Aircraft seat frame with enhanced dynamic response

Abstract

A frame beam member for an aircraft seat frame with enhanced dynamic response may include a tubular volume. The tubular volume may include at least one wall having one or more undulations in a radial direction along the length of the tubular volume. The one or more undulations may be configured to allow the tubular volume to absorb energy from 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 a load is applied. The second curvature may be different from the first curvature. The frame beam member may be one of a plurality of frame beam members of an aircraft seat frame. The plurality of frame beam members may be configured to be coupled to a plurality of joints of the aircraft seat frame. The present application also relates to an aircraft seat frame with enhanced dynamic response.

Description

[0001] CROSS-REFERENCE TO RELATED APPLICATIONS

[0002] This application is related to and claims the benefit of the earliest available effective filing date of the following application; this application claims the benefit of U.S. Provisional Application No. 63 / 011,162, filed on April 16, 2020, which is incorporated herein by reference in its entirety. Technical Field

[0003] The present application relates to a frame beam member for an aircraft seat frame with enhanced dynamic response. In addition, the present application also relates to an aircraft seat frame with enhanced dynamic response. Background Art

[0004] An aircraft seat frame may be subjected to dynamic loads and corresponding dynamic reactions during flight, which may generate additional stresses within a frame beam member of the aircraft seat frame. Conventional frame beam members may include a beam element having a tubular volume and having a uniform axial cross-section along the entire length of the tubular volume. Although the uniform axial cross-section may have or generate high stiffness and / or high strength required in static and / or quasi-static loads, the uniform axial cross-section may not have sufficient elasticity and / or the ability to absorb dynamic load energy. Summary of the invention

[0005] According to one or more embodiments of the present disclosure, a frame beam member for an aircraft seat frame with enhanced dynamic response is disclosed. The frame beam member may include a tubular volume. The tubular volume may include at least one wall having one or more undulations in a radial direction along the length of the tubular volume. The one or more undulations may be configured to allow the tubular volume to absorb energy from a load applied during a flight scenario by 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 a load is applied. The second curvature may be different from the first curvature. The frame beam member may be one of a plurality of frame beam members of an aircraft seat frame. The plurality of frame beam members may be configured to be coupled to a plurality of joints of an aircraft seat frame. At least one of the plurality of joints or at least one of the plurality of frame beam members may be configured to be coupled to an aircraft body.

[0006] In some embodiments, the at least one wall of the tubular volume may comprise a single section having the one or more undulations.

[0007] In some embodiments, the at least one wall of the tubular volume may include at least one section having the one or more undulations and at least one section having a uniform axial cross-section.

[0008] In some embodiments, the at least one wall of the tubular volume may include a single section having the one or more undulations at the midpoint of the length of the tubular volume and sections having a uniform axial cross-section at each end of the tubular volume.

[0009] In some embodiments, the at least one wall of the tubular volume may include a single section of uniform axial cross-section at the midpoint of the length of the tubular volume and sections having the one or more undulations at each end of the tubular volume.

[0010] In some embodiments, the at least one wall of the tubular volume may include a single section with a uniform axial cross-section at a first end of the tubular volume and a section with the one or more undulations at a second end of the tubular volume.

[0011] In some embodiments, the one or more undulations may be respectively positioned at selected distances along the length of the tubular volume from an end of the tubular volume.

[0012] In some embodiments, the one or more undulations may be in a helical configuration around the tubular volume along the length of the tubular volume.

[0013] In some embodiments, the one or more undulations may include at least one of the following shapes in an axial cross section: a double curvature shape, a polygon, a mixed shape of a polygon and a convex curvature, a mixed shape of a polygon and a concave curvature, or a combination thereof.

[0014] In some embodiments, the one or more undulations are arranged radially outwardly along the length of the tubular volume and / or at least radially inwardly along the length of the tubular volume.

[0015] In some embodiments, the frame beam member may be made of a fiber-reinforced polymer matrix composite material. The reinforcing fibers may include at least one of carbon fibers, glass fibers, organic fibers, or a combination thereof. The polymer matrix may be a thermosetting material or a thermoplastic material.

[0016] In some embodiments, the one or more undulations of the at least one wall of the tubular volume may be formed on an outer surface of a mold, the mold being configured to be removed after manufacturing is complete.

[0017] In some embodiments, the one or more undulations of the at least one wall of the tubular volume may be formed on an outer surface of a mold, the mold being configured to remain inserted after manufacturing is complete.

[0018] In some embodiments, the frame beam members may be made of a metal, an alloy, a metalloid, a non-metallic component, or a compound including at least one of a metal, an alloy, a metalloid, or a non-metallic component.

