Aircraft seat frame with enhanced dynamic response

A frame beam member may include a tubular volume. The tubular volume may include at least one wall with one or more undulations in a radial direction along a length of the tubular volume. The one or more undulations may be configured to allow the tubular volume to absorb energy of a load applied during a flight scenario through local bending of the one or more undulations. The one or more undulations may be configured to have a first curvature when unloaded, and may be configured to have a second curvature when the load is applied. The second curvature may be different than the first curvature. The frame beam member may be one of a plurality of frame beam members of the aircraft seat frame. The plurality of frame beam members may be configured to couple to a plurality of joints of the aircraft seat frame.

BACKGROUND

Aircraft seat frames may be subjected to dynamic loads and corresponding dynamic reactions during a flight, which may generate additional stresses within the frame beam members of the aircraft seat frame. Conventional frame beam members may include beam elements with a tubular volume and a uniform axial cross-section along the entire length of the tubular volume. Although the uniform axial cross-section may have or result in a high stiffness and/or strength that is desirable in static and/or quasi-static loads, the uniform axial cross-section may not have a sufficient elasticity and/or capability to absorb energy of the dynamic loads.

SUMMARY

A frame beam member for an aircraft seat frame with enhanced dynamic response is disclosed, in accordance with one or more embodiments of the disclosure. The frame beam member may include a tubular volume. The tubular volume may include at least one wall with one or more undulations in a radial direction along a length of the tubular volume. The one or more undulations may be configured to allow the tubular volume to absorb energy of a load applied during a flight scenario through local bending of the one or more undulations. The one or more undulations may be configured to have a first curvature when unloaded. The one or more undulations may be configured to have a second curvature when the load is applied. The second curvature may be different than the first curvature. The frame beam member may be one of a plurality of frame beam members of the aircraft seat frame. The plurality of frame beam members may be configured to couple to a plurality of joints of the aircraft seat frame. At least one joint of the plurality of joints or at least one frame beam member of the plurality of frame beam members may be configured to couple to an aircraft body.

In some embodiments, the at least one wall of the tubular volume may include a single segment with the one or more undulations.

In some embodiments, the at least one wall of the tubular volume may include at least one segment with the one or more undulations and at least one segment with a uniform axial cross-section.

In some embodiments, the at least one wall of the tubular volume may include a single segment with the one or more undulations located at a mid-length point of the tubular volume and a segment with the uniform axial cross-section located at each end of the tubular volume.

In some embodiments, the at least one wall of the tubular volume may include a single segment with the uniform axial cross-section located at a mid-length point of the tubular volume and a segment with the one or more undulations located at each end of the tubular volume.

In some embodiments, the at least one wall of the tubular volume may include a single segment with the uniform axial cross-section located at a first end of the tubular volume and a single segment with the one or more undulations located at a second end of the tubular volume.

In some embodiments, the one or more undulations may be separately positioned a select distance along the length of the tubular volume from an end of the tubular volume.

In some embodiments, the one or more undulations may be in a spiral formation around the tubular volume along the length of the tubular volume.

In some embodiments, the one or more undulations may include, in an axial cross-section, at least one of a double curvature shape, a polygonal shape, a hybrid polygonal and convex curvature shape, a hybrid polygonal and concave curvature shape, or a combination.

In some embodiments, the one or more undulations being arranged at least one of radially outward along the length of the tubular volume or radially inward along the length of the tubular volume.

In some embodiments, the frame beam member may be fabricated from a fiber-reinforced polymer-matrix composite material. The reinforced fibers may include at least one of carbon fibers, glass fibers, organic fibers, or a combination. The polymer-matrix may be a thermoset or a thermoplastic.

In some embodiments, the one or more undulations of the at least one wall of the tubular volume may be formed on an exterior surface of a mold configured to be removed following fabrication.

In some embodiments, the one or more undulations of the at least one wall of the tubular volume may be formed on an exterior surface of a mold configured to remain inserted following fabrication.

In some embodiments, the frame beam member may be fabricated from a metal, alloy, metalloid, non-metal element, or a compound including at least one of a metal, alloy, metalloid, or non-metal element.

