

The forces that occur are introduced by the device preferably in the region of the neutral fibers of the component. The susceptibility to volume formation of a linear component in relation to vertical loads is reduced by the articulated connection of the component at the fixation point.

As a result, the relevant component can be scaled to be statically lighter and thus save weight.

Additional advantageous device configurations are explained in the additional patent claims.

Figure 1 illustrates an illustrative embodiment of a previously known connecting rod;

Figure 2 shows a first embodiment of the device according to the invention;

Figures 3 and 4 show a simplified main view of a second embodiment of the device according to the invention;

Figures 5 to 7 illustrate detailed views of the second modality variant;

Figures 9 and 10 illustrate a further variation of the device for the articulated connection of one side of the components to the fuselage structure.

The same design elements have the same numerical references in the drawings respectively.

Figure 1 illustrates a device formed with a conventional connecting rod to enclose or secure the components to a fuselage structure.

A connecting rod 1 comprises, among other things, a central part 2 and two end parts 3, 4. A eye bolt 5, 6 is screwed respectively into both end parts 3, 4. The eye bolts 5 , 6 are secured with nuts 7, 8. The connection rod 1 to the fuselage structure 9, 10 is connected with two fasteners 11, 12 that are riveted to the fuselage structure 9, 10 by means of rivets that are not illustrated in greater detail. The articulated connection between the eye bolts 5, 6 and the fasteners 11, 12 is made by two screw connections 13, 14. As a result of the eye bolts 5, 6 that can be screwed into the end parts 3, 4, a length adjustment capability of the connecting rod 1 is produced in parallel to the longitudinal axis 15. As a result of the screw connections 13, 14, an ability to articulate the connecting rod 1 with respect to the fasteners 11, 12 around a geometric axis is respectively provided, as indicated by both double arrows 16, 17.

Figure 2 illustrates a first embodiment of the device according to the invention.

A device 18 is embodied as a short connecting rod 19 which has a constant cross section for weight reduction compared to the conventional connecting rod described above. The connecting rod 19 comprises, among other things, a central part 20 which is adjacent on both sides by the end parts 21, 22. The central part 20 is embodied in the form of a tube and is provided on both sides with a internal thread. The internal threads in the end parts 21, 22 can be substantiated in the opposite direction or in the same direction (left and / or right thread). The internal threads in the end parts 21, 22 are preferably embodied in the opposite direction so that a length adjustment of the connecting rod 19 can occur by simply rotating the central part 20 around its longitudinal geometric axis. The central part 20 can have flat sections, grooves, sheared areas or the like in order to facilitate the rotation of the central part 20 by means of a tool substantially corresponding to the length adjustment. Threaded rods 23, 24 can be screwed into end parts 21, 22 respectively. Threaded rods 23, 24 are secured with nuts 25, 26 to end parts 21, 22 against unintentional detachment. Alternatively, the central part 20 can also have an external thread in which, in this case, the threaded rods substantially cylindrically hollow with an internal thread can be screwed. In addition, the end parts 21, 11 can be substantially conical (as shown in figure 1). The end parts 21, 22 and the central part 20 can be substantially cylindrically hollow and / or at least solid sections. It is vital that the threaded rods 23, 24 can be screwed a sufficient distance into the end parts 21, 22 to carry out the length adjustment.

A gasket 29, 30 is integrated into a fuselage structure 27, 28 respectively. The fuselage structure 27, 28 can, for example, be an integral structure, a structure or an annular structure. The joints 29, 30 are formed with two cylindrical nuts 31, 32 which are hinged respectively in a support hole 33, 34 within the fuselage structure 27, 28. The cylindrical nuts 31, 32 are received in support holes 33, 34 articulated around both geometric axes of rotation 35, 36 (respectively perpendicular to the drawing plane), as indicated by both double arrows 37, 38. In the view of figure 2, the cylindrical nuts 31, 32 respectively have a threaded hole which is not illustrated in greater detail for a better overview in the drawing and within which the threaded rods 23, 24 can be screwed.