[0019] According to one or more embodiments of the present disclosure, an aircraft seat frame with enhanced dynamic response is disclosed. The aircraft seat frame may include a plurality of frame beam members. Each of the plurality of frame beam members may include a tubular volume. The tubular volume may include at least one wall having one or more undulations along at least a portion of the length of the tubular volume. The one or more undulations may be configured to allow the tubular volume to absorb energy from 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 a load is applied. The second curvature may be different from the first curvature. The aircraft seat frame may include a plurality of joints configured to be coupled to the plurality of frame beam members. At least one of the plurality of joints or at least one of the plurality of frame beam members may be configured to be coupled to an aircraft body.

[0020] The present disclosure is provided only as an introduction to the subject matter fully described in the detailed description and drawings. The present disclosure should not be considered to describe necessary technical features, nor should it be used to determine the scope of the claims. In addition, it should be understood that the above-mentioned summary of the invention and the following detailed description are merely exemplary and explanatory, and are not intended to be necessary limitations of the subject matter claimed. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] The detailed description is described with reference to the accompanying drawings. The same reference numerals used in different instances in the specification and the drawings may indicate similar or identical items. Various embodiments or examples ("examples") of the present disclosure are disclosed in the following detailed description and the accompanying drawings. The drawings are not necessarily drawn to scale. In general, the operations of the disclosed methods can be performed in any order unless otherwise specified in the claims. In the drawings:

[0022] Figure 1A shows a simplified schematic diagram of an aircraft seat frame according to one or more embodiments of the present disclosure;

[0023] Figure 1B A perspective view showing a section of a frame beam member of an aircraft seat frame according to one or more embodiments of the present disclosure;

[0024] Figure 1CA schematic diagram showing a single composite layer of a frame beam member of an aircraft seat frame according to one or more embodiments of the present disclosure;

[0025] Figure 1D A schematic diagram showing a cross section of a frame beam member of an aircraft seat frame under a dynamic load state according to one or more embodiments of the present disclosure;

[0026] Figure 1E shows an axial uniform cross-sectional view of a frame beam member according to one or more embodiments of the present disclosure;

[0027] Figure 2A A perspective view showing a frame beam member with undulations of an aircraft seat frame with enhanced dynamic response in an unloaded state according to one or more embodiments of the present disclosure;

[0028] Figure 2B A perspective view showing a frame beam member with undulations of an aircraft seat frame with enhanced dynamic response in a compressive load state according to one or more embodiments of the present disclosure;

[0029] 2C illustrates a side view of a frame beam member with undulations of an aircraft seat frame with enhanced dynamic response in an unloaded state according to one or more embodiments of the present disclosure;

[0030] 2D illustrates a side view of a frame beam member with undulations of an aircraft seat frame with enhanced dynamic response under a compressive load state according to one or more embodiments of the present disclosure;

[0031] Figure 3A An axial cross-sectional view of a frame beam member having undulations of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure is shown;

[0032] Figure 3B An axial cross-sectional view of a frame beam member having undulations of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure is shown;

[0033] Figure 3C An axial cross-sectional view of a frame beam member having undulations of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure is shown;

[0034] Figure 3D An axial cross-sectional view of a frame beam member having undulations of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure is shown;

[0035] Figure 3EAn axial cross-sectional view of a frame beam member having undulations of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure is shown;

[0036] Figure 3F An axial cross-sectional view of a frame beam member having undulations of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure is shown;

[0037] Figure 3G An axial cross-sectional view of a frame beam member having undulations of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure is shown;

[0038] Figure 3H An axial cross-sectional view of a frame beam member having undulations of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure is shown;

[0039] Figure 4A An axial cross-sectional view showing an undulation of a frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure;

[0040] Figure 4B An axial cross-sectional view showing an undulation of a frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure;

[0041] Figure 4C An axial cross-sectional view showing an undulation of a frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure;

[0042] Figure 4D An axial cross-sectional view showing an undulation of a frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure;

[0043] Figure 4E An axial cross-sectional view showing an undulation of a frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure;

[0044] Figure 4F An axial cross-sectional view showing an undulation of a frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure;

[0045] Figure 4G An axial cross-sectional view showing an undulation of a frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure;

[0046] Figure 4HAn axial cross-sectional view showing an undulation of a frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure;

[0047] Figure 5A An axial cross-sectional view showing a mold and a frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure;

[0048] Figure 5B An axial cross-sectional view showing a mold and frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure; and

[0049] Figure 5C An axial cross-sectional view of a mold and frame beam member of an aircraft seat frame having enhanced dynamic response according to one or more embodiments of the present disclosure is shown. DETAILED DESCRIPTION

[0050] Reference will now be made in detail to the disclosed subject matter, which is illustrated in the accompanying drawings.