An aircraft seat frame with enhanced dynamic response is disclosed, in accordance with one or more embodiments of the disclosure. The aircraft seat frame may include a plurality of frame beam members. Each frame beam member of the plurality of frame beam members may include a tubular volume. The tubular volume may include at least one wall with one or more undulations along at least a portion of a length of the tubular volume. The one or more undulations may be configured to allow the tubular volume to absorb energy of a load applied during a flight scenario through local bending of the one or more undulations. The one or more undulations may be configured to have a first curvature when unloaded. The one or more undulations may be configured to have a second curvature when the load is applied. The second curvature may be different than the first curvature. The aircraft seat frame may include a plurality of joints configured to couple to the plurality of frame beam members. At least one joint of the plurality of joints or at least one frame beam member of the plurality of frame beam members may be configured to couple to an aircraft body.

DETAILED DESCRIPTION OF THE INVENTION

As used herein a letter following a reference numeral may be used to reference an embodiment of the feature or element that may be similar, but not necessarily identical, to a previously described element or feature bearing the same reference numeral (e.g.,1,1a,1b). In addition, a letter following a reference numeral may be used to reference a sub-feature or sub-element or sub-system of a larger feature or element or system (e.g.,1aor1bbeing a component of 1). Such shorthand notations are used for purposes of convenience only and should not be construed to limit the disclosure in any way unless expressly stated to the contrary.

Further, the terms or transitional phrases “including” and “having” may be considered equivalent, for purposes of the disclosure. In this regard, the term or transitional phrase “having” should not be interpreted as a limitation on the present disclosure, including with respect to the openness of the claim language.

FIGS. 1A-5Cin general illustrate an aircraft seat frame with enhanced dynamic response, in accordance with one or more embodiments of the disclosure.

FIGS. 1A-1Ein general illustrate an aircraft seat frame100, in accordance with one or more embodiments of the disclosure.

Referring now to at leastFIG. 1A, the aircraft seat frame100may include one or more frame beam members102. The one or more frame beam members102may be coupled via one or more joints104, where the one or more frame beam members102and/or the one or more joints104may be configured to couple to an aircraft body. For example, the aircraft body may include, but is not limited to, a floor100aof an aircraft cabin100b(e.g., either directly or indirectly via an intermediate frame foot). For example, the one or more frame beam members102and the one or more joints104may be coupled via at least one of, but are not limited to, one or more interlocking assemblies (e.g., self-locking joints, or the like), one or more fasteners (e.g., rivets, screws, or the like), an adhesive, or some combination of the above. The one or more joints104may be fabricated from a metal, alloy, metalloid, or non-metal element or a compound including a metal, alloy, metalloid, or non-metal element. It is noted herein that aircraft seat frame joints are further described in U.S. Pat. No. 10,532,518 B2, issued on Jan. 14, 2020, which is incorporated herein in the entirety. In addition, it is noted herein that “frame beam member” and “frame element” may be considered equivalent, for purposes of the disclosure.

Referring now to at leastFIG. 1B, the one or more frame beam members102may be fabricated from a lightweight composite material. The one or more frame beam members102may be fabricated with a laminated design. For example, a frame beam member102may include an exterior laminated structure106and one or more individual layers108. Where there are multiple individual layers108, the multiple individual layers108may be oriented in a crisscross or other overlapping pattern defined in one or more directions110within the frame beam member102. It is noted herein that the multiple individual layers108may be fabricated from the same composite material or a different composite material.

Although embodiments of the disclosure illustrate the one or more frame beam members102being fabricated with a laminated design, it is noted herein the one or more frame beam members may be fabricated with composite designs via fabrication processes including, but not limited to, Automated Fiber Placing (AFP), filament-winding, braiding, a combination of these fabrication processes, or the like. In addition, composite layups may include, but are not limited to, laminated designs based on an arrangement of uni-directionally reinforced layers, laminated designs based on fabric layers, 3D reinforcement layups, and their combinations. The composite design may be fabricated from a fiber-reinforced polymer-matrix composite material. For example, the reinforced fibers may include at least one of carbon fibers, glass fibers, organic fibers, a combination of these fibers, or the like. By way of another example, the polymer-matrix may be a thermoset or a thermoplastic. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

Referring now to at leastFIG. 1C, an individual layer108may include a plurality of reinforced fibers112in the one or more directions110set within a polymeric matrix114. For example, the plurality of reinforced fibers112may include, but are not limited to, reinforced carbon fibers, reinforced organic fibers, reinforced glass fibers, or a combination of fibers used in the fabrication of composite beam elements. By way of another example, the polymeric matrix114may include, but is not limited to, a thermoset or a thermoplastic.

