Device for attaching object to attachment rail, arrangement for attaching object, method, and seat rail

Abstract

To provide a device for attaching an object to an attachment rail, an arrangement for attaching an object, a method, and a seat rail.SOLUTION: A device for attaching an object to an attachment rail, in particular a seat rail in an aircraft or spacecraft comprises: a base part 21 having a support surface 22 adapted to be placed onto an outer surface of the rail; and a locking element 28 adapted to partially protrude from the support surface 22 along a line of protrusion 36. The base part and locking element are coupled or configured to be coupled in such a manner that the locking element can be moved relative to the base part along the line of protrusion 36 and rotated with respect to the base part. An end section 29 of the locking element has a tip portion 30 shaped in a dovetail-type manner. The device comprises a tensioning arrangement 45 for tensioning the locking element with respect to the rail. Furthermore, the invention relates to an arrangement 100 comprising such a device as well as an attachment rail comprising a rail main body 50 and a plurality of bushes 55.SELECTED DRAWING: Figure 3

Description

Technical Field

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[0001] The present invention relates to a device for attaching an object to a mounting rail, particularly a seat rail of an aircraft or a spacecraft. Further, the present invention relates to a mechanism and a method for attaching an object in an aircraft or a spacecraft. Furthermore, the present invention particularly relates to a seat rail for an aircraft or a spacecraft.

Background Art

[0002] Although the present invention may be useful for attaching various types of objects in many fields of use, hereinafter, the present invention and the underlying problems will be described in more detail with respect to a seat rail used in an aircraft cabin as an example of a mounting rail.

[0003] It is generally known to attach an aircraft passenger seat to a seat rail disposed in the area of the cabin floor. An exemplary conventional seat rail design is generally I-shaped and is based on a profiled rail including a protruding portion having an undercut groove extending along the length of the rail on its upper surface facing the cabin, and the inlet of the groove is enlarged at equal intervals, for example, by circular holes. The holes may be regularly spaced from each other at intervals of 25.4 mm (1 inch) in a conventional example. A seat is fixed to such a rail using a specific insert.

[0004] A seat rail having such an undercut groove and holes of this kind is shown, for example, in Patent Document 1. It has been found that such a conventional seat rail made of an aluminum alloy can corrode particularly in areas where spilled liquid often comes into contact with the seat rail and adjacent floor elements. This particularly applies to areas where galleys or lavatories are located. This type of corrosion can be promoted by surface scratches, which can occur, for example, when an insert is moved relative to the rail during seat installation or the like.

[0005] Therefore, seat rails made of titanium alloy, which have much higher corrosion resistance, have been proposed. However, such seat rails are much more expensive than conventional aluminum rails, undesirably increasing the overall cost.

[0006] A seat rail made of titanium alloy, including an upper portion and a lower portion made of aluminum alloy connected thereto, has been proposed in Patent Documents 2 and 3. Furthermore, a seat track having multiple spaced-apart openings and a mounting device for connecting to such an aircraft seat track is described in Patent Document 4.

[0007] Furthermore, devices and methods for connecting a payload to a support truck are described, for example, in Patent Documents 5, 6, and 7. Furthermore, when using many existing types of mounting fixtures, assembly operators or technicians must spend a considerable amount of time connecting objects to seat rails inside the aircraft. This contributes even more to increased costs, especially considering the large number of seats in commercial aircraft.

[0008] Given this background, it would be desirable to be able to mount objects such as seats, monuments, or other devices in an improved and lower-cost manner. In particular, it would be desirable to at least reduce the effort and cost that has been required to prevent or delay corrosion of mounting rails, and / or to enable the mounting of objects in a faster and more labor-saving manner. [Prior art documents] [Patent Documents]

[0009] [Patent Document 1] German Patent Application Publication No. 4224821 [Patent Document 2] European Patent Application Publication No. 1544105 [Patent Document 3] U.S. Patent Application Publication No. 20050156095 [Patent Document 4] U.S. Patent Application Publication No. 20100038483 [Patent Document 5] U.S. Patent No. 7370832 [Patent Document 6] U.S. Patent No. 7413143 [Patent Document 7] U.S. Patent No. 7607613 [Overview of the Initiative] [Problems that the invention aims to solve]

[0010] In view of the above, the problem to be solved by the present invention is to provide an improved device for attaching an object to a mounting rail, which enables the secure and rapid attachment of the object, while also being suitable for use with rails that help prevent corrosion in a cost-effective manner. Correspondingly improved mechanisms and methods are also proposed. Furthermore, mounting rails, particularly seat rails, are provided that enable corrosion to be avoided in a simple and low-cost manner. [Means for solving the problem]

[0011] According to the present invention, this problem is solved by a device for mounting an object having the features of claim 1, and / or a mechanism for mounting an object having the features of claim 10, and / or a method for mounting an object having the features of claim 14, and / or a seat rail having the features of claim 15.

[0012] Accordingly, a device is proposed for attaching an object to a mounting rail, particularly a seat rail in an aircraft or spacecraft, the device comprising a base having a support surface adapted to be mounted on the outer surface of the mounting rail, and at least one locking element adapted to partially protrude from the support surface of the base along a line of projection. The base and the locking element are connected or configured to be connected such that the locking element can be moved along the line of projection relative to the base and rotated relative to the base. The end portion of the locking element has a tip portion in the shape of a dovetail joint. The device further comprises at least one tensioning mechanism for tensioning the locking element against the mounting rail when the support surface of the base rests on the outer surface of the mounting rail and the tip portion is in an engaged position with respect to the mounting rail.

[0013] Furthermore, a mechanism for mounting an object within an aircraft or spacecraft has been proposed, which comprises at least one device according to the present invention and at least one mounting rail. The device comprises at least one locking element, the end portion of which has a dovetail-shaped tip. The mounting rail comprises a rail body and a plurality of bushings, the rail body having an upper flange, the upper flange having a plurality of through holes arranged along the upper flange according to a predetermined pattern, and the bushings are connected to the upper flange from below. Each bushing is positioned in a location corresponding to one of the relevant through holes, and furthermore, each bushing is formed having an internal passage through which it passes. The locking element of the device extends into one of the internal passages of the bushing, and its tip portion is engageable with the bushing.

