Sliding joint, fuselage structural assembly and related methods

Abstract

An example method and system for isolating and mitigating loads in an aircraft is described, including providing a sliding joint between a seat track and a cockpit floor panel. The sliding joint includes a lug having a first end and a second end opposite the first end, wherein the first end is adapted to be attached to the seat track and the second end includes an elongated hole; and a clevis including an oblong slider bushing coupled to the lug.

Description

Technical Field

[0001] The present disclosure relates generally to mitigating load transfer between two floor components of an aircraft, and more particularly to providing a sliding joint for isolating thermal loads and bending deformation between a seat track and a flight deck floor panel during cycling of the aircraft. Background Art

[0002] In modern commercial airliners, two or more seats are connected to a chassis to form a seat row, and this chassis is, in turn, securely mounted to one or more underlying longitudinally extending tracks. These seat tracks connect to the cockpit floor panel, which is located toward the front of the aircraft and contains, among other compartments, the lavatory and cockpit. Typically, there is a vertical step of at least several inches at the transition between the floor containing the seat tracks and the cockpit floor panel.

[0003] During cruising, aircraft motion causes thermal loading and bending of floor components. Thermal stresses and bending can accumulate and be transferred through the joints between the seat tracks and the cockpit floor panels. Thermal and bending loads can often reach levels sufficient to cause significant jostling between the two sections of the aircraft. Furthermore, these loads can lead to binding and fatigue in the joints.

[0004] There is a need for improved systems and methods capable of isolating thermal loads and body bending between aircraft floor panels, such as between passenger seat tracks and cockpit floor panels. Summary of the Invention

[0005] In one example, a sliding joint for isolating load transfer between a seat track and a cockpit floor panel of an aircraft is described. The sliding joint includes a lug having a first end and a second end opposite the first end, wherein the first end is adapted to be attached to the seat track and the second end includes an elongated hole. The sliding joint also includes a clevis including an oblong slider bushing coupled to the lug.

[0006] In another example, a fuselage structure assembly is provided. The fuselage structure assembly includes a seat track, a cockpit floor panel, and a sliding joint. The sliding joint includes a lug having a first end and a second end opposite the first end, wherein the first end is adapted to be attached to the seat track and the second end includes an elongated hole; and a clevis including an oblate slider bushing coupled to the lug.

[0007] In another example, a method for isolating load transfer between a passenger seat track and a cockpit floor panel of an aircraft is provided. The method includes attaching a first end of a lug to the seat track, the lug further including a second end having an elongated hole therethrough; attaching a first end of a clevis to the cockpit floor panel, the first end of the clevis including a platform and a pair of arms extending from the platform; coupling an oblong slider bushing to the pair of arms of the clevis; and receiving the oblong slider bushing within the elongated hole to secure the clevis to the lug.

[0008] The features, functions, and advantages that have been discussed can be achieved independently in various examples or may be combined in yet other examples, further details of which can be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] The novel features which are believed to be characteristic of the illustrative examples are set forth in the appended claims. However, the illustrative examples, together with the preferred mode of use, further objects and description thereof, will be best understood by reference to the following detailed description of illustrative examples of the disclosure when read in conjunction with the accompanying drawings, in which:

[0010] Figure 1 A fuselage structure assembly including a sliding joint between a seat track and a cockpit floor panel is shown according to an example embodiment.

[0011] Figure 2a A perspective view of a sliding joint according to an example embodiment is shown, such as in Figure 1 Sliding joints used in fuselage structural components.

[0012] Figure 2b Shows assembly to cockpit floor panel and seat tracks according to example embodiments Figure 2a Side view of the slip joint.

[0013] Figure 2c Shown in accordance with an example embodiment Figure 2b Cross-section of the oblate slider bushing within the lug of a sliding joint.

[0014] Figure 3 Shown are a series of example sliding joints positioned within an aircraft according to example embodiments.

[0015] Figure 4 Shown according to example embodiments Figure 3 Perspective and enlarged views of a series of sliding joints.

[0016] Figure 5 A method for isolating load transfer between a seat track and a cockpit floor panel of an aircraft is shown according to an example embodiment.