The composite material from which the one or more frame beam members102may be fabricated may be selected to reduce weight of the aircraft seat frame100(and thus the enclosing aircraft seat). The composite material may possess high strength and stiffness properties, making it suitable for use in major load-bearing parts such as the one or more frame beam members102within the aircraft seat frame100.

Referring now to at leastFIG. 1D, the aircraft seat frame100may be subjected to dynamic loads and corresponding dynamic reactions during a flight, which may generate additional stresses within the one or more frame beam members102of the aircraft seat frame100. For example, the dynamic loads may include, but are not limited to, an emergency landing, a rapid stop, excessive acceleration, a fast takeoff, an impact event (e.g., due to bird strikes), a ballistic impact, or the like. The dynamic loads may generate local dynamic reactions or dynamic load conditions116distributed axially within the one or more frame beam members102. Depending on seat frame configuration and/or designs of joints104, the dynamic loads may also generate bending and/or torsional loads in the one or more frame beam members102.

Referring now to at leastFIG. 1E, conventional frame beam members may include beam elements with a tubular volume (e.g., a volume with a tubular design) and a uniform axial cross-section118with a constant radius r along a length z along the entire length of the tubular volume. Although the uniform axial cross-section118of the frame beam member102may have or result in a high stiffness and/or strength that is desirable in static and/or quasi-static loads, the uniform axial cross-section118may not have a sufficient elasticity and/or capability to absorb energy of the dynamic loads.

As such, it may be desirable to provide one or more frame beam members102that have a design configured to combine the advantages of the stiffness and strength properties of composite materials necessary during static or quasi-static load conditions and the elasticity and/or capability to absorb energy under dynamic load conditions. For example, it may be desired to reduce the risk of damage to the aircraft seat frame100. By way of another example, it may be desired to reduce the risk of the injury of a seat occupant during dynamic load conditions. By way of another example, it may be desired to provide a higher comfort in static or quasi-static load conditions.

FIGS. 2A-3Hin general illustrate the one or more frame beam members102, in accordance with one or more embodiments of the disclosure.

In general, the one or more frame beam members102may include a tubular volume with one or more walls200. A wall200may include one or more undulations. It is noted herein that “undulations” and “undulating portions” may be considered equivalent, for purposes of the disclosure.

The one or more undulations may be the same shape or may be different shapes. For example, as illustrated inFIGS. 2A-2D, the one or more undulations may be a plurality of undulations including one or more undulations202with a first shape and one or more undulations204with a second shape, where the first shape of the one or more undulations202may include a more aggressive curvature and the second shape of the one or more undulations204may include a less aggressive curvature.

In contrast with the uniform axial cross-section118as illustrated inFIG. 1E, the one or more undulations may allow for additional local bending deformation at higher load levels. For example, under relatively low levels of static or quasi-static loads, a frame beam member102with one or more undulations may deform similarly to a frame beam member102with a uniform axial cross-section118. By way of another example, under increased levels of dynamic loads, the non-linearity of deformation may be more substantial due to local bending of the one or more undulations. As such, local bending deformation of the at least one wall of frame beam members102may provide additional elasticity and enhanced energy-absorbing capacity. In this regard, the one or more frame beam members102with the one or more undulations may act similar to a spring-like elastic element.

The tubular volume may be solid, such that there may not be a cavity defined within the interior of the tubular volume. It is noted herein, however, that there may be a cavity defined within the interior of the tubular volume. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

The one or more walls200may be solid, such that there are no holes through a solid tubular volume or to a cavity defined within the interior of the tubular volume. It is noted herein, however, that the one or more walls200may include at least one pass-through hole through a solid tubular volume or to the cavity defined within the interior of the tubular volume. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

As illustrated inFIGS. 2A and 2C, the frame beam member102may be unloaded. As illustrated inFIGS. 2B and 2D, the frame beam member102may be compressive-loaded. As the frame beam member102deforms with a corresponding change in length Δz206due to an applied load the one or more undulations202,204may be configured to see a change in their local curvatures.

