Locking panel assembly

Abstract

The present invention relates to a locking panel assembly. The panel assembly is for mounting to a track beam, the track beam including a beam flange having a nonlinear edge. The panel assembly includes a panel and a lockable clip movably connected to the panel. The lockable clip includes a lockable mating edge configured to selectively mate with the nonlinear edge of the beam flange of the track beam. The lockable clip further includes a lockable clip edge extending beyond the lockable mating edge. The lockable clip is movable on a lower surface of the panel between an unlocked position and a locked position. In the unlocked position, the lockable clip edge is retracted. In the locked position, the lockable mating edge mates with the nonlinear edge of the beam flange and the lockable clip edge holds the panel on the track beam.

Description

Technical Field

[0001] This disclosure generally relates to a panel assembly, and more specifically to a panel assembly including a lockable latch configured to hold the panel on a track beam. Background Technology

[0002] In many applications, panels can be secured to a structural frame using numerous fasteners such as rivets, bolts, nails, or screws. Due to the sheer number of fasteners, installing and removing such panels can be a laborious and time-consuming task. Summary of the Invention

[0003] A panel assembly for mounting to a track beam is disclosed, the track beam including a beam flange with a non-linear edge. The panel assembly includes a panel and a lockable latch movably connected to the panel. The lockable latch includes a lockable mating edge configured to selectively engage with a non-linear edge of the beam flange of the track beam. The lockable latch also includes a lockable latch edge extending beyond the lockable mating edge. The lockable latch is movable on a lower surface of the panel between an unlocked position and a locked position. In the unlocked position, the lockable latch edge retracts. In the locked position, the lockable mating edge engages with the non-linear edge of the beam flange, and the lockable latch edge holds the panel on the track beam.

[0004] The features and functions already discussed can be implemented independently in various implementations or combined in other implementations, further details of which can be seen in the following description and figures. Attached Figure Description

[0005] Figure 1 An example implementation of the aircraft is shown, in which the aircraft floor panel assembly is mounted on the aircraft seat track beam.

[0006] Figure 2 An example implementation of an aircraft floor panel assembly mounted on an aircraft seat track beam is shown.

[0007] Figures 3 to 4 An example implementation of the aircraft floor panel assembly in the unlocked position is shown.

[0008] Figures 5 to 6 This shows the transition from the unlocked position to the locked position. Figures 3 to 4 Aircraft floor panel components.

[0009] Figures 7 to 8 The locked position is shown. Figures 3 to 4 Aircraft floor panel components.

[0010] Figure 9An example embodiment of an aircraft floor panel assembly is shown, featuring a lockable snap with a lockable mating edge shaped with a scalloped pattern.

[0011] Figure 10 An example embodiment of a lockable snap fastener for an aircraft floor panel assembly is shown, the lockable snap fastener having a lockable mating edge and a lockable snap edge shaped with a wave pattern.

[0012] Figure 11 An example embodiment of an aircraft floor panel assembly is shown, featuring a lockable snap with a lockable mating edge shaped with a serrated pattern.

[0013] Figure 12 An example embodiment of a lockable snap fastener for an aircraft floor panel assembly is shown, the lockable snap fastener having a lockable mating edge and a lockable snap edge shaped with a serrated pattern.

[0014] Figure 13 An example implementation of a key configured to switch an aircraft floor panel assembly between an unlocked position and a locked position is shown.

[0015] Figure 14 Another example implementation of a key configured to switch an aircraft floor panel assembly between an unlocked position and a locked position is shown. Detailed Implementation

[0016] Traditional panels are mechanically fastened to the corresponding structural frame using a large number of fasteners (e.g., rivets, bolts, nails, or screws) to properly transfer shear forces and / or other loads from the panel to the structural frame. Because of the extensive use of fasteners to hold the panel to the structural frame, installing and removing such panels can be a laborious and time-consuming task.

[0017] This specification relates to a panel assembly that uses a reduced number of fasteners to mount the panel to a corresponding structural frame compared to conventional panels. The panel assembly is designed to use movable panel locks to selectively hold the panel to the structural frame, rather than relying solely on fasteners. As described in more detail below, this panel assembly can significantly reduce or even completely eliminate the number of fasteners used to secure the panel to the structural frame compared to conventional methods. This significantly reduces the time required for panel installation and / or removal. Furthermore, the overall weight of the assembly can be reduced due to the reduced number of fasteners. This panel assembly may be particularly advantageous when used as a floor panel assembly in aircraft. However, the panel assembly described herein is not limited to aircraft floor panel assemblies and can be used in any panel application.

[0018] Figure 1 An illustrative aircraft 100 including a fuselage 102 is shown. The fuselage 102 includes an interior cabin section 104, shown in increased detail in the enlarged view. The interior cabin section 104 includes a plurality of passenger seats 106 arranged in multiple rows oriented perpendicular to the longitudinal axis 108 of the fuselage 102. Each row of passenger seats 106 is mechanically fastened to two or more aircraft seat track beams 110, which are generally coaxially oriented with the longitudinal axis 108 of the fuselage 102. The aircraft seat track beams 110 provide a structural frame for anchoring the passenger seats 106 to the fuselage 102. An aircraft floor panel assembly 112 is mounted on top of a pair of aircraft seat track beams 110. The aircraft floor panel assembly 112 provides a structural floor to support passengers, baggage, and other equipment within the interior cabin section 104. The aircraft floor panel assembly 112 is configured to use movable, lockable latches 228 (… Figure 2 (As shown in the figure) it can be quickly and easily installed on the aircraft seat track beam 110, which allows the aircraft floor panel assembly 112 to be installed on the aircraft seat track beam 110 with a reduced number of fasteners compared to conventional floor panel assemblies.

[0019] Figures 2 to 8 An exemplary aircraft floor panel assembly 200 for mounting to spaced-apart aircraft seat track beams, such as aircraft seat track beam 202 and aircraft seat track beam 204, is shown. Aircraft seat track beam 202 includes a beam flange 206 having a non-linear edge 208 (i.e., not straight in the longitudinal direction of the beam). An illustrative shape of the non-linear edge 208 is shown in cutout 210. Aircraft seat track beam 204 includes a beam flange 212 spaced apart from the beam flange 206. The beam flange 212 has a non-linear edge 214. An illustrative shape of the non-linear edge 214 is shown in cutout 216. Aircraft seat track beam 202 and / or aircraft seat track beam 204 can be made of any suitable material, including but not limited to metals (e.g., aluminum, titanium, steel) and composite materials (e.g., carbon fiber).