[0017] Figure 6 Shown according to example embodiments Figure 5 Another method that can be used together with the method shown. DETAILED DESCRIPTION

[0018] The disclosed examples will now be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all, disclosed examples are shown. Indeed, several different examples may be described, and they should not be construed as limited to the examples set forth herein. Rather, these examples are described so that this disclosure will be thorough and complete and will fully convey the scope of the disclosure to those skilled in the art.

[0019] Examples, methods, and systems for a sliding joint for isolating load transfer between an aircraft's seat track and cockpit floor panel are described. To this end, a lug positioned within the seat track's open channel receives a clevis with an oblong bushing, allowing the bushing to translate forward and rearward within the lug's elongated hole. In this example, the clevis has a platform adapted for attachment to the cockpit floor panel. This translation of the sliding joint assembly's components prevents the accumulation of thermal and bending loads between the seat track and cockpit floor panel during aircraft cruising, while also accommodating complex geometries including vertical steps between the two surfaces.

[0020] Furthermore, the oblate shape of the bushing provides an enlarged contact surface area of ​​the bushing within the elongated opening of the lug during translation, which prevents wear of the bushing itself and thus improves the service life of the joint.

[0021] As used herein, a seat track may include any passenger seat track that accommodates one or more seat units of an aircraft. The seat unit and seat track comprise standard equipment used throughout the aviation industry, wherein the seat track includes a plurality of longitudinally spaced mounting brackets to enable the seat unit to be positioned in various positions along the seat track. The seat track is formed of a rigid material such as metal (e.g., titanium, etc.), which facilitates its ability to serve as a mounting platform for the seat unit.

[0022] As used herein, a cockpit may include the aircraft cabin from which the pilots and crew operate the aircraft and in which various equipment and controls are placed. The cockpit may also include additional rooms and compartments, such as lavatories, food preparation stations, and storage rooms.

[0023] refer to Figure 1 , shows a fuselage structure assembly 100 according to an example, which includes a seat track 130, a cockpit floor panel 140 and a sliding joint 110. The sliding joint 110 is positioned between the seat track 130 and the cockpit floor panel 140. Figure 1 , fuselage structural components are shown within aircraft 200 .

[0024] Aircraft 200 may be a commercial aircraft used to accommodate and transport passengers, wherein the passengers sit on seat units 132 mounted to seat tracks 130 .

[0025] exist Figure 1 , the cockpit floor panel 140 is shown positioned on a different plane than the seat tracks 130. Figure 1 In some examples, the cockpit floor panel 140 is located on a plane that is parallel to and higher than the plane in which the seat tracks 130 are located. In some examples, the cockpit floor panel 140 is located on a plane that is approximately 5-10 inches above the seat tracks 130. In some examples, the cockpit floor panel 140 is located on a plane that is approximately 7 inches above the seat tracks 130.

[0026] The sliding joint 110 provides the primary structural connection between the seat track 130 and the cockpit floor panel 140. The sliding joint 110 may be covered with vertical panels or floor beams to form a step between the seat track 130 and the cockpit floor panel 140. Figure 2a The sliding joint 110, described in further detail in FIG. 1A -c, provides for free translation in the fore and aft directions. Thus, when one or both of the seat track 130 and the cockpit floor panel 140 experience turbulence or otherwise move during flight, certain components of the sliding joint also move without extending that movement to the other floor panel.

[0027] Figure 2a A perspective view of a sliding joint according to an example embodiment is shown, such as in Figure 1 A sliding joint 110 is used in the fuselage structural assembly 100.

[0028] The sliding joint 110 includes a lug 112 configured to be received on a seat track such as Figure 1 The seat rail 130 is provided with an open channel 133 . Figure 1 A portion of the seat rail 130 is located in Figure 2a The first end 113 of the lug 112 is Figure 2a 1 is shown as including an engagement portion 114 to engage a seat track 130. Figure 2a In FIG. 1 , the engagement portion 114 includes a plurality of holes 115 that engage a plurality of bolts therethrough to secure the engagement portion 114 within the seat track 130 .

[0029] The second end 116 of the lug 112 includes an elongated hole 117. In this example, the elongated hole 117 includes a rounded end 118, the two rounded ends being Figure 2bThe rounded end 118 accommodates the shape of the oblong slider bushing, allowing it to move freely from one end to the other within the elongated hole 117 without becoming stuck. The size and shape of the elongated hole 117 are designed to provide one-dimensional movement of the bushing therein. This one-dimensional movement accounts for thermal expansion, contraction, or bending deformation of the seat track 130 and cockpit floor panel 140 during flight of the aircraft 200.