In one non-limiting example as illustrated inFIGS. 2C and 2D, a particular undulation202is considered before and after an applied load. A curvature of the particular undulations202may be defined by radii R′208and R″210in un-deformed and deformed states, respectively, as curvature is a characteristic inversely proportional to a corresponding radius. A change in curvature (or similarly a change in radii R′208and R″210) may be a result of local deformation due to bending of walls of the frame beam member102, which indicates a mechanism of local bending under applied compressive load with associated additional elasticity of the entire frame beam member102and an opportunity for additional energy absorption due to visco-elastic properties of materials.

It is noted herein that where the at least one wall200of the tubular volume includes a non-uniformly distributed radius R′208along a length of an individual undulation, similar non-uniform change in radii R′208and R″210may be expected along a length of other undulations on the at least one wall200of the tubular volume.

In general, a curvature of the one or more undulations202,204when in a deformed state may be different from the curvature of the one or more undulations202,204when in an un-deformed state. Where the frame beam member102is under a compressive load, the curvature of the one or more undulations202when in the deformed state may be greater than the curvature of the one or more undulations202,204when in the un-deformed state. It is noted herein, however, that the frame beam member102may be under an alternative type of load including, but not limited to, tension, bending, torque, or a combination of load types. Here, the curvature of the one or more undulations202,204when in the deformed state may be different (e.g., not greater than, but instead including, but not limited to, less than) the curvature of the one or more undulations202,204when in the un-deformed state. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

The one or more undulations202,204may be configured to bend simultaneously under an applied load. The one or more undulations202,204may be configured to bend sequentially (e.g., through a multi-step progressive deformation or even folding). An opportunity to control process of local bending of the frame beam member through modification of shapes of individual undulations can be especially valuable for optimization of an amount of energy absorption and/or member elasticity under dynamic loads.

The introduction of the one or more undulations202,204in the frame beam member102may be configured to control an overall elasticity (or stiffness) of the frame beam member102. For example, the elasticity may be controlled based on the number of the one or more undulations202,204and/or the types of shapes of the one or more undulations202,204. Controlling the number and/or the shapes of the one or more undulations202,204may result in a frame beam member102that is relatively stiff under a low load level (e.g., during a static or quasi-static condition) and is less stiff under a high load level (e.g., during a dynamic load condition).

The frame beam member102may include a select cross-section at any part along the length of the frame beam member102. The cross-section may have any shape known in the art. For example, the cross-section may be circular or elliptic. By way of another example, the cross-section may be polygonal (e.g., include at least one side with a flat shape). For instance, the cross-section may be rectangular. The frame beam member102may have a varying cross-section shape along the length of the frame beam member102.

Referring now to at leastFIGS. 3A-3H, the one or more undulations202may be dispersed along all or a part of the length of the frame beam member102. For example, as illustrated inFIGS. 3A and 3E, the entire length of the frame beam member102may be a segment300including one or more undulations202. By way of another example, as illustrated inFIGS. 3B and 3F, the frame beam member102may include a segment302with a uniform axial cross-section118located at a mid-length point of the frame beam member102and multiple segments300each including one or more undulations202located at respective ends of the frame beam member102. By way of another example, as illustrated inFIGS. 3C and 3G, the frame beam member102may include a segment300including one or more undulations202located at a mid-length point of the frame beam member102and multiple segments302each including a uniform axial cross-section118located at respective ends of the frame beam member102. By way of another example, as illustrated inFIGS. 3D and 3H, the frame beam member102may include a segment300including one or more undulations202located at one end of the frame beam member102and a segment302including a uniform axial cross-section118located at a second end of the frame beam member102.

The frame beam member102may include a primary radius304along the entire length of the frame beam member102. One or more area(s) with uniform axial cross-section(s)118may be a select distance from a central axis equal or substantially equal to the primary radius304. It is noted herein, however, that the one or more area(s) with uniform axial cross-section(s)118may be a select distance from the central axis less than or greater than the primary radius304. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

The one or more undulations202may undulate between an outward secondary radius306greater than the primary radius304and an inward secondary radius308less than the primary radius304. For example, the outward secondary radius306and the inward secondary radius308may be set at a same (but opposite sign) distance from the primary radius304. It is noted herein, however, the outward secondary radius306and the inward secondary radius308may be different distances from the primary radius304. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

As illustrated inFIGS. 3A-3D, the one or more undulations202may form hoops or rings around the frame beam member102, with each undulation202being separately positioned a select distance from an end of the frame beam member102along the length of the tubular volume.