[0051] Before describing in detail one or more embodiments of the present disclosure, it should be understood that the embodiments are not limited in their application to the details of the construction and arrangement of the components or steps or methods of the components set forth in the following description or shown in the accompanying drawings. In the detailed description of the following embodiments, many specific details may be set forth in order to provide a more comprehensive understanding of the present disclosure. However, it is apparent to those of ordinary skill in the art who benefit from the present disclosure that the embodiments disclosed herein may be implemented in the absence of some of these specific details. In some cases, well-known features may not be described in detail to avoid unnecessarily complicating the present disclosure.

[0052] As used herein, letters following a reference numeral may be used to designate embodiments of features or elements that may be similar but not necessarily identical to previously described elements or features having the same reference numeral (e.g., 1, 1a, 1b). Additionally, letters following a reference numeral may be used to designate sub-features or sub-elements or sub-systems of a larger feature or element or system (e.g., 1a or 1b is a component of 1). Unless expressly stated to the contrary, the use of such simple notations is merely for convenience and should not be construed as limiting the present disclosure in any way.

[0053] In addition, unless expressly stated to the contrary, "or" refers to an inclusive or rather than an exclusive or. For example, any of the following situations satisfies condition A or B: A is true (or exists) and B is false (or does not exist), A is false (or does not exist) and B is true (or exists), and both A and B are true (or exist).

[0054] In addition, "a" or "an" may be used to describe elements and components of the embodiments disclosed herein. This is done only for convenience, and "a" and "an" should be understood to include "one" or "at least one", and the singular form also includes the plurality, unless it is obvious that there is another meaning.

[0055] In addition, for the purpose of this disclosure, the terms or transitional phrases "including" and "having" may be considered equivalent. In this regard, the term or transitional phrase "having" should not be interpreted as a limitation on the disclosure (including the openness of the claim terms).

[0056] Finally, as used herein, any reference to "one embodiment" or "some embodiments" means that a particular element, feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment disclosed herein. The phrase "in some embodiments" appearing in various places in the specification does not necessarily refer to the same embodiment, and an embodiment may include one or more of the features expressly described or inherently present herein, or any combination or subcombination of two or more such features, as well as any other features that may not necessarily be expressly described or inherently present in the present disclosure.

[0057] Figures 1A-5C An aircraft seat frame with enhanced dynamic response according to one or more embodiments of the present disclosure is generally shown.

[0058] Figures 1A-1E An aircraft seat frame 100 is generally shown in accordance with one or more embodiments of the present disclosure.

[0059] Now refer to at least Figure 1A, the aircraft seat frame 100 may include one or more frame beam members 102. One or more frame beam members 102 may be connected via one or more joints 104, wherein one or more frame beam members 102 and / or one or more joints 104 may be configured to be connected to the aircraft body. For example, the aircraft body may include, but is not limited to, the floor 100a of the aircraft cabin 100b (e.g., directly or indirectly connected via an intermediate frame leg). For example, one or more frame beam members 102 and one or more joints 104 may be connected via at least one of the following means (but not limited to the following means): one or more interlocking components (e.g., self-locking joints, etc.), one or more fasteners (e.g., rivets, screws, etc.), adhesives, or some combination of the above means. One or more joints 104 may be made of metal, alloy, semimetal, or non-metallic components, or compounds including metal, alloy, semimetal or non-metallic components. It is noted herein that the aircraft seat frame joint is further described in U.S. Patent US10532518 B2 published on January 14, 2020, the entire contents of which are incorporated herein. Additionally, for the purposes of this disclosure, it is noted herein that "frame beam members" and "frame elements" may be considered equivalent.

[0060] Now refer to at least Figure 1B , one or more frame beam members 102 can be made of a lightweight composite material. One or more frame beam members 102 can be made of a laminated design. For example, the frame beam member 102 can include an outer laminate structure 106 and one or more monolayers 108. In the case where multiple monolayers 108 are provided, the multiple monolayers 108 can be oriented within the frame beam member 102 in a cross or other overlapping pattern defined along one or more directions 100. It is noted herein that the multiple monolayers 108 can be made of the same composite material or different composite materials.

[0061] Although the embodiments of the present disclosure illustrate one or more frame beam members 102 manufactured in a stacked design, it is noted herein that one or more frame beam members can be manufactured in a composite design via the following manufacturing processes, including but not limited to: automatic fiber placement (AFP), fiber winding, weaving, and combinations of these manufacturing processes, etc. In addition, the composite stack may include but is not limited to: a stacked design based on a unidirectional reinforcement layer arrangement, a stacked design based on a fabric layer, a 3D reinforced stack, and combinations thereof. The composite design can be made of a fiber-reinforced polymer matrix composite material. For example, the reinforcing fibers may include at least one of carbon fibers, glass fibers, organic fibers, and combinations of these fibers, etc. As another example, the polymer matrix may be a thermosetting material or a thermoplastic material. Therefore, the above description should not be construed as a limitation of the present disclosure, but is merely an exemplary illustration.

