Fixed joint for aircraft cabin floor, aircraft floor mounting system, aircraft floor arrangement, aircraft and method for providing fixed joint for aircraft cabin floor

Abstract

The invention relates to a fixed joint for an aircraft cabin floor, an aircraft floor mounting system, an aircraft floor arrangement, an aircraft and a method for providing a fixed joint for an aircraft cabin floor. The joint includes a primary connection stud and a secondary attachment joint member. The main connection stud includes a mounting foot region and a joint head region. The mounting foot region is configured to be fastened to a fastening point. The joint head region includes a protrusion. The secondary attachment joint component is configured to be mounted to the joint head region. The secondary attachment engagement member is positioned to the engagement head region in a positioning movement and locked in a locking movement to achieve positive fit retention. The secondary attachment engagement members include a first type of engagement member positioned in a first positioning movement and locked in a first locking movement and a second type of engagement member positioned in a second positioning movement and locked in a second locking movement different from the first locking movement.

Description

Technical Field

[0001] The present invention relates to fastening points of an aircraft floor structure and, in particular, to a fixed joint for an aircraft cabin floor, an aircraft floor mounting system, an aircraft floor device, an aircraft, and a method for providing a fixed joint for an aircraft cabin floor. Background Art

[0002] Interior cabin equipment, such as passenger seats, can be installed on the floor structure of an aircraft cabin through dedicated fastening points. An example of such a fastening point is a so-called seat track. The seat track can be provided as a longitudinal profile with a defined cross-section, and the seat track allows, for example, a seat leg fitting or a seat track cover to be clamped along the track. The upper part of the seat track can provide a recess or a protrusion as a joint for form-fitting engagement of the fitting. However, such a seat track design may have limitations regarding its applicability to certain floor structures. In addition, the seat track design itself may limit the applicability of the seat track joint to interior cabin equipment. Summary of the Invention

[0003] Therefore, there may be a need to provide an improved fixed joint that has a high adaptability to its construction environment.

[0004] The object of the present invention is solved by the subject matter of the main aspects of the present invention; additional embodiments are incorporated into other aspects of the present invention. It should be noted that the aspects described below of the present invention are also applicable to a fixed joint for an aircraft cabin floor, an aircraft floor mounting system, an aircraft floor device, an aircraft, and a method for providing a fixed joint for an aircraft cabin floor.

[0005] According to the present invention, a fixed joint for an aircraft cabin floor is provided. The joint includes a plurality of main connecting studs and a plurality of secondary attachment joint members. Each of the plurality of main connecting studs includes a mounting foot region and a joint head region, and the mounting foot region and the joint head region are arranged along the longitudinal axis of each of the plurality of main connecting studs. The mounting foot region is configured to be fastened to one of a plurality of fastening points linearly arranged in a floor device by a form-fitting connection with one of the plurality of fastening points. On two opposite lateral sides, the joint head region of each of the plurality of main connecting studs includes a plurality of protrusions extending transversely to the longitudinal axis. Each of the plurality of secondary attachment joint members is configured to be mountable to each of the joint head regions of the plurality of main connecting studs by engaging the plurality of protrusions in a form-fitting manner in the longitudinal direction. Each of the plurality of secondary attachment joint members is positionable in a positioning movement to the joint head region and lockable in a locking movement to achieve form-fitting retention. The plurality of secondary attachment joint members includes a first type of joint member and a second type of joint member. The first type of joint member can be positioned in a first positioning movement and locked in a first locking movement, and the second type of joint member can be positioned in a second positioning movement and locked in a second locking movement, and the first locking movement is different from the second locking movement.

[0006] As an advantage, a fixed joint for cabin equipment is provided, which can be applied to various types of seat tracks. As another advantage, a fixed joint for cabin equipment is provided, which can be applied to various types of floor devices. As another advantage, a continuous fixed joint for cabin equipment is provided for various types of floor devices and seat tracks.

[0007] According to an example, the first type of joint member is an attachment part configured to form a seat track part for fixing a seat to an aircraft cabin floor.

[0008] According to an example, the second type of joint member is a track covering section for closing a gap between floor panels adjacent to a plurality of linearly arranged fastening points.

[0009] According to an example, one of the plurality of connecting studs is configured to be fastened to one of the plurality of fastening points in a floor device to provide a longitudinally extending fixed joint section configured to form an adaptable seat track.

[0010] According to the present invention, there is also provided an aircraft floor installation system. The system includes: at least one longitudinally extending clamping profile; a plurality of fastening elements configured to provide a plurality of fastening points; and at least one fixed joint having a plurality of main connecting studs according to one of the foregoing examples. The longitudinally extending clamping profile includes: at least one outer section for holding an edge of at least one floor panel; and a central recessed section for attaching the longitudinally extending clamping profile to a floor support beam of an aircraft cabin. The plurality of fastening elements are configured to be arranged along the central recessed section in an installed state. The longitudinally extending clamping profile is configured to be attached to the floor support beam by the plurality of fastening elements. One of the plurality of main connecting studs is configured to be installed as part of one of the plurality of fastening points.

[0011] As an advantage, the same fixed joint can be applied to various clamping profiles with different thicknesses and geometries.