As illustrated inFIGS. 3E-3H, the one or more undulations202may be non-constant in their position along the length of the frame beam member102. For example, the one or more undulations202may be set in a spiral formation along the length of the tubular volume of the frame member102. Where there are multiple spiral formations, the multiple spiral formations may wind clockwise or counter-clockwise along the length of the tubular volume of the frame beam member102. For example, the multiple spiral formations may wind in different directions (e.g., as illustrated inFIG. 3F). By way of another example, the multiple spiral formations may wind in a same direction.

The one or more undulations202may be uniform (e.g., in amplitude, frequency, shape, or the like) along the length of the tubular volume of the frame member102. It is noted herein, however, that at least one of the one or more undulations202may be different (e.g., in amplitude, frequency, shape, or the like) from the other undulations202along the length of the tubular volume of the frame member102. For example, non-uniform undulations may be useful to control a sequential deformation (e.g., through a multi-step progressive deformation, folding, or the like), to increase an amount of energy absorption and/or increase overall elasticity (e.g., should the aircraft seat frame100be subjected to dynamic loads). Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

Referring now toFIGS. 4A-4H, an undulation202may include one or more curved segments400(e.g., smooth transition surfaces between adjacent lines or edges) and/or one or more linear segments402(e.g., corners between adjacent lines or edges). For example, as illustrated inFIGS. 4A and 4E, the undulation202may include only curved segments400, resulting in the undulation202having a double curvature shape. By way of another example, as illustrated inFIGS. 4B and 4F, the undulation202may include only linear segments402, resulting in the undulation202having a polygonal shape. By way of another example, as illustrated inFIGS. 4C and 4G, the undulation202may include a curved segment400surrounded by linear segments402, resulting in the undulation202having a hybrid polygonal and convex curvature shape. By way of another example, as illustrated inFIGS. 4D and 4H, the undulation202may include linear segments402surrounded by curved segments400, resulting in the undulation202having a hybrid polygonal and concave curvature shape.

As illustrated inFIGS. 4A-4D, the undulation202may be arranged radially outward and configured to undulate between the primary radius304and the outward secondary radius306.

As illustrated inFIGS. 4E-4H, the undulation202may be arranged radially inward and configured to undulate between the primary radius304and the inward secondary radius308.

Although the embodiments illustrated inFIGS. 4A-4Hinclude a fully-convex undulation202(e.g., as illustrated inFIGS. 4A-4D) or a fully-concave undulation202(e.g., as illustrated inFIGS. 4E-4H), it is noted herein an undulation202illustrated inFIGS. 4A-4Dand an undulation202illustrated inFIGS. 4E-4Hmay each be a component of a full undulation202, such that the full undulation202may include a convex component and a concave component. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

FIGS. 5A-5Cin general illustrate methods or processes used for fabricating the frame beam member102, in accordance with one or more embodiments of the disclosure.

Referring now toFIG. 5A, the frame beam member102may be fabricated with a mold500that is configured to be removed following the fabrication of the frame beam member102.

In a step, the mold500may be formed. In a step, the composite material may be placed on the mold500. For example, the composite material may be placed on the mold500after the mold500is formed. By way of another example, the composite material may be placed on the mold500as the mold500is formed (e.g., via additive manufacturing, or the like).

An exterior surface of the mold500may trace and/or form the undulations202along the length of the frame beam member102, such that the mold500may have a varying radius and may mimic the shape of the interior surface of the frame beam member102(e.g., depending on positioning of the mold500).

In a step, the mold500may be removed from the interior or the exterior of the frame beam member102via a removal process. The removal process may include, but is not limited to, washing it out/off, chemical decomposition or stripping, or the like. For example, the mold500may be removed from the interior or the exterior after the frame beam member102cures to a select hardness (e.g., where the frame beam member102is fabricated from a thermoset). By way of another example, the mold500may be removed from the interior or the exterior after the frame beam member102solidifies to a select hardness (e.g., where the frame beam member102is fabricated from a thermoset).

Although embodiments of the disclosure illustrate the mold500as being an interior removable mold500, it is noted herein the mold500may be an exterior removable mold (e.g., a mold used during injection molding, casting, or the like; a mold formed during additive manufacturing; or the like). Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

Referring now toFIGS. 5B and 5C, the frame beam member102may be fabricated with a mold502that is configured to remain inserted within the frame beam member102following the fabrication of the frame beam member102. For example, the mold502may be fabricated from a lightweight polymer (e.g., including, but not limited to, a thermoplastic) with a thickness that will not substantially affect the elasticity and/or capability of the frame beam member102to absorb energy under dynamic load conditions.