[0020] For ease of explanation, in some cases, features associated with aircraft seat track beam 202 may be characterized as "first," and features associated with aircraft seat track beam 204 may be characterized as "second." For example, aircraft seat track beam 202 may be referred to as the first aircraft seat track beam, and aircraft seat track beam 204 may be referred to as the second aircraft seat track beam. Furthermore, beam flange 206 may be referred to as the first beam flange, and beam flange 212 may be referred to as the second beam flange. Additionally, nonlinear edge 208 may be referred to as the first nonlinear edge, and nonlinear edge 214 may be referred to as the second nonlinear edge.

[0021] The aircraft floor panel assembly 200 includes an aircraft floor panel 218 configured to be mounted on top of aircraft seat track beams 202, 204. The aircraft floor panel 218 may have any suitable size to span any suitable distance between the aircraft seat track beams 202, 204. The aircraft floor panel 218 may comprise any suitable material, including but not limited to metal, wood, carbon fiber, or other composite materials.

[0022] The aircraft floor panel assembly 200 includes a retaining clip 220 fixedly connected to the lower surface 222 of the aircraft floor panel 218. The retaining clip 220 includes a retaining edge 224 and a retaining edge 226. The retaining edge 224 is configured to selectively engage with a non-linear edge 214 of the beam flange 212 of the aircraft seat track beam 204. Specifically, the retaining edge 224 is non-linearly shaped to match the non-linear edge 214 of the beam flange 212. An illustrative shape of the retaining edge 224 is shown in cutout 217. Note that the non-linear edge of the beam flange 212 is not shown in cutout 217 to illustrate the non-linear shape of the retaining edge 224. In some embodiments, the retaining edge 226 may have a non-linear shape. For example, the retaining edge 226 may have a shape similar to the retaining edge 224. In other embodiments, the retaining edge 226 may have a linear shape (e.g., a straight edge) different from the retaining edge 224. The retaining clip edge 226 extends beyond the retaining mating edge 224. Thus, when the aircraft floor panel assembly 200 is mounted on the aircraft seat track beams 202, 204, the retaining mating edge 224 intersects with the non-linear edge 214 of the beam flange 212; and the retaining clip edge 226 extends below the beam flange 212 to hold the aircraft floor panel 218 on the aircraft seat track beam 204.

[0023] The aircraft floor panel assembly 200 includes a lockable latch 228 movably connected to the lower surface 222 of the aircraft floor panel 218. The lockable latch 228 is movable on the lower surface 222 of the aircraft floor panel 218 between an unlocked position and a locked position. The lockable latch 228 can be movably connected to the lower surface 222 of the aircraft floor panel 218 in any suitable manner. In one example, the lockable latch 228 includes a frame portion and a movable portion connected to the frame portion. The frame portion can be fastened in a fixed position (e.g., via screws, adhesive) to the lower surface 222 of the aircraft floor panel 218, and the movable portion can be movably connected to the frame portion such that the movable portion can be laterally translated relative to the beam flange 206 of the aircraft seat track beam 202. In another example, the lockable latch 228 can be movably connected to the lower surface 222 of the aircraft floor panel 218 via one or more floating inserts mounted within the aircraft floor panel 218. The floating insert allows the lockable latch 228 to be laterally translated relative to the beam flange 206 of the aircraft seat track beam 202 while being held in the floating insert.

[0024] The lockable latch 228 includes a lockable mating edge 230 and a lockable latching edge 232. The lockable mating edge 230 is configured to selectively mate with a non-linear edge 208 of the beam flange 206 of the aircraft seat track beam 202. Specifically, the lockable mating edge 230 is non-linearly shaped to match the non-linear edge 208. An illustrative shape of the lockable mating edge 230 is shown in cutout 219. Note that the non-linear edge of the beam flange 206 is not shown in cutout 219 to illustrate the non-linear shape of the lockable mating edge 230. In some embodiments, the lockable latching edge 232 may have a non-linear shape. For example, the lockable latching edge 232 may have a shape similar to the lockable mating edge 230. In other embodiments, the lockable latching edge 232 may have a linear shape (e.g., a straight edge) different from the lockable mating edge 230. The lockable latching edge 232 extends beyond the lockable mating edge 230.

[0025] In the unlocked position, the lockable latch edge 232 is sufficiently away from the beam flange 206 and retracts toward the fixed latch edge 226 so that the aircraft floor panel 218 is mounted on the aircraft seat track beams 202, 204. Specifically, in the unlocked position, the lockable latch edge 232 is sufficiently retracted away from the non-linear edge 208, such that the lockable latch edge 232 can be lowered past the beam flange 206 of the aircraft seat track beam 202. Furthermore, the lockable latch edge 232 is spaced sufficiently far from the beam flange 206 of the aircraft seat track beam 202 to allow the fixed latch edge 226 to move away from the non-linear edge 214, such that the fixed latch edge 226 can be lowered past the beam flange 212 of the aircraft seat track beam 204.

[0026] Once the retaining clip edge 226 is lowered beyond the beam flange 212 of the aircraft seat track beam 204, the aircraft floor panel 218 can be laterally translated toward the aircraft seat track beam 204. After this translation, the retaining edge 224 engages with the non-linear edge 214 of the beam flange 212 of the aircraft seat track beam 204, and the retaining clip edge 226 extends below the beam flange 212. Thus, the aircraft floor panel 218 is positioned on the aircraft seat track beams 202, 204, and the retaining clip 228 is ready to move to the locked position.

[0027] During locking, the lockable mating edge 230 laterally translates toward the nonlinear edge 208 of the beam flange 206 of the aircraft seat track beam 202. In the locked position, the lockable mating edge 230 engages with the nonlinear edge 208 of the beam flange 206 of the aircraft seat track beam 202, and the lockable latching edge 232 extends below the beam flange 206 of the aircraft seat track beam 202. Similarly, when the lockable latch 228 is in the locked position, the retaining mating edge 224 remains engaged with the nonlinear edge 214 of the beam flange 212 of the aircraft seat track beam 204, and the retaining latching edge 226 extends below the beam flange 212 of the aircraft seat track beam 204. In this way, the lockable latching edge 232 and the retaining latching edge 226 cooperatively hold the aircraft floor panel 218 on the aircraft seat track beams 202, 204, for example, by preventing the aircraft floor panel 218 from separating from the aircraft seat track beams 202, 204.

