Apparatus for attaching objects, device for attaching objects and method

Abstract

The invention relates to a device for attaching an object, a device for attaching an object and a method. The device comprises a base portion having a support surface adapted to be placed on an outer surface of a rail, and a locking element adapted to partially protrude from the support surface along a protrusion line. The base portion and the locking element are coupled or configured to be coupled such that the locking element can be moved along the protrusion line and rotated relative to the base portion. An end section of the locking element has a tip portion shaped in a dovetail fashion. The device comprises a tensioning device for tensioning the locking element relative to the rail. The invention can facilitate reliable and fast attachment of objects and can in particular be used to prevent corrosion of the attached rail in a cost-effective manner.

Description

Technical Field

[0001] This invention relates to an apparatus for attaching an object to an attachment track, particularly a seat track in an aircraft or spacecraft. Furthermore, this invention relates to a device and method for attaching an object within an aircraft or spacecraft. Additionally, this invention relates to a seat track, particularly a seat track for an aircraft or spacecraft. Background Technology

[0002] Although the present invention can be used to attach various types of objects in many application areas, the invention and potential problems will be explained in more detail below with regard to seat tracks used in the passenger cabin of an aircraft (as an example of an attachment track).

[0003] It is generally known to attach passenger seats in an aircraft to seat tracks located in an area on the cabin floor.

[0004] An exemplary conventional seat track design is based on a profile track having an integral I-shape and including a protrusion on its upper side facing the cabin. This protrusion includes an undercut groove extending along the length of the track, with the groove's entrance widening at regular intervals through, for example, circular orifices. In a conventional example, these orifices may be regularly spaced 1 inch apart. The seat is secured to this track using specific inserts.

[0005] For example, DE 42 24 821 A1 shows a seat rail with this type of undercut groove and orifice.

[0006] It has been recognized that conventional seat tracks made of aluminum alloy are susceptible to corrosion, particularly in areas where spilled liquids may periodically come into contact with the seat tracks and adjacent floor components. This is especially true for areas with kitchens or bathrooms. This type of corrosion can be exacerbated by surface scratches, which may occur, for example, during seat installation, as the insert moves relative to the track.

[0007] Therefore, seat tracks made of titanium alloys, which have significantly higher corrosion resistance, have been proposed. However, such seat tracks are much more expensive than conventional aluminum tracks and undesirably increase the overall cost.

[0008] A seat track has been proposed in EP 1 544 105 A1 and US 2005 / 0156095 A1, which includes an upper section made of titanium alloy and connected to a lower section made of aluminum alloy.

[0009] Furthermore, US 2010 / 0038483 A1 describes a seat track with multiple spaced-apart openings and an assembly for connecting to such an aircraft seat track.

[0010] In addition, apparatus and methods for connecting a payload to a support track are described, for example, in US 7,370,832 B2, US 7,413,143 B2 and US 7,607,613 B2.

[0011] Furthermore, when using many of the existing types of assemblies, assembly operators or technicians must typically spend a significant amount of time attaching the objects to the seat tracks within the aircraft. This further increases costs, especially considering the large number of seats in, for example, commercial aircraft.

[0012] In this context, it will be desirable to be able to attach objects (such as seats, structures, or other equipment) in a further improved, cost-effective manner. In particular, it will be desirable to at least reduce the effort and cost required to date to prevent or delay attachment track corrosion, and / or to enable objects to be attached in a faster and less strenuous manner. Summary of the Invention

[0013] In view of this, the problem to be solved by the present invention is to provide an improved device for attaching an object to an attachment track, which enables the attachment of an object in a reliable and rapid manner, and is also adapted for use with tracks that help prevent corrosion in a cost-effective manner. A correspondingly improved apparatus and method will also be proposed. Furthermore, an attachment track, particularly a seat track, will be provided that allows corrosion to be avoided in an advantageous and cost-effective manner.

[0014] According to the present invention, this problem is solved by a device for attaching an object according to the present invention, and / or by a means for attaching an object according to the present invention, and / or by a method for attaching an object according to the present invention, and / or by a seat track according to the present invention.

[0015] Therefore, an apparatus for attaching an object to an attachment track, particularly a seat track in an aircraft or spacecraft, is proposed, wherein the apparatus includes: a base portion having a support surface adapted to rest on an outer surface of the attachment track, and at least one locking element adapted to partially protrude from the support surface of the base portion along a projection line. The base portion and the locking element are coupled or configured to be coupled such that the locking element is movable relative to the base portion along the projection line and is rotatable relative to the base portion. An end section of the locking element has a dovetail-shaped end portion. The apparatus further includes at least one tensioning device for tensioning the locking element relative to the attachment track when the support surface of the base portion rests on the outer surface of the attachment track and the end portion is in an engaged position relative to the attachment track.

[0016] Furthermore, an apparatus for attaching an object within a spacecraft or aircraft is proposed, comprising at least one device according to the invention and at least one attachment rail. The device includes at least one locking element, wherein an end section of the locking element has a dovetail-shaped end portion. The attachment rail includes a rail body and a plurality of bushings, wherein the rail body has an upper flange having a plurality of through holes arranged along the upper flange according to a predetermined pattern, and wherein the bushings are connected to the upper flange from the underside of the upper flange. Each bushing is arranged at a position corresponding to the position of one of the associated through holes, and further, each bushing forms an internal channel therethrough. The locking element of the device extends into the internal channel of one of the bushings, wherein the end portion is engageable with the bushing.

[0017] Furthermore, a method for attaching objects within an aircraft or spacecraft is provided. This method includes the following steps:

[0018] - Provide at least one device according to the invention, the device comprising at least one locking element, wherein the end section of the locking element has an end portion formed in a dovetail shape;

[0019] - Provide at least one attachment rail, the attachment rail including a rail body and a plurality of bushings, wherein the rail body has an upper flange having a plurality of through holes arranged along the upper flange according to a predetermined pattern, and wherein the bushings are connected to the upper flange from the underside of the upper flange, each bushing being arranged at a position corresponding to the position of one of the through holes, and further wherein each bushing forms an internal channel therethrough;

[0020] - Insert the locking element of the device into the internal channel of one of the bushings; and

[0021] - Engage the end portion of the locking element with the bushing.

[0022] Furthermore, the present invention provides a seat track adapted for attaching objects, particularly seats or structures, to a seat track within an aircraft or spacecraft, wherein the seat track comprises a body formed of a fiber-reinforced synthetic material. In particular, the body of the seat track may be formed of a fiber-reinforced thermoplastic synthetic material.