[0014] Furthermore, a method for attaching objects inside an aircraft or spacecraft is proposed. This method is - A step of providing at least one device according to the present invention, wherein the device includes at least one locking element, the end portion of the locking element having a dovetail-shaped tip portion, - Providing at least one mounting rail including a rail body and a plurality of bushes, wherein the rail body has an upper flange which is provided with a plurality of through holes arranged along the upper flange according to a predetermined pattern, the bushes are connected to the upper flange from below thereof, each bush is arranged at a position corresponding to a related one of the through holes, and further, each of the bushes is formed with an internal passage therethrough; - Inserting a locking element of the device into an internal passage of one of the bushes; - Engaging a tip portion of the locking element with the bush and including.

[0015] Furthermore, the present invention provides a seat rail adapted to attach an object, particularly a seat or a monument, to a seat rail in an aircraft or a spacecraft, the seat rail including a body formed of a fiber-reinforced composite material. In particular, the body of the seat rail may be formed of a fiber-reinforced thermoplastic composite material.

[0016] The idea underlying the present invention is that by using a locking element whose tip portion can be rotated to tension against a mating part which is part of the mounting rail and can be moved along a rotation axis, the device can be easily and quickly engaged and locked to the rail. Thus, the installation of a seat or other object can be easily performed in a short time by a bayonet method. In particular, the present invention provides an improved method for attaching an object to a mounting rail having a row of spaced holes.

[0017] At the same time, this device enables an object to be quickly and securely attached to the mounting rail even when, for example, most of the rail in the form of the body-forming part of the rail is made of a material other than metal, particularly a fiber-reinforced composite material.

[0018] Thus, the present invention enables an object, such as a seat or a monument, to be securely and quickly attached to a mounting rail having a geometric shape that can be suitably manufactured by a method other than metal extrusion. More specifically, the present invention enables an object to be securely and quickly attached to a mounting rail, particularly a seat rail, made of a fiber-reinforced plastic material useful for preventing corrosion of the rail in a cost-effective manner.

[0019] Advantageous improvements and developments of the present invention are included in the dependent claims of the patent claims and the description relating to the drawings. According to a development, the locking element has a substantially pin-like shape. Such a locking element can be easily manufactured.

[0020] According to an improvement, the locking element has a substantially cylindrical outer shape and includes a portion configured to be received within and extend through an opening in the base portion. In this way, the locking element can be configured to allow its linear movement and rotation relative to the base portion in a simple manner.

[0021] According to an improvement, the end portion of the locking element is formed to have a shape flattened with respect to the portion having a substantially cylindrical outer shape, and the end portion is laterally accommodated within an imaginary extension of the side surface of the portion having a substantially cylindrical outer shape. In this way, connecting the locking element to the base portion can be achieved in a simple manner.

[0022] According to another development, the locking element is adapted to be partially inserted into a passage extending from its outer surface into the mounting rail with its tip portion forward. Thus, the locking element can be easily and quickly engaged with the mounting rail.

[0023] In one developmental form, the end portion includes recesses on both sides of its narrow edges, each of which includes a retaining surface extending obliquely to the longitudinal axis of the locking element. This can further contribute to simplifying the manufacture of the locking element, as the recesses can be formed in a simple manner on the narrow edges of the flattened end portion to produce a dovetail joint shape.

[0024] In particular, the dovetail joint design is formed symmetrically, which contributes to even load distribution. In one developed form, the tensioning mechanism includes at least one cam pivotably connected to the locking element, and / or the tensioning mechanism includes a lever for applying a tension load to the locking element. In particular, the lever may be operable to pivot one or more cams. The lever and cams may be formed in particular as integral parts of a single tensioning component, each including the lever and cam. In this way, the locking element can be tensioned by hand in a quick and simple manner, without the use of any special tools. The lever and cams may preferably be configured such that when one or more cams are in a tensioned state, one or more cams remain in that state unless the lever is actuated.

[0025] In one improved configuration, the base is further formed with a projection on the support surface at a position spaced apart from the locking element. In this improved configuration, the projection may be formed integrally with the base or may be formed by an additional element fixed to and connected thereto. Furthermore, in this improved configuration, the projection is adapted to be inserted into a further passage extending from the outer surface into the mounting rail. In this way, the device, particularly its base, is prevented from rotating relative to the rail, and loads applied to the device parallel to its outer surface, particularly in the X direction parallel to the longitudinal axis of the mounting rail, can be transmitted to the rail via the projection.

[0026] In one developed form, the base includes a plate-like portion with a support surface. In another developmental form, the base is provided with a connecting portion adapted to be mechanically connected to the object to which it is attached.

[0027] In another developmental form, the device may include multiple locking elements and / or multiple tensioning mechanisms. In particular, the device may include two locking elements and two tensioning elements. In this way, even greater loads can be transmitted to the rail, for example, when mounting larger and / or heavier objects.

[0028] The object to be attached may be a seat, for example, a passenger seat in an aircraft or spacecraft. In a preferred development, the device is formed as a fixture, particularly a rear fixture, for attaching a passenger seat of an aircraft or spacecraft to a mounting rail. By using the device proposed by the present invention, a seat can be quickly and easily installed or re-installed and attached to a seat mounting rail, particularly a mounting rail made of fiber-reinforced synthetic material.

[0029] In alternative developmental forms, the object to be mounted may be, for example, a monument, particularly a galley monument, or a restroom monument, or a storage monument to be placed inside the cabin of an aircraft or spacecraft. In particular, the device may be formed as a fixture for attaching the monument to mounting rails inside the cabin of an aircraft or spacecraft. Thus, the monument can also be easily and quickly mounted inside the cabin.

[0030] In one developed form, each internal passage of the bush includes a passage portion formed with an elongated cross-section. This passage portion may be centrally located relative to other axial portions of the internal passage. Due to the passage portion and its elongated shape, engagement between the tip portion and the bush can be achieved in a quick and simple manner, particularly by rotating or swiveling the locking element by, for example, less than 180 degrees, preferably about 90 degrees.

[0031] In another embodiment, each bushing includes a contact surface adjacent to a passage portion formed with an elongated cross-section on the side of the bushing facing away from the upper flange of the rail body, and the contact surface of the bushing is adapted to contact the retaining surface of the tip portion of the locking element. In this development, the contact surface of the bushing is shaped to create a recess on the side of the bushing facing away from the upper flange. In particular, the contact surface of the bushing may be concave. This development contributes to surface contact between the tip portion and the bushing and helps prevent stress concentration. In this way, large loads acting on the locking element can be safely and reliably transmitted to the rail.