[0028] Note that the interlacing of the locking mating edge 230 with the matching nonlinear edge 208 of the beam flange 206 of the aircraft seat track beam 202 allows shear and / or other loads to be transferred from the aircraft floor panel 218 to the aircraft seat track beam 202 using a reduced number of fasteners compared to conventional floor panel assemblies. Similarly, the interlacing of the fixing mating edge 224 with the matching nonlinear edge 214 of the beam flange 212 of the aircraft seat track beam 204 allows shear and / or other loads to be transferred from the aircraft floor panel 218 to the aircraft seat track beam 204 using a reduced number of fasteners compared to conventional floor panel assemblies.

[0029] The aircraft floor panel assembly 200 includes a key 234 configured to switch a lockable latch 228 between an unlocked and a locked position. The key 234 is accessible from above the upper surface 236 of the aircraft floor panel 218 for operation by an operator, thereby switching the lockable latch 228 between the unlocked and locked positions, for example, during installation or removal of the aircraft floor panel 218. Additionally or alternatively, the key 234 may be accessible from the lower surface 222 of the aircraft floor panel 218.

[0030] Key 234 is configured to hold the lockable latch 228 in a locked position until key 234 is actuated to move the lockable latch 228 from the locked position to the unlocked position and vice versa. Specifically, key 234 extends through the aircraft floor panel 218 and is mechanically coupled to the lockable latch 228. Key 234 includes a translation mechanism 238 mechanically coupled to the lockable latch 228. Translation mechanism 238 is configured to convert movement of key 234 into movement of the lockable latch 228 between the unlocked and locked positions. The translation mechanism 238 of key 234 can take any suitable form. (See reference...) Figures 3 to 8 A non-limiting example describing a translation mechanism.

[0031] Figures 3 to 8 An illustrative aircraft floor panel assembly 200 is shown transitioning from an unlocked position to a locked position. The aircraft floor panel assembly 200 includes a translation mechanism 238 in the form of a wedge, which is configured to switch a lockable latch 228 between a locked position and an unlocked position. Figure 3 An illustrative top view of an aircraft floor panel assembly 200 is shown, in which the aircraft floor panel 218 is not shown, so as to expose the lockable latch 228 in the unlocked position. Figure 4 This is a cross-sectional view of the aircraft floor panel assembly 200, showing the aircraft floor panel 218 in the unlocked position and the lockable latch 228.

[0032] As per the above reference Figure 2 As stated, and as Figure 3As further shown, the nonlinear edges 208 and 214 of the beam flanges 206 and 212 are shaped to have nonlinear, fan-shaped, or sinusoidal patterns that match the fixed-fit edge 224 and the lockable-fit edge 230. This staggering of the matching nonlinear edges of the beam flanges and latches allows shear and / or other loads to be transferred from the aircraft floor panel 218 to the aircraft seat track beams 202 and 204 using a reduced number of fasteners compared to conventional floor panel assemblies. In other embodiments, the nonlinear edges of the beam flanges of the aircraft seat track beams may be shaped to have other nonlinear patterns. In other embodiments, the nonlinear edges of the beam flanges of the aircraft seat track beams may be shaped to have non-repeating, arbitrary nonlinear edges that allow shear and / or other loads to be transferred from the aircraft floor panel to the aircraft seat track beams using a reduced number of fasteners compared to conventional floor panel assemblies. In the illustrated embodiment, the edge of the beam flange opposite beam flange 206 has a different linear shape (e.g., a straight edge) than the nonlinear edge 208 of beam flange 206. Similarly, the edges of the beam flanges opposite to beam flange 212 have a linear shape (e.g., straight edges) different from the nonlinear edge 214 of beam flange 212. For ease of explanation, the edges of these opposing beam flanges are shown as linear. In other embodiments, the edges of these opposing beam flanges may have nonlinear edges with the same shape as nonlinear edges 208, 214, such that additional aircraft floor panels can be fastened to the seat track beams 202, 204 on each side of the aircraft floor panel 218 in the same manner as the aircraft floor panel assembly 200 is fastened to the seat track beams 202, 204. In other embodiments, these beam flanges may have edges shaped differently from the nonlinear edges 208, 214.

[0033] like Figure 3 As shown, the retaining clip 220 engages with the aircraft seat track beam 204. Note that when the aircraft floor panel 218 is initially placed on top of the aircraft seat track beams 202, 204 (by... Figure 4 The downward-pointing dashed arrow shown indicates that when the lockable latch 228 is in the unlocked position, the unlocking distance (D) between the edge 232 of the lockable latch and the edge 226 of the fixed latch is... U The gap distance (D) between the nonlinear edge 208 of the beam flange 206 of the aircraft seat track beam 202 and the nonlinear edge 214 of the beam flange 212 of the aircraft seat track beam 204 is smaller than that between the nonlinear edge 208 of the beam flange 206 of the aircraft seat track beam 202 and the nonlinear edge 214 of the beam flange 212 of the aircraft seat track beam 204. C In the unlocked position, the locking clip edge 232 and the fixing clip edge 226 are spaced apart to allow the aircraft floor panel 218 to be mounted on the aircraft seat track beams 202, 204. Specifically, as... Figure 4As shown, in the unlocked position, the locking latch edge 232 is fully retracted to avoid interference with the beam flange 206 of the aircraft seat track beam 202, allowing the aircraft floor panel 218 to be placed on the aircraft seat track beams 202 and 204. Once the aircraft floor panel 218 is placed on the aircraft seat track beams 202 and 204, the aircraft floor panel assembly 200 is laterally translated toward the second aircraft seat track beam 204 (by...). Figure 3 and Figure 4 (As indicated by the dashed arrow pointing to the left in the image), the fixed mating edge 224 mates with the nonlinear edge 214 of the beam flange 212, and the fixed snap-fit ​​edge 226 extends below the nonlinear edge 214 of the beam flange 212 of the aircraft seat track beam 204, as shown in the image. Figure 3 As shown.