[0062] Now refer to at least Figure 1C , the single layer 108 may include a plurality of reinforcing fibers 112 arranged along one or more directions 110 within a polymer matrix 114. For example, the plurality of reinforcing fibers 112 may include, but are not limited to, reinforcing carbon fibers, reinforcing organic fibers, reinforcing glass fibers, or a fiber combination used to manufacture a composite beam element. As another example, the polymer matrix 114 may include, but are not limited to, a thermosetting material or a thermoplastic material.

[0063] The composite material from which the one or more frame beam members 102 can be made can be selected to reduce the weight of the aircraft seat frame 100 (and thus encapsulate the aircraft seat). The composite material can have high strength and high stiffness properties to make it suitable for use in primary support components, such as the one or more frame beam members 102 within the aircraft seat frame 100.

[0064] Now refer to at least Figure 1D , the aircraft seat frame 100 may be subjected to dynamic loads and corresponding dynamic reactions during flight, which may generate additional stresses within one or more frame beam members 102 of the aircraft seat frame 100. For example, dynamic loads may include, but are not limited to, emergency landings, rapid stops, excessive acceleration, rapid takeoffs, impact events (e.g., due to bird strikes), ballistic impacts, etc. The dynamic loads may generate localized dynamic reactions or dynamic load states 116 distributed axially within one or more frame beam members 102. Depending on the seat frame configuration and / or the design of the joints 104, the dynamic loads may also generate bending and / or torsional loads in one or more frame beam members 102.

[0065] Now refer to at least Figure 1E , conventional frame beam members may include a beam element having a tubular volume (e.g., a volume having a tubular design) and a uniform axial cross-section 118 along the entire length of the tubular volume having a constant radius r along the length z. Although the uniform axial cross-section 118 of the frame beam member 102 may have or produce high stiffness and / or high strength desirable in static and / or quasi-static loads, the uniform axial cross-section 118 may not have sufficient elasticity and / or the ability to absorb dynamic load energy.

[0066] Thus, it may be desirable to provide one or more frame beam members 102 that are designed and configured to combine the advantages of the stiffness and strength properties required of composite materials during static or quasi-static loading conditions with the advantages of the ability to absorb energy under elastic and / or dynamic loading conditions. For example, it may be desirable to reduce the risk of damage to the aircraft seat 100. As another example, it may be desirable to reduce the risk of injury to a seat occupant during dynamic loading conditions. As another example, it may be desirable to provide greater comfort under static or quasi-static loading conditions.

[0067] Figures 2A-3H One or more frame beam members 102 are generally shown in accordance with one or more embodiments of the present disclosure.

[0068] Generally, one or more frame beam members 102 may include a tubular volume having one or more walls 200. The wall 200 may include one or more undulations. It is noted herein that for the purposes of this disclosure, "undulations" and "undulated portions" may be considered equivalent.

[0069] One or more undulations may be of the same shape, or may be of different shapes. Figure 2A -As shown in FIG2D, the one or more undulating portions may be a plurality of undulating portions including one or more undulating portions 202 having a first shape and one or more undulating portions 204 having a second shape, wherein the first shape of the one or more undulating portions 202 may include a larger curvature, and the second shape of the one or more undulating portions 204 may include a smaller curvature.

[0070] and Figure 1E The one or more undulations may allow for additional localized bending deformation at higher load levels compared to the uniform axial cross-section 118 shown. For example, under relatively low levels of static or quasi-static loads, the frame beam member 102 having one or more undulations may deform similarly to the frame beam member 102 having the uniform axial cross-section 118. As another example, at increased dynamic load levels, nonlinear deformation may become more significant due to localized bending of the one or more undulations. Thus, localized bending deformation of at least one wall of the frame beam member 102 may provide additional resilience and enhanced energy absorption capabilities. In this regard, the one or more frame beam members 102 having one or more undulations may function similarly to a spring-like elastic element.

[0071] The tubular volume may be solid so that there may be no cavity defined inside the tubular volume. However, it is noted herein that a cavity defined inside the tubular volume may be provided. Therefore, the above description should not be interpreted as limiting the present disclosure, but merely as an exemplary illustration.