[0032] In another improved form, the bushing includes a substantially cylindrical cavity at least partially located within a through-hole associated with the bushing, on its surface toward the upper flange of the mounting rail. In particular, the internal dimensions of the cylindrical cavity, more specifically the internal diameter, may substantially correspond to or be slightly larger than the internal dimensions, particularly the internal diameter, of the opening of the base portion adapted to receive a portion of the locking element having a substantially cylindrical outer shape. In this way, the portion having a substantially cylindrical outer shape can be partially received and guided within the substantially cylindrical cavity, which contributes to the stable and reliable operation of the device.

[0033] The inner cross-sections of both the cylindrical cavity and the opening at the base can be substantially circular in particular. In certain developmental forms, the bush includes a substantially rotationally symmetrical external shape. For example, the bush may be formed with a substantially circular external contour. Such bushes can be manufactured relatively easily.

[0034] Furthermore, according to one improved configuration, the bushing includes an outwardly extending collar adapted to support the bushing against the rail body. In this way, the force introduced into the bushing can be transmitted to the rail body, and extremely high stresses are not induced at the interface between the bushing and the rail body, thereby ensuring that damage to the rail body in particular is prevented.

[0035] In a preferred development, the rail body is made from a fiber-reinforced synthetic material, particularly a carbon fiber-reinforced synthetic material. Preferably, the synthetic material is a thermoplastic material. In particular, the rail body includes a cross-section formed with a substantially omega shape. The omega-shaped design is particularly suitable for manufacturing composite rail bodies from fiber-reinforced synthetic materials in a continuous manufacturing process.

[0036] According to an alternative development, the rail body can be manufactured from sheet metal material by folding. In another improved form, the locking element, and / or base, and / or cam and lever are each made from a metallic material. In this way, a robust device can be obtained. Furthermore, forming the locking element from a metallic material helps to reliably transmit the load acting on the locking element to the rail in cooperation with a bushing, which is also made of metallic material.

[0037] In a preferred development, the bushes are each made from a metallic material, particularly titanium or steel. In another development, the device may be configured to prevent rotation of the locking element and / or operation of the lever when the locking element is tensioned against the mounting rail by a tensioning mechanism. In this way, unintended unlocking and disengagement of the device can be avoided.

[0038] In one advanced form of a seat rail proposed by the present invention, the body formed of a fiber-reinforced synthetic material is the rail body, and the rail body has a flange, particularly an upper flange, and the flange, particularly the upper flange, is provided with a plurality of through holes arranged along the flange according to a predetermined pattern. According to this advanced form, the seat rail further includes a plurality of bushings connected to the flange, each bushing positioned in a location corresponding to one of the relevant through holes, and further each bushing is formed having a passage through it. In particular, the bushings are made of a metallic material, particularly titanium or steel.

[0039] Furthermore, the above-described advanced and improved forms relating particularly to bushings and rail bodies formed from fiber-reinforced synthetic materials can be applied to the seat rails proposed by the present invention. The improved, enhanced, and advanced forms of the present invention can be combined with each other as appropriate, insofar as it is meaningful. Furthermore, other conceivable improved, advanced, and implementation forms of the present invention include combinations of the features of the present invention described above or later in relation to the detailed description of the embodiments, even if such combinations are not explicitly stated.

[0040] In particular, the improved, enhanced, and advanced forms of the present invention described above can be similarly applied to each of the devices, mechanisms, methods, and seat rails proposed herein. The present invention will be described below with reference to schematic diagrams illustrating embodiments of the present invention. [Brief explanation of the drawing]

[0041] [Figure 1] An exemplary aircraft in which embodiments of the present invention may be used is shown in a side view. [Figure 2] An apparatus and mechanism according to one embodiment of the present invention are shown in a top-down perspective view. [Figure 3] The apparatus and mechanism according to the embodiment shown in Figure 2 are illustrated in the central longitudinal section II. [Figure 4] Figures 2 and 3 show top views of the mechanisms according to the embodiments. [Figure 5] Figures 2-4 show end view diagrams of the mechanisms according to the embodiments. [Figure 6] Figure 6A shows side views of three exemplary bushes used in the embodiments shown in Figures 2-5. Figure 6B shows a top view of the bush in Figure 6A. Figure 6C shows another side view of the bush in Figure 6A. Figure 6D shows cross-sectional view II-II of the bush shown in Figure 6B. Figure 6E shows another cross-sectional view III-III of the bush shown in Figure 6B. [Figure 7] Figure 7A shows a front view of the locking element in the form of a central pin of the device according to the embodiments shown in Figures 2-5. Figure 7B shows a side view of the locking element of Figure 7A. [Figure 8] Figure 8A shows a side view of the base of the apparatus according to the embodiments shown in Figures 2-5. Figure 8B shows a top view of the base of Figure 8A. Figure 8C shows an end view of the base of Figure 8A. [Figure 9] Figure 9A shows a side view of the components of the tensioning mechanism of the device according to the embodiments shown in Figures 2-5. Figure 9B shows a top view of the components of Figure 9A. Figure 9C shows an end view of the components of Figure 9A. [Figure 10] Figure 10A shows a top view of the mounting rail body of the mechanism according to the embodiments shown in Figures 2-5. Figure 10B shows the rail body of Figure 10A in a specific longitudinal section IV-IV shown in Figure 10A. Figure 10C shows an end view of the rail body of Figure 10A. [Figure 11] Several components of the mechanism according to the embodiments shown in Figures 2-5 are shown in perspective views from above the mounting rail. [Modes for carrying out the invention]

[0042] The accompanying drawings illustrate embodiments of the present invention so that the invention may be better understood. The drawings, together with the explanatory text, illustrate the principles and concepts of the present invention. Many other embodiments and advantages described can be inferred from the drawings. Elements in the drawings are not necessarily drawn to exact scale.

[0043] In drawings, elements, features, and components that are the same or have the same function or effect shall be represented by the same reference numeral unless otherwise explicitly stated. Figure 1 shows a passenger aircraft 1 including the fuselage 3, wings, stabilizers, and engines. Within the fuselage 3, the aircraft 1 includes a passenger cabin having a cabin floor 6 schematically shown in Figure 1.

[0044] To securely and quickly attach passenger seats to the cabin floor 6, the cabin floor 6 includes a plurality of seat mounting rails or seat rails 15. In the exemplary aircraft 1 shown in Figure 1, each seat mounting rail 15 extends along the cabin floor 6 in the longitudinal direction X of the aircraft 1. Direction Z indicates the longitudinal direction; see Figure 1 for this. Furthermore, the transverse direction Y is shown.

