Rail assembly for an interior space of an aircraft

Abstract

A rail assembly for an interior space (12) of an aircraft (2) has a first section (14) with a first rail (16) for receiving a passenger seat and a second rail extending transversely to the first rail for receiving an insert. The rails are fastened on a floor support arranged in the interior space. The fastening of the insert is thus separated from the floor support.

Description

Technical Field

[0001] The present invention relates to a guide rail assembly for the internal space of an aircraft and an aircraft having an internal space and such a guide rail assembly. Background Technology

[0002] For securing components within the interior space of an aircraft, a generally accepted approach exists. Passenger seats or passenger seat assemblies and monuments in the cylindrical fuselage area are typically arranged on so-called seat rails that extend along the longitudinal axis of the relevant interior space of the aircraft. Furthermore, these seat rails are equipped with defined profiles that allow for the reception and locking of corresponding fastening elements. Such rails are typically secured in fixed, pre-defined, lateral positions.

[0003] However, the components in the conical fuselage area are usually arranged at dedicated, personalized fastening points. These components are typically located in the front and rear areas of the aircraft and have structures (such as galleys or toilets) installed in the front and rear areas of the aircraft.

[0004] Because the walls of a building are located in different positions depending on the building's size, design, and function, the floor support must always be adapted to the building's geometry to provide individualized fastening points. Therefore, specific support positions may need to be provided, repositioned, or additional supports may be required in relevant sections of the floor support to provide underlying fastening points for different locations of the building.

[0005] Therefore, it is advantageous to provide an internal component that allows for more flexible fastening of the installed components without requiring significant modifications to the floor support. Eliminating dedicated fastening points may enable faster and more flexible configuration of the internal space. Summary of the Invention

[0006] Therefore, the object of the present invention is to provide a system, method or component for the interior space of an aircraft, which enables personalized, flexible, rapid and cost-effective configuration of the section next to the pure passenger seating row.

[0007] This objective is achieved through components used for the internal space of the aircraft. Advantageous implementations and improvements can be found in the following description.

[0008] A guide rail assembly for the interior space of an aircraft is proposed, the guide rail assembly comprising: a floor support capable of being positioned within the interior space; a plurality of first guide rails arranged parallel to each other in a first section of the floor support and along a first extending direction of the floor support, the first guide rails being designed to receive passenger seats; and a plurality of second guide rails arranged parallel to each other in a second section of the floor support and along a second extending direction of the floor support, the second guide rails being designed to receive fastening devices for securing inserts. The second extending direction extends transversely to the first extending direction. The second section follows the first section along the first extending direction. The second guide rails are fastened to the floor support at a selectable position along the first extending direction.

[0009] Therefore, a guide rail assembly for the interior space of an aircraft is proposed, which can be easily customized. The floor support, positionable within the interior space, can largely correspond to the floor supports of conventional transportation aircraft. This floor support, in particular, can include a row of spaced-apart supports that unfold into a grid, serving as a mechanical base for the floor within the interior space. Typically, the floor support is configured as an integral part of the aircraft's overall structure, and it can also absorb lateral forces from the main structure of the aircraft. In principle, the floor structure can have at least lateral supports.

[0010] The first guide rail is used to receive the passenger seat and can therefore correspond to common floor rails or seat rails. These first guide rails have an elongated, closed cavity on their top surface, the upper boundary of which is penetrated by a slot with a plurality of evenly spaced openings arranged in the slot. Fastening devices can be introduced into the cavity, for example, through one of these openings, and clamped to the top surface of the guide rail.

[0011] The first guide rail is preferably arranged continuously in the first section and in a preferably unchanged lateral position. Typically, the first guide rail is interrupted only by a gap at locations such as door areas.

[0012] A second section is arranged at the end of the first section along the extension direction of the first guide rail. This second section has multiple second guide rails, which are also spaced apart from each other and arranged parallel to each other, but extend transversely to the first guide rails. Therefore, if a long compartment is located within a predominantly cylindrical fuselage, the second guide rails can extend transversely to the longitudinal direction of the fuselage. This arrangement allows for the fastening of components at different locations along the second guide rails and thus transversely to the first extension direction. Therefore, different fastening locations can be used or provided depending on the size and shape of the component to be fastened to the second guide rails. Thus, dedicated, floor-embedded fastening points are only required in exceptional cases for customized constructions.