[0072] The one or more walls 200 may be solid, such that there are no holes passing through the solid tubular volume or cavities defined within the tubular volume. However, it is noted herein that the one or more walls 200 may include at least one through hole passing through the solid tubular volume or cavities defined within the tubular volume. Therefore, the above description should not be construed as limiting the present disclosure, but is merely exemplary.

[0073] like Figure 2AAs shown in FIG. 2C , the frame beam member 102 may be unloaded. Figure 2B 2D, the frame beam member 102 may be compressively loaded. As the frame beam member 102 deforms (with a corresponding change in length Δz 206) due to the applied load, one or more undulations 202, 204 may be configured to exhibit a change in its local curvature.

[0074] In one non-limiting example shown in FIGS. 2C and 2D , a particular undulation 202 is considered before and after a load is applied. The curvature of the particular undulation 202 can be represented by a radius R' 208 in an undeformed state and a radius R" 210 in a deformed state, respectively, since the curvature is a characteristic that is inversely proportional to the corresponding radius. The change in curvature (or similarly, the change in radius R' 208 and R" 210) can be the result of local deformation due to bending of the wall of the frame beam member 102, which indicates a mechanism of local bending when a compressive load is applied with the associated additional elasticity of the entire frame beam member 102 and an opportunity to absorb additional energy due to the viscoelastic properties of the material.

[0075] It is noted herein that at least one wall 200 of the tubular volume comprises a non-uniformly distributed radius R' 208 along the length of a single undulation, and similar non-uniform variations of the radii R' 208 and R" 210 can be envisioned along the lengths of other undulations on at least one wall 200 of the tubular volume.

[0076] In general, the curvature of the one or more undulations 202, 204 in the deformed state may be different from the curvature of the one or more undulations 202, 204 in the undeformed state. When the frame beam member 102 is under a compressive load, the curvature of the one or more undulations 202 in the deformed state may be greater than the curvature of the one or more undulations 202, 204 in the undeformed state. However, it is noted herein that the frame beam member 102 may be under alternative types of loads, including but not limited to tension, bending, torque, or a combination of multiple load types. Here, the curvature of the one or more undulations 202, 204 in the deformed state may be different from (e.g., not greater than, but also including but not limited to, less than) the curvature of the one or more undulations 202, 204 in the undeformed state. Therefore, the above description should not be construed as limiting the present disclosure, but is merely exemplary.

[0077] One or more undulations 202, 204 may be configured to bend simultaneously under applied load. One or more undulations 202, 204 may be configured to bend sequentially (e.g., by multiple steps of gradual deformation or even by folding). The opportunity to control the process of localized bending of a frame beam member by changing the shape of a single undulation may be particularly valuable for optimizing the amount of energy absorption and / or member resilience under dynamic loading.

[0078] The one or more undulations 202, 204 introduced into the frame beam member 102 may be configured to control the overall elasticity (or stiffness) of the frame beam member 102. For example, the elasticity may be controlled based on the number of the one or more undulations 202, 204 and / or the type of shape of the one or more undulations 202, 204. Controlling the number and / or shape of the one or more undulations 202, 204 may result in the frame beam member 102 being relatively stiff at low load levels (e.g., during static or quasi-static conditions) and being less stiff at high load levels (e.g., during dynamic load conditions).

[0079] The frame beam member 102 can include a selected cross-section at any portion along the length of the frame beam member 102. The cross-section can have any shape known in the art. For example, the cross-section can be circular or elliptical. As another example, the cross-section can be polygonal (e.g., including at least one side having a flat shape). For example, the cross-section can be rectangular. The frame beam member 102 can have a varying cross-sectional shape along the length of the frame beam member 102.

[0080] Now at least reference Figures 3A-3H , one or more undulations 202 may be dispersed along all or a portion of the length of the frame beam member 102. For example, Figure 3A and 3E As shown, the entire length of the frame beam member 102 can be a section 300 including one or more undulations 202. As another example, Figure 3B and 3F As shown, the frame beam member 102 may include a section 302 having a uniform axial cross-section 118 located at the midpoint of the length of the frame beam member 102 and a plurality of sections 300 located at each end of the frame beam member 102, each section 300 including one or more undulations 202. As another example, Figure 3C and 3G As shown, the frame beam member 102 may include a section 300 including one or more undulations 202 at the midpoint of the length of the frame beam member 102 and a plurality of sections 302 located at each end of the frame beam member 102, each section 302 including a uniform axial cross-section 118. As another example, Figure 3D and3H As shown, the frame beam member 102 may include a section 300 including one or more undulations 202 at one end of the frame beam member 102 and a section 302 including the uniform axial cross-section 118 at a second end of the frame beam member 102 .