[0045] A mechanism 100 for mounting objects 91 such as passenger seats inside an aircraft 1 is shown in Figures 2-5 and 11. The mechanism 100 includes a seat mounting rail 15 and a device 10 used to mount the passenger seat 91 to the seat mounting rail 15. Figures 2-5 and 11 also show the method according to an embodiment of the present invention and the seat rail 15, which is part of the mechanism 100.

[0046] A short portion of the rail 15 is shown in Figure 2. The cabin floor 6 and any support structures for the cabin floor 6 that support, for example, the seat rail 15, have been omitted from Figures 2-5 for clarity. When installed as part of the cabin floor 6, the seat mounting rail 15 is typically much longer than the portion shown in Figure 2 for illustrative purposes.

[0047] In Figure 2, only a portion of the rear leg of the seat 91 is schematically shown. In the examples of Figures 2-5, the device 10 is formed as a rear mounting fixture for attaching the rear leg of the seat 91. Figures 2-5 show the device 10 in its locked state, where the attachment of the rear leg of the seat 91 schematically shown in Figure 2 is already fitted.

[0048] The seat mounting rail 15 in Figures 2-5 includes a rail body 50 having a cross-section formed substantially in an omega shape. The cross-sectional shape of the rail body 50 is symmetrical, and its basic shape is essentially constant along the longitudinal direction of the rail 15, which is shown parallel to the X-axis as defined with respect to the aircraft in Figure 1. The rail body 50 is again shown separately in Figures 10A-10C.

[0049] For more details, see, for example, Figure 2, where the rail body 50 is provided with an upper flange 51, a web 52, and a lower flange 53. When the rail 15 is installed as part of the cabin floor 6, the upper flange 51 and the lower flange 53 extend parallel to the XY plane, respectively, and each of the webs 52 extends parallel to the XZ plane. Thus, when the aircraft 1 is on the ground, the web 52 is substantially longitudinal, and the flanges 51 and 53 are substantially horizontal.

[0050] Once the mounting rail 15 is installed as part of the cabin floor 6, the upper surface of the flange 51 forms the outer upper surface 16 of the rail 15, and the upper surface 16 faces inward into the cabin. The webs 52 extend parallel to each other. The first ends of the webs 52 are integrally connected to the upper flanges 51, and the second ends of the webs 52 are integrally connected to one of the lower flanges 53. Between the webs 52, a channel 54 is formed when viewed from the underside of the rail 15, which is bounded on the upper side of the rail 15 by the upper flanges 51. The lower flanges 53 extend laterally outward from the second lower ends of the webs 52. The upper flanges 51 project laterally beyond the first upper ends of the webs 52.

[0051] Figure 2 also shows that the rail body 50 is provided with a row of through holes 60 in the upper flange 51, which are preferably formed to have a circular cross-section. In the example in Figure 2, the through holes 60 are spaced equally along the longitudinal direction of the mounting rail 15 corresponding to the X direction in Figure 2, i.e., with equal distances between adjacent through holes 60. In particular, all the through holes 60 in Figure 2 are the same shape. The through holes 60 can be formed, for example, by drilling holes in the upper flange 51.

[0052] The rail bodies 50 in Figures 2-5, 10A-10C and 11 are manufactured from fiber-reinforced synthetic materials, preferably fiber-reinforced thermoplastic synthetic materials. In particular, the rail bodies 50 may preferably contain carbon fibers as reinforcing fibers embedded in a synthetic, preferably thermoplastic matrix material. Such rail bodies 50 are relatively lightweight, can be manufactured at low cost, and help to avoid corrosion of the seat rails 15. For example, the rail bodies 50 can be manufactured by producing semi-finished products using a continuous manufacturing method and then drilling through holes 60.

[0053] A portion of the cabin floor 6 may be fitted with seat rails 15 of the type shown in Figures 2-5 and 11, which are in particular so-called "wet" areas where spills are expected. However, as will be explained in particular with respect to Figures 2-5 and 11, seat rails 15 may be installed over substantially the entire cabin floor 6, which are both so-called "wet" areas and so-called "dry" areas where spills are less likely to occur. Therefore, by using the rails 15 of Figures 2-5 and 11, the process of installing seat rails on the cabin floor 6 can be greatly simplified, reducing the corresponding labor and costs.

[0054] The device 10 shown in Figure 2 is again shown in Figures 3 to 5 in the same locked state as in Figure 2. The device 10 or rear mounting bracket includes a base 21, which can also be seen in Figures 8A to 8C. The base 21 includes a plate-like portion 21a, and a basically flat support surface 22 of the base 21 is formed on the lower surface of portion 21a. Furthermore, the plate-like portion 21a is provided with a circular opening 23, which forms a through hole from the lower surface to the upper surface of portion 21a.

[0055] Figures 3, 8A and 8C further show that the plate-like portion 21a of the base 21 is provided with a projection 78 which protrudes from the support surface 22 at a position on the surface 22 that is separate from the position of the opening 23.

[0056] The projection 78 may be formed integrally with the plate-like portion 21a, for example, or it may be formed by fixing and connecting a protruding element to the plate-like portion 21a. The outer surface 79 of the projection 78 has a cylindrical shape.

[0057] The base portion 21 is basically symmetrical with respect to its longitudinal centerline corresponding to the X direction in the installed state shown in Figure 2. On the upper surface of the plate-like portion 21a opposite the support surface 22 of the base portion 21, the base portion 21 further includes three additional projections, which are shaped as upright plate-like first, second, and third portions 24, 25a, and 25b extending from the upper surface of portion 21.

[0058] The first upright portion 24 forms a connecting portion on portion 21a, positioned forward of the opening 23 on its centerline, and adapted to be mechanically connected to the seat 91 to be installed. For attaching the seat 91, particularly the rear legs, the connecting portion 24 is provided with an opening 24a as a through hole or eyelet.

[0059] The second and third sections 25a and 25b are substantially the same shape and are symmetrically positioned on both sides of the centerline of the base 21, towards the rear of the opening 23. The functions of sections 25a and 25b will be described later.

[0060] The device 10 further includes a locking element 28, which has a pin shape and is shown separately in Figures 7A and 7B. The locking element 28 serves as the central pin 28 of the device 10.

[0061] The locking element 28 includes a portion 31 corresponding to the upper portion of the locking element 28 in Figures 7A and 7B, which has a substantially cylindrical shape defined by the cylindrical side surface 32 of the portion 31. The axis of the cylindrical side surface 32 also defines the longitudinal axis A of the locking element 28. The outer contour of the portion 31 is substantially circular.