[0034] The aircraft floor panel assembly 200 includes a key 234 mechanically coupled to a lockable latch 228. The key 234 includes a wedge 238 having an angled side 300 intersecting with an angled side 302 opposite to the lockable latch 228. For example, by means of a first direction 304 (e.g., with...). Figure 1 A sliding key 234 (aligned with the longitudinal axis 108 of the fuselage 102 of the illustrated aircraft 100) is used to manipulate the key 234, causing the wedge 238 to also move in the first direction 304. The wedge 238 is configured to move in the first direction 304, thereby moving the lockable latch 228 in a second direction 306 perpendicular to the first direction 304 to switch the lockable latch 228 from an unlocked position to a locked position. Specifically, when the wedge 238 moves in the first direction 304, the wider portion of the wedge 238 interacts with the wider portion of the lockable latch 228, causing the lockable latch 228 to move toward the aircraft seat track beam 202 in the second direction 306. The angled side 300 of the wedge 238 provides uniform pressure across most of the corresponding angled side 302 of the lockable latch 228 to move the lockable latch toward the aircraft seat track beam 202. Note that in the illustrated embodiment, when the lockable latch 228 is in the unlocked position, the side 308 of the lockable latch 228 is substantially aligned with the side 310 of the wedge 238.

[0035] Figures 5 to 6 An aircraft floor panel assembly 200 with a lockable latch 228 is shown, which transitions from an unlocked position to a locked position. Figure 5As shown, the retaining clip 220 engages with the aircraft seat track beam 204, such that the retaining edge 224 and the non-linear edge 214 intersect; and the retaining clip edge 226 extends below the beam flange 212 of the aircraft seat track beam 204. Furthermore, the key 234 and the corresponding wedge 238 have moved in the first direction 304, causing the lockable clip 228 to move toward the aircraft seat track beam 202 in the second direction 306. When the lockable clip 228 is in this position, the intermediate distance (D) between the lockable clip edge 232 and the retaining clip edge 226 is... I The gap distance (D) between the nonlinear edge 208 of the beam flange 206 of the aircraft seat track beam 202 and the nonlinear edge 214 of the beam flange 212 of the aircraft seat track beam 204 is greater than that between the two nonlinear edges. C ).like Figure 4 As shown, in this position, the locking snap edge 232 is vertically aligned with the nonlinear edge 208 of the beam flange 206 of the aircraft seat track beam 202. Furthermore, it is noted that the wedge 238 has already traveled in the first direction 304, causing the side 308 of the locking snap 228 to no longer align with the side 310 of the wedge 238.

[0036] Figures 7 to 8 An aircraft floor panel assembly 200 with a lockable latch 228 is shown, wherein the lockable latch is in a locked position. Figure 7 As shown, key 234 has been further manipulated in the first direction 304. Correspondingly, wedge 238 has moved in the first direction 304, causing lockable latch 228 to move toward the aircraft seat track beam 202 in the second direction 306 to shift lockable latch 228 into the locked position. When lockable latch 228 is in the locked position, the locking distance (D) between lockable latch edge 232 and fixed latch edge 226... L The gap distance (D) between the nonlinear edge 208 of the beam flange 206 of the aircraft seat track beam 202 and the nonlinear edge 214 of the beam flange 212 of the aircraft seat track beam 204 is greater than that between the two nonlinear edges. C ).like Figure 8As shown, in the locked position, the lockable mating edge 230 engages with the nonlinear edge 208 of the beam flange 206 of the aircraft seat track beam 202, and the lockable snap-fit ​​edge 232 extends below the nonlinear edge 208 of the beam flange 206. Furthermore, the fixed snap-fit ​​edge 226 remains below the nonlinear edge 214 of the beam flange 212 of the aircraft seat track beam 204. Thus, the lockable snap-fit ​​edge 232 and the fixed snap-fit ​​edge 226 cooperatively hold the aircraft floor panel 218 on the aircraft seat track beams 202 and 204 to prevent separation of the aircraft floor panel 218 from the aircraft seat track beams 202 and 204 in the third direction 312. Furthermore, the engagement / interlacing of the lockable mating edge 230 with the nonlinear edge 208 and the engagement / interlacing of the fixed mating edge 224 with the nonlinear edge 214 jointly hold the aircraft floor panel 218 to prevent movement of the aircraft floor panel 218 in the first direction 304. In both cases, this retention / maintenance is achieved by using a reduced number of fasteners compared to conventional floor panel assemblies.

[0037] In the illustrated embodiment, a wedge is provided as a non-limiting example of a translation mechanism configured to convert key actuation into movement of a lockable latch between an unlocked and locked position. In other embodiments, other types of translation mechanisms may be employed. As an alternative example, the translation mechanism may include a scissor-type translation mechanism configured to extend and retract based on key actuation. In this example, the key may include a knob that can be rotated clockwise / counterclockwise to extend / retract the lockable latch. In some keyless embodiments, the lockable latch may be moved by an electronically controlled motor.

[0038] In some implementations, the aircraft floor panel may include lockable latches on each side of the panel, instead of one lockable latch and one fixed latch.

[0039] In different implementations, the aircraft seat track beam may include a beam flange with a non-linear edge of a different shape. Accordingly, the lockable and retaining clips of the aircraft floor panel assembly may include corresponding mating edges that are complementary in shape to the non-linear edge of the beam flange, such that the lockable and retaining clips are configured to mate with the beam flange. Figures 9 to 12 Different example implementations of lockable snaps with edges of different shapes are shown. Figure 9A lockable latch 900 is shown, comprising a lockable mating edge 902 shaped with a wavy pattern complementary to the wavy pattern of a corresponding edge of a beam flange (not shown), the lockable latch being configured to selectively mate with the beam flange. The lockable latch 900 also includes a lockable latch edge 904 extending beyond the lockable mating edge 902 and having a linear or straight shape configured to extend below the beam flange when the lockable mating edge 902 mates with a non-linear edge of the beam flange. Note that in such an embodiment, the lockable latch is capable of sufficient lateral translation (i.e., toward the fixed latch) to allow both the lockable latch and the fixed latch to disengage from the non-linear edge of the beam flange of the aircraft seat track beam, such that the aircraft floor panel can be mounted on top of the aircraft seat track beam.

[0040] Figure 10 A lockable snap fastener 1000 is shown, comprising a lockable mating edge 1002 shaped with a wavy pattern complementary to the wavy pattern of a corresponding edge of a beam flange (not shown), the snap fastener being configured to selectively engage with the beam flange. The snap fastener 1000 also includes a lockable snap edge 1004 extending beyond the lockable mating edge 1002 and shaped with a wavy pattern similar to that of the lockable mating edge 1002. The lockable snap edge 1004 is configured to extend below the beam flange when the lockable mating edge 1002 engages with a non-linear edge of the beam flange.