[0012] According to the present invention, there is also provided an aircraft floor device. The aircraft floor device includes: at least one floor support beam; a plurality of fastening points arranged on an upper side along at least a part of the floor support beam; a plurality of fastening elements; and at least one fixed joint having a plurality of main connecting studs according to one of the foregoing examples. One of the plurality of fastening points is configured to receive an installation foot area of one of the plurality of main connecting studs. The plurality of fastening points are configured to fix the plurality of connecting studs against the floor support beam by the plurality of fastening elements.

[0013] As an advantage, a floor device with cabin equipment and various types of floor support beams can be established.

[0014] According to the present invention, there is also provided an aircraft. The aircraft includes: a fuselage; a wing device attached to the fuselage; an aircraft cabin; and an aircraft floor device according to one of the foregoing examples. The aircraft cabin is provided in the fuselage, and the aircraft cabin includes the aircraft floor device.

[0015] As an advantage, an aircraft with high customizability is provided. As an advantage, an aircraft cabin with high adaptability is provided.

[0016] According to the present invention, there is also provided a method for providing a fixed joint for an aircraft cabin floor. The method includes the following steps:

[0017] - providing a plurality of main connecting studs; and

[0018] - Provide a plurality of secondary attachment engagement members. Each of the plurality of main connection studs includes a mounting foot region and an engagement head region, and the mounting foot region and the engagement head region are arranged along the longitudinal axis of each of the plurality of main connection studs. The mounting foot region is configured to be fastened to one of a plurality of fastening points linearly arranged in a floor device by a form-fitting connection with one of the plurality of fastening points. On two opposite lateral sides, the engagement head region of each of the plurality of main connection studs includes a plurality of protrusions extending transversely to the longitudinal axis. Each of the plurality of secondary attachment engagement members is configured to be mountable to each of the engagement head regions of the plurality of main connection studs by engaging the plurality of protrusions in a form-fitting manner in the longitudinal direction. Each of the plurality of secondary attachment engagement members is capable of being positioned to the engagement head region in a positioning movement and locked in a locking movement to achieve a form-fitting retention. The plurality of secondary attachment engagement members includes a first type of engagement member and a second type of engagement member. The first type of engagement member can be positioned in a first positioning movement and locked in a first locking movement, and the second type of engagement member can be positioned in a second positioning movement and locked in a second locking movement, and the first locking movement is different from the second locking movement.

[0019] As an advantage, an aircraft can be retrofitted with adaptable seat tracks.

[0020] According to one aspect, there is provided a highly adaptable and versatile seat track for an aircraft cabin floor.

[0021] According to one aspect, there is provided a longitudinal support bolt having a cabin equipment supply element. The support bolt includes an attachment portion at its lower end, which enables the support bolt to be attached to any desired support. At the upper end, the support bolt provides a length-adjustable form-locking connection with the cabin equipment supply element. The form-locking connection is configured to adjust the position of the cabin equipment supply element relative to the distance of the support member in the longitudinal direction. A plurality of longitudinal support bolts can be arranged along a line to provide a seat track. Also taking into account the form-locking connection spatially restricted by the structural environment of the seat track, the adjustability of the form-locking connection is configured to provide a direct, simple and comfortable adjustment.

[0022] These and other aspects of the invention will become apparent and be elucidated with reference to the embodiments described hereinafter. Description of the Drawings

[0023] Exemplary embodiments of the invention will be described hereinafter with reference to the following drawings:

[0024] Figure 1A general scheme schematically showing an example of a fixed joint is presented.

[0025] Figure 2 A cross - section of a general scheme showing an example of a fixed joint is presented, the fixed joint including first - type joint components and second - type joint components in an interleaved arrangement.

[0026] Figure 3 A cross - section of a general scheme showing an example of a fixed joint including a partially - radial toothed element is presented.

[0027] Figure 4 A cross - section of a general scheme showing an example of an aircraft floor mounting system and an aircraft floor device is presented.

[0028] Figure 5 An example of an aircraft including an aircraft floor device is presented.

[0029] Figure 6 An example of the basic steps of a method for providing a fixed joint for an aircraft cabin floor is presented. Detailed implementation

[0030] Certain embodiments will now be described in more detail with reference to the accompanying drawings. In the following description, the same reference numerals are used for the same elements even in different drawings. The content defined in the specification, such as detailed construction and elements, is provided to assist in a comprehensive understanding of the exemplary embodiments. In addition, well - known functions or structures are not described in detail because they would obscure the embodiments with unnecessary details. Further, expressions such as "at least one of..." when preceding a list of elements modify the entire list of elements rather than individual elements of the list.