[0023] The basic idea of ​​this invention lies in using a locking element that is rotatable and movable along a rotation axis to tension the end portion of the locking element against a corresponding portion that is part of the attachment track. This allows the device to easily and quickly engage and lock onto the track. Therefore, the installation of a seat or other object can be easily performed in a bayonet-like manner in a short time. In particular, this invention provides an improved method for attaching an object to an attachment track having a row of spaced-apart orifices.

[0024] At the same time, if the important parts of the track (e.g., in the form of a body that forms part of the track) are made of a material other than metal, especially fiber-reinforced synthetic materials, the device makes it possible to attach objects to the attachment track quickly and reliably.

[0025] Therefore, the present invention provides a reliable and rapid attachment of objects (e.g., seats or structures) to attachment tracks having a geometry that can be suitably manufactured using methods other than metal extrusion. More specifically, the present invention provides a reliable and rapid attachment of objects to attachment tracks, particularly seat tracks, made of fiber-reinforced plastic materials to prevent track corrosion in a cost-effective manner.

[0026] Advantageous improvements and developments of the invention are contained in the appended aspects of the invention and in the description with reference to the accompanying drawings.

[0027] As developed, the locking element has a roughly pin-shaped form. This type of locking element can be easily manufactured.

[0028] According to the improvement, the locking element includes a portion having a generally cylindrical external shape and configured to be received in an opening in the base portion and extend through the opening. In this way, the locking element can be conveniently configured to allow it to move and rotate linearly relative to the base portion.

[0029] According to the improvement, the end section of the locking element is formed with a shape that is flattened relative to the portion having a generally cylindrical external shape, wherein the end section is laterally contained within an imaginary extension of the side surface of the portion having a generally cylindrical external shape. In this way, the connection between the locking element and the base portion can be achieved in a simple manner.

[0030] With further development, the locking element is adapted to be inserted forward and partially into a channel that extends from the outer surface of the attachment rail into the attachment rail. Therefore, the locking element can engage with the attachment rail in a simple and quick manner.

[0031] According to the development, the end section includes recesses on its opposite narrow side, wherein each recess includes a retaining surface extending obliquely relative to the longitudinal axis of the locking element. This further facilitates the simplification of the production of the locking element, as the recesses can be conveniently implemented in the narrow side of the flattened end section to produce a dovetail shape.

[0032] In particular, the dovetail shape is formed symmetrically, which promotes uniform load distribution.

[0033] In development, the tensioning device includes at least one cam pivotally coupled to a locking element, and / or the tensioning device includes a lever for applying a tension load to the locking element. Specifically, the lever may be operable to pivot one or more cams. In particular, the lever and cam may both be formed as an integral part of a single tensioning component comprising the lever and(s) of the cam(s). In this way, the locking element can be tensioned quickly and easily, particularly by hand, without the need for special tools. The lever and cam may preferably be configured such that once one or more cams are in a tensioned state, they remain in that tensioned state unless the lever is operated.

[0034] According to the improvement, the base portion has an additional protrusion formed on the support surface at a location spaced apart from the locking element. In this improvement, the protrusion can be integrally formed with the base portion or can be formed by an additional element fixedly connected to the base portion. Furthermore, in this improvement, the protrusion is adapted to insert into another channel extending from the outer surface into the attachment rail. In this way, rotation of the device, particularly its base portion, relative to the rail is prevented, and loads acting on the device parallel to its outer surface, particularly loads in the X direction parallel to the longitudinal axis of the attachment rail, can be transmitted to the rail via the protrusion.

[0035] According to development, the base section includes a plate-shaped section with a supporting surface.

[0036] In further development, the base portion is provided with a connection section adapted to mechanically connect with the object to be attached.

[0037] In a further improvement, the device may include several locking elements and / or several tensioning devices. In particular, the device may include two locking elements and two tensioning devices. In this way, even higher loads (e.g., loads for attaching larger and / or heavier objects) can be transferred to the track.

[0038] The object to be attached can be, in particular, a seat for an aircraft or spacecraft, such as a passenger seat. In a preferred development, the device is formed as an assembly, particularly a rear assembly, for attaching a passenger seat of an aircraft or spacecraft to an attachment track. Using the device proposed in this invention, the seat can be quickly and easily installed or reinstalled and attached to a seat attachment track, and particularly to an attachment track made of fiber-reinforced synthetic material.

[0039] In alternative developments, the object to be attached can be, for example, a structure, particularly a kitchen structure, lavatory structure, or storage structure located in the cabin of an aircraft or spacecraft. Specifically, the device can be configured as an assembly for attaching the structure to an attachment track within the cabin of the aircraft or spacecraft. Therefore, the structure can be attached to the cabin in a simple and rapid manner.

[0040] In development, the internal channel of each bushing includes a channel portion forming an elongated cross-section. In particular, the channel portion can be centered relative to another axial portion of the internal channel. Due to the channel portion and its elongated shape, engagement between the end portion and the bushing can be achieved quickly and easily, especially by rotational or pivotal movement of the locking element, for example by an angle of less than 180 degrees, preferably about 90 degrees.

[0041] In a further development, each bushing includes a contact surface on the side of the bushing opposite to the upper flange of the track body. This contact surface is adjacent to a channel portion with an elongated cross-section, and the contact surface of the bushing is adapted to contact the retention surface of the end portion of the locking element. In this development, the contact surface of the bushing is shaped such that a recess is formed on the side of the bushing opposite to the upper flange. In particular, the contact surface of the bushing can be concave. This development promotes surface contact between the end portion and the bushing and helps prevent stress concentration. In this way, significant loads acting on the locking element can be safely and reliably transferred to the track.

[0042] In a further improvement, the bushing includes a generally cylindrical cavity on its upper flange side facing the attachment track, which is at least partially disposed within a through-hole associated with the bushing. Specifically, the internal dimensions of the cylindrical cavity, more particularly the inner diameter, may correspond approximately to the internal dimensions, especially the inner diameter, of the opening in the base portion (which is adapted to receive a portion of the locking element having a generally cylindrical external shape), or may be slightly larger. In this way, the portion having a generally cylindrical external shape can be partially received within and guided within the generally cylindrical cavity, which facilitates stable and reliable operation of the device.