[0041] Figure 11 A lockable latch 1100 is shown, comprising a lockable mating edge 1102 formed with a serrated pattern complementary to the serrated pattern of a corresponding edge of a beam flange (not shown), the lockable latch being configured to selectively mate with the beam flange. The lockable latch 1100 also includes a lockable latch edge 1104 extending beyond the lockable mating edge 1102 and having a linear or straight shape configured to extend below the beam flange when the lockable mating edge 1102 mates with a non-linear edge of the beam flange. Note that in such an embodiment, the lockable latch is capable of sufficient lateral translation (i.e., toward the fixed latch) to allow both the lockable latch and the fixed latch to disengage from the non-linear edge of the beam flange of the aircraft seat track beam, such that the aircraft floor panel can be mounted on top of the aircraft seat track beam.

[0042] Figure 12A lockable snap fastener 1200 is shown, comprising a lockable mating edge 1202 formed with a serrated pattern complementary to the serrated pattern of a corresponding edge of a beam flange (not shown), the lockable snap being configured to selectively engage with the beam flange. The lockable snap fastener 1200 also includes a lockable snap edge 1204 extending beyond the lockable mating edge 1202 and formed with a serrated pattern similar to that of the lockable mating edge 1002. The lockable snap edge 1204 is configured to extend below the beam flange when the lockable mating edge 1202 engages with a non-linear edge of the beam flange.

[0043] It should be understood that the nonlinear edge of the beam flange can have any suitable nonlinear shape, which facilitates interlocking with the corresponding nonlinear edges of the lockable and fixed latches to transfer shear and / or other loads from the aircraft floor panel to the aircraft seat track beam. In some, but not all, embodiments, the nonlinear shaped edge can be patterned and / or periodic.

[0044] In different implementations, the aircraft floor panel assembly may include keys with different configurations that can be manipulated in different ways to move a lockable latch between an unlocked position and a locked position. Figures 13 to 14 Different example implementations of a key are shown, which is configured to switch a lockable latch from an unlocked position to a locked position.

[0045] Figure 13An illustrative key 1300 including a sliding handle 1302 is shown. The sliding handle 1302 is fitted into a recess 1304 formed in the upper surface 1306 of the aircraft floor panel 1308. The sliding handle 1302 extends through the aircraft floor panel 1308 to engage with a wedge 1310 positioned below the lower surface 1312 of the aircraft floor panel 1308. At time T0, when a lockable latch (not shown) engaging with the wedge 1310 is in the unlocked position, the sliding handle 1302 is positioned in the recess 1304 in a first orientation. The sliding handle 1302 is held in the recess 1304 in the first orientation by a removable retainer 1314. The removable retainer 1314 is configured to occupy the empty space in the recess 1304 to prevent the sliding handle 1302 from unintentionally sliding in the recess 1304 and to hold the locking latch in the unlocked position until the key 1300 is actuated to move the locking latch from the unlocked position to the locked position. At time T1, the removable retainer 1314 is removed from the recess 1304 to allow the sliding handle 1302 to slide within the recess 1304. At time T2, the sliding handle 1302 slides in the recess 1304 from a first orientation to a second orientation on the other side of the recess 1304, thereby moving the wedge 1310 and engaging the locking latch in the locked position with the aircraft seat track beam (not shown). Additionally, the removable retainer 1314 rotates to align with the sliding handle 1302 in the recess 1304 in the second orientation. At time T3, the removable retainer 1314 is returned to the recess 1304 to hold the sliding handle 1302 in the second orientation, and thereby retain the lockable latch in the locked position. The removable retainer can be held in the recess in any suitable manner. In some embodiments, the removable retainer may include a fastener or lock configured to hold the removable retainer in the recess. In other embodiments, the removable retainer may be held in the recess via a tension fit. Note that... Figure 13 The key actions shown can be performed in reverse order to switch the lockable latch from the locked position to the unlocked position.

[0046] Figure 14An illustrative key 1400 including lever 1402 is shown. Lever 1402 is pivotally connected to wedge 1404 via hinge 1406. Lever 1402 is configured to pivot 180 degrees about hinge 1406. At time T0, lever 1402 pivots to engage with recess 1408 formed in upper surface 1410 of aircraft floor panel 1412. Lever 1402 and hinge 1406 extend together through aircraft floor panel 1412 to engage with wedge 1404 positioned below lower surface 1414 of aircraft floor panel 1412. At time T0, lever 1402 pivots about hinge 1416 such that when a lockable latch (not shown) engaging with wedge 1404 is in the unlocked position, lever 1402 is positioned in a first orientation in recess 1408. Lever 1402 is oriented in a first orientation to occupy the empty space in recess 1408, thereby holding the lockable latch in the unlocked position until key 1400 is actuated to move the lockable latch from the unlocked position to the locked position. At time T1, lever 1402 is pivoted clockwise about hinge 1406 such that lever 1402 extends perpendicularly to aircraft floor panel 1412 beyond recess 1408. Lever 1402 is oriented in this way to allow lever 1402 to be actuated to move the lockable latch from the unlocked position to the locked position. At time T2, lever 1402 slides to the other side of recess 1408, thereby moving wedge 1404 and causing the lockable latch to engage in the locked position with aircraft seat track beam (not shown). At time T3, lever 1402 is pivoted clockwise about hinge 1406 such that lever 1402 is fitted into recess 1408 in a second orientation opposite to the first orientation to occupy the empty space in recess 1408. In this way, lever 1402 holds wedge 1404 and lockable latch in the locked position until key 1400 is actuated to move lockable latch from the locked position to the unlocked position. The lever can be configured to retain this orientation in a recess until further actuation. For example, the lever can be held in place using fasteners, cams, tension, or retaining devices. Note that... Figure 14 The lever action shown can be performed in reverse order to change the lockable latch from the locked position to the unlocked position.

[0047] The illustrated embodiments are provided as non-limiting examples of keys. Other types of keys may be used in other embodiments. As an alternative example, the key may include a knob that can be rotated clockwise / counterclockwise to extend / retract the lockable latch. Furthermore, the key can be held in the aircraft floor panel in any suitable manner. In some embodiments, the key may be attached to the aircraft floor panel via a floating insert. In other embodiments, the key may be attached to the aircraft floor panel using mechanical fasteners and / or adhesives. In some keyless embodiments, the lockable latch may be moved by an electronically controlled motor.

[0048] Although the panel assembly is shown as operating without any fasteners, in some embodiments, the panel assembly may be combined with some fasteners. For example, in some embodiments, fasteners may be used to hold the lockable latch in place when locked.