[0031] Figure 1A general scheme schematically shows an example of a fixed joint 10. The fixed joint 10 for an aircraft cabin floor 12 includes a plurality of main connection studs 14 and a plurality of secondary attachment joint members 16. Each of the plurality of main connection studs 14 includes a mounting foot region 18 and a joint head region 20, and the mounting foot region 18 and the joint head region 20 are arranged along the longitudinal axis 21 of each of the plurality of main connection studs 14. The mounting foot region 18 is configured to be fastened to one of a plurality of fastening points 22 linearly arranged in the floor device 24, as shown by the dashed line 23, by a form-fitting connection with one of the plurality of fastening points 22. On two opposite lateral sides 26, the joint head region 20 of each of the plurality of main connection studs 14 includes a plurality of protrusions 28 extending transversely to the longitudinal axis 21. Each of the plurality of secondary attachment joint members 16 is configured to be mountable to each of the joint head regions 20 of the plurality of main connection studs 14 by engaging the plurality of protrusions 28 in a form-fitting manner in the longitudinal direction. Each of the plurality of secondary attachment joint members 16 can be positioned to the joint head region 20 during a positioning movement and can be locked during a locking movement to achieve a form-fitting retention. The plurality of secondary attachment joint members 16 includes a first type of joint member 30 and a second type of joint member 32. The first type of joint member 30 can be positioned during a first positioning movement 34 and can be locked during a first locking movement 36, and the second type of joint member 32 can be positioned during a second positioning movement 38 and can be locked during a second locking movement 40, and the first locking movement 36 is different from the second locking movement 40.

[0032] The term "fixed joint" relates to a device that provides a mechanical interaction for mounting parts to the cabin floor. These parts can be releasably fixed by the joint.

[0033] The fixed joint can also be referred to as a fixing device, a mounting joint, a mounting device, a connecting joint, or a connecting device.

[0034] The term "aircraft cabin floor" relates to the floor within the aircraft cabin, which, for example, defines the cabin area and the cargo area arranged below the cabin area within the aircraft fuselage. Figure 1 Not shown in the figure.

[0035] The term "main connection stud" relates to a pin-shaped element that can be inserted into a recess of a floor support member, such as Figure 1 in the aircraft cabin floor 12, for use as a connecting joint. The stud can also be referred to as a bolt or a pin. Thus, the connecting stud 14 can have an insertion or installation direction. In one option, when installing, i.e., assembling, the insertion or installation direction in the aircraft is alongFigure 1 The longitudinal axis 21 therein is aligned with the Z direction.

[0036] The plurality of main connection studs may also be referred to as main connection studs, connection studs, studs, fixing studs or stop studs.

[0037] In the example, the fixing studs or stop studs also provide a seal, such as a sealing device, between the cabin space and the lower structure, which is not shown in Figure 1 .

[0038] In the example, the fixing studs or stop studs are made of stainless steel, i.e., a corrosion-resistant material.

[0039] The term "secondary attachment joint member" relates to an element that enables the connection joint of the main connection stud 14 to be applicable to a large number of devices and components associated with the cabin floor, which is not shown in Figure 1 .

[0040] The plurality of secondary attachment joint members may also be referred to as the plurality of secondary attachment joint members or secondary attachment joint members.

[0041] The term "device" relates to seats, structures, lavatories, kitchens and other parts provided in the cabin space, which is not shown in Figure 1 .

[0042] The term "mounting foot area" relates to the lower end of the connection stud 14 that is connected to the floor support structure.

[0043] The term "joint head area" relates to the upper end of the connection stud 14, which is arranged to be joined by the secondary attachment joint member 16, and the secondary attachment joint member is to be fixed by the connection stud 14.

[0044] The term "longitudinal axis" relates to an axis that extends along the longest dimension of the connection stud 14, and this axis includes the mounting foot area 18 and the joint head area 20.

[0045] In the example, the longitudinal axis 21 is perpendicular to the aircraft cabin floor 12, as Figure 1 shown.

[0046] The plurality of fastening points may also be referred to as each fastening point or fastening points, or fixing points, or fixing or attachment points, or linearly arranged fastening points.

[0047] The term "fastening point" relates to a connection part or connection section that is arranged to serve as a mechanical joint for the stud. The fastening points 22 can be added to the floor support structure or can be provided in an integrated manner.

[0048] The term "protrusion" relates to the deepest part or recess in the surface profile of the stud, as Figure 1as shown.

[0049] The plurality of protrusions 28 may also be referred to as each protrusion.

[0050] In the example, the protrusion 28 and the connecting stud 14 are made of a single piece.

[0051] The term "longitudinal direction" relates to the direction defined by the longest dimension of the stud, as Figure 1 shown.

[0052] Engagement may also be referred to as locking.

[0053] In the example, the engagement applies a preloading force on the components involved in the engagement, which is not shown in Figure 1 the [figure].

[0054] The term "positioning movement" relates to the change in the position of the secondary attachment engagement member 16 relative to the position of the connecting stud 14 before the position of the secondary attachment engagement is fixed at the position defined at the connecting stud 14, as Figure 1 shown.

[0055] The term "locking movement" relates to the change in the position and orientation of the secondary attachment engagement member 16, which fixes the position and orientation of the secondary attachment engagement member 16 to the position and orientation of the connecting stud, as Figure 1 shown.

[0056] The term "form - fit retention" relates to preventing the movement of one of the plurality of secondary attachment engagement members 16 along the longitudinal direction by one of the plurality of protrusions 22.

[0057] In the example, the first - type engagement member 30 and the second - type engagement member 32 are associated with the same engagement head region 20 of one of the plurality of main connecting studs 14, which is not shown in Figure 1 the [figure].