[0043] The internal cross-sections of both the cylindrical cavity and the opening in the base portion can be approximately circular.

[0044] In development, bushings have incorporated generally rotationally symmetrical external shapes. For example, bushings can be formed with a generally circular external profile. Such bushings can be manufactured relatively easily.

[0045] Furthermore, according to the improvement, the bushing includes an outwardly extending collar adapted to abut against the track body to support the bushing. In this way, forces introduced into the bushing can be transmitted to the track body without causing excessive stress at the interface between the bushing and the track body, thereby reliably preventing damage, especially damage to the track body.

[0046] In a preferred development, the track body is made of fiber-reinforced synthetic material, particularly carbon fiber-reinforced synthetic material. Preferably, the synthetic material is a thermoplastic material.

[0047] Specifically, the track body comprises a cross-section generally shaped like an omega. The omega-shaped design is well-suited for manufacturing composite track bodies from fiber-reinforced synthetic materials, particularly in continuous manufacturing processes.

[0048] In alternative development, the track body can be made of sheet metal using a folding process.

[0049] With further improvements, the locking element and / or the base portion and / or the cam and lever are all made of metallic material. In this way, a robust device can be obtained. Furthermore, forming the locking element from metallic material facilitates the reliable transfer of loads acting on the locking element to the track, particularly in cooperation with bushings made of metallic material.

[0050] According to preferred developments, the bushings are all made of metallic materials, particularly titanium or steel.

[0051] In further development, the device can be configured to prevent rotation of the locking element and / or lever operation when the locking element is tensioned relative to the attachment rail by the tensioning device. In this way, accidental unlocking and disengagement of the device can be avoided.

[0052] In the development of the seat track proposed in this invention, the body formed of a fiber-reinforced synthetic material is the track body, wherein the track body has a flange, particularly an upper flange, which is provided with a plurality of through holes arranged along the flange according to a predetermined pattern. According to this development, the seat track further includes a plurality of bushings connected to the flange, wherein each bushing is arranged at a position corresponding to the position of one of the associated through holes, and further wherein each bushing forms a channel therethrough. In particular, the bushings are made of a metallic material, particularly titanium or steel.

[0053] Furthermore, in particular, the aforementioned developments and improvements related to the bushing and the track body formed of fiber-reinforced synthetic material can be applied to the seat track proposed in this invention.

[0054] Wherever meaningful, improvements, enhancements, and developments of the present invention can be combined arbitrarily with each other. Moreover, other possible enhancements, developments, and implementations of the present invention include combinations of features of the present invention (which have been described above or will be described in the detailed description of the embodiments below), even if such combinations are not explicitly mentioned.

[0055] In particular, the improvements, enhancements and developments of the invention described above can be applied in a similar manner to each of the devices, apparatuses, methods and seat tracks proposed herein. Attached Figure Description

[0056] The present invention will now be explained with reference to the accompanying drawings illustrating embodiments thereof. Wherein:

[0057] Figure 1 An exemplary aircraft is shown in a side view, in which embodiments of the present invention can be used;

[0058] Figure 2 The device and apparatus according to embodiments of the present invention are shown in a perspective top view;

[0059] Figure 3 The central longitudinal section view I-I shows the results according to Figure 2 The apparatus and devices of the embodiments;

[0060] Figure 4 Showing according to Figure 2 and Figure 3 A top view of the apparatus of an embodiment;

[0061] Figure 5 Showing according to Figures 2 to 4 An end view of the device in an embodiment;

[0062] Figure 6A As shown in Figures 2 to 5 Side views of three exemplary bushings used in the device;

[0063] Figure 6B Showing Figure 6A Top view of the bushing;

[0064] Figure 6C Showing Figure 6A Another side view of the bushing;

[0065] Figure 6D It shows, as Figure 6B Sectional view II-II of the bushing indicated in the figure;

[0066] Figure 6E It shows, as Figure 6B Another cross-sectional view of the bushing indicated in the figure, III-III;

[0067] Figure 7A The previous view showed according to Figures 2 to 5 The device in the embodiment has a locking element in the form of a center pin;

[0068] Figure 7B Shown in side view Figure 7A Locking element;

[0069] Figure 8A The side view shows the results according to Figures 2 to 5 The base portion of the device in an embodiment;

[0070] Figure 8B Shown in top view Figure 8A The base portion;

[0071] Figure 8C Shown in end view Figure 8A The base portion;

[0072] Figure 9A The side view shows the results according to Figures 2 to 5 Components of the tensioning device of the embodiment of the equipment;

[0073] Figure 9B Shown in top view Figure 9A Components;

[0074] Figure 9C Shown in end view Figure 9A Components;

[0075] Figure 10A Shown in top view according to Figures 2 to 5The track body of the attachment track of the embodiment of the device;

[0076] Figure 10B For example Figure 10A The central longitudinal section view IV-IV, as indicated in the figure, shows... Figure 10A The main body of the track;

[0077] Figure 10C Showing Figure 10A An end view of the main track structure; and

[0078] Figure 11 A perspective view showing the situation from below the attached track. Figures 2 to 5 Some components of the apparatus in the embodiments.

[0079] The accompanying drawings are intended to illustrate embodiments of the invention, enabling a further understanding of the invention. In conjunction with the description, the drawings are intended to explain the principles and concepts of the invention. Other described embodiments and numerous advantages can be inferred from the drawings. Elements in the drawings are not necessarily drawn to scale.

[0080] Identical elements, features, and parts that have the same function or effect are labeled with the same reference numerals in the drawings, unless otherwise expressly stated. Detailed Implementation

[0081] Figure 1 The image shows a passenger aircraft 1, which includes a fuselage 3, wings, stabilizers, and engines. Inside the fuselage 3, aircraft 1 includes a passenger cabin with a cabin floor 6, such as... Figure 1 Indicative indication.

[0082] To reliably and quickly attach passenger seats to the cabin floor 6, the cabin floor 6 includes multiple seat attachment rails or seat rails 15. Figure 1 In the exemplary aircraft 1, the seat attachment rails 15 all extend along the cabin floor 6 in the longitudinal direction X of the aircraft 1. Direction Z represents the vertical direction; see [reference needed]. Figure 1 In addition, the lateral direction Y is shown.

[0083] Figures 2 to 5 and Figure 11 The image shows a device 100 for attaching objects 91, such as passenger seats, inside an aircraft 1. The device 100 includes a seat attachment rail 15 and a device 10, which is used to attach the passenger seat 91 to the seat attachment rail 15. Figures 2 to 5 and Figure 11 The invention also demonstrates a method and a seat track 15, which is part of the device 100, according to an embodiment of the invention.