[0049] Although panel assemblies are discussed in the context of floor panels for aircraft, it should be understood that the various features and techniques disclosed herein are broadly applicable to mounting panels on structural frames with any suitable orientation (e.g., on floors, walls, or ceilings). Furthermore, the various features and techniques disclosed herein are broadly applicable to mounting panels on structural frames in any suitable means of transportation (e.g., aircraft, ships, automobiles), buildings (e.g., residential buildings, commercial buildings, industrial buildings), or other structures (e.g., shipping containers, boxes).

[0050] This disclosure includes example implementations according to the following terms:

[0051] Clause 1. An aircraft floor panel assembly 200 for mounting to an aircraft seat track beam 202, the aircraft seat track beam including a beam flange 206 having a non-linear edge 208, the aircraft floor panel assembly 200 comprising:

[0052] Aircraft floor panel 218; and

[0053] A lockable latch 228 is movably connected to the aircraft floor panel 218 and includes a lockable mating edge 230 and a lockable latch edge 232, the lockable mating edge being configured to selectively engage with the non-linear edge 208 of the beam flange 206, the lockable latch edge extending beyond the lockable mating edge 230.

[0054] The lockable buckle 228 is movable between an unlocked position and a locked position on the lower surface 222 of the aircraft floor panel 218;

[0055] In the unlocked position, the locking latch edge 232 is fully retracted, allowing the aircraft floor panel 218 to be mounted on the aircraft seat track beam 202; and

[0056] In the locked position, the lockable mating edge 230 engages with the nonlinear edge 208 of the beam flange 206, and the lockable snap-fit ​​edge 232 holds the aircraft floor panel 218 on the aircraft seat track beam 202.

[0057] Clause 2. A panel assembly 200 for mounting to a first track beam 202, the first track beam including a first beam flange 206 having a first non-linear edge 208, the panel assembly 200 comprising:

[0058] Panel 218; and

[0059] A lockable latch 228 is movably connected to the panel 218 and includes a lockable mating edge 230 and a lockable latch edge 232, the lockable mating edge being configured to selectively engage with the first nonlinear edge 208 of the first beam flange 206 of the first track beam 202, the lockable latch edge extending beyond the lockable mating edge 230.

[0060] The lockable latch 228 is movable between an unlocked position and a locked position on the lower surface 222 of the panel 218;

[0061] In the unlocked position, the locking buckle edge 232 retracts; and

[0062] In the locked position, the lockable mating edge 230 engages with the first nonlinear edge 208 of the first beam flange 206, and the lockable snap-fit ​​edge 232 holds the panel 218 on the first track beam 202; and

[0063] Key 234, the key being configured to switch the lockable latch 228 from the unlocked position to the locked position.

[0064] Clause 3. The panel assembly 200 described in Clause 2, wherein the key 234 is accessible from above the upper surface 236 of the panel 218.

[0065] Clause 4. Panel assembly 200 as described in Clause 2 or 3, wherein the key 234 is configured to hold the lockable latch 228 in the locked position until the key 234 is actuated to move the lockable latch 228 from the locked position to the unlocked position.

[0066] Clause 5. The panel assembly 200 of any one of Clauses 2 to 4, the panel assembly further comprising a retaining clip 220, the retaining clip including a retaining edge 224 and a retaining clip edge 226 extending beyond the retaining edge 224, the retaining edge being configured to selectively engage with a second non-linear edge 214 of a second beam flange 212 of a second track beam 204 spaced apart from the first track beam 202.

[0067] Clause 6. The panel assembly 200 of Clause 5, wherein, when the lockable latch 228 is in the unlocked position, the unlocking distance between the edge 232 of the lockable latch and the edge 226 of the fixed latch is less than the gap distance between the first nonlinear edge 208 of the first beam flange 206 of the first track beam 202 and the second nonlinear edge 214 of the second beam flange 212 of the second track beam 204; and

[0068] When the lockable buckle 228 is in the locked position, the locking distance between the edge 232 of the lockable buckle and the edge 226 of the fixed buckle is greater than the gap distance between the first nonlinear edge 208 of the first beam flange 206 of the first track beam 202 and the second nonlinear edge 214 of the second beam flange 212 of the second track beam 204.

[0069] Clause 7. The panel assembly 200 of any one of Clauses 2 to 6, wherein the first nonlinear edge 208 of the first beam flange 206 is shaped to have a wave pattern, and wherein the lockable mating edge 230 is shaped to have a complementary wave pattern.

[0070] Clause 8. Panel assembly 200 of any one of Clauses 2 to 6, wherein the first nonlinear edge 208 of the first beam flange 206 is formed with a serrated pattern, and wherein the lockable mating edge 230 is formed with a complementary serrated pattern.

[0071] Clause 9. Panel assembly 200 of any one of Clauses 2 to 8, wherein the key 234 includes a wedge 238.

[0072] The panel assembly 200 of Clause 10.9, wherein the wedge 238 is configured to move in a first direction 304, thereby moving the lockable latch 228 in a second direction 306 perpendicular to the first direction 304, so as to transition the lockable latch 228 from the unlocked position to the locked position.

[0073] Clause 11. The panel assembly 200 of Clause 10, wherein the key 234 includes a handle 1302 fixed to the wedge 1310 and configured to slide in a first direction 304, thereby moving the wedge 1310 in the first direction 304 and moving the lockable latch 228 in a second direction 306 to transition the lockable latch 228 from the unlocked position to the locked position.

[0074] Clause 12. The panel assembly 200 of Clause 11, wherein the panel 218 includes a recess 1408, wherein the handle 1402 includes a lever 1402 pivotally coupled to the wedge 1404, wherein when the lockable latch 228 is in the locked position, the handle 1402 is fitted into the recess 1408 in a first orientation, and wherein when the lockable latch 228 is in the unlocked position, the handle 1402 is fitted into the recess 1408 in a second orientation opposite to the first orientation.