[0062] Near one end of the locking element 28, the cylindrical portion 31 is provided with a lateral through-hole 49 formed as a cylindrical bore with a circular cross-section. The function of the through-hole 49 will be described later.

[0063] The diameter of portion 31 may be selected, for example, to substantially correspond to the diameter of the opening 23, and any error or play may be selected so that the cylindrical portion 31 is slidably and rotatably received within the opening 23. In this way, the locking element 28 can be inserted into the opening 23, for example, from above the base 21, in Figures 2, 3, and 5, thereby connecting to the base 21.

[0064] The locking element 28, of which a portion 31 is partially received within and extending through the opening 23 in the state shown in Figures 2-5 and 11, is capable of both axial linear movement along axis A and rotation about axis A within the opening 23. When the locking element 28 is inserted into the opening 23, axis A coincides with the central axis of the opening 23.

[0065] The locking element 28 further includes an end portion 29, which corresponds to the lower portion of the locking element 28 in Figures 7A and 7B. The shape of the end portion 29 is flattened relative to the upper portion 31. Figures 7A and 7B show that the end portion 29 is housed laterally within an imaginary extension of the basically cylindrical side surface 32 of the portion 31. For example, the locking element 28 may be easily manufactured by removing a pin, which is originally cylindrical, from it, for example, by milling or other material removal process.

[0066] For example, Figures 7A-7B also show that the end portion 29 includes a tip portion 30 at the end of the locking element 28 opposite to the end containing its lateral bore 49, and the tip portion 30 has a dovetail joint shape. The narrow sides 34 on both sides of the end portion 29 are provided with recesses 33 symmetrically with respect to axis A. The recesses 33 can be formed, for example, by cutting into the narrow sides 34 during the manufacture of the locking element 28. Each of the recesses 33 includes a retaining surface 35 that extends obliquely with respect to the longitudinal axis A of the locking element 28. By forming these recesses 33, the dovetail joint shape of the tip portion 30 is obtained. Each retaining surface 35 may be flat, but may preferably be concave to more uniformly distribute the pretensioning force and retaining force, which will be described in more detail below.

[0067] In the assembled device 10, as shown in Figures 2-4, the pin 48 passes through the through hole 49 of the locking element 28. The pin 48 pivotably connects the two cams 46 on either side of the portion 31 to the locking element 28. The two cams 46 are formed in the same shape and are both integrally formed with the lever 47. Thus, the cams 46 and the lever 47 form part of a single component, which is again shown separately in Figures 9A-9C.

[0068] Each cam 46 is provided with an opening 46a, each receiving the end of a pin 48. The pin 48 can be tightly fitted either in the through hole 49 or in the opening 46a. The mounting rail 15 is provided with a plurality of bushings 55, for which refer specifically to Figures 3, 5, 6A-6E and 11. At each position along the longitudinal direction of the rail 15 in one of the through holes 60 of the upper flange 51, one of the plurality of bushings 55 is connected to the upper flange 51 from its lower surface. Thus, with one bushing 55 provided in each of the through holes 60, the rail 15 is installed as part of the cabin floor 6.

[0069] In the embodiments shown in these figures, the bushes 55 are all formed similarly, and each is made from a metallic material, such as a titanium alloy or steel. Each bush 55 has a substantially rotationally symmetrical external shape. More specifically, the outer diameter of each bush 55 is basically cylindrical, having a circular outer cross-sectional shape, and is provided with an outwardly extending annular collar 55a. The collar 55a extends circumferentially on the outer surface of the bush 55; see Figures 3, 5, 6A-6E and 11 for details. Viewed from its outer surface along the longitudinal central axis of the bush 55, the bush 55 has two axial parts, and the boundary between these two parts is defined by the collar 55a.

[0070] The upper portion 61 of the bush 55 is located on the upper side of the collar 55a in Figures 3 and 6A, and is configured so that the bush 55 is introduced into one of the corresponding through holes 60 to which it is associated. For each bush 55, the portion 61 thus forms an insertion portion 61, which is introduced into the corresponding through hole 60 until the collar 55a abuts against the lower surface of the upper flange 51. In this state, preferably, the end face of the insertion portion 61, farther from the collar 55a, may be substantially coplanar with the outer surface 16 of the upper flange 51, or may be slightly offset toward the interior of the through hole 60.

[0071] The collar 55a is fitted so that the bush 55 is supported by the rail body 50 by contacting the lower surface of the upper flange 51. In particular, the collar 55a is fitted so as to introduce a force to the upper flange 51, which acts on the bush 55 perpendicular to the upper flange 51 in the positive Z direction, i.e., upward in Figure 3.

[0072] By using the contact surface portion between the upper flange 51 and the bush 55, the bush 55 and the rail body 50 are fixed and connected, for example, by welding or adhesive bonding, particularly inside the through hole 60 and around the bush 55 on the lower surface of the upper flange 51. Welding can be achieved, for example, by local melting or softening of the thermoplastic matrix of the rail body 50.

[0073] Figure 11 shows three bushings 55 connected to the upper flange 51 for illustrative purposes. However, as previously stated, it should be understood that preferably each of the through holes 60 is provided with one of the bushings 55. Thus, the seat rail 15 of this embodiment is typically provided with many bushings 55 along its length.

[0074] Each bush 55 has an internal longitudinal passage 56 that extends from the upper end to the lower end of the bush 55. Above the bush 55, which is directed toward the upper flange 51 when the bush 55 is connected to the rail 15 and partially inserted into the through hole 60, the first portion of the passage 56 is formed having a substantially cylindrical cavity 59, which is at least partially within the through hole 60 associated with the bush 55.

[0075] The inner diameter of the substantially cylindrical cavity 59 may be substantially equivalent to or slightly larger than the lateral dimension of the opening 23, i.e., its diameter. The inner cross-section of the cavity 59 is substantially circular.

[0076] The bottom of the cavity 59 is preferably basically flat. The portion 57 of the internal passage 56 extends through the bottom of the cavity 59, for which refer to Figures 6B and 6D, and is formed with an elongated cross-section. The passage portion 57 is centrally located at the bottom of the cavity 59, and therefore the centerlines of both the cavity 59 and the passage portion 57 coincide.