[0084] Figure 2The image shows a short segment of orbit 15. For greater clarity, in... Figures 2 to 5 The cabin floor 6 and any supporting structures for it (such as those supporting the seat rail 15) are omitted. When installed as part of the cabin floor 6, the seat attachment rail 15 will typically be significantly longer than [the specified length]. Figure 2 The section shown is for demonstration purposes.

[0085] exist Figure 2 Only a portion of the rear legs of seat 91 is shown schematically. Figures 2 to 5 In the example, device 10 is configured as a rear assembly for attaching the rear legs of seat 91. Figures 2 to 5 The device 10 is shown in its locked state, in which the completion has been... Figure 2 The attachment of the rear legs of seat 91 is indicated schematically in the middle.

[0086] Figures 2 to 5 The seat attachment track 15 includes a track body 50 having a cross-section that is generally shaped like an omega. The cross-sectional shape of the track body 50 is symmetrical, and its basic shape is substantially constant along the longitudinal direction of the track 15, which is shown as parallel to the direction of view. Figure 1 The X direction defined by aircraft 1. Figures 10A to 10C The main body of the track 50 is shown separately again in the image.

[0087] More specifically, see, for example Figure 2 The track body 50 is provided with an upper flange 51, a web 52, and a lower flange 53. When the track 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, while the web 52 extends parallel to the XZ plane. Therefore, when the aircraft 1 is on the ground, the web 52 is oriented approximately vertically, while the flanges 51 and 53 are approximately horizontal.

[0088] When the attachment 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, wherein the upper surface 16 faces the cabin interior.

[0089] The webs 52 extend parallel to each other. The first end of each web 52 is integrally connected to an upper flange 51, while the second end of each web 52 is integrally connected to one of the lower flanges 53. A passage 54 is formed between the webs 52 (viewed from below the track 15), defined by the upper flange 51 on the top side of the track 15. The lower flanges 53 all extend laterally outward from the second lower end of each web 52. The upper flange 51 laterally protrudes beyond the first upper end of each web 52.

[0090] Figure 2It is also shown that the track body 50 has a row of through holes 60 in the upper flange 51, and these through holes preferably each have a circular cross-section. Figure 2 In the example, the through holes 60 are arranged at equal intervals, that is, they are spaced at equal distances between adjacent through holes 60 along the longitudinal direction of the attachment track 15. Figure 2 This corresponds to the X direction. Specifically, Figure 2 All through holes 60 are formed in the same manner. Through holes 60 can be formed, for example, by drilling into the upper flange 51.

[0091] Figures 2 to 5 , Figures 10A to 10C and Figure 11 The track body 50 is made of a fiber-reinforced synthetic material, preferably a fiber-reinforced thermoplastic synthetic material. In particular, the track body 50 may preferably include carbon fibers as reinforcing fibers embedded in the synthetic matrix material, preferably a thermoplastic matrix material. This track body 50 is relatively lightweight, can be produced at a reasonable cost, and helps to prevent corrosion of the seat track 15. For example, the track body 50 can be produced by using a continuous production method to manufacture a semi-finished product and then drilling through holes 60.

[0092] Part of the cabin floor 6 can be equipped with Figures 2 to 5 and Figure 11 (Especially in the so-called "wet" area, where liquid spillage is expected) the type of seat track 15 shown. However, specifically, the entire cabin floor 6 can be provided with, as referenced, in both the so-called "wet" and so-called "dry" areas. Figures 2 to 5 and Figure 11 The seat track 15, in which liquid spillage is unlikely to occur in the "dry" area. Therefore, using Figures 2 to 5 and Figure 11 The track 15 can significantly facilitate the process of equipping the cabin floor 6 with seat tracks, and can reduce the corresponding effort and cost.

[0093] Figure 2 The device 10 shown is in Figures 3 to 5 It is shown again in the middle, in the position of and Figure 2 The same locked state.

[0094] Equipment 10 or rear assembly including base portion 21, see also Figures 8A to 8C The base portion 21 includes a plate-shaped section 21a, wherein a substantially flat support surface 22 is formed on the bottom side of the section 21a. Furthermore, the plate-shaped section 21a is provided with a circular opening 23, which forms a through-hole from the bottom side to the top side of the section 21a.

[0095] Figure 3 , Figure 8A and Figure 8C Additionally, the plate-shaped section 21a of the base portion 21 is further provided with a protrusion 78, which protrudes from the support surface 22 at a position spaced apart from the position of the opening 23 on the surface 22.

[0096] The protrusion 78 may be integrally formed with the plate-shaped section 21a, for example, or the protrusion 78 may be formed by fixing a protruding element to the plate-shaped section 21a. The lateral outer surface 79 of the protrusion 78 has a cylindrical shape.

[0097] The base portion 21 is substantially symmetrical with respect to its longitudinal centerline, which corresponds to Figure 2 The X direction is shown in the installation state.

[0098] On the upper side of the plate-shaped section 21a, opposite to the supporting surface 22 of the base portion 21, the base portion 21 further includes three additional protrusions, which are shaped in the manner of upright plate-shaped first sections 24, second sections 25a and third sections 25b extending from the upper side of section 21a.

[0099] A connecting section is formed by a first upright section 24 arranged on the centerline of section 21a and positioned on the front side relative to opening 23. This connecting section is adapted to mechanically connect with the seat 91 to be attached. For attaching the seat 91, particularly its rear legs, the connecting section 24 is provided with an opening 24a in the form of a through hole or eyelet.

[0100] The second section 25a and the third section 25b have approximately the same shape and are symmetrically arranged on both sides of the center line of the base portion 21, on the rear side relative to the opening 23. The functions of sections 25a and 25b will be explained further below.

[0101] Device 10 further includes a locking element 28, which has a pin-shaped form and, Figure 7A , Figure 7B Shown separately. Locking element 28 serves as the center pin 28 of device 10.

[0102] Locking element 28 includes portion 31, in Figure 7A , Figure 7B The middle corresponds to the upper portion of the locking element 28, which has a generally cylindrical external 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 section 31 is generally circular.

[0103] Near one end of the locking element 28, the cylindrical portion 31 is provided with a transverse through hole 49, which is formed as a cylindrical hole with a circular cross-section. The function of the through hole 49 will be further described below.