[0058] In the example, the fixed engagement portion 10 includes the first - type engagement members 30 and the second - type engagement members 32 in a staggered arrangement. One of the first - type engagement members 30 that is attached to the first of the plurality of main connecting studs 14 follows one of the second - type engagement members 32 that is attached to the second of the plurality of main connecting studs 14 along the fixed engagement portion 10.

[0059] In the example, one of the first - type engagement members 30 seals against one of the second - type engagement members 32.

[0060] Figure 2A cross-section of an overall solution showing an example of a fixed joint 10 is shown. The fixed joint 10 includes a first type of joint member 30 and a second type of joint member 32 in an interleaved arrangement. The first type of joint member 30 is an attachment portion 42, and the attachment portion 42 is configured to form a seat track portion 44 for fixing the seat to the aircraft cabin floor 12.

[0061] In the example, the connecting stud 14 and the secondary attachment joint member 16 are configured to form a specific type of track. It can be said that the supporting floor structure serves to provide the body structure of the track, while the connecting stud 14 and the second attachment joint member 16 provide joint profile segments, as Figure 2 shown. The advantage of using this type of profile, namely the easy connection of the fittings along a small pitch, allows a large degree of freedom in the attachment position, while eliminating the disadvantage that this type of profile is limited to certain sizes and geometries along the entire length.

[0062] As an advantage, the same seat structure can be installed on various types of floor support structures. As another advantage, the same seat structure can be widely used in local variations of the floor support structure.

[0063] In Figure 2 an example not shown, the first positioning movement 34 is a movement along the longitudinal axis 21, and the first locking movement 36 is an angular rotation within an angular range of approximately 45° to 135° about the longitudinal axis 21.

[0064] In the example, the angular range includes all angles from 0° to 180°.

[0065] As an advantage, rapid and tight installation of the seat structure is achieved.

[0066] In Figure 2 the example shown, the second type of joint member 32 is a track covering segment 46, and the track covering segment 46 is used to close the gap 48 between the floor panels 50 adjacent to a plurality of linearly arranged fastening points 22.

[0067] The term "track covering segment" refers to a floor filling section that can generally be used to level the deepened part on the aircraft cabin floor 12, as Figure 2 shown.

[0068] In the example, the track covering segment 46 conforms to the shape of the gap, which is not shown in Figure 2 this.

[0069] The term "gap" refers to a deepened part or recess or simply a longitudinally extending part formed by providing a fixed joint 10 between two surface components of the aircraft cabin floor 12, as Figure 2 shown.

[0070] As an advantage, quick installation and removal of the seat track cover are provided. As an advantage, a secure and protected fixed engagement is provided. As an advantage, the fixed engagement is protected from liquids and dirt. As another advantage, a more reliable fixed engagement is provided because the formation of lumps of liquids and dirt over time, which could impede the positioning and locking movements over time, is prevented. As an advantage, the fixed engagement can be applied to gaps of different geometries.

[0071] In Figure 2 an example not shown, the second positioning movement 38 is a downward movement to position the track cover section 46 along a plurality of linearly arranged fastening points 22, and the second locking movement 40 is a translational movement in the direction of the plurality of linearly arranged fastening points 22.

[0072] The term "downward movement" relates to a movement from the entrance of the gap 48 to the bottom of the gap. The entrance of the gap 48 is provided on the cabin floor surface.

[0073] The term "translational movement" relates to a movement along the longitudinal extension of the gap.

[0074] As an effect, the simple movements provide quick and easy adaptability of the fixed track. As an effect, the simple movements provide easy adaptability in the longitudinal direction from the entrance point of the gap of the fixed track, while the fixed engagement cannot be accessed from the sides surrounded by the floor panel.

[0075] As an advantage, quick installation and quick removal of the track cover section are achieved. As an advantage, quick installation and quick removal of the track cover section between the cabin equipment already installed at the fixed engagement are achieved.

[0076] Figure 3 A cross-section of an overall scheme of an example of the fixed engagement 10 including a partially radial toothed element 52 is shown. A plurality of protrusions 28 are provided as a plurality of partially radial toothed elements 52, as indicated by the arrow 54, which indicates an enlarged image section of the plurality of protrusions 28 at the joint head section. Each of the plurality of first-type engagement members and second-type engagement members 32 has a matching toothed mating part 56, which is configured for locking engagement 58 with the plurality of partially radial toothed elements 52.

[0077] The term "partially radial toothed element" relates to a plurality of protrusions 28 provided by, for example, deepened portions and recesses arranged on the radially outer edge of the profile cross-section of the connecting stud 14. The protrusions 28 follow the radial circumference of the connecting stud 14, but are interrupted in a circumferential region extending parallel to the longitudinal axis 21 of the connecting stud 14, asFigure 3 as shown

[0078] The plurality of partial - radial toothing elements may also be referred to as the plurality of partial - radial toothing elements or toothing elements.

[0079] The term "matching toothing mating part" relates to a form - fit shape of the shape along a cross - section of the longitudinal axis 21 of the connecting stud 14, as Figure 3 shown

[0080] In the example, the cross - section of the partial - radial toothing element 52 along the longitudinal axis 21 has a triangular shape, as Figure 3 shown

[0081] In the example, the angles and shapes of the edges of the triangular shape are changed to affect the joining force or to generate a pre - load force at the connecting stud 14 and the matching toothing mating part 56.