In order to receive the cylindrical nuts 31, 32, the fuselage structure 27, 28 has a thickening 39, 40 respectively in the region of the support holes 33, 34. The through holes 41, 42 are respectively arranged in the fuselage structure 27, 28, through holes 41, 42 being used to pass through both threaded rods 23, 24. Through holes 41, 42 are oversized with respect to threaded rods 23, 24, that is, a diameter of through holes 41, 42 is respectively selected to be greater than a diameter of threaded rods 23, 24 to in order to guarantee a sufficient articulation capacity of both threaded rods 23, 24. The introduction of force by means of both cylindrical nuts 31, 32 occurs preferably in the region of neutral fibers 43, 43 within the fuselage structure 27, 28. As a result, the occurrence of local load spikes in the fuselage structure 27 , 28 is reduced compared to the previous technique as a result of the leverage of the fasteners 11,12 (as shown in figure 1).

As a result of the cylindrical nuts 31, 32 integrally arranged in the fuselage structure 27, 28, the fasteners 11, 12 (fork brackets), the eye bolts 5, 6 and the associated screw connections that are generally formed respectively with a screw and a screw nut are no longer needed to connect connecting rod 19 to the fuselage structure 27, 28. As a result, significant weight savings are produced along with simultaneously increased reliability against failure of the entire device 18 due to the reduced number of components.

Figures 3 and 4 to which reference is made simultaneously in the next part of the specification, illustrate a simplified view (one side) of a second modality variant of the device according to the invention. Figure 3 shows a top view and Figure 4 shows a side view of the second modality variant. The geometric axes x, y and z of a coordinate system symbolize orientation in space.

In contrast to the view according to figure 2, the views only show one side of the fuselage structure and a joint disposed therein with a screwed threaded rod. The connecting rod and the right part of the device including the right fuselage structure have been omitted in figures 3, 4 respectively to allow a more clear view. The aforementioned sets are embodied in a mirrored symmetric way with respect to the illustrated parts. In contrast to the modality variant according to figure 2, the biaxial barrel-type joint used in figures 3 and 4 allows the articulation of the threaded rod or respectively the connecting rod connected to it around the two rotating geometric axes in space.

An external cylindrical nut 47 which is rotatable about the geometric axis z is embedded in a fuselage structure 45 in a support hole 46. The fixation of the external cylindrical nut 47 against axial displacement parallel to the geometric axis z is performed, for example , with a flange 48 and a retaining ring 49 arranged in a groove that is not designated. In order to be able to receive the outer cylindrical nut 47, the fuselage structure 45 has a thickening 50 in the region of the support hole 46. A smaller inner cylindrical nut 51 is rotatably received in an additional hole 52 in the cylindrical nut external 47. The internal cylindrical nut 51 is rotatable about the geometric axis x, that is, the rotating geometric axes (geometry axis z and geometric axis x) of the cylindrical nut (external) 47 and the internal cylindrical nut 51 contain an angle of 90 and together form a joint (cardan) 53 or a so-called biaxial barrel joint that has two degrees of freedom. In order to connect the connecting rod not shown in figures 3 and 4, the inner cylindrical nut 51 has a threaded hole which is not provided with a numerical reference and into which a threaded rod 54 can be screwed. In order to ensure a sufficient articulating capacity of the threaded rod 54 and thus of a thread, a through hole 55 whose diameter is sufficiently large in comparison to a diameter of the threaded rod 54 is positioned in the fuselage structure 45 .

In comparison to the variation of the modality according to figure 2, the variant of the modality according to figures 3, 4 offers greater mobility of the connecting rod in relation to the fuselage structure 45 around two geometric axes of rotation 56 , 57 (x-axis, z-axis, 2 degrees of freedom) in space as indicated by the double arrows 58, 59 over only a slightly increased number of necessary components.

An additional hole 60 is positioned in the cylindrical (outer) nut 47 to ensure sufficient mobility of the threaded rod 54. The hole 60 is designed with an excessively suitable size with respect to its diameter in relation to the diameter of the threaded rod 54.