[0077] Below the bush 55, facing away from the upper flange 51 of the rail body 50, the passage portion 57 is followed by a relatively shallow cavity or recess defined by a contact surface 58, as shown in Figure 6E, 11. This shallow cavity or recess forms the final portion of the internal passage 56 of the bush 55 in this embodiment. The passage portion 57 is open in the center to the recess within the contact surface 58. The contact surface 58 may be formed, for example, as part of a conical or spherical surface.

[0078] In particular, note that the height of the bush 55 in the direction perpendicular to the upper flange 51 may differ from that shown, for example, in Figures 3, 6A to 6E. For example, in various examples, the axial size of the bush 55 and the length of the locking element 28 may be changed to be shorter or longer than those shown in the figures.

[0079] To attach objects such as passenger seats 91 to seat rails 15 which are installed as part of the cabin floor 6 inside the aircraft 1, the device 10 is installed on the mounting rail 15 such that the support surface 22 is positioned on the upper surface 16 of the rail 15. This is shown in Figure 2. The device 10 is positioned so that the centerline of the opening 23 coincides with the centerline of one of the through holes 60 and the bush 55 assigned to that through hole 60.

[0080] The locking element 28 can be connected to the base portion 21 when the base portion 21 is installed on the rail 15, or the locking element 28 can be inserted into and through the opening 23 with its tip portion 30 facing forward when the base portion 21 is on the outer surface 16 of the rail 15.

[0081] In all of these cases, the cylindrical portion 31 is slidably and rotatably received in the opening 23, and after insertion, the locking element 28 partially protrudes downward from the support surface 22 along the projection line 36, as shown in Figure 3. The projection line 36 corresponds to axis A of the locking element 28 in Figure 3. In this way, when the base portion 21 and the locking element 28 are connected, the locking element 28 is movable relative to the base portion 21 along the projection line 36 and rotatable relative to the base portion 21 around the line 36 within the opening 23, before the device 10 is fixedly mounted to the rail 15 as described later.

[0082] Each portion 61 of the bush 55 is located within one of the through holes 60. Thus, the passage 56 of each bush 55 is accessible from the outer surface 16 of the upper flange 51. When installing the device 10 on the rail 15 or when inserting the locking element 28 after the base 21 has been installed on the rail 15, the locking element 28 is partially inserted, with its tip portion 30 facing forward, through the bush 55 and thus into the passage 56 that extends through the upper flange 51 of the mounting rail 15.

[0083] Inserting the tip portion 30 of the locking element 28 into the passage 56 is performed with the longer side of the tip portion 30 oriented laterally, particularly perpendicular to the longitudinal direction of the rail 15, which coincides with the X direction in Figure 2. This corresponds to the unlocking orientation U of the tip portion 30, schematically shown by the dashed line in Figures 2 and 4. Furthermore, when inserting the tip portion 30 into the passage 56, the component including the lever 47 and the cam 46 is in a position not shown, with the lever 47 oriented vertically from the plate portion 21, for example, approximately parallel to axis A.

[0084] In other words, in order to insert the tip portion 30 into the internal passage 56, compared to the situation shown in Figures 2-5, the lever 47 will be rotated upward by, for example, an angle of about 90 degrees, and the locking element 28 will be rotated, for example, by rotating the locking element 28 by an angle of about 90 degrees, so that the long side of the tip portion 30 faces the lateral direction indicated by the dashed line U.

[0085] Furthermore, when the base portion 21 is positioned on the upper surface 16 of the mounting rail 15, with the opening 23 centered over one of the through holes 60 and the associated bush 55, the projection 78 can be inserted into one of the cavities 59 of the bush 55 assigned to the other through hole 60. In the embodiments shown in these figures, the projection 78 can be inserted into the cavities 59 of the bush 55 at the location of the through hole 60 adjacent to the through hole 60 on which the opening 23 is centered. However, in various variations of this embodiment, the distance between the projection 78 and the opening 23 may vary, for example, so that the projection 78 can be inserted into the next subsequent bush 55 as seen from the opening 23, i.e., one bush between them can be left unused.

[0086] In this embodiment, the outer diameter of the cylindrical projection 78 may be slightly larger than the outer diameter of the portion 31 of the locking element 28. In addition to preventing the overall rotation of the device 10 on the surface 16, i.e., in the Z direction, a projection 78 of such dimensions allows for reliable transmission of forces acting along the X direction from the base 21 through the projection 78 to the rail 15. The projection 78 thus forms a so-called passive forward interface point, which does not transmit loads acting perpendicular to the surface of the upper flange 51 in the positive Z direction.

[0087] After inserting the locking element 28 into and through the passage 56, and after the tip portion 30 is fully guided within the passage portion 57 and exits therein in the region of the lower end of the bush 55, the tip portion 30 can engage with the bush 55 by rotating the locking element 28 around axis A due to its dovetail joint shape. More specifically, in order to lock the device 10 to the mounting rail 15, the locking element 28 is rotated, for example, about 90 degrees around axis A so that the long side of the tip portion 30 aligns with the longitudinal direction of the rail 15. This orientation of the tip portion 30 corresponds to its locked orientation L, which is shown, for example, in Figure 11. Figure 11 also shows that the passage portion 57 of each bush 55 is oriented such that the longitudinal direction of the portion 57, which is parallel to the long side of the passage portion 57, extends laterally with respect to the longitudinal direction of the rail 15, which is shown parallel to direction X. Thus, the device 10 can engage with and lock to the rail 15 like a bayonet mechanism.

[0088] The aforementioned lever 47, cam 46, and pin 48 form a tensioning mechanism 45. After engaging the tip portion 30 of the locking element 28 with the bush 55 by rotating the locking element 28, the lever 47 is swung downward by the operator to the position shown in Figures 2 and 3. As the lever 47 is swung, the cam 46, which is integrally formed with the lever 47, rotates around the axis of the pin 48. The cam 46 is supported on the upper surface of the plate portion 21a. By moving the lever 47 downward and rotating the cam 46, the pin 48 and locking element 28 are pulled upward in the positive Z direction. As a result, the tip portion 30 is pulled against the bush 55, the retaining surface 35 is pressed against the contact surface 58, a tension load is applied to the lock 28, and tension is applied to the device 10, including the base portion 21, against the rail 15. The configuration of the pin 48, lever 47, and cam 46, including in particular the position of the pin 48 and the contour of the cam 46, is selected so that, in the state shown in Figures 2 and 3, the tensioning mechanism 45 is fixed and held in a tensioned state unless the lever 47 is lifted.