[0075] Clause 13. An aircraft floor panel assembly 200 for mounting to a spaced-apart first aircraft seat track beam 202 and a second aircraft seat track beam 204, each including a spaced-apart first beam flange 206 and a second beam flange 212, the first beam flange and the second beam flange having spaced-apart first nonlinear edges 208 and second nonlinear edges 214, respectively, the aircraft floor panel assembly 200 comprising:

[0076] Aircraft floor panel 218;

[0077] A lockable latch 228 is movably connected to the aircraft floor panel 218 and includes a lockable mating edge 230 and a lockable latch edge 232, the lockable mating edge being configured to selectively engage with the first nonlinear edge 208 of the first beam flange 206 of the first aircraft seat track beam 202, the lockable latch edge extending beyond the lockable mating edge 230;

[0078] A retaining clip 220 is fixedly connected to the aircraft floor panel 218 and includes a retaining edge 224 and a retaining edge 226, the retaining edge being configured to selectively engage with the second nonlinear edge 214 of the second beam flange 212 of the second aircraft seat track beam 204, the retaining edge extending beyond the retaining edge 224;

[0079] The lockable buckle 228 is movable between an unlocked position and a locked position on the lower surface 222 of the aircraft floor panel 218;

[0080] In the unlocked position, the lockable latch edge 232 is fully retracted toward the fixed latch edge 226, so that the aircraft floor panel 218 is mounted on the first aircraft seat track beam 202 and the second aircraft seat track beam 204; and

[0081] In the locked position, the lockable engagement edge 230 engages with the first nonlinear edge 208 of the first beam flange 206, the fixed engagement edge 224 engages with the second nonlinear edge 214 of the second beam flange 212, and the lockable snap-fit ​​edge 232 and the fixed snap-fit ​​edge 226 cooperate to hold the aircraft floor panel 218 on the first aircraft seat track beam 202.

[0082] Clause 14. The aircraft floor panel assembly 200 of Clause 13, the aircraft floor panel assembly further comprising a key 234 configured to switch the lockable latch 228 from the unlocked position to the locked position.

[0083] Clause 15. The aircraft floor panel assembly 200 of Clause 14, wherein the key 234 is accessible from above the upper surface 236 of the panel 218.

[0084] Clause 16. The aircraft floor panel assembly 200 described in Clause 14 or 15, wherein the key 234 is configured to hold the lockable latch 228 in the locked position until the key 234 is actuated to move the lockable latch 228 from the locked position to the unlocked position.

[0085] Clause 17. The aircraft floor panel assembly 200 of any one of Clauses 14 to 16, wherein the key 234 includes a wedge 238.

[0086] Clause 18. The aircraft floor panel assembly 200 of any one of Clauses 13 to 17, wherein, when the lockable latch 228 is in the unlocked position, the unlocking distance between the edge 232 of the lockable latch and the edge 226 of the fixed latch is less than the gap distance between the first nonlinear edge 208 of the first beam flange 206 of the first aircraft seat track beam 202 and the second nonlinear edge 214 of the second beam flange 212 of the second aircraft seat track beam 204; and

[0087] When the lockable buckle 228 is in the locked position, the locking distance between the edge 232 of the lockable buckle and the edge 226 of the fixed buckle is greater than the gap distance between the first nonlinear edge 208 of the first beam flange 206 of the first aircraft seat track beam 202 and the second nonlinear edge 214 of the second beam flange 212 of the second aircraft seat track beam 204.

[0088] Clause 19. The aircraft floor panel assembly 200 of any one of Clauses 13 to 18, wherein the first nonlinear edge 208 and the second nonlinear edge 214 of the spaced-apart first beam flange 206 and second beam flange 212 are shaped to have a wave pattern, and wherein the lockable mating edge 230 and the fixed mating edge 224 are shaped to have complementary wave patterns.

[0089] Clause 20. The aircraft floor panel assembly 200 of any one of Clauses 13 to 18, wherein the first nonlinear edge 208 and the second nonlinear edge 214 of the spaced-apart first beam flange 206 and second beam flange 212 are formed with a serrated pattern, and wherein the lockable mating edge 230 and the fixed mating edge 224 are formed with complementary serrated patterns.

[0090] This disclosure includes all novel and non-obvious combinations and sub-combinations of the various features and techniques disclosed herein. Not all features and techniques disclosed herein are necessary for all examples of this disclosure. Furthermore, the various features and techniques disclosed herein may define patentable subject matter beyond the disclosed examples, and utility may be found in other implementations not expressly disclosed herein.

Claims

1. An aircraft floor panel assembly (200) for mounting to an aircraft seat track beam (202), the aircraft seat track beam including a beam flange (206) having a non-linear edge (208), the aircraft floor panel assembly (200) comprising: Aircraft floor panel (218); as well as A lockable latch (228) is movably connected to the lower surface (222) of the aircraft floor panel (218) and includes a lockable mating edge (230) and a lockable latch edge (232), the lockable mating edge being configured to selectively engage with the non-linear edge (208) of the beam flange (206), the lockable latch edge extending beyond the lockable mating edge (230). The lockable latch (228) is movable between an unlocked position and a locked position on the lower surface (222) of the aircraft floor panel (218); In the unlocked position, the locking latch edge (232) is fully retracted so that the aircraft floor panel (218) is mounted on the aircraft seat track beam (202); and In the locked position, the lockable mating edge (230) engages with the nonlinear edge (208) of the beam flange (206), and the lockable snap-fit ​​edge (232) holds the aircraft floor panel (218) on the aircraft seat track beam (202).

2. A panel assembly (200) for mounting to a first track beam (202), the first track beam including a first beam flange (206) having a first non-linear edge (208), the panel assembly (200) comprising: Panel (218); as well as A lockable latch (228) is movably connected to the lower surface (222) of the panel (218) and includes a lockable mating edge (230) and a lockable latch edge (232), the lockable mating edge being configured to selectively engage with the first nonlinear edge (208) of the first beam flange (206) of the first track beam (202), the lockable latch edge extending beyond the lockable mating edge (230). The lockable latch (228) is movable on the lower surface (222) of the panel (218) between an unlocked position and a locked position; In the unlocked position, the locking buckle edge (232) retracts; and In the locked position, the lockable mating edge (230) engages with the first nonlinear edge (208) of the first beam flange (206), and the lockable snap-fit ​​edge (232) holds the panel (218) on the first track beam (202); and A key (234) is configured to switch the lockable latch (228) from the unlocked position to the locked position.

3. The panel assembly (200) according to claim 2, wherein, The key (234) can be accessed from above the upper surface (236) of the panel (218).

4. The panel assembly (200) according to claim 2 or 3, wherein, The key (234) is configured to hold the lockable latch (228) in the locked position until the key (234) is actuated to move the lockable latch (228) from the locked position to the unlocked position.