The fuselage structure 9, 10, 27, 28, 45 is preferably formed with an aluminum alloy material. All cylindrical nuts 31, 32, 47, 51 can be supplied with a friction reduction layer, such as, for example, a layer of teflon® as a permanent lubricant. Alternatively, the cylindrical nuts 31, 32, 47, 51 can also be fully formed with a friction reducing material that is suitable with respect to the aluminum alloy material of the sealing structure 9, 10, 27, 28, 45, such as, for example, bronze or other heavy non-ferrous metals.

Figures 5 to 7, to which reference is made in parallel below, illustrates a detailed internal view of the gasket used (cardan) 53 (according to figures 3 and 4) from several views. The three spatial directions are illustrated by the geometric axes x, y and z of a coordinate system. The inner cylindrical nut 51 is received in a rotating manner in the outer cylindrical nut 47 and forms, in interaction with the outer cylindrical nut 47, the joint 53 or the cardan joint that allows the mobility of the device according to the invention around two rotating geometric axes .

The orifice 60 positioned excessively in the outer cylindrical nut 47. As is particularly apparent from figure 7, the orifice 60 has an oval transverse geometry in order to achieve sufficient mobility of the threaded rod (joint mobility 53). Other transverse geometries such as, for example, circular or elliptical are also possible.

Figures 8 to 10 illustrate an additional modality of variation of the device which is particularly intended for the attachment of vertical stringer of a lining structure to the fuselage structure of an aircraft. In contrast to the modality variations described above, only a single-sided hinge connection is produced with this device. The position of the device in space is illustrated by means of the geometric axes x, y and z that form a coordinate system.

Figure 8 shows a cross-sectional view through a device

61.

Figure 9 illustrates the same device 61, but in a view that is articulated by 90 around the geometric axis y so that the reference can also be made below for both figures 8 and 9.

Device 61 comprises, among other things, a central part substantially cylindrically hollow or substantially cylindrical 62 that is adjacent to end parts 63, 64 on both sides. A thread, not designated in greater detail, is applied to end parts 63, 64 respectively. Both end parts 63, 64 together with the central part 62 form a single piece threaded screw, but can nevertheless be hollow in cuts for weight reduction where necessary. In order to connect a component 65, the component 65 has a support hole 66 in which a cylindrical (outer) nut 67 is hingedly received. Component 65, which, in the illustrative embodiment illustrated in Figures 8 to 10, is a vertical support of a so-called ceiling structure, can have a thickening 68 in the region of the support hole 66 to provide sufficient material strength to position the support hole 66. The outer cylindrical nut 67 is pivoted about the z axis as a rotary geometry axis. A second internal cylindrical nut 69 is hingedly received within the cylindrical nut 67. For this purpose, the external cylindrical nut 67 has a hole with a corresponding diameter to support the internal cylindrical nut 69. The inner cylindrical nut 69 is hinged around the x axis as a rotary geometry axis, that is, the hinged geometry axes or the rotating geometry axes (geometry axes z and x) of the (biaxial) joint 70 formed by means of both cylindrical nuts. 67, 69 with two degrees of freedom form an intersection with each other at a 90 ° angle. An intersection point of the pivot or rotary geometry axes is preferably selected so that it is approximately in the region of a neutral fiber of component 65 in order to achieve an optimum introduction of force in component 65. The freedom of moment of force transmission between component 65 and the fuselage structure not shown in figures 8 and 9 are guaranteed in this case by the articulated connection by means of a biaxial barrel joint. as a result of the introduction of the moment free force, the risk of volume formation that is substantially only decisive, for example, for the dimensioning of such vertical supports is reduced as a result of mobility at the connection point. Therefore, the weight of the vertical support that is connected to the fuselage structure with the device according to the invention can be reduced compared to a rigid (fixed) moment connection to the (primary) fuselage structure.