[0104] For example, the diameter of portion 31 can be selected to substantially correspond to the diameter of opening 23, and tolerances or clearances are selected such that the cylindrical portion 31 can be slidably and rotatably received within opening 23. In this way, locking element 28 can be inserted into opening 23. Figure 2 , Figure 3 and Figure 5 For example, it can be inserted into the opening from above the base portion 21, and thus can be connected to the base portion 21.

[0105] Make locking element 28 (in) Figures 2 to 5 and Figure 11 In the current state, the locking element 28 is partially received in the opening 23 and extends through the opening, and is able to move linearly along axis A and rotate 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.

[0106] Locking element 28 further includes an end section 29, the end section being in Figure 7A , Figure 7B The middle corresponds to the lower part of the locking element 28. The shape of the end section 29 is flattened relative to the upper part 31. Figure 7A , Figure 7B The end section 29 is shown to be laterally contained within an imaginary extension of the substantially cylindrical side surface 32 of the portion 31. For example, it may be advantageous to manufacture the locking element 28 by removing material from the initial cylindrical pin, such as by milling or other material removal processes.

[0107] For example, Figures 7A to 7B The end section 29 is also shown to include an end portion 30 located at the end of the locking element 28 opposite to the end including the transverse hole 49, wherein the end portion 30 is formed in a dovetail shape. On the opposite narrow side 34 of the end section 29, recesses 33 are symmetrically arranged with respect to axis A. The recesses 33 may, for example, be cut into the narrow side 34 during the manufacture of the locking element 28. Each recess 33 includes a retaining surface 35 extending obliquely with respect to the longitudinal axis A of the locking element 28. The dovetail shape of the end portion 30 is obtained by forming these recesses 35. While each retaining surface 35 may be flat, it is preferably convex for a more uniform distribution of pretension and retaining force, as will be described in more detail below.

[0108] In the assembled state of device 10, such as Figures 2 to 4As shown, pin 48 passes through through hole 49 of locking element 28. Pin 48 pivotally connects two cams 46 on both sides of section 31 to locking element 28. The two cams 46 are formed to have the same shape, and both are integrally formed with lever 47. Therefore, cams 46 and lever 47 form part of an integral component, which in Figures 9A to 9C It is shown separately again in the text.

[0109] Each cam 46 is provided with an opening 46a, each opening receiving the end of a pin 48. The pin 48 can be tightly fitted into the through hole 49 or the opening 46a.

[0110] The attachment rail 15 is provided with multiple bushings 55, see details. Figure 3 , Figure 5 , Figures 6A to 6E and Figure 11 At each location of a through-hole 60 in the upper flange 51 along the longitudinal direction of the track 15, one of a plurality of bushings 55 is connected from the underside of the upper flange 51 to the upper flange. Thus, before the track 15 is installed as part of the cabin floor 6, each through-hole 60 is equipped with one of the bushings 55.

[0111] In the embodiment shown in the accompanying drawings, all bushings 55 are formed in the same manner, and each bushing is made of a metallic material, such as titanium alloy or steel.

[0112] Each bushing 55 comprises a generally rotationally symmetrical external shape. More specifically, the external shape of each bushing 55 is that of a substantially cylindrical body having a circular external cross-sectional shape and being provided with an outwardly extending annular collar 55a. The collar 55a extends circumferentially on the outer side of the bushing 55, see [reference needed]. Figure 3 , Figure 5 , Figures 6A to 6E and Figure 11 Along the longitudinal central axis of the bushing 55 and viewed from its outer side, the bushing 55 has two sections in the axial direction, wherein the boundary between the two sections is defined by the collar 55a.

[0113] exist Figure 3 and Figure 6A The upper section 61 of the bushing 55 located on the side above the collar 55a is configured to be introduced into a corresponding through-hole 60 assigned to the bushing 55. For each bushing 55, section 61 thus forms an insertion section 61, which is introduced into the corresponding through-hole 60 until the collar 55a is adjacent to the lower side of the upper flange 51. In this state, preferably, the end face of the insertion section 61 away from the collar 55a can be substantially flush with the outer surface 16 of the upper flange 51, or can be slightly offset toward the interior of the through-hole 60.

[0114] The collar 55a is adapted to abut against the track body 50 to support the bushing 55 via the lower side adjacent to the upper flange 51. Specifically, the collar 55a is adapted to introduce a force into the upper flange 51, which is in the positive Z direction, i.e. Figure 3 The upward force, perpendicular to the upper flange 51, acts on the bushing 55.

[0115] Using the contact surface portions of the upper flange 51 and the bushing 55, particularly inside the through-hole 60 on the underside of the upper flange 51 and the contact surface portions around the bushing 55, the bushing 55 and the track body 50 are securely connected, for example, by welding or by adhesive bonding. Welding can be accomplished, for example, by localized melting or softening of the thermoplastic matrix of the track body 50.

[0116] For demonstration purposes, Figure 3 Three bushings 55 connected to the upper flange 51 are shown. However, it should be understood that, as described above, preferably, each of the through holes 60 will be provided with one of the bushings 55. Therefore, the seat track 15 of this embodiment will typically have a plurality of bushings 55 along its length.

[0117] Each bushing 55 has an internal longitudinal channel 56 extending from the upper end of the bushing 55 to the lower end.

[0118] On the upper side of the bushing 55 (which turns toward the upper flange 51 when the bushing 55 is connected to the track 15 and is partially inserted into the through hole 60), a first portion of the channel 56 is formed with a generally cylindrical cavity 59, which is at least partially located inside the through hole 60 associated with the bushing 55.

[0119] The inner diameter (as its lateral dimension) of the roughly cylindrical cavity 59 can roughly correspond to the lateral dimension or diameter of the opening 23, or can be slightly larger. The internal cross-section of the cavity 59 is roughly circular.

[0120] The bottom of cavity 59 is preferably substantially flat. A portion 57 of the internal channel 56 extends through the bottom of cavity 59, see [reference needed]. Figure 6B , Figure 6D It has an elongated cross-section. The channel portion 57 is centrally located at the bottom of the cavity 59, so the center lines of the cavity 59 and the channel portion 57 coincide.