[0013] Secure the second guide rail at different locations along the first extension direction, which also allows for the adaptation of the mounting position of the insert along the first extension direction and therefore, particularly along the longitudinal axis of the interior space. Furthermore, the implementation is not limited to providing only a single second section. More precisely, it can be provided that multiple first sections and / or multiple second sections with the insert are provided on the floor structure within the relevant interior space. Additionally, the second guide rail does not necessarily have to extend entirely along the available space, but can also cover sub-areas of the interior space or floor structure. The securing of the insert can be separated from rigidly pre-defined or costly mounting points on the floor support. This allows for standardized, faster, more personalized, and modular solutions for the insert, even in very late development stages and during aircraft retrofitting or upgrades.

[0014] Preferably, the second guide rail has an elongated guide rail body, the guide rail body having a support surface, an elongated cavity formed in the guide rail body, and two support flanges arranged on opposite longitudinal sides of the guide rail body, the support flanges optionally extending outward from the longitudinal sides in a manner flush with the support surface. Therefore, the second guide rail can have a guide rail body constructed similarly to a floor guide rail or seat guide rail. It is not necessary to equip the guide rail body with openings distributed in a grid pattern along the guide rail body. More precisely, the cavity of the guide rail body can be used to receive fastening elements that can clamp to the guide rail body. The support flanges extend outward from the guide rail body. Therefore, the support flanges extend along opposite longitudinal sides. The support flanges increase the surface area on which the second guide rail can be placed. Furthermore, it should be noted that when the first guide rail relates to a floor guide rail for a passenger seat, the second guide rail is arranged transversely to the longitudinal direction of the aircraft. The higher loads generated by heavy structures along the longitudinal direction can be absorbed by optional support flanges with correspondingly sized dimensions. Under longitudinal loads, the guide rail body can be supported by the support flanges with optimized force transmission to prevent torsion about the transverse axis.

[0015] In an advantageous embodiment, the second guide rails are respectively clamped onto the supports of the floor bracket using multiple clamps. By clamping the second guide rails onto the supports of the floor bracket, the position of the second guide rails along the x-direction on the support can be fully variable. The clamps allow for selection of the position of the support, particularly along continuously extending surfaces. Therefore, the absence of a grid allows for highly personalized positioning.

[0016] However, if desired, the second guide rail can also be preferably screwed onto the floor bracket.

[0017] Advantageously, the clamps each have a first leg for pressing against the support and a second leg for fastening to the second guide rail, wherein the second leg has a first fastening device for receiving a second fastening device, which is connected to the associated second guide rail. Such clamps may, for example, be located at the bottom surface of the second guide rail and abut against, for example, the slats of the support from below. These clamps can be fastened to the second guide rail in such a way that they allow for reliable clamping of the second guide rail.

[0018] The second leg may have a support protrusion that can be placed into a hole in the second guide rail, wherein the diameter of the hole is smaller than the external dimension of the support protrusion. This allows for a particularly reliable, clamping connection with the associated support. The support protrusion allows the clamp to be placed onto the second guide rail, thus enabling the support protrusion to function as a type of hinge. By tensioning the combination of the first and second fastening devices, the clamp, and in particular the first leg, can pivot around the support protrusion, thereby adjusting the distance between the first leg and the second guide rail. Clamping is performed if a slat or another face of the support is located between the second guide rail and the first leg.

[0019] Preferably, one of the first and second fastening devices may be a hole or a threaded hole, wherein the other of the first and second fastening devices is a screw device. Therefore, tensioning can be achieved by the screw device, which in its simplest case is a bolt. The screw device can be screwed into a nut or another element with a threaded hole located on the side of the second leg opposite to the second guide rail. However, the threaded hole can also be directly arranged in the second leg, allowing clamping of the fixture to be achieved by screwing in the screw device. A protective layer can be present on the fixture to protect the floor support or the supports located therein from damage and to optimize the frictional fit connection.