5. The panel assembly (200) according to claim 2 or 3, the panel assembly further comprising a retaining clip (220) including a retaining edge (224) and a retaining clip edge (226) extending beyond the retaining edge (224), the retaining edge being configured to selectively engage with a second nonlinear edge (214) of a second beam flange (212) of a second track beam (204) spaced apart from the first track beam (202).

6. The panel assembly (200) according to claim 5, wherein, When the lockable latch (228) is in the unlocked position, the unlocking distance between the edge (232) of the lockable latch and the edge (226) of the fixed latch is less than the gap distance between the first nonlinear edge (208) of the first beam flange (206) of the first track beam (202) and the second nonlinear edge (214) of the second beam flange (212) of the second track beam (204); and When the lockable buckle (228) is in the locked position, the locking distance between the edge of the lockable buckle (232) and the edge of the fixed buckle (226) is greater than the gap distance between the first nonlinear edge (208) of the first beam flange (206) of the first track beam (202) and the second nonlinear edge (214) of the second beam flange (212) of the second track beam (204).

7. The panel assembly (200) according to claim 2 or 3, wherein, The first nonlinear edge (208) of the first beam flange (206) is shaped to have a wave pattern, and wherein the lockable mating edge (230) is shaped to have a complementary wave pattern.

8. The panel assembly (200) according to claim 2 or 3, wherein, The first nonlinear edge (208) of the first beam flange (206) is shaped to have a serrated pattern, and wherein the lockable mating edge (230) is shaped to have a complementary serrated pattern.

9. The panel assembly (200) according to claim 2 or 3, wherein, The key (234) includes a wedge (238).

10. The panel assembly (200) according to claim 9, wherein, The wedge (238) is configured to move in a first direction (304) such that the lockable latch (228) moves in a second direction (306) perpendicular to the first direction (304) to change the lockable latch (228) from the unlocked position to the locked position.

11. The panel assembly (200) according to claim 10, wherein, The key (234) includes a handle (1302) fixed to the wedge (1310) and configured to slide in the first direction (304), thereby moving the wedge (1310) in the first direction (304) and moving the lockable latch (228) in the second direction (306) to switch the lockable latch (228) from the unlocked position to the locked position.

12. The panel assembly (200) according to claim 11, wherein, The panel (218) includes a recess (1408), wherein the handle (1402) includes a lever (1402) pivotally connected to the wedge (1404), wherein when the lockable latch (228) is in the locked position, the handle (1402) is fitted into the recess (1408) in a first orientation, and wherein when the lockable latch (228) is in the unlocked position, the handle (1402) is fitted into the recess (1408) in a second orientation opposite to the first orientation.

13. An aircraft floor panel assembly (200) for mounting to a spaced-apart first aircraft seat track beam (202) and a second aircraft seat track beam (204), each including a spaced-apart first beam flange (206) and a second beam flange (212), the first beam flange and the second beam flange having spaced-apart first nonlinear edges (208) and second nonlinear edges (214), the aircraft floor panel assembly (200) comprising: Aircraft floor panel (218); A lockable latch (228) is movably connected to the lower surface (222) of the aircraft floor panel (218) and includes a lockable mating edge (230) and a lockable latch edge (232), the lockable mating edge being configured to selectively engage with the first nonlinear edge (208) of the first beam flange (206) of the first aircraft seat track beam (202), the lockable latch edge extending beyond the lockable mating edge (230). A retaining clip (220) is fixedly connected to the aircraft floor panel (218) and includes a retaining edge (224) and a retaining clip edge (226), the retaining edge being configured to selectively engage with the second nonlinear edge (214) of the second beam flange (212) of the second aircraft seat track beam (204), the retaining clip edge extending beyond the retaining edge (224). The lockable latch (228) is movable between an unlocked position and a locked position on the lower surface (222) of the aircraft floor panel (218); In the unlocked position, the lockable latch edge (232) is fully retracted toward the fixed latch edge (226) so that the aircraft floor panel (218) is mounted on the first aircraft seat track beam (202) and the second aircraft seat track beam (204); and In the locked position, the lockable engagement edge (230) engages with the first nonlinear edge (208) of the first beam flange (206), the fixed engagement edge (224) engages with the second nonlinear edge (214) of the second beam flange (212), and the lockable snap-fit ​​edge (232) and the fixed snap-fit ​​edge (226) cooperate to hold the aircraft floor panel (218) on the first aircraft seat track beam (202).

14. The aircraft floor panel assembly (200) of claim 13, further comprising a key (234) configured to switch the lockable latch (228) from the unlocked position to the locked position.

15. The aircraft floor panel assembly (200) according to claim 14, wherein, The key (234) can be accessed from above the upper surface (236) of the panel (218).

16. The aircraft floor panel assembly (200) according to claim 14 or 15, wherein, The key (234) is configured to hold the lockable latch (228) in the locked position until the key (234) is actuated to move the lockable latch (228) from the locked position to the unlocked position.

17. The aircraft floor panel assembly (200) according to claim 14 or 15, wherein, The key (234) includes a wedge (238).

18. The aircraft floor panel assembly (200) according to any one of claims 13 to 15, wherein, When the lockable latch (228) is in the unlocked position, the unlocking distance between the edge (232) of the lockable latch and the edge (226) of the fixed latch is less than the gap distance between the first nonlinear edge (208) of the first beam flange (206) of the first aircraft seat track beam (202) and the second nonlinear edge (214) of the second beam flange (212) of the second aircraft seat track beam (204); and When the lockable latch (228) is in the locked position, the locking distance between the edge (232) of the lockable latch and the edge (226) of the fixed latch is greater than the gap distance between the first nonlinear edge (208) of the first beam flange (206) of the first aircraft seat track beam (202) and the second nonlinear edge (214) of the second beam flange (212) of the second aircraft seat track beam (204).

19. The aircraft floor panel assembly (200) according to any one of claims 13 to 15, wherein, The first nonlinear edge (208) and the second nonlinear edge (214) of the spaced-apart first beam flange (206) and second beam flange (212) are shaped to have a waveform pattern, and wherein the lockable mating edge (230) and the fixed mating edge (224) are shaped to have complementary waveform patterns.

20. The aircraft floor panel assembly (200) according to any one of claims 13 to 15, wherein, The first nonlinear edge (208) and the second nonlinear edge (214) of the spaced-apart first beam flange (206) and second beam flange (212) are shaped to have a serrated pattern, and wherein the lockable mating edge (230) and the fixed mating edge (224) are shaped to have complementary serrated patterns.

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