The internal cylindrical nut 69 has a threaded hole, not designated by a numerical reference for a better overview in the drawing, in which the (first) end part 63 of the device 61 can be screwed. In order to pass through the end part 63, the component 65 has a through hole 71. In order to ensure sufficient mobility of the end part 63 in the direction of both double arrows around both hinge axes, the through hole 71 is designed with an excessive size in relation to an outside diameter of the end part 63. The (second) end portion 64 is likewise provided with a thread and is used in this case to substantially rigidly connect component 65 to the parts not shown in figures 8 and 9 of an aircraft fuselage structure.

Figure 10 illustrates the connection of component 65 by means of device 61 to a part of an aircraft fuselage structure 74.

For this purpose, the (second) end part 64 of the central part 62 of the device 61 is guided by holes, not described in greater detail, in the fuselage structure 74 and, for example, screwed and fixedly fixed to the structure of fuselage 74 by means of threaded nuts 75, 76 bolted to the left and / or right end 63, 64. In this context, the device 61 represents a mechanical reinforcement of the component 65 against the formation of volume in case of high loads running in parallel to the geometric axis x or a fixing means to fix the component 65 to the fuselage structure 74.

In the illustrated illustrative embodiment, component 65 is a vertical support, which runs perpendicular to the drawing plane, of a lining structure (secondary structure) that is used to suspend a plurality of material seats that are arranged transversely to the direction flight of the aircraft while forming two rows (seat) on both sides along the longitudinal sides of the fuselage.

Reference List

<td> 1.</td><td>connecting rod</td>

<td> 2.</td><td>the center, the middle part, the nucleus</td>

<td> 3.</td><td>end part</td>

<td> 4.</td><td>end part</td>

<td> 5.</td><td>eye bolt</td>

<td> 6.</td><td>eye bolt</td>

<td> 7.</td><td>nut</td>

<td> 8.</td><td>nut</td>

<td> 9.</td><td>fuselage structure</td>

<td> 10.</td><td>fuselage structure</td>

<td> 11.</td><td>fastener</td>

<td> 12.</td><td>fastener</td>

<td> 13.</td><td>screw connection</td>

<td> 14.</td><td>screw connection</td>

<td> 15.</td><td>longitudinal geometric axis</td>

<td> 16.</td><td>double arrow</td>

<td> 17.</td><td>double arrow</td>

<td> 18.</td><td>device</td>

<td> 19.</td><td>connecting rod</td>

<td> 20.</td><td>the center, the middle part, the nucleus</td>

<td> 21.</td><td>end part</td>

<td> 22.</td><td>end part</td>

<td> 23.</td><td>threaded rod</td>

<td> 24.</td><td>threaded rod</td>

<td> 25.</td><td>nut</td>

<td> 26.</td><td>nut</td>

<td> 27.</td><td>fuselage structure</td>

<td> 28.</td><td>fuselage structure</td>

<td> 29.</td><td>Joins</td>

<td> 30.</td><td>Joins</td>

<td> 31.</td><td>cylindrical nut</td>

<td> 32.</td><td>cylindrical nut</td>

33. support hole

34. support hole

35. rotating geometric axis (cylindrical nut)

36. rotating geometric axis (cylindrical nut)

37. double arrow

38. double arrow

39. thickening

40. thickening

41. through hole

42. through hole

43. neutral fibers

44. neutral fibers

45. fuselage structure

46. support hole

47. outer cylindrical nut

48. flange

49. retaining ring

50. thickening

51. inner cylindrical nut

52. hole

53. Joins

54. threaded rod

55. through hole

56. rotating geometry axis (geometry x axis)

57. rotating geometry axis (geometry z axis)

58. double arrow

59. double arrow

60. hole

61. device

62. the center, the middle part, the nucleus

63. (first) end part

64. (second) end part

65. component

66. support hole

67. cylindrical nut (external)

68. thickening

69. inner cylindrical nut

70. Joins

71. through hole

72. double arrow

73. double arrow

74. fuselage structure

75. threaded nut

76. threaded nut