[0020] In a particularly preferred embodiment, the clamps are each equipped with a cylindrical nut for receiving the helical device. The cylindrical nut may, for example, have a cylindrical shape, allowing it to be inserted into a hole in the clamp. A threaded hole extending perpendicular to the longitudinal axis of the cylindrical nut can receive the helical device. With this design, the cylindrical nut can be accurately aligned with the tensile force during clamping.

[0021] In a similarly advantageous embodiment, the second guide rails each have a plurality of holes arranged at uniform intervals to receive the helical device and the support protrusion. Retention points can be reliably provided by the spaced-apart, uniformly distributed holes, which are successive to each other along the second extension direction. Therefore, in addition to continuous positions along the first extension direction, more or less finely selected positions along the second extension direction can be readily provided. Selection in this direction is permissible because the inserts (e.g., structures) clearly extend along the second extension direction in the installed state, and the fastening of these inserts can be easily adapted to the selection.

[0022] Advantageously, the second guide rails each have elongated slots extending along the second extension axis, wherein a locking body can be introduced into the cavity of the second guide rail and engaged with a retaining device extending through the slot. The retaining device can be a bolt, etc., introduced from the corresponding insert into the locking body to secure the insert to the locking body and thus to the second guide rail. Here, the locking body serves to transmit force from the insert or component to the second guide rail. Preferably, the locking body may be designed to be displaceable along the second extension direction, where the space available between the longitudinal sides of the cavity should be fully utilized as much as possible. However, care should be taken to reliably avoid warping. This may be achieved by correspondingly rounding the locking body and by a corresponding fit.

[0023] Particularly preferably, the locking body can be positioned in the cavity in a displaceable manner. The locking body can be secured in the cavity, particularly by clamping. The position suitable for securing can be selected by displacement before clamping. Pre-positioning the locking body allows for protective measures (such as corrosion protection) to be taken in the early stages of assembly and allows for subsequent, rapid installation of the building.

[0024] In an advantageous embodiment, the locking body has a resiliently positioned clamping body that fixes the locking body in position before the retaining device is assembled. The retaining device may be implemented as a pin or a circle (e.g., a ball) and may have rounded ends that readily clamp the locking body inside the second guide rail by spring force. This can be achieved, for example, by pressing the locking body against the upper boundary of the second guide rail. The clamping body is arranged in the second guide rail in a manner offset relative to the opening.

[0025] The guide rail assembly may also have a cover strip for covering the second guide rail, wherein the cover strip is constructed corresponding to the second guide rail. The cover strip can be used to prevent contaminants from entering or to prevent mechanical damage. These cover strips may be arranged flush with the top surface of the guide rail body, or these cover strips may be inserted into slots, thereby closing the vertical extensions pointing towards the slots.

[0026] The present invention also relates to an aircraft having an interior space and at least one rail assembly arranged in the interior space according to the above description. The aircraft can particularly be a transportation aircraft with a cabin having a central aisle and two outer passenger seating areas. However, in principle, the rail assembly according to the invention can also be used in larger aircraft having a cabin with two aisles.

[0027] The first section can be arranged in a cylindrical region of the interior space, while the second section is arranged in a gradually narrowing region of the interior space. In these sections, larger installations (such as lavatory structures and / or galley structures) are typically arranged, replacing or excluding passenger seats, and these larger installations can be flexibly adapted to the needs of the aircraft operator. To this end, a rail assembly according to the invention is provided, which enables the separation of the fastening of such installations from the floor support. Therefore, personalized design schemes can be implemented significantly faster compared to the requirement of always personalizing the floor support.

[0028] Particularly preferably, at least in the region where the interior space gradually tapers to a cone shape, a second guide rail is arranged in front of the front door or behind the rear door. Particularly preferably, only the second guide rail is present in the region between the cockpit and the front (cabin) door. Equally preferably, only the second guide rail is present in the region between the aft pressure bulkhead and the rear (cabin) door.