[0082] As an advantage, the joining force between the connecting stud and the secondary attachment joining part 16 can be manipulated. As an advantage, a viscous tolerance tooth part is provided between the connecting stud and the secondary attachment joining part 16. As an advantage, the tolerance between the fixed joint and the floor device can be more easily compensated. As another advantage, the same fixed joint can be used for different types of floor devices.

[0083] In Figure 3 the example, the plurality of partial - radial toothing elements 52 includes two radial parts 60 located on opposite sides of each of the plurality of main connecting studs 14, as indicated by the arrow 62, and the arrow 62 indicates an alternative depiction of the secondary attachment joining part 16 at the joint head region 20 having the plurality of partial - radial toothing elements 52. The two radial parts 60 are configured to engage with the matching inner radial parts 64 of each of the first - type joining parts 30. The two radial parts 60 and the matching inner radial parts 64 are configured to allow each of the first - type joining parts 30 to slide longitudinally to a predetermined step. The two radial parts 60 and the matching inner radial parts 64 are configured to lock each of the first - type joining parts 30 at the predetermined step by rotation of each of the first - type joining parts 30 about the longitudinal axis 21, not shown in Figure 3 Each of the first - type joining parts 30 and each of the plurality of main connecting studs 14 provides a flange 66 for fitting for joining the cabin equipment.

[0084] The term "two radial parts" refers to the area where the protrusion 28 provided by the deepening part and the concave part is interrupted, that is, the area where the protrusion 28 is flattened and includes a flat surface extending parallel to the longitudinal axis 21 of the connecting stud 14. In other words, the connecting stud 14 is cut at the position of the joint head area 20 of the connecting stud, as Figure 3 shown.

[0085] The term "matching inner radial part" refers to a form-fit shape along the cross-sectional shape of the longitudinal axis 21 of the connecting stud 14 including two radial parts 60, which is Figure 3 not shown.

[0086] The term "predetermined step" refers to the maximum value of the protrusion 28 at the connecting stud 14, which defines a specific quantified height along the longitudinal axis 21 of the connecting stud, as Figure 3 shown.

[0087] The term "fitting" refers to the attachment point of the cabin equipment that can be joined by the flange 66, as Figure 3 shown.

[0088] In the example, the connecting stud 14 and the plurality of partially radial toothed elements 52 are configured to provide a stepped variable flange 66 clearance with the first type of engagement member 30. The stepped variable flange 66 clearance is configured to be joined by the fitting of the cabin equipment, which is Figure 3 not shown.

[0089] In the example, the main connecting stud 14 and the plurality of partially radial toothed elements 52 are configured to apply a preloading force on the engagement fitting in the stepped variable flange 66 clearance, which is Figure 3 not shown.

[0090] As an advantage, safe and rapid fastening of the cabin equipment at the fixed joint is achieved. As an advantage, the first type of engagement member 30 provides fastening for fittings of various geometries of the cabin equipment. As another advantage, a variety of different cabin equipment can be installed to a variety of different floor devices through the same fixed joint.

[0091] In Figure 3 the example, the mounting foot area 18 has a threaded section 68, which is configured to establish a form-fit connection with one of the fastening points 22 set as a blind nut 70.

[0092] The term "threaded section" refers to a part having deepening parts and concave parts following a spiral path along the longitudinal axis 21 of the connecting stud.

[0093] The term "blind nut" refers to a sleeve for fastening of the fastening structure.

[0094] In an alternative option, the mounting foot region 18 is provided with a laterally extending portion that forms a bayonet connection with a fastening point 22, which is provided as a bushing with a groove to receive the laterally extending portion, as shown in Figure 3 not shown.

[0095] In the example, the joint head region 20 further includes a tool engagement portion for installing and removing the connecting stud 14 at the fastening point 22, as shown in Figure 3 not shown.

[0096] In the example, the connecting head region further includes a marking element to distinguish the radial tooth-shaped elements among a plurality of radial tooth-shaped elements, as shown in Figure 3 not shown.

[0097] As an advantage, the fastening points can be provided at different positions of the floor device.

[0098] In Figure 3 an example not shown, one of the plurality of connecting studs 14 is configured to be fastened to one of the plurality of fastening points 22 in the floor device 24 to provide a longitudinally extending fixed joint section, which is configured to form an adaptable seat track.

[0099] The term "longitudinally extending" relates to a section that is longer than its width and extends, for example, in a direction along a linear arrangement of the fastening points 22 transverse to the longitudinal direction of the connecting stud 14.

[0100] The term "fixed joint section" relates to a joint provided by a number of connecting studs 14, which is capable of receiving fittings or the like for fixing cabin equipment. The term "section" indicates a linear arrangement along the fastening points 22, and additional sections can also be provided. This section forms a kind of track section. Thus, a number of sections form a virtual track having track sections, i.e., track segments, and interrupted track sections, i.e., interrupted track segments.