[0121] On the lower side of bushing 55 (which faces away from the upper flange 51 of track body 50), channel portion 57 leads to a relatively shallow cavity or recess defined by contact surface 58, such as Figure 6E , Figure 11As shown in the diagram. In this embodiment, the shallow cavity or recess forms the final portion of the internal channel 56 of the bushing 55. The channel portion 57 extends centrally into the recess within the contact surface 58. The contact surface 58 may, for example, be formed as part of a conical or spherical surface.

[0122] It should be noted that the height of bushing 55, especially in the direction perpendicular to the upper flange 51, may differ from, for example, Figure 3 , Figures 6A to 6E The height shown in the figure. For example, in a variant, the axial dimension of bushing 55 and the length of locking element 28 can be varied to be shorter or longer than shown in the figure.

[0123] To attach objects such as passenger seats 91 to seat tracks 15 installed within the aircraft 1 as part of the cabin floor 6, the device 10 is placed on the attachment track 15 such that the support surface 22 is arranged on the upper surface 16 of the track 15. This is shown in Figure 2 In the middle. The device 10 is arranged such that the center line of the opening 23 coincides with the center line of one of the through holes 60 and the center line of the bushing 55 assigned to the through hole 60.

[0124] When the base portion 21 is placed on the track 15, the locking element 28 may already be attached to the base portion 21, or once the base portion 21 rests on the outer surface 16 of the track 15, the locking element 28 may be inserted into the opening 23 with its end portion 30 in front and pass through the opening.

[0125] In both cases, the cylindrical portion 31 is slidably and rotatably received in the opening 23, and upon insertion, the locking element 28 protrudes downward from the support surface 22 along the protrusion line 36, see [reference needed]. Figure 3 Protruding line 36 Figure 3 The axis A corresponds to the locking element 28. In this way, when the base portion 21 and the locking element 28 are connected, and before the device 10 is securely attached to the track 15 (as will be described below), the locking element 28 can move relative to the base portion 21 along the protruding line 36, and can rotate relative to the base portion 21 about the line 36 in the opening 23.

[0126] Each bushing 55 has a segment 61 located within a through hole in the through hole 60. Therefore, access to the channel 56 of each bushing 55 is possible from the outer surface 16 of the upper flange 51. When the device 10 is placed on the track 15, or when the locking element 28 is inserted after the base portion 21 has been placed on the track 15, the locking element 28 is inserted forward, partially, with its end portion 30 inserted into the channel 56, which extends through the bushing 55 and thus through the upper flange 51 of the attached track 15.

[0127] Inserting the end portion 30 of the locking element 28 into the channel 56 is such that the long side of the end portion 30 is transverse to, and particularly perpendicular to, the longitudinal direction of the track 15 (and). Figure 2 This is performed under the condition that the X direction is consistent (in the same direction). This corresponds to the unlocking orientation U of the end portion 30, which is in Figure 2 and Figure 4 The diagram is schematically shown with a dotted line. Furthermore, when the end portion 30 is inserted into the channel 56, the components including the lever 47 and the cam 46 are in a position (not shown) in which the lever 47 is oriented upright from the plate-shaped section 21, for example, generally parallel to axis A.

[0128] In other words, in order to insert the end portion 30 into the internal channel 56, and with Figures 2 to 5 Compared to the case shown, lever 47 will pivot upward by, for example, an angle of about 90 degrees, and locking element 28 will be rotated to orient the long side of end portion 30 laterally (as indicated by the dotted line U), for example by rotating locking element 28 by an angle of about 90 degrees.

[0129] Furthermore, when the base portion 21 is placed on the upper surface 16 of the attachment track 15 such that the opening 23 is centered on one of the through holes 60 and the associated bushing 55, the protrusion 78 can be inserted into the cavity 59 of another bushing in the bushing 55 assigned to another through hole 60. In the embodiment shown in the figures, the protrusion 78 can be inserted into the cavity 59 of the bushing 55 at a position adjacent to the through hole 60, with the opening 23 centered on that through hole. However, in a variation of this embodiment, the distance between the protrusion 78 and the opening 23 can be different, for example, so that the protrusion 78 can be inserted into the bushing 55 after the next protrusion seen from the opening 23, i.e., leaving an unused bushing 55 in between.

[0130] In this embodiment, the outer diameter of the cylindrical protrusion 78 can be slightly larger than the outer diameter of the segment 31 of the locking element 28. Besides preventing the device 10 from rotating as a whole on the surface 16, i.e., about the Z direction, the protrusion 78, sized in this way, allows forces acting in the X direction to be reliably transmitted from the base portion 21 to the track 15 via the protrusion 78. The protrusion 78 thus forms a so-called passive forward interface point, which does not transmit loads acting in the positive Z direction perpendicular to the surface 16 of the upper flange 51.

[0131] After the locking element 28 is inserted and passes through the channel 56, such that the end portion 30 has been fully guided through the channel portion 57 and has exited the channel portion in the lower end region of the bushing 55, the end portion 30 can engage with the bushing 55 by means of its dovetail shape through rotation of the locking element 28 about axis A. More specifically, in order to lock the device 10 to the attachment rail 15, the locking element 28 is rotated about axis A by, for example, approximately 90 degrees, so as to align the long side of the end portion 30 with the longitudinal direction of the rail 15. For example, this orientation of the end portion 30 corresponds to its locking orientation L, which in Figure 11 As shown in the image. Figure 11 It is also shown that the channel portion 57 of each bushing 55 is oriented such that the longitudinal direction of the portion 57 (parallel to the long side of the channel portion 57) extends transversely to the longitudinal direction of the track 15 (shown as parallel to direction X). Therefore, the device 10 can engage with and lock onto the track 15 in a bayonet mechanism.

[0132] The lever 47, cam 46, and pin 48 described above form the tensioning device 45. After engaging the end portion 30 of the locking element 28 with the bushing 55 by rotating the locking element 28, the operator pivots the lever 47 in a downward direction. Figure 2 and Figure 3 The position shown is indicated. According to the pivoting motion of lever 47, cam 46, integrally formed with lever 47, rotates about the axis of pin 48. Cam 46 is supported on the upper surface of plate-shaped section 21a. By moving lever 47 downward and rotating cam 46, pin 48 and locking element 28 are pulled upward in the positive Z direction. Therefore, end portion 30 is pulled against bushing 55, such that retaining surface 35 is pressed against contact surface 58, and tension load is applied to locking element 28 to pre-tension the device 10 including base portion 21 relative to track 15. The configuration of pin 48, lever 47, and cam 46, particularly including the position of pin 48 and the profile of cam 46, is chosen such that... Figure 2 and Figure 3 In this state, unless lever 47 is raised, tensioning device 45 will remain in a clamped and tensioned state.