[0029] The second section can be connected to the first section. In one embodiment, the second section may only have the second guide rail. However, it is also conceivable to design a transition area in which both the first and second guide rails are arranged. If the interior space is divided, for example, by one or more passageways, the first guide rail may extend further on one side of the passageway than on the other side. The second guide rail may be arranged on the other side of the passageway. Such a transition area may be located, for example, in a doorway area or adjacent to a doorway area. Attached Figure Description

[0030] Other features, advantages, and applications of the invention will become apparent from the following description of the embodiments and drawings. Hereinafter, all described and / or illustrated features, in themselves and in any combination, constitute the subject matter of the invention, regardless of their relationship to the individual claims or the claims to which they are referenced. In the drawings, the same reference numerals denote the same or similar objects.

[0031] Figure 1 The fuselage of the aircraft is shown, which has a first guide rail and a second guide rail mounted therein.

[0032] Figure 2 A portion of the floor support is shown, which has a second guide rail arranged thereon.

[0033] Figure 3 A schematic diagram of the second guide rail is shown in a sub-section.

[0034] Figure 4 The second guide rail is shown being clamped between two supports.

[0035] Figure 5 The first variant of the second guide rail together with the clamp is shown.

[0036] Figure 6a and Figure 6b Show Figure 5 A variation of the second guide rail.

[0037] Figure 7 The cover for the second guide rail is shown.

[0038] Figure 8 A variation of the cover for the second guide rail is shown. Detailed Implementation

[0039] Figure 1The aircraft 2 is shown in a simplified diagram, with only the fuselage 4 shown. The fuselage 4 has a nose 6 and a tail 8, with a cylindrical fuselage section 10 extending between the nose and tail. An internal space 12 is designed within the fuselage 4, which extends largely throughout the entire fuselage 4. A floor support (not shown here) is arranged in this internal space, serving as a base for the internal structure. A plurality of first guide rails 16 are arranged in a first section 14 of the floor support, extending parallel to and spaced apart from each other along the longitudinal axis x. The first guide rails 16 are largely arranged throughout the cylindrical region 10.

[0040] The first guide rail 16 can be implemented as a floor guide rail or a seat guide rail, having, for example, a so-called Douglas profile. Preferably, the passenger seat can be fastened to the first guide rail 16 in an inch grid pattern. An exemplary extension direction of the first guide rail 16 parallel to the longitudinal axis x is referred to as the first extension direction.

[0041] A plurality of second guide rails 18 are arranged in the region outside the cylindrical region 10 (i.e., at the head 6 and tail 8), extending transversely to the first guide rail 16. The direction of extension of the second guide rails 18 (hereinafter also referred to as the second extension direction) corresponds to the transverse axis y. These second guide rails 18 are used to receive larger inserts at variable positions. The sections in which the second guide rails 18 are arranged are also referred to hereinafter as second sections 20 and 22.

[0042] The second section 22 at the front has a tapered region 21, which is fitted only with the second guide rails 18 and is exemplarily positioned between the front door 19 and the cockpit. A transition region 17 is arranged between the tapered region 21 and the cylindrical region 10, in which several second guide rails 18 may be located and a portion of the first guide rail 16 may extend into the transition region. The second guide rails 18 in the transition region 17 may, for example, extend only on the side of the cabin half.

[0043] The second section 20 at the rear is implemented similarly. Here, a tapered region 15 is arranged behind the door 13, with only the second guide rail 18 located in this region. The tapered region 15 may extend to the rear pressure bulkhead (not shown). The second guide rail 18 is located in a transition region 11, which extends between the door 13 and the cylindrical region 10. A portion of the first guide rail 16 may extend into the transition region 11.

[0044] Figure 2The floor support 24 is shown in a slightly enlarged spatial and exemplary illustration. The second section 20 at the tail 8 is shown exemplary. Here, a total of three second guide rails 18 are arranged on the support 26 and can be variably positioned along a first extension direction (i.e., exemplary along the x-direction). Therefore, the arrangement of the inserts can be separated from the support 26, and the second guide rails 18 can be implemented such that all inserts can be secured to these second guide rails.