[0101] The term "adaptable" relates to selecting joint segments of the connecting stud 14 that are provided only where needed.

[0102] The adaptable seat track can also be referred to as an adaptable seat fixing joint or an adaptable mounting fixing joint.

[0103] As an advantage, the seat track is provided with a fixed joint that can adapt to geometric variations of the support member around the seat track in the longitudinal direction. As another advantage, a fixed joint that can be applied to the seat track is provided, and the geometric dimensions of the seat track vary in the longitudinal direction.

[0104] Figure 4A cross-section of an example overall scheme of an aircraft floor mounting system 100 and an aircraft floor device 200 is shown. The aircraft floor mounting system 100 includes: at least one longitudinally extending clamping profile 102; a plurality of fastening elements 104 configured to provide a plurality of fastening points 22; and at least one fixed joint 110 having a plurality of main connection studs 14 according to one of the foregoing examples. The longitudinally extending clamping profile 102 includes: at least one outer section 112 for holding an edge of at least one floor panel 114; and a central recessed section 116 for attaching the longitudinally extending clamping profile 102 to a floor support beam 118 of an aircraft cabin. The plurality of fastening elements 104 are configured to be arranged along the central recessed section 116 in the installed state. The longitudinally extending clamping profile 102 is configured to be attached to the floor support beam 118 by the plurality of fastening elements 104. One of the plurality of main connection studs 14 is configured to be mounted to a part of one of the plurality of fastening points 22.

[0105] The term "clamping profile" relates to a profile for attaching a floor panel 114 by pressing the floor panel against a support surface. Thus, the floor panel 114 is clamped at the edge of the floor panel, as Figure 4 shown.

[0106] As an example, the floor panel 114 is provided with a corrugated profile, i.e., a corrugated panel.

[0107] Figure 4 A cross-section of an example overall scheme of an aircraft floor device 200 is also shown. The aircraft floor device 200 includes: at least one floor support beam 202; a plurality of fastening points 204 arranged on an upper side along at least a part of the floor support beam 202; a plurality of fastening elements 206; and at least one fixed joint 210 having a plurality of main connection studs 14 according to one of the foregoing examples. One of the plurality of fastening points 204 is configured to receive a mounting foot area 18 of one of the plurality of main connection studs 14. The plurality of fastening points 204 are configured to fix the plurality of connection studs 14 against the floor support beam 202 by the plurality of fastening elements 206.

[0108] The term "upper side" relates to the side of the floor support beam 202 facing the aircraft floor device.

[0109] In Figure 4In the example, a plurality of fastening points 204 are provided as through-holes 212 in the upper flange section of the floor support beam 202, and a plurality of fastening elements 206 are provided as blind nuts 214. The blind nuts 214 provide holes aligned with the through-holes 212, and the mounting foot area 18 of one of the main connecting studs 14 among the plurality of main connecting studs 14 is inserted into the through-hole 212 in a manner that engages with the blind nut 214. One of the main connecting studs among the plurality of main connecting studs 14 and one of the blind nuts 214 are configured to establish a threaded or riveted form-fitting connection.

[0110] As an advantage, the floor device can be arranged for seat tracks at different positions.

[0111] In Figure 4 In the example, the floor device 200 according to one of the foregoing examples further includes: at least one floor panel 216, the at least one floor panel 216 being rested on the floor support beam 202; and at least one clamping profile 218. The clamping profile 218 is configured to hold the upper lateral edge 220 of the floor panel 216 in a clamping manner. The clamping profile 218 is configured to be attached to the floor support beam 202 by fastening a plurality of main connecting studs 222 with a plurality of fastening elements at the plurality of fastening points 204. The engagement head area 223 of one of the main connecting studs 222 among the plurality of main connecting studs 222 includes a track covering section 224. The track covering section 224 can be attached to the upper lateral edge 220 of the floor panel 216 by sliding the track covering section 224 along the upper lateral edge 220 until the mating pair 226 of the track covering section 224 engages with the engagement head area 223 of one of the main connecting studs 222.

[0112] In the example, the floor support beam 202 is made of a corrosive material, and the clamping profile is made of a corrosion-resistant material.

[0113] As an advantage, fixed tracks can be applied to various types of floor panels. As another advantage, the floor panels can vary throughout the floor device.

[0114] Figure 5 An example of an aircraft 300 including an aircraft floor device 308 is shown. The aircraft 300 includes: a fuselage 302; a wing device 304 attached to the fuselage; an aircraft cabin 306; and an aircraft floor device 308 according to one of the foregoing examples. The aircraft cabin 306 is provided within the fuselage 302 and the aircraft cabin 306 includes the aircraft floor device 308.

[0115] Figure 6 An example of the basic steps of a method for providing a fixed joint 10 for an aircraft cabin floor 12 is shown. Referring toFigure 1 , method 200 includes the following steps:

[0116] - In a first step 402, a plurality of main connecting studs 14 are provided.