[0030] Sliding joint 110 also includes a clevis 120. Clevis 120 includes an oblate-shaped slider bushing 122. The elongated hole 117 of lug 112 is sized and shaped to receive oblate-shaped slider bushing 122, which slidably secures clevis 120 to lug 112. Oblate-shaped slider bushing 122 is typically made of a strong material that is not prone to rapid wear, such as metal, such as steel. In some examples, oblate-shaped slider bushing 122 is formed from corrosion-resistant steel. In other examples, oblate-shaped slider bushing 122 is formed from titanium.

[0031] Because of the contact between the oblate slider bushing 122 and the surface defining the elongated hole 117, the outer surface of the oblate slider bushing 122 is considered a wear surface, and the oblate spheroid shape of the bushing increases the area of ​​the wear surface of the slider bushing 122. The expanded contact surface area of ​​the bushing within the elongated opening of the lug during translation provided by the oblate spheroid shape prevents wear of the bushing itself, thereby improving joint service life. Figure 2c The illustrated flat top and bottom surfaces 121 form enlarged wear surfaces.

[0032] Figure 2b Shown is a diagram of a circuit according to an example embodiment. Figure 1 The seat tracks 130 and the cockpit floor panels 140 Figure 1 1. A cross-sectional side view of the sliding joint 110. The U-shaped clamp 120 includes a platform 124 at a first end of the U-shaped clamp 120 and a pair of arms 126 extending from the platform 124 (at Figure 2b An oblong slider bushing 122 extends through the pair of arms 126 .

[0033] like Figure 2b As shown, the platform 124 is adapted to be attached to a cockpit floor panel 140. The platform 124 may be attached directly to the cockpit floor panel, or may be attached to a reinforcement member, such as a Figure 2bThe reinforcement 127 shown in FIG. The reinforcement 127 can be a metal or other rigid structure that can additionally be present behind the vertical floor panel 128 to structurally support the vertical panel 128. The vertical floor panel 128 covers the step or transition gap between the seat track 130 and the cockpit floor panel 140.

[0034] Figure 2c Shown in the elongated hole of the lug according to an example embodiment Figure 2b The cross section of the flat circular slider bushing of the sliding joint. Figure 2b As previously mentioned, the flat top and bottom surfaces 121, 122 of the slider bushing 122 form an enlarged wear surface, which is beneficial for extending the life of the bushing. The rounded or rounded side surfaces 123 maintain the ellipsoidal shape of the bushing, thereby allowing smooth translation between the ends 118 of the elongated hole.

[0035] During the cruising period of flight, the accumulation of thermal loads and body bending can account for half an inch or more. The sliding joint 110 described in detail above improves the service life of the joint because the size and shape of the elongated hole are designed to allow the oblate slider bushing to move within the elongated hole, thereby addressing the thermal expansion, contraction, or bending deformation of the passenger seat track and the cockpit floor panel during aircraft flight. The movement only includes one-dimensional movement. Therefore, by reducing the accumulation of thermal loads and body bending applied to the joint (which causes joint fatigue or joint binding during the cruising period of the aircraft), the service life of the joint can be extended.

[0036] Figure 3 A series of example sliding joints 110 are shown positioned within an aircraft 200 according to an example embodiment. Figure 3 As shown, multiple sliding joints, such as reference Figure 1-2c The sliding joint 110 described may span an aircraft (such as a Figure 1 The width of the aircraft 200) is 170 to locate.

[0037] Figure 4 Shown according to example embodiments Figure 3 A perspective view and an enlarged view of a series of sliding joints 110. Figure 4 Show Figure 2b The reinforcement 127 and vertical panel 128, the U-shaped clip 120 and the lug 112.