[0133] Due to the dovetail shape of the end portion 30, when the locking element 28 is not tensioned, the end portion 30 can rotate smoothly within a shallow recess at the lower end of the bushing 55. The contact surface 58 is adapted to make surface contact with the retaining surface 35. See also Figure 1 , Figure 2 and Figure 3The force acting on the locking element 28 in the positive Z direction is transmitted to the bushing 55 via the retaining surface 35. These surface contacts with the contact surface 58 avoid localized stress concentration and help to evenly distribute the force to be transmitted. Furthermore, the dovetail shape of the end portion 30 can help improve the centering of the locking element 28 or the center pin 28 relative to the bushing 55.

[0134] When the device 10 is locked and tensioned onto the track 15, the force acting on the locking element 28 in the positive Z direction is transmitted via the collar 55a at the opening 23 to the upper flange 51, and thus to the track body 50. The force (e.g., weight) acting on the base portion 21 in the negative Z direction is supported via the support surface 22. Moreover, the strong connection between the bushing 55 and the track body 50, for example by welding or adhesive bonding, prevents the bushing 55 from separating from the track body 50 due to forces acting during the installation of the device 10, particularly downward forces.

[0135] Device 10 may preferably be adapted to prevent the locking element 28 from rotating about axis A when the locking element 28 is tensioned relative to the attachment rail 15, so as to prevent, for example, accidental unlocking of device 10. Figure 2 and Figure 3 The anti-rotation sections 25a and 25b shown can be configured to at least prevent or avoid rotation of the lever 47 coupled to the locking element 28 about axis A by providing lateral guidance and lateral stops. Additional means for preventing rotation of the lever 47 about the axis of the pin 48 may be included, if desired, to prevent unintentional unlocking and / or misuse. For example, a cover, latch, or stop mechanism that can only be released using special tools may be provided for this purpose.

[0136] In the embodiments described above, the locking element 28, the body of the base portion 21 including sections 21a, 24, 25a-b and protrusion 78, the component integrally including cam 46 and lever 47, and pin 48 are all made of a metallic material, which may in particular be an aluminum alloy, a titanium alloy, or steel. The same or different materials may be used for components 28, 21, 46, 47, and 48 of the device 10.

[0137] Because the bushing 55 and locking element 28 are formed from one or more metallic materials (such as titanium or steel), these components can be formed to be wear-resistant and corrosion-resistant at a limited cost. The body 50 of the track 15 can be made of fiber-reinforced composite materials, such as carbon fiber reinforced thermoplastic, and is therefore lightweight and promotes corrosion resistance. The use of bushing 55 and locking element 28 made of metal prevents damage to the track body 50 and excessive loads on the surface of this composite material during the installation and locking of the device 10. In this way, the device 10 also helps to avoid edge deterioration, for example, at the through hole 60, when the device 10 is repeatedly installed and removed. When the device 10 is installed and under load, the bushing 55 ensures a smoother and more distributed load application from the center pin 28 to the seat track 15.

[0138] Furthermore, the omega shape of the track body 50, combined with the load introduced via bushings 55 (which are arranged at the locations of the through holes 60 in the upper flange 51 along its centerline), not only prevents damage to the composite track body 50 by preventing excessive local concentration of contact forces, but also provides a stable flange 51 that resists deformation or unfolding due to its geometry and symmetrical loads, thereby preventing damage to the substrate.

[0139] In another variation of the device 10 described above, the base portion 21 may be provided with a section 21a having more than one opening 23 (e.g., two openings 23), more than one locking element 28 (e.g., two locking elements 28), and more than one tensioning device 45 (e.g., two devices 45). In this variation, the openings 23 are arranged along the longitudinal direction of the section 21a such that each of the two locking elements 28, both received in one of the openings 23, can be inserted into the channel 56 associated with the two through holes 60. Furthermore, in this variation, the lever 47 and cam 46 of each tensioning device 45 can be operated independently of the other device 45, thereby allowing the locking elements 28 to be tensioned independently of each other. For example, when engaging and locking the device 10, the free ends of each lever 47 can point towards each other. In this way, higher loads can be supported by the device 10 and transmitted to the track 15.

[0140] It should be noted that, in a further variation of the embodiment explained above, an intermediate protective layer (not shown in the figures) may be disposed between the plate-shaped segment 21a and the outer surface 16 of the upper flange 51. For example, such a protective layer (e.g., a protective layer made of a metal sheet or a sheet of synthetic material) may be disposed over the entire surface 16, or preferably on the bottom surface of the plate-shaped segment 21a, such that the protective layer becomes part of the base portion 21, wherein in the latter case, the supporting 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 synthetic material on the bottom surface of the plate-shaped segment 21. In this way, corrosion can be prevented in a further improved manner by means of the intermediate layer.

[0141] The attachment of passenger seat 91 to attachment rail 15 using device 10 has been described in detail above. However, the present invention can be used to attach other objects to attachment rail 15. In some examples, device 10 may be configured as an assembly for attaching a structure (not shown) to the cabin. For example, the attached structure may be a galley structure, a lavatory structure, a storage structure, or other types of objects to be attached to attachment rail 15. In particular, the coupling section 24 may be modified or adjusted if it is suitable for attaching an object 91 other than the seat.

[0142] Furthermore, while it is particularly preferred that the track body 50 of the seat attachment track 15 be made of fiber-reinforced synthetic materials, especially thermoplastic reinforced with carbon fiber, the track body 50 may be formed of metallic materials, for example, using folded metal sheet technology, in alternative embodiments.

[0143] Although the present invention has been fully described above with reference to preferred embodiments, the present invention is not limited to these embodiments, but can be modified in various ways.