In a step, the mold502may be formed. In a step, the composite material may be placed on the mold502. For example, the composite material may be placed on the mold502after the mold502is formed.

An exterior surface of the mold502may trace and/or form the undulations202along the length of the frame beam member102along an exterior edge, such that the mold502may have a varying radius and may mimic the shape of the interior surface of the frame beam member102(e.g., depending on positioning of the mold502).

As illustrated inFIG. 5B, the mold502may have an interior edge with a constant radius, such that the mold502has a defined cylindrical cavity.

As illustrated inFIG. 5C, the mold502may have a corresponding interior edge that may trace the exterior edge, such that the exterior edge has a corresponding varying radius. In this regard, the mold502may include a thin-wall shape.

In comparingFIGS. 5B and 5C, the mold502illustrated inFIG. 5Bmay be thicker but easier to make, while the mold502illustrated inFIG. 5Cmay be thinner by requiring additional methods or processes including, but not limited to, gas-assisted forming.

[moo] In one example, where the mold502is a polymeric mold fabricated from a thermoplastic, the melting temperature of the mold502may need to be higher than the curing temperature of the frame beam member102if the frame beam member102is fabricated from a thermoset, or may need to be higher than the melting temperature of the frame beam member102if the frame beam member102is fabricated from a second thermoplastic.

In general, the frame beam member102may be fabricated via one or more methods or processes including, but not limited to, AFP, filament-winding, braiding, a combination of these one or more methods or processes, or the like.

Although embodiments of the disclosure illustrate the frame beam member102as being hollow (e.g., as including a defined cavity), it is noted herein at least a portion of the frame beam member102may have a solid portion for at least a length of the frame beam member102, to the extent the solid portion does not interfere with the elasticity and/or capability of the frame beam member102to absorb energy under dynamic load conditions. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

Although embodiments of the disclosure illustrate the frame beam member102as being fabricated from a composite material, it is noted herein the frame beam member102may be fabricated from any material (e.g., a metal, alloy, metalloid, or non-metal element or a compound including a metal, alloy, metalloid, or non-metal element) configured to provide the frame beam member102with the elasticity and/or capability of the frame beam member102to absorb energy under dynamic load conditions.

In this regard, the one or more undulations202may result in the frame beam member102having an exterior surface configured to combine the advantages of the stiffness and strength properties of composite materials necessary during static or quasi-static load conditions and the elasticity and/or capability of the frame beam member102to absorb energy under dynamic load conditions. For example, this form of enhanced dynamic response may reduce the risk of damage to the aircraft seat frame100. By way of another example, this form of enhanced dynamic response may reduce the risk of injury during dynamic load conditions. By way of another example, this form of enhanced dynamic response may provide a higher comfort in static or quasi-static load conditions.

It is noted herein the aircraft seat frame100and/or the components of the aircraft seat frame100(e.g., the one or more frame beam members102including the one or more undulations202) may be installed within an aviation environment which may be configured in accordance with aviation guidelines and/or standards put forth by, but not limited to, the Federal Aviation Administration (FAA), the European Aviation Safety Agency (EASA) or any other flight certification agency or organization; the American National Standards Institute (ANSI), Aeronautical Radio, Incorporated (ARINC), the Society of Automotive Engineers (SAE), or any other standards setting organization or company; the Radio Technical Commission for Aeronautics (RTCA) or any other guidelines agency or organization; or the like.

Although embodiments of the disclosure are directed to an aviation environment, it is noted herein the one or more frame beam members102including the one or more undulations202are not limited to the aircraft seat frame100within the aviation environment and/or the aircraft components within the aviation environment. For example, the one or more frame beam members102including the one or more undulations202may be configured to operate in any type of vehicle known in the art. For example, the vehicle may be any air, space, land, or water-based personal equipment or vehicle; any air, space, land, or water-based commercial equipment or vehicle; any air, space, land, or water-based military equipment or vehicle known in the art. For instance, the vehicle may include an automobile. By way of another example, the one or more frame beam members102including the one or more undulations202may be coupled to and/or configured to operate with an apparatus sold for commercial or industrial use in either a home or a business. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.