[0038] Figure 5 A flow chart illustrating an example of a method 500 for isolating load transfer between a passenger seat track and a cockpit floor panel of an aircraft, according to an example embodiment. Figure 5The illustrated method 500 presents a method that may be used, for example, with the fuselage structure assembly 100 and / or by Figure 1 The method 500 is performed by the fuselage structure assembly 100 shown. The method 500 includes one or more operations, functions, or actions as shown in one or more of blocks 502-508. Although the blocks are shown in a sequential order, the blocks may also be performed in parallel and / or in an order different from that described herein. In addition, various blocks may be combined into fewer blocks, divided into additional blocks, and / or eliminated based on the desired implementation.

[0039] It should be understood that for this and other processes and methods disclosed herein, the flowchart illustrates the functionality and operation of one possible implementation of this example. As reasonably understood by those skilled in the art, alternative implementations are included within the scope of the examples disclosed herein, wherein, depending on the functionality involved, the functionality may be performed in a different order than that shown or discussed, including substantially simultaneously or in reverse order.

[0040] At block 502 , method 500 includes attaching a first end of a lug to a seat track, the lug also including a second end having an elongated hole therethrough.

[0041] The lugs may be the same or similar to lugs 112 and the seat track may be the same as reference lugs 112. Figure 1-2b The seat track 130 described is similar or identical. Figure 2a In the example shown in FIG-b, the first end 113 of the lug 112 includes an engagement portion to engage the seat track 130. In this example, the first end 113 is attached to the seat track 130 by inserting the first end 113 into a channel or other opening in the seat track 130. The first end 113 of the lug 112 can then be secured within the seat track 130 by any of a number of fasteners, such as, but not limited to, bolts, screws, etc. Figure 1-2b If the geometry is different from the geometry shown in the example, the first end 113 of the lug 112 can be formed to accommodate and fit within the geometry.

[0042] At block 504, method 500 includes attaching a first end of a U-shaped clamp to the cockpit floor panel, the first end of the U-shaped clamp including a platform 124 and a pair of arms extending from the platform 124. The platform 124 is Figure 2a -b example is shown with a flat surface that can be attached directly to the cockpit panel or to a component attached to the cockpit panel, such as a vertical floor beam or a reinforcement located behind the vertical floor beam, e.g. Figure 2b shown.

[0043] At block 506, method 500 includes coupling an oblong slider bushing to a pair of arms of a clevis. The oblong slider bushing may be coupled to a pair of arms of a clevis. Figure 2a The oblong slider bushing 122 is shown as including flat top and bottom surfaces 121 and rounded or circular sides 123.

[0044] At block 508, the method 500 includes receiving the oblong slider bushing within the elongated hole to secure the U-clip to the lug. The elongated hole 117 at the second end 116 of the lug 112 includes Figure 2a -b shows a rounded end 118 to accommodate the shape of the oblong slider bushing, thereby allowing the oblong slider bushing to move from one end to the other in the elongated hole 117.

[0045] In one example, movement of the cockpit floor panel 140 will cause the clevis 120 and associated oblong slider bushing 122 to move in the fore-aft direction within the elongated hole 117. And in another example, movement of the seat track 130 will cause the lug to move in the fore-aft direction.

[0046] Figure 6 Shows the implementation according to the example Figure 5 Another method is used in conjunction with the method 500 shown. Figure 6 In the present invention, at block 510, the method includes translating the oblate slider bushing in a forward and aft direction within the elongated hole during cruising of the aircraft. When the aircraft 200 takes off and then continues to fly through the air, one or both of the seat track 130 and the cockpit panel 140 may move or jolt. Such movement causes the slider bushing 122 to move in a forward or aft direction within the elongated hole 117.

[0047] In this example, the translation of the components of the sliding joint assembly consistently accommodates the complex geometry between the seat track 130 and the cockpit floor panel 140, preventing the accumulation of thermal and bending loads between the seat track and the cockpit floor panel during aircraft cruising. The oblate shape of the bushing provides an increased contact surface area of ​​the bushing within the elongated opening of the lug during translation, which prevents wear of the bushing itself and thus further improves the service life of the joint.

[0048] The description of different advantageous arrangements has been presented for purposes of illustration and description and is not intended to be exhaustive or limited to the examples of the disclosed form. Many modifications and variations will be apparent to those of ordinary skill in the art. In addition, different advantageous embodiments may describe different advantages compared to other advantageous embodiments. The selected one or more embodiments are selected and described in order to explain the principles of the embodiments, practical applications, and to enable others of ordinary skill in the art to understand the disclosure of the various embodiments with various modifications as are suitable for specific intended uses.