[0144] List of reference numerals

[0145] 1 aircraft

[0146] 3 fuselage

[0147] 6 Cabin Floor

[0148] 10 devices

[0149] 15 Attached Rails

[0150] 16 outer surfaces

[0151] 21 Base Part

[0152] 21a plate-shaped section

[0153] 22 Support Surface

[0154] 23 openings

[0155] 24 connecting sections

[0156] 24a opening

[0157] 25a Anti-rotation section

[0158] 25b anti-rotation section

[0159] 28 locking elements

[0160] 29 end sections

[0161] 30 end section

[0162] 31 Cylindrical section

[0163] 32 side surfaces

[0164] 33 concavity

[0165] 34 Narrow Side

[0166] 35 fixed surface

[0167] 36 protruding lines

[0168] 45 tensioning device

[0169] 46 Cams

[0170] 46a opening

[0171] 47 levers

[0172] 48 sales

[0173] 49 holes

[0174] 50 track main body

[0175] 51 Upper flange

[0176] 52 webs

[0177] 53 Lower flange

[0178] 54 channels

[0179] 55 bushing

[0180] 55a collar

[0181] 56 Internal passage (shroud)

[0182] 57-channel section

[0183] 58 contact surfaces

[0184] 59 cavities

[0185] 60 through hole

[0186] Section 61 (Bushing)

[0187] 78 protrusions

[0188] 79 Lateral outer surface (protrusion)

[0189] 91 objects

[0190] 100 devices

[0191] A. Longitudinal axis (locking element)

[0192] L-shaped locking orientation (locking element)

[0193] U-shaped unlocking orientation (locking element)

[0194] XX direction

[0195] YY direction

[0196] ZZ direction

Claims

1. A device (10) for attaching an object (91) to an attachment track (15). The device (10) includes: The base portion (21) has a support surface (22) adapted to be placed on the outer surface (16) of the attachment track (15); and at least one locking element (28) adapted to partially protrude from the support surface (22) of the base portion (21) along a protrusion line (36). The base portion (21) and the locking element (28) are connected or configured to be connected in such a way that the locking element (28) can move relative to the base portion (21) along the protruding line (36) and can rotate relative to the base portion (21). The locking element (28) has an end section (29) with a dovetail-shaped end portion (30); and The device (10) further includes at least one tensioning device (45) for tensioning the locking element (28) relative to the attachment rail (15) when the support surface (22) of the base portion (21) rests on the outer surface (16) of the attachment rail (15) and the end portion (30) is in the engagement position (L) relative to the attachment rail (15). The locking element (28) includes a portion (31) having a cylindrical external shape and configured to be received in an opening (23) in the base portion (21) and extend through the opening. The end section (29) of the locking element (28) is flattened relative to the portion (31) having the cylindrical outer shape, and The end section (29) is completely laterally contained within the imaginary extension of the side surface (32) of the portion (31) having the cylindrical outer shape in the direction of the longitudinal axis (A) of the locking element.

2. The device according to claim 1, Its features are, The locking element (28) has a pin-shaped form.

3. The device according to claim 1 or 2, Its features are, The locking element (28) is adapted to be inserted in the front, partially into the channel (56) with the end portion (30) extending from the outer surface (16) of the attachment rail (15) into the attachment rail.

4. The device according to claim 1 or 2, Its features are, The end section (29) includes a recess (33) on its opposite narrow side (34), wherein each of the recesses (33) includes a retaining surface (35) that extends obliquely relative to the longitudinal axis (A) of the locking element (28).

5. The device according to claim 1 or 2, Its features are, The tensioning device (45) includes at least one cam (46) pivotally coupled to the locking element (28), and / or the tensioning device (45) includes a lever (47) for applying a tension load on the locking element (28).

6. The device according to claim 3, Its features are, The base portion (21) has an additional protrusion (78) formed on the support surface (22) at a location spaced apart from the location of the locking element (28). The protrusion (78) is integrally formed with the base portion (21) or formed by an additional element fixedly connected to the base portion. The protrusion (78) is adapted to be inserted into another channel (56) extending from the outer surface (16) into the attachment track (15).

7. The device according to claim 1 or 2, Its features are, The device (10) is configured as an assembly for attaching a passenger seat (91) of an aircraft (1) to the attachment rail (15), or the device (10) is configured as an assembly for attaching a structure to the attachment rail (15) within the cabin of the aircraft (1).

8. The device according to claim 1, wherein, The attachment track (15) is the seat track (15) in the aircraft (1).

9. A device (100) for attaching an object (91) inside an aircraft (1), the device (100) comprising: At least one device (10) according to any one of claims 1 to 8, the device comprising at least one locking element (28), wherein an end section (29) of the locking element (28) has a dovetail-shaped end portion (30); and At least one attachment rail (15) includes a rail body (50) and a plurality of bushings (55), wherein the rail body (50) has an upper flange (51) having a plurality of through holes (60) arranged along the upper flange (51) according to a predetermined pattern, and wherein the bushings (55) are connected to the upper flange from the underside of the upper flange (51), each bushing (55) being arranged at a position corresponding to the position of one of the through holes (60), and further wherein each of the bushings (55) forms an internal channel (56) therethrough. The locking element (28) of the device (10) extends into the internal channel (56) of one of the bushings (55), wherein the end portion (30) is engageable with the bushing (55).

10. The apparatus according to claim 9, Its features are, The internal channel (56) of each bushing (55) includes a channel portion (57) with an elongated cross-section.

11. The apparatus according to claim 10, Its features are, Each of the bushings (55) includes a contact surface (58) on the side of the bushing (55) opposite to the upper flange (51) of the track body (50), the contact surface being adjacent to the channel portion (57) having the elongated cross-section, the contact surface (58) of the bushing (55) being adapted to contact the retaining surface (35) of the end portion (30) of the locking element (28), wherein the contact surface (58) of the bushing (55) is shaped such that a recess is formed on the side of the bushing (55) opposite to the upper flange (51).

12. The apparatus according to any one of claims 9 to 11, Its features are, The track body (50) includes a cross section formed in the shape of an omega.

13. A method for attaching an object (91) inside an aircraft (1), the method comprising the steps of: Provide at least one device (10) according to any one of claims 1 to 8, the device (10) comprising at least one locking element (28), wherein the end section (29) of the locking element (28) has an end portion (30) formed in a dovetail shape. At least one attachment rail is provided, the at least one attachment rail comprising a rail body (50) and a plurality of bushings (55), wherein the rail body (50) has an upper flange (51) having a plurality of through holes (60) arranged along the upper flange (51) according to a predetermined pattern, and wherein the bushings (55) are connected to the upper flange from the underside of the upper flange (51), each bushing (55) being arranged at a position corresponding to the position of one of the through holes (60), and further wherein each of the bushings (55) forms an internal channel (56) therethrough. Insert the locking element (28) of the device (10) into the internal channel (56) of one of the bushings (55); and Engage the end portion (30) of the locking element (28) with the bushing (55).

Images