[0089] The dovetail joint shape of the tip portion 30 allows it to rotate smoothly within the shallow recess at the lower end of the bush 55 when the locking element 28 is not under tension. The contact surface 58 is adapted to make surface contact with the retaining surface 35. Refer to Figures 1, 2, and 3. A force acting on the locking element 28 in the positive Z direction is transmitted to the bush 55 via the retaining surface 35. The surface contact between these surfaces and the contact surface 58 helps to avoid localized stress concentration and to distribute the transmitted force evenly. The dovetail joint shape of the tip portion 30 may also help to improve the centering of the locking element 28, i.e., the centering pin 28, with respect to the bush 55.

[0090] When the device 10 is locked to the rail 15 and tensioned thereon, the force acting on the locking element 28 in the positive Z direction is transmitted to the rail body 50 via the upper flange 51 and thus the collar 55a at the position of the opening 23. Forces acting on the base 21 in the negative Z direction, such as weight, are supported by the support surface 22. Furthermore, a firm connection between the bush 55 and the rail body 50, for example by welding or adhesive bonding, prevents the bush 55 from detaching from the rail body 50 due to forces acting during the installation of the device 10, particularly downward forces.

[0091] The device 10 may preferably be adapted to prevent the locking element 28 from rotating around axis A when the locking element 28 is tensioned against the mounting rail 15, thereby preventing, for example, unintentional unlocking of the device 10. The anti-rotation sections 25a and 25b shown in Figures 2 and 3 may be configured to avoid or prevent rotation of at least the lever 47 connected to the locking element 28 around axis A by providing lateral guidance and a lateral stopper. If necessary, additional means may be included to prevent rotation of the lever 47 around the axis of the pin 48 in order to prevent unintentional unlocking and / or abuse. For example, for this purpose, a cover, latch, or locking mechanism that cannot be released without the use of a special tool may be provided.

[0092] In the embodiments described above, the locking element 28, the body of the base 21 including parts 21a, 24, 25a-b and projection 78, the component comprising the cam 46 and lever 47, and the pin 48 are each made of a metallic material, which may be aluminum alloy, titanium alloy, or steel in particular. The same or different of these materials may be used for components 28, 21, 46 and 47 and 48 of the device 10.

[0093] By forming the bushings 55 and locking elements 28 from one or more metallic materials, such as titanium or steel, these components can be made to withstand wear and corrosion at a limited cost. The body 50 of the rail 15 can be made from a fiber-reinforced composite material such as a carbon fiber-reinforced thermoplastic, which is therefore lightweight and contributes to corrosion prevention. Damage to the rail body 50 during installation and locking of the device 10 and excessively high loads on the surface of such composite materials can be prevented by using the metallic bushings 55 and locking elements 28. The device 10 thus also helps to avoid deterioration of the edges, for example, in the through-holes 60, when the device 10 is repeatedly installed and removed. When the device 10 is installed and loaded, the bushings 55 ensure a smoother and more distributed load transfer from the center pin 28 to the seat rail 15.

[0094] In addition, the omega shape of the rail body 50, along with the introduction of load through the bush 55 positioned at the through-hole 60 along its centerline within the upper flange 51, prevents excessive localized concentration of contact force and thus prevents damage to the composite rail body 50. Furthermore, its geometric shape and symmetrical load application provide a stable flange 51 that can withstand deformation or unfolding, thereby preventing damage to the matrix.

[0095] In another variant of the aforementioned device 10, the base 21 may be provided with a portion 21a having a plurality of openings 23, for example two openings 23, a plurality of locking elements 28, for example two locking elements 28, and a plurality of tensioning mechanisms 45, for example two mechanisms 45. In this variant, the openings 23 are arranged along the longitudinal direction of the portion 21a, so that each of the two locking elements 28 can be received in one of the openings 23 and inserted into a passage 56 associated with two through holes 60. Furthermore, in such a variant, the levers 47 and cams 46 of each tensioning mechanism 45 may be operable independently of the other mechanisms 45, so that the locking elements 28 can be tensioned independently of each other. For example, the free ends of each lever 47 may be directed toward each other when the device 10 is engaged and locked. In this way, a higher load can be supported by the device 10 and transmitted to the rail 15.

[0096] It should be noted that in another variation of the above-described embodiment, an intermediate protective layer, not shown in the figures, may be positioned between the plate-like portion 21a and the outer surface 16 of the upper flange 51. For example, such a protective layer may be made from, for example, sheet metal or a sheet-like composite material and positioned over the entire surface 16, or preferably positioned on the bottom surface of the plate-like portion 21a, such that the protective layer becomes part of the base 21, in which case the support surface 22 is thus formed on the intermediate layer. Furthermore, in the latter case, the intermediate protective layer may preferably be formed as a layer of composite material on the bottom surface of the plate-like portion 21. In this way, corrosion can be prevented in an improved manner by utilizing the intermediate layer.

[0097] The above describes in detail how to attach passenger seats 91 to the mounting rails 15 using the device 10. However, the present invention can also be used to attach other objects to the mounting rails 15. In some examples, the device 10 may be formed as a fixture for mounting monuments (not shown) inside the cabin. The monument to be mounted may be, for example, a galley monument, or a restroom monument, or a storage monument, or other types of objects that can be attached to the mounting rails 15. In particular, the connecting portion 24 may be modified or adapted as appropriate, if necessary, to mount objects 91 other than seats.

[0098] Furthermore, while it is particularly preferable that the rail body 50 of the seat mounting rail 15 be manufactured from a fiber-reinforced synthetic material, especially a thermoplastic reinforced with carbon fibers, in alternative embodiments the rail body 50 may be formed from a metallic material, for example, using folded metal sheet technology.