[0045] In principle, the second guide rail 18 can be securely mounted on the support 26 or (if desired) on other elements of the floor bracket 24. It is conceivable that the second guide rail 18 enables a standardized configuration of the interior space 12, allowing for the standardized fastening of disparate installations. However, the second guide rail 18 can also be used to retrofit existing aircraft. To achieve maximum possible flexibility, the second guide rail 18 can be inserted at varying positions along the longitudinal direction x, which is determined by… Figure 2 The arrow in the image indicates this.

[0046] Figure 3 A simplified illustration of the second guide rail 18 is shown. Here, the guide rail body 28 can be seen, which has a support surface 30. Support flanges 36 and 38 are arranged on the longitudinal sides 32 and 34 and extend outward from the outer edges 32 and 34. Here, these support flanges terminate flush with the support surface 30. This provides excellent support for the second guide rail 18, preventing rotation about the second extension direction.

[0047] Furthermore, the second guide rail 18 has a cavity 40 within the guide rail body 28, which preferably extends constantly along a second extending direction and has a slot 42 on its side opposite to the support surface 30. As further shown below, all locking bodies can be introduced into the cavity 40 and used for clamping within the cavity. Holes 44 can be used to secure the second guide rail 18.

[0048] To secure the second guide rail 18 to the support member 26, a clamping mechanism is provided. For this purpose, clamps 46 are provided, which are equipped with a first leg 48 and a second leg 50. The two legs 48 and 50 extend parallel to each other and are offset from each other by a relatively short distance. Exemplarily, the second leg 50 has a support protrusion 52 that extends outward from the second leg 50 and can extend into a hole, such as a hole 44 in the second guide rail 18 (see also...). Figure 3In this example, the support protrusion 52 may be at least partially constructed as a sphere and thus form, for example, a support ball or articulated head. The hole 44 has a diameter smaller than the width of the support protrusion 52. Therefore, the clamp 46 can pivot around the hole 44 around the support protrusion 52. In addition, in the second leg 50, a screw device 54, which serves as a second fastening device, is provided in the hole 53, which serves as a first fastening device. This screw device can be connected to the second leg 50 and the second guide rail 18. By screwing the screw device 54, the position of the clamp 46 can be selected around the support protrusion 52, thereby also affecting the position of the first leg 48. If there is a strip 56 of the support member 26 between the second guide rail 18 and the first leg 48, the strip can therefore be clamped between the clamp 46 and the second guide rail 18 by screwing the screw device 54. Thus, the second guide rail 18 is clamped to the support member 26 by the clamp 46.

[0049] As in Figure 4 As shown, multiple such clamps 46 can be used to clamp the second guide rail 18 onto multiple supports 26. To prevent mechanical damage to the clamps 46, slats 56, and the second guide rail 18, protective layers 58, 60, and 62 are provided on each contact surface. These protective layers can be made of, for example, plastic, to prevent dents or other defects from forming on the connecting surfaces during clamping.

[0050] Figure 5 A possible implementation of the clamp 46 is shown in a lateral sub-section. Here, a support protrusion 52 can be seen, which enters into one of the holes 44 in the second guide rail 18. Furthermore, the second guide rail 18 is shown in a top view of its bottom surface. There, a plurality of holes 44 can be seen, distributed in a grid pattern along a second extending direction. Exemplarily, the holes 44 may be spaced apart from each other by a distance of 20 mm to 30 mm (preferably 24 mm, 25 mm, or 26 mm).

[0051] For example, a cylindrical nut 64 is arranged in the clamp 46, located in a cylindrical hole 66 that is slightly widened on one side at the bottom surface 68 for removing the screw device. A bolt 70, as such a screw device, is guided through the second leg 50 and screwed into the cylindrical nut 64. Due to this arrangement, the orientation of the bolt 70 can be changed about the axis of rotation 72 of the cylindrical nut 64. If the support protrusion 52 is inserted into one of these openings 44 and the bolt 70 is inserted into the hole 44 adjacent to that opening, the clamp 46 can thus be clamped, thereby tensioning the first leg 48 onto the slat 56. Here, stress within the clamp 46 can be avoided by means of the cylindrical nut 64.