[0117] - In a second step 404, a plurality of secondary attachment engagement members 16 are provided. Each of the plurality of main connecting studs 14 includes a mounting foot region 18 and an engagement head region 20, and the mounting foot region 18 and the engagement head region 20 are arranged along the longitudinal axis 21 of each of the plurality of main connecting studs 14. The mounting foot region 18 is configured to be fastened to one of a plurality of fastening points 22 linearly arranged in the floor device 24 by a form-fitting connection with one of the plurality of fastening points 22. On two opposite lateral sides 26, the engagement head region 20 of each of the plurality of main connecting studs 14 includes a plurality of protrusions 28 extending transversely to the longitudinal axis 21. Each of the plurality of secondary attachment engagement members 16 is configured to be mountable to each of the engagement head regions 20 of the plurality of main connecting studs 14 by engaging the plurality of protrusions 28 in a form-fitting manner in the longitudinal direction. Each of the plurality of secondary attachment engagement members 16 is capable of being positioned in a positioning movement to the engagement head region 20 and locked in a locking movement to achieve form-fitting retention. The plurality of secondary attachment engagement members 16 includes a first type of engagement member 30 and a second type of engagement member 32. The first type of engagement member 30 can be positioned in a first positioning movement 34 and locked in a first locking movement 36, and the second type of engagement member 32 can be positioned in a second positioning movement 38 and locked in a second locking movement 40, and the first locking movement 36 is different from the second locking movement 40.

[0118] It must be noted that the embodiments of the present invention are described with reference to different subjects. In particular, some embodiments are described with reference to method-type claims, while other embodiments are described with reference to apparatus-type claims. However, based on the above and following descriptions, those skilled in the art will understand that, unless otherwise indicated, any combination of features related to different subjects is also considered to be disclosed together with this application in addition to any combination of features belonging to one type of subject. However, all features can be combined to provide a synergistic effect that exceeds a simple superposition of the features.

[0119] Although the invention has been illustrated and described in detail in the drawings and foregoing description, such illustration and description are to be considered illustrative or exemplary and not restrictive. The invention is not limited to the disclosed embodiments. Other variations of the disclosed embodiments can be understood and effected by those skilled in the art in practicing the claimed invention, from a study of the drawings, the disclosure, and the dependent claims.

[0120] In the claims, the word "comprising" does not exclude other elements or steps, and a reference to an indefinite article does not exclude a plurality. A single processor or other unit may fulfill the functions of several items recited in the claims. The fact that certain measures are recited in mutually different dependent claims does not indicate that a combination of these measures cannot be used to advantage. Any reference signs in the claims should not be construed as limiting the scope.

Claims

1. A fixed joint (10) for an aircraft cabin floor (12), the joint comprising: - a plurality of main connection studs (14); as well as - a plurality of secondary attachment engagement members (16); Each of the plurality of main connection studs comprises a mounting foot region (18) and a joint head region (20), wherein the mounting foot region (18) and the joint head region (20) are arranged along a longitudinal axis (21) of each of the plurality of main connection studs; wherein the mounting foot region is configured to be fastened to one of the plurality of fastening points (22) by a form-fitting connection with one of the plurality of fastening points linearly arranged in the floor device (24); wherein, on two opposite lateral sides (26), the joint head region of each of the plurality of main connection studs comprises a plurality of protrusions (28) extending transversely to the longitudinal axis; wherein each of the plurality of secondary attachment engagement members is configured to be mountable to each of the engagement portion head regions of the plurality of primary connection studs by engaging the plurality of protrusions in a form-fitting manner in a longitudinal direction; wherein each of the plurality of secondary attachment engagement members is positionable to the engagement portion head region in a positioning movement and is lockable in a locking movement to achieve a form-fitting retention; wherein the plurality of secondary attachment engagement members include a first type of engagement member (30) and a second type of engagement member (32); and The first type of engagement component is positionable in a first positioning movement (34) and lockable in a first locking movement (36), and the second type of engagement component is positionable in a second positioning movement (38) and lockable in a second locking movement (40), the first locking movement being different from the second locking movement.

2. The joint according to claim 1, wherein: The first type of engagement component is an attachment portion (42) configured to form a seat track portion (44) for securing a seat to the aircraft cabin floor.

3. The joint according to claim 1 or 2, wherein: The first positioning movement is a movement along the longitudinal axis and the first locking movement is an angular rotation about the longitudinal axis within an angular range of approximately 45° to 135°.

4. The joint according to claim 1, 2 or 3, wherein: The second type of engagement component is a track cover segment (46) for closing a gap (48) between floor panels (50) adjacent to a plurality of linearly arranged fastening points.

5. The joint according to one of the preceding claims, wherein The second positioning movement is a downward movement to position the rail cover segment along the plurality of linearly arranged fastening points, and the second locking movement is a translational movement in the direction of the plurality of linearly arranged fastening points.

6. The joint according to one of the preceding claims, wherein The plurality of protrusions are configured as a plurality of partially radial toothed elements (52); and Each of the plurality of first type engagement components and the second type engagement components has a matching toothed counterpart (56) configured for locking engagement (58) with the plurality of partially radial toothed elements.