[0099] Although the present invention has been described in detail above with respect to preferred embodiments, the present invention is not limited to these embodiments and can be modified in various ways. [Explanation of symbols]

[0100] 1 aircraft 3 Torso 6 Cabin floor 10 equipment 15 Mounting rail 16 Exterior 21 Base 21a Plate-shaped portion 22 Support surface 23 Aperture 24 Connecting part 24a aperture 25a Anti-rotation part 25b Anti-rotation part 28. Rock elements 29 End part 30 Tip part 31 Cylindrical section 32 Side view 33 Recess 34 Narrow side 35 Holding surface 36. Lines of protrusion 45 Tension mechanism 46 Cam 46a aperture 47 Lever 48 pins 49 Boa 50 Rail body 51 Upper flange 52 Web 53 Lower flange 54 channels 55 Bush 55a Color 56 Internal passageway (bush) 57 Passage section 58 Contact surface 59 Cavity 60 through holes 61 parts (bush) 78 Protrusion 79 Outer surface (protrusion) 91 Object 100 mechanisms A Longitudinal axis (locking element) L Suitable for rock music (rock elements) U Suitable for unlocking (lock element) XX direction YY direction ZZ direction

Claims

1. A device (10) for mounting an object (91) to a mounting rail (15), in particular a seat rail (15) in an aircraft or spacecraft (1), comprising: a base (21) having a support surface (22) adapted to be placed on an outer surface (16) of the mounting rail (15) and at least one locking element (28) adapted to protrude partially from the support surface (22) of the base (21) along a line of projection (36); the base (21) and the locking element (28) are connected or configured to be connected such that the locking element (28) can be moved along the line of projection (36) relative to the base (21) and can be rotated relative to the base (21); The end portion (29) of the locking element (28) has a tip portion (30) having a dovetail shape; The device (10) further includes at least one tensioning mechanism (45) for tensioning the locking element (28) against the mounting rail (15) when the support surface (22) of the base portion (21) rests on the outer surface (16) of the mounting rail (15) and the tip portion (30) is in an engagement position (L) relative to the mounting rail (15).

2. 2. The device according to claim 1, characterized in that the locking element (28) has a substantially pin-shaped configuration.

3. 2. The apparatus of claim 1, wherein the locking element (28) has a substantially cylindrical outer shape and includes a portion (31) configured to be received in and extend through an opening (23) in the base (21).

4. 4. The device according to claim 3, characterized in that the end portion (29) of the locking element (28) is formed with a shape that is flattened with respect to the portion (31) having the substantially cylindrical outer shape, the end portion (29) being received laterally in an imaginary extension of a side surface (32) of the portion (31) having the substantially cylindrical outer shape.

5. 2. The apparatus of claim 1, wherein the locking element (28) is adapted to be partially inserted, with the tip portion (30) forward, into a passage (56) extending into the mounting rail (15) from the outer surface (16) thereof.

6. 2. The device according to claim 1, characterized in that the end portion (29) includes recesses (33) on both narrow sides (34) thereof, each of the recesses (33) including a retaining surface (35) extending obliquely with respect to the longitudinal axis (A) of the locking element (28).

7. 2. The device according to claim 1, characterized in that the tensioning mechanism (45) comprises at least one cam (46) pivotally connected to the locking element (28) and / or that the tensioning mechanism (45) comprises a lever (47) for applying a tensioning load to the locking element (28).

8. 2. The device according to claim 1, characterized in that the base (21) is further formed with a protrusion (78) on the support surface (22) at a position spaced apart from the position of the locking element (28), the protrusion (78) being formed integrally with the base (21) or by an additional element fixedly connected thereto, the protrusion (78) being adapted to be inserted into a further passage (56) extending from the outer surface (16) into the mounting rail (15).

9. 2. The device according to claim 1, characterized in that it is formed as a mounting fixture, in particular a rear mounting fixture, for mounting a passenger seat (91) of an aircraft or spacecraft (1) to the mounting rail (15) or as a mounting fixture for mounting a monument to the mounting rail (15) in the cabin of an aircraft or spacecraft (1).

10. A mechanism (100) for mounting an object (91) in an aircraft or spacecraft (1), comprising: At least one device (10) according to any one of claims 1 to 9, wherein the end portion (29) of the locking element (28) has a tip portion (30) in the shape of a dovetail; at least one mounting rail (15) including a rail body (50) and a plurality of bushings (55), said rail body (50) having an upper flange (51) provided with a plurality of through holes (60) arranged along said upper flange (51) according to a predetermined pattern, said bushings (55) connected to said upper flange (51) from an underside thereof, each bushing (55) being arranged at a position corresponding to the position of an associated one of said through holes (60), and further, each of said bushings (55) being formed with an internal passage (56) therethrough; wherein the locking element (28) of the device (10) extends into the internal passage (56) of one of the bushings (55), and the tip portion (30) is engagable with the bushing (55).

11. 11. The arrangement of claim 10, wherein the internal passage (56) of each of the bushes (55) includes a passage portion (57) formed with an elongated cross section.

12. 12. The mechanism according to claim 11, characterized in that each of the bushes (55) comprises, on a face of the bush (55) facing away from the upper flange (51) of the rail body (50), a contact surface (58) adjacent to the passage portion (57) formed with the elongated cross section, the contact surface (58) of the bush (55) being adapted to contact a retaining surface (35) of the tip portion (30) of the locking element (28), the contact surface (58) of the bush (55) being shaped to present a recess in the face of the bush (55) facing away from the upper flange (51).

13. The arrangement of claim 10, wherein the rail body (50) includes a cross section formed substantially with an omega shape.

14. A method for mounting an object (91) in an aircraft or spacecraft (1), comprising the steps of: Providing at least one device (10) according to any one of claims 1 to 9, said device (10) comprising at least one locking element (28), an end portion (29) of said locking element (28) having a tip portion (30) in a dovetail shape; providing at least one mounting rail comprising a rail body (50) and a plurality of bushings (55), said rail body (50) having an upper flange (51), said upper flange (51) being provided with a plurality of through holes (60) arranged along said upper flange (51) according to a predetermined pattern, said bushings (55) being connected to said upper flange (51) from its underside, each bushing (55) being disposed at a position corresponding to the position of an associated one of said through holes (60), and further each of said bushings (55) being formed with an internal passage (56) therethrough; inserting the locking element (28) of the device (10) into the internal passage (56) of one of the bushes (55); engaging said tip portion (30) of said locking element (28) with said bushing (55); The method includes:

15. A seat rail (15) adapted for attaching an object (91), in particular a seat or monument, to said seat rail (15) in an aircraft or spacecraft (1), comprising a body (50) made of a fiber-reinforced synthetic material, in particular a fiber-reinforced thermoplastic synthetic material.

16. 16. The seat rail according to claim 15, characterized in that the body (50) is a rail body (50) having a flange (51), the flange (51) being provided with a plurality of through holes (60) arranged along the flange (51) according to a predetermined pattern, and the seat rail (15) further comprises a plurality of bushes (55) connected to the flange (51), each bush (55) being arranged at a position corresponding to the position of an associated one of the through holes (60), and further, each of the bushes (55) being formed with a passage (56) therethrough.

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