[0081] The frame beam member 102 may include a major radius 304 along the entire length of the frame beam member 102. The selected distance from the central axis of one or more regions having a uniform axial cross-section 118 may be equal to or approximately equal to the major radius 304. However, it is noted herein that the selected distance from the central axis of one or more regions having a uniform axial cross-section 118 may be less than or greater than the major radius 304. Therefore, the above description should not be construed as limiting the present disclosure, but is merely exemplary.

[0082] One or more undulations 202 may undulate between an outer second radius 306 that is larger than the main radius 304 and an inner second radius 308 that is smaller than the main radius 304. For example, the outer second radius 306 and the inner second radius 308 may be set to be the same distance from the main radius 304 (but with opposite signs). However, it is noted herein that the distances between the outer second radius 306 and the inner second radius 308 and the main radius 304 may be different. Therefore, the above description should not be construed as limiting the present disclosure, but is merely exemplary.

[0083] like Figures 3A-3D As shown, one or more undulations 202 may be formed in a hoop or loop around the frame beam member 102 , with each undulation 202 being positioned at a selected distance from an end of the frame beam member 102 along the length of the tubular volume, respectively.

[0084] like Figure 3E-3H As shown, one or more undulations 202 may be non-constant in their position along the length of the frame beam member 102. For example, one or more undulations 202 may be arranged as a spiral structure along the length of the tubular volume of the frame beam member 102. Where multiple spiral structures are provided, the multiple spiral structures may wind clockwise or counterclockwise along the length of the tubular volume of the frame beam member 102. For example, the multiple spiral structures may wind in different directions (e.g., Figure 3F As another example, the plurality of spiral structures can be wound in the same direction.

[0085] The one or more undulations 202 may be uniform along the length of the tubular volume of the frame member 102 (e.g., in terms of amplitude, frequency, shape, etc.). However, it is noted herein that at least one of the one or more undulations 202 may be different from the other undulations 202 along the length of the tubular volume of the frame member 102 (e.g., in terms of amplitude, frequency, shape, etc.). For example, non-uniform undulations may be used to control sequential deformation (e.g., through multiple steps of gradual deformation, folding, etc.) to increase the amount of energy absorption and / or increase overall resilience (e.g., in the event that the aircraft seat frame 100 is subjected to dynamic loads). Therefore, the above description should not be construed as limiting the present disclosure, but is merely exemplary.

[0086] Reference now Figures 4A-4H The undulating portion 202 may include one or more curved segments 400 (e.g., smooth transition surfaces between adjacent lines or edges) and / or one or more linear segments 402 (e.g., corners between adjacent lines or edges). Figure 4A and 4E As shown, the undulating portion 202 may include only the curved section 400 to obtain the undulating portion 202 having a double curvature shape. As another example, Figure 4B and 4F As shown, the undulating portion 202 may include only linear segments 402 to obtain an undulating portion 202 having a polygonal shape. As another example, Figure 4C and 4G As shown, the undulating portion 202 may include a curved segment 400 surrounded by a linear segment 402 to obtain an undulating portion 202 having a mixed shape of a polygonal and convex curvature. As another example, Figure 4D and 4H As shown, the undulation 202 may include a linear segment 402 surrounded by a curved segment 400 to result in an undulation 202 having a hybrid shape of a polygonal and concave curvature.

[0087] like Figures 4A-4D As shown, the undulations 202 may be disposed radially outward and configured to undulate between a major radius 304 and an outer second radius 306 .

[0088] like Figure 4E-4H As shown, the undulation 202 may be disposed radially inwardly and configured to undulate between a major radius 304 and an inner second radius 308 .

[0089] although Figures 4A-4H The illustrated embodiment includes a fully convex relief 202 (e.g., Figures 4A-4D ) or a fully concave relief 202 (e.g., as Figure 4E-4H However, it should be noted in this article that Figures 4A-4DThe undulating portion 202 and Figure 4E-4H The undulations 202 shown in the figure may each be a component of a complete undulation 202, so that the complete undulation 202 may include a convex component and a concave component. Therefore, the above description should not be interpreted as limiting the present disclosure, but is merely an exemplary illustration.

[0090] Figures 5A-5C A method or process for manufacturing a frame beam member 102 according to one or more embodiments of the present disclosure is generally shown.

[0091] Reference now Figure 5A , the frame beam member 102 may be manufactured using a mold 500 that is configured to be removed after manufacturing of the frame beam member 102 is complete.

[0092] In one step, the mold 500 can be formed. In one step, the composite material can be placed on the mold 500. For example, the composite material can be placed on the mold 500 after the mold 500 is formed. As another example, the composite material can be placed on the mold 500 when the mold 500 is formed (e.g., via additive manufacturing, etc.).