[0052] like Figure 6aAs shown, other variations can also be used. The second guide rail 18 may also have two rows of adjacent holes 44, which are also arranged in rows along the second extension direction of the second guide rail 18. Thus, the corresponding clamps with two adjacent support protrusions 52 and two helical devices 54 can be prevented from twisting.

[0053] like Figure 6b As shown, the locking body 74, as a fastening device, can be introduced into the cavity 40 of the second guide rail 18 so as to be displaced along the slot 42. A retaining device 75, in the form of a bolt, can extend through the slot 42 into the locking body 74; this bolt can be connected to the object to be fastened. The locking body 74 can be easily clamped onto the second guide rail 18 by means of a spring-loaded clamping body 76 before the retaining device 75 is tightened, thereby facilitating the easy introduction of the retaining device 75 into the locking body 74. For example, after the second guide rail 18 is manufactured, the locking body 74 can already be pushed to a predetermined position. This occupied position can be secured by slight clamping of the clamping body 76. The occupied position is maintained even during vibrations caused by transporting the second guide rail 18 or during the transfer of an aircraft with the second guide rail 18 for equipment assembly.

[0054] The second guide rail 18 may also have an open slit 78 extending upward through the slot 42, through which the locking body 74 can be pushed into the cavity 40. Depending on the length of the second guide rail 18, multiple slits may be arranged on a single second guide rail 18, so that multiple locking bodies 74 can be pushed into the cavity 40 at different positions.

[0055] As in Figure 7 As shown, a cover strip 80 can be provided, which can be placed on the second guide rail 18 and, exemplarily, locked into the slot 42. A stop button 82 is provided for this purpose, capable of locking the cover strip 80 into the slot 42. This allows the second guide rail 18 to be flush with the adjacent flooring 84. This in particular allows, for example, the wheels 86 of a service cart (trolley) to enter or drive over the second guide rail 18.

[0056] Figure 8 An alternative variation is shown in which adjacent floor layers 84 terminate flush with the top surface of the second guide rail 18. A cover strip 88 can be used here, which can be inserted vertically through the slot 42 and secured at the hole 44 by means of a stop button 90.

[0057] Additionally, it should be noted that "having" does not exclude other elements or steps, and "an" or "a" does not exclude multiple. Furthermore, it should be noted that combinations of features already described with reference to one of the above embodiments, as well as other features of the other embodiments described above, may be used. Reference numerals in the claims should not be considered limiting.

[0058] List of reference numerals

[0059] 2 aircraft

[0060] 4 fuselage

[0061] 6 heads

[0062] 8 tail

[0063] 10 fuselage sections / cylindrical areas

[0064] 11. Transition Zone (Tail)

[0065] 12 interior spaces

[0066] 13 Backdoors

[0067] 14 First Section

[0068] 15. The region gradually transforms into a cone shape (tail).

[0069] 16 First guide rail

[0070] 17. Transitional area (head)

[0071] 18 Second Guide Rail

[0072] 19 Qianmen

[0073] 20 Second Section

[0074] 21. The area gradually transforms into a cone shape (head).