7. The joint according to one of the preceding claims, wherein The plurality of partially radial toothed elements include two radial portions (60) located on opposite sides of each of the plurality of main connection studs; wherein the two radial portions are configured to engage with a matching inner radial portion (64) of each of the first type of engagement components; wherein the two radial portions and the matching inner radial portion are configured to allow each of the first type of engagement components to slide to a predetermined step along the longitudinal direction; wherein the two radial portions and the matching inner radial portion are configured to lock each of the first type of engagement components at the predetermined step by rotation of each of the first type of engagement components about the longitudinal axis; and Wherein each of the first type of engagement components and each of the plurality of main connection studs provide a flange (66) for engaging an accessory of cabin equipment.

8. The joint according to one of the preceding claims, wherein The mounting foot region has a threaded section (68) which is designed to produce a positive connection with one of the plurality of fastening points which is provided as a blind hole nut (70).

9. The joint according to one of the preceding claims, wherein: One of the plurality of connection studs is configured to be fastened to one of the plurality of fastening points in the floor arrangement to provide a longitudinally extending fixed joint section configured to form an adaptable seat track.

10. An aircraft floor mounting system (100), the aircraft floor mounting system comprising: - at least one longitudinally extending clamping profile (102); - a plurality of fastening elements (104) configured to provide a plurality of fastening points; and - at least one fixing joint (110) having a plurality of main connecting studs according to one of claims 1 to 9; wherein the longitudinally extending clamping profile comprises: at least one outer section (112) for holding an edge of at least one floor panel (114); and a central recessed section (116) for attaching the longitudinally extending clamping profile to a floor support beam (118) of an aircraft cabin; wherein the plurality of fastening elements are configured to be arranged along the central recessed section in an installed state; wherein the longitudinally extending clamping profile is configured to be attached to the floor supporting beam by means of the plurality of fastening elements; and Wherein, one of the plurality of main connection studs is configured to be mounted to a portion of one of the plurality of fastening points.

11. An aircraft floor device (200), the aircraft floor device (200) comprising: - at least one floor supporting beam (202); - a plurality of fastening points (204) arranged on the upper side along at least a portion of the floor support beam; - a plurality of fastening elements (206); as well as - at least one fixing joint (210) having a plurality of main connecting studs according to one of claims 1 to 9; wherein one of the plurality of fastening points is configured to receive a mounting foot region of one of the plurality of main connection studs; and Wherein, the plurality of fastening points are configured to secure the plurality of connection studs against the floor support beams via the plurality of fastening elements.

12. The floor device according to claim 11, wherein The plurality of fastening points are provided as through holes (212) in the upper flange section of the floor support beam, and the plurality of fastening elements are provided as blind nuts (214); wherein the blind hole nut provides a hole aligned with the through hole, and a mounting foot region of one of the plurality of main connection studs is inserted into the through hole in a manner engaging with the blind hole nut; Wherein, one main connection stud among the plurality of main connection studs and one blind hole nut among the blind hole nuts are configured to establish a threaded or riveted form-fitting connection.

13. The floor device according to claim 11 or 12, further comprising: - at least one floor panel (216), said at least one floor panel (216) resting on said floor support beams; as well as - at least one clamping profile (218); wherein the clamping profile is configured to hold the upper lateral edge (220) of the floor panel in a clamping manner; wherein the clamping profile is configured to be attached to the floor support beam by fastening the plurality of main connection studs with the plurality of fastening elements at the plurality of fastening points; wherein the joint head region of one of the plurality of main connection studs comprises a track cover section (222); and wherein the track cover section is attachable to the upper lateral edge of the floor panel by sliding the track cover section along the upper lateral edge until a matching counterpart (224) of the track cover section engages the engagement portion head region (226) of one of the plurality of primary connection studs (228).

14. An aircraft (300), comprising: - fuselage (302); - a wing device (304) attached to the fuselage; - an aircraft cabin (306); and - an aircraft floor device (308) according to one of claims 11 to 13; wherein the aircraft cabin is arranged in the fuselage; and Therein, the aircraft cabin comprises the aircraft floor device.

15. A method (400) for providing a fixed joint for an aircraft cabin floor, the method comprising the steps of: - providing (402) a plurality of main connection studs; and - providing (404) a plurality of secondary attachment engagement members; wherein each of the plurality of main connection studs comprises a mounting foot region and a joint head region, wherein the mounting foot region and the joint head region are arranged along a longitudinal axis of each of the plurality of main connection studs; wherein the mounting foot region is configured to be fastened to one of a plurality of fastening points arranged linearly in the floor arrangement by a form-fitting connection with one of the plurality of fastening points; wherein, on two opposing lateral sides, the engagement portion head region of each of the plurality of main connection studs comprises a plurality of projections extending transversely to the longitudinal axis; wherein each of the plurality of secondary attachment engagement members is configured to be mountable to each of the engagement portion head regions of the plurality of primary connection studs by engaging the plurality of protrusions in a form-fitting manner in a longitudinal direction; wherein each of the plurality of secondary attachment engagement members is positionable to the engagement portion head region in a positioning movement and is lockable in a locking movement to achieve a form-fitting retention; wherein the plurality of secondary attachment engagement members include a first type of engagement member and a second type of engagement member; and The first type of engagement component is positionable in a first positioning movement and lockable in a first locking movement, and the second type of engagement component is positionable in a second positioning movement and lockable in a second locking movement, the first locking movement being different from the second locking movement.

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