[0093] The outer surface of the mold 500 may follow and / or form the undulations 202 along the length of the frame beam member 102 such that the mold 500 may have a varying radius and may mimic the shape of the inner surface of the frame beam member 102 (eg, depending on the positioning of the mold 500 ).

[0094] In one step, the mold 500 can be removed from the inside or outside of the frame beam member 102 via a removal process. The removal process can include, but is not limited to, washing / flushing off, chemical decomposition or peeling, etc. For example, after the frame beam member 102 hardens to a selected hardness (e.g., the frame beam member 102 is made of a thermosetting material), the mold 500 can be removed from the inside or outside. As another example, after the frame beam member 102 is cured to a selected hardness (e.g., the frame beam member 102 is made of a thermosetting material), the mold 500 can be removed from the inside or outside.

[0095] Although the embodiment of the present disclosure illustrates that the mold 500 is an internally removable mold 500, it should be noted that the mold 500 may be an externally removable mold (e.g., a mold used during injection molding, casting, etc.; a mold formed during additive manufacturing, etc.). Therefore, the above description should not be interpreted as limiting the present disclosure, but is merely an exemplary description.

[0096] Reference now Figure 5B and 5C, the frame beam member 102 can be manufactured using a mold 502 that is configured to remain inserted into the frame beam member 102 after the frame beam member 102 is manufactured. For example, the mold 502 can be manufactured from a lightweight polymer (e.g., including but not limited to a thermoplastic material) having a thickness that does not substantially affect the resilience and / or energy absorption ability of the frame beam member 102 under dynamic loading conditions.

[0097] In one step, mold 502 can be formed. In one step, composite material can be placed on mold 502. For example, composite material can be placed on mold 502 after mold 502 is formed.

[0098] The outer surface of the mold 502 may follow and / or form the undulations 202 along the length of the frame beam member 102 along the outer edge such that the mold 502 may have a varying radius and may mimic the shape of the inner surface of the frame beam member 102 (eg, depending on the positioning of the mold 502 ).

[0099] like Figure 5B As shown, the mold 502 may have an inner edge with a constant radius such that the mold 502 has a defined cylindrical cavity.

[0100] like Figure 5C As shown, the mold 502 can have a corresponding inner edge that can follow the outer edge, so that the outer edge has a corresponding varying radius. In this regard, the mold 502 can include a thin-walled shape.

[0101] Compare Figure 5B and Figure 5C , Figure 5B The mold 502 shown in FIG. 5 can be thicker but easier to manufacture, while Figure 5C The mold 502 shown may be thinner, but may require additional methods or processes, including but not limited to gas assist forming.

[0102] In one example, the mold 502 is a polymer mold made of a thermoplastic material. If the frame beam member 102 is made of a thermosetting material, the melting temperature of the mold 502 may need to be higher than the hardening temperature of the frame beam member 102; if the frame beam member 102 is made of a second thermoplastic material, the melting temperature of the mold 502 may need to be higher than the melting temperature of the frame beam member 102.

[0103] Generally speaking, the frame beam member 102 may be manufactured via one or more methods or processes, including but not limited to AFP, filament winding, weaving, and combinations of one or more such methods or processes, and the like.

[0104] Although the embodiments of the present disclosure show that the frame beam member 102 is hollow (e.g., including a defined cavity), it should be noted herein that at least a portion of the frame beam member 102 may have a solid portion over at least a length of the frame beam member 102, and the extent of the solid portion cannot affect the elasticity and / or energy absorption capability of the frame beam member 102 under dynamic load conditions. Therefore, the above description should not be interpreted as limiting the present disclosure, but is merely an exemplary illustration.

[0105] Although the embodiments of the present disclosure illustrate that the frame beam member 102 is made of a composite material, it should be noted herein that the frame beam member 102 can be made of any material (e.g., a metal, alloy, metalloid, or non-metallic component, or a compound including a metal, alloy, metalloid, or non-metallic component) that is configured to provide elasticity to the frame beam member 102 and / or provide the frame beam member 102 with the ability to absorb energy under dynamic load conditions.

[0106] In this regard, the one or more undulations 202 may result in the frame beam member 102 having an outer surface that is configured to combine the advantages of the desired stiffness and strength properties of the composite material during static or quasi-static loading with the advantages of the resilience and / or energy absorbing ability of the frame beam member 102 under dynamic loading conditions. For example, this form of enhanced dynamic response may reduce the risk of damage to the aircraft seat 100. As another example, this form of enhanced dynamic response may reduce the risk of injury during dynamic loading conditions. As another example, this form of enhanced dynamic response may provide greater comfort under static or quasi-static loading conditions.