[0075] 22 Second Section

[0076] 24 floor supports

[0077] 26 support components

[0078] 28 guide rail body

[0079] 30 support surfaces

[0080] 32 longitudinal side

[0081] 34 longitudinal side

[0082] 36 Support Flanges

[0083] 38 Support Flanges

[0084] 40 cavity

[0085] 42 grooves

[0086] 44 holes

[0087] 46 clamps

[0088] 48 First leg

[0089] 50 Second leg

[0090] 52 Support Protrusions

[0091] 53 holes / First fastener

[0092] 54 Spiral Device / Second Fastening Device

[0093] 56 strips

[0094] 58 protective layers

[0095] 60 protective layers

[0096] 62 protective layers

[0097] 64 cylindrical nuts

[0098] 66 cylindrical holes

[0099] 68 bottom

[0100] 70 bolts

[0101] 72-spindle

[0102] 74 Locked Body

[0103] 75 Retaining Device / Bolt

[0104] 76 clamping body

[0105] 78 incisions

[0106] 80 Cover Strip

[0107] 82 Stop button

[0108] 84 Flooring Layer

[0109] Wheels of the 86 service vehicle

[0110] 88 Cover Strip

[0111] 90 Stop button

[0112] x-axis / first extension direction

[0113] y-axis / second extension direction

Claims

1. A guide rail assembly for the internal space (12) of an aircraft (2), the guide rail assembly having: Floor support (24), which can be positioned in the interior space (12); A plurality of first guide rails (16) are arranged parallel to each other in a first section (14) of the floor support (24) and along a first extension direction (x) of the floor support (24), and the first guide rails are designed to accommodate passenger seats. A plurality of second guide rails (18) are arranged parallel to each other and along a second extension direction (y) of the floor bracket (24) in a second section (20, 22), and the second guide rails are designed to receive fastening devices for fastening inserts. The second extension direction (y) extends laterally to the first extension direction (x). The second segment (20, 22) follows the first segment (14) along the first extension direction (x), and The second guide rail (18) is fastened to the floor bracket (24) at a position selectable along the first extension direction (x).

2. The guide rail assembly according to claim 1, The second guide rail (18) has an elongated guide rail body (28) with a support surface (30), an elongated cavity (40) formed in the guide rail body (28), and two support flanges (36, 38). The support flanges are arranged on opposite longitudinal sides (32, 34) of the guide rail body (28) and extend outward from the longitudinal sides (32, 34) in a manner flush with the support surface (30).

3. The guide rail assembly according to claim 1 or 2, The second guide rail (18) is clamped onto the support (26) of the floor bracket (24) by a plurality of clamps (46).

4. The guide rail assembly according to claim 3, The clamps (46) each have a first leg (48) for pressing against the support (26) and a second leg (50) for fastening the clamps (46) to the second guide rail (18). The second leg (50) has a first fastening device (53) for receiving a second fastening device (54), the second fastening device being connected to an associated second guide rail (18).

5. The guide rail assembly according to claim 4, The second leg (50) has a support protrusion (52) that can be placed into a hole (44) in the second guide rail (18), wherein the diameter of the hole (44) is smaller than the outer dimension of the support protrusion (52).

6. The guide rail assembly according to claim 4 or 5, One of the first fastening device (53) and the second fastening device (54) is a hole or a threaded hole, and the other of the first fastening device (53) and the second fastening device (54) is a screw device.

7. The guide rail assembly according to claim 6, The clamps (46) are each equipped with a cylindrical nut (64) for receiving the spiral device.

8. The guide rail assembly according to claim 5, The second guide rail (18) has a plurality of holes (44) arranged at a uniform interval between each other, the holes being used to receive the helical device and the support protrusion (52).

9. The guide rail assembly according to claim 2, The second guide rail (18) has an elongated slot (42) extending along the second extension direction (y), and The locking body (74) can be introduced into the cavity (40) of the second guide rail (18) and connected to the retaining device (75) extending through the slot (42).

10. The guide rail assembly according to claim 9, The locking body (74) can be positioned in the cavity (40) in a displaceable manner.

11. The guide rail assembly according to claim 10, The locking body (74) has a resiliently positioned clamping body (76) that fixes the position of the locking body (74) before the retaining device (75) is assembled.

12. The guide rail assembly according to any one of the preceding claims, The guide rail assembly further has a cover strip (80, 88) for covering the second guide rail (18), wherein the cover strip (80, 88) is constructed corresponding to the second guide rail (18).

13. An aircraft (2) having an internal space (12) and at least one rail assembly according to any one of claims 1 to 12 located in the internal space.

14. The aircraft (2) according to claim 13. The first segment (14) is arranged in the cylindrical region (10) of the interior space (12), and the second segment (20, 22) is arranged in the gradually narrowing region of the interior space (12).

15. The aircraft (2) according to claim 14, wherein at least in the regions (15, 21) of the interior space (12) that gradually become conical, only a second guide rail (18) is arranged in front of the front door (19) or behind the rear door (13).

Images