[0049] Item 1: A sliding joint for isolating load transfer between a seat track and a cockpit floor panel of an aircraft, comprising: a lug including a first end and a second end opposite the first end, wherein the first end is adapted to be attached to the seat track and the second end includes an elongated hole; and a U-shaped clamp including an oblate slider bushing coupled to the lug.

[0050] Clause 2: The slip joint of clause 1, wherein the elongated hole of the lug is sized and shaped to receive the oblong slider bushing to slidably secure the clevis to the lug.

[0051] Clause 3: The slip joint of clause 2, wherein the elongated hole includes a rounded end.

[0052] Clause 4: The sliding joint of any of clauses 1-3, wherein the first end of the lug includes an engagement portion to engage the seat track.

[0053] Clause 5: The slip joint of any of clauses 1-4, wherein the clevis comprises a platform at a first end of the clevis and a pair of arms extending from the platform.

[0054] Clause 6: The sliding joint of clause 5, wherein the oblong slider bushing extends through the pair of arms.

[0055] Clause 7: The sliding joint of clause 6, wherein the oblate slider bushing comprises an oblate ellipsoid shape, thereby increasing the wear surface area of ​​the oblate slider bushing.

[0056] Clause 8: The sliding joint of any of clauses 1-7, wherein the platform of the clevis is adapted to be attached to the cockpit floor panel.

[0057] Clause 9: A sliding joint according to any one of clauses 1-8, wherein the size and shape of the elongated hole are designed to provide one-dimensional movement of the oblong slider bushing within the elongated hole, thereby accounting for thermal expansion or contraction or bending deformation of the seat track and the cockpit floor panel during flight of the aircraft.

[0058] Clause 10: The sliding joint of clause 9, wherein the one-dimensional motion comprises forward and rearward translation of the oblate slider bushing within the elongated bore.

[0059] Clause 11: A fuselage structure assembly comprising a seat track; a cockpit floor panel; and a sliding joint, the sliding joint comprising: a lug defining a first end and a second end opposite the first end, wherein the second end includes an elongated hole; and a U-shaped clamp comprising an oblate slider bushing coupled to the lug.

[0060] Clause 12: The fuselage structure assembly of clause 11, wherein the first end of the lug is attached to the seat track.

[0061] Clause 13: The fuselage structure assembly of clause 12, wherein the clevis includes a first end having a platform and includes a pair of arms extending from the platform, the first end being attached to the cockpit floor panel.

[0062] Clause 14: The fuselage structure assembly of clause 13, wherein the oblong slider bushing is coupled to and extends between the pair of arms, and wherein the oblong slider bushing is received within the elongated aperture of the lug.

[0063] Clause 15: The fuselage structural assembly of clause 14, wherein the size and shape of the elongated hole are designed to provide movement of the oblong slider bushing within the elongated hole to account for thermal expansion or contraction or bending deformation of the seat track and the cockpit floor panel during flight of the aircraft.

[0064] Clause 16: The fuselage structural assembly of clause 15, wherein said motion comprises motion in only one dimension.

[0065] Clause 17: The fuselage structure assembly of clause 16, wherein said motion comprises forward and aft translation of said oblate slider bushing within said elongated bore.

[0066] Clause 18: The fuselage structure assembly of any of clauses 11-17, wherein the oblate slider bushing comprises an oblate ellipsoid shape.

[0067] Item 19: A method of isolating load transfer between a passenger seat track and a cockpit floor panel of an aircraft, the method comprising: attaching a first end of a lug to the passenger seat track, the lug further comprising a second end having an elongated hole therethrough; attaching a first end of a U-shaped clamp to the cockpit floor panel, the first end of the U-shaped clamp comprising a platform and a pair of arms extending from the platform; coupling an oblong slider bushing to the pair of arms of the U-shaped clamp; and receiving the oblong slider bushing within the elongated hole to secure the U-shaped clamp to the lug.

[0068] Clause 20: The method of clause 19, further comprising translating the oblong slider bushing in the elongated bore in forward and aft directions during cruise of the aircraft.

Claims

1. A sliding joint (110) for isolating load transfer between a seat track (130) and a cockpit floor panel (140) of an aircraft (200), comprising: a lug (112) comprising a first end (113) and a second end (116) opposite the first end (113), wherein the first end (113) is adapted to be attached to the seat track (130) and the second end (116) comprises an elongated hole (117); and A clevis (120) includes an oblong slider bushing (122) coupled to the second end of the lug (112), wherein the first end of the clevis is configured to be attached to the cockpit floor panel.

2. The sliding joint (110) according to claim 1, wherein The elongated hole (117) of the lug (112) is sized and shaped to receive the oblong slider bushing (122) to slidably secure the U-clip (120) to the lug (112).

3. The sliding joint (110) of claim 2, wherein the elongated hole includes a rounded end.

4. The sliding joint (110) according to claim 1, wherein The first end (113) of the lug (112) includes an engagement portion (114) for engaging the seat track (130).

5. The sliding joint (110) according to claim 1, wherein The clevis includes a platform at a first end of the clevis and includes a pair of arms extending from the platform.

6. The sliding joint (110) of claim 5, wherein the oblong slider bushing extends through the pair of arms.

7. The sliding joint (110) of claim 5, wherein the oblate slider bushing comprises an oblate ellipsoid shape, thereby increasing the wear surface area of ​​the oblate slider bushing.

8. The sliding joint (110) according to claim 5, wherein The platform of the clevis is adapted to be attached to the cockpit floor panel (140).

9. The sliding joint (110) according to any one of claims 1 to 8, wherein The size and shape of the elongated hole (117) are designed to provide one-dimensional movement of the oblong slider bushing within the elongated hole (117), thereby accounting for thermal expansion or contraction or bending deformation of the seat track and the cockpit floor panel (140) during flight of the aircraft (200).

10. The sliding joint (110) of claim 9, wherein the one-dimensional motion comprises forward and rearward translation of the oblate slider bushing within the elongated hole (117).

11. A fuselage structural assembly comprising: Seat track (130); cockpit floor panels (140); as well as A sliding joint (110), the sliding joint (110) comprising: a lug (112) defining a first end (113) and a second end (116) opposite the first end (113), wherein the first end is configured to be attached to the seat track, and wherein the second end includes an elongated hole (117); and A clevis includes an oblong slider bushing coupled to a second end of the lug (112), wherein a first end of the clevis is configured to be attached to the cockpit floor panel.

12. The fuselage structure assembly of claim 11, wherein the first end of the clevis has a platform and includes a pair of arms extending from the platform.

13. The fuselage structure assembly of claim 12, wherein the oblong slider bushing is coupled to and extends between the pair of arms, and wherein the oblong slider bushing is received within the elongated hole (117) of the lug (112).

14. The fuselage structural assembly according to claim 13, wherein: The size and shape of the elongated hole (117) are designed to provide movement of the oblate slider bushing (122) within the elongated hole (117), thereby accounting for thermal expansion or contraction or bending deformation of the seat track (130) and the cockpit floor panel (140) during flight of the aircraft (200).

15. The fuselage structure assembly according to claim 14, wherein: The motion comprises motion in only one dimension.

16. The fuselage structural assembly according to claim 15, wherein: The movement includes forward and rearward translation of the oblong slider bushing (122) within the elongated hole (117).

17. The fuselage structural assembly according to any one of claims 11 to 16, wherein: The oblate slider bushing (122) comprises an oblate ellipsoid shape.

18. A method for isolating load transfer between a passenger seat track (130) and a cockpit floor panel (140) of an aircraft (200), the method comprising: attaching a first end (113) of a lug (112) to the passenger seat track, the lug (112) further comprising a second end (116) having an elongated hole (117) therethrough; attaching a first end of a U-shaped clamp (120) to the cockpit floor panel (140), the first end of the U-shaped clamp (120) comprising a platform (124) and a pair of arms (126) extending from the platform (124); coupling an oblong slider bushing (122) to the pair of arms (126) of the clevis (120); and The oblate slider bushing (122) is received in the elongated hole (117) to secure the U-shaped clip (120) to the lug (112).

19. The method according to claim 18, further comprising: During cruising of the aircraft (200), the oblate slider bushing (122) is translated within the elongated hole (117) in forward and aft directions.

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