[0107] It is noted herein that the aircraft seat frame 100 and / or components of the aircraft seat frame 100 (e.g., one or more frame beam members 102 including one or more undulations 202) may be installed within an aviation environment that may be configured in accordance with aviation guidelines and / or standards set forth by, but not limited to, the Federal Aviation Administration (FAA), the European Aviation Safety Agency (EASA), or any other aviation certification agency or organization; the American National Standards Institute (ANSI), the American Aeronautical Radio Corporation (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 guiding agency or organization, etc.

[0108] Although the embodiments of the present disclosure relate to an aviation environment, it should be noted herein that the one or more frame beam members 102 including one or more undulations 202 are not limited to aircraft seat frames 100 and / or aircraft components within an aviation environment. For example, the one or more frame beam members 102 including one or more undulations 202 can be configured to operate within any type of vehicle known in the art. For example, the vehicle can be any personal device or vehicle based on air, space, land, or water known in the art; any commercial device or vehicle based on air, space, land, or water; any military device or vehicle based on air, space, land, or water. For example, the vehicle can include a car. As another example, the one or more frame beam members 102 including one or more undulations 202 can be coupled to a home or commercial device for commercial sale or industrial use and / or be configured to operate with a home or commercial device for commercial sale or industrial use. Therefore, the above description should not be interpreted as a limitation of the present disclosure, but is merely an exemplary illustration.

[0109] Although the present disclosure has been described with reference to the embodiments shown in the accompanying drawings, equivalents may be used or substituted without departing from the scope of the claims. The components described and illustrated herein are merely examples of systems / devices and components that may be used to implement embodiments of the present disclosure, and may be replaced with other devices and components without departing from the scope of the claims. In addition, unless otherwise specified in the claims, any dimensions, angles, and / or numerical ranges provided herein should be understood as non-limiting examples.

Claims

1. A frame beam member for an aircraft seat frame having enhanced dynamic response, comprising: a tubular volume comprising at least one wall having a plurality of first undulations and a plurality of second undulations arranged in sequence and extending radially outward along a length of the tubular volume, the plurality of first undulations and the plurality of second undulations being configured to allow the tubular volume to absorb energy of a compressive load applied during a flight scenario by localized bending of the plurality of first undulations and the plurality of second undulations; The plurality of first undulations are configured to have a first curvature when unloaded, the plurality of first undulations are configured to have a second curvature when a compressive load is applied, the second curvature being greater than the first curvature, and the plurality of second undulations are configured to have a third curvature when unloaded, the first curvature being greater than the third curvature, whereby the plurality of first undulations are configured to deform before the plurality of second undulations; The frame beam member is one of a plurality of frame beam members of an aircraft seat frame, the plurality of frame beam members being configured to be coupled to a plurality of joints of the aircraft seat frame, at least one of the plurality of joints or at least one of the plurality of frame beam members being configured to be coupled to an aircraft body.

2. The frame beam member according to claim 1, wherein: The at least one wall of the tubular volume comprises a single section having the plurality of first undulations and the plurality of second undulations.

3. The frame beam member according to claim 1, wherein: The at least one wall of the tubular volume includes at least one section having the plurality of first undulations and the plurality of second undulations and at least one section having a uniform axial cross-section.

4. The frame beam member according to claim 3, wherein: The at least one wall of the tubular volume includes a single section having the plurality of first undulations and the plurality of second undulations at a midpoint in the length of the tubular volume and a section having a uniform axial cross-section at each end of the tubular volume.

5. The frame beam member according to claim 3, wherein: The at least one wall of the tubular volume comprises a single section having a uniform axial cross-section at a midpoint in the length of the tubular volume and sections having the plurality of first undulations and the plurality of second undulations at each end of the tubular volume.

6. The frame beam member according to claim 3, wherein: The at least one wall of the tubular volume comprises a single section having a uniform axial cross-section at a first end of the tubular volume and a single section having the plurality of first undulations and the plurality of second undulations at a second end of the tubular volume.

7. The frame beam member according to claim 1, wherein: The plurality of first undulations and the plurality of second undulations are each positioned at a selected distance along the length of the tubular volume from an end of the tubular volume.

8. The frame beam member according to claim 1, wherein: The plurality of first undulations and the plurality of second undulations are in a spiral configuration around the tubular volume along a length of the tubular volume.

9. The frame beam member according to claim 1, wherein: The plurality of first undulations and the plurality of second undulations include at least one of the following shapes in an axial cross section: a double curvature shape, a polygon, a mixed shape of a polygon and a convex curvature, a mixed shape of a polygon and a concave curvature, or a combination thereof.

10. The frame beam member according to claim 1, wherein: The frame beam member is made of a fiber reinforced polymer matrix composite material, The reinforcing fibers include at least one of carbon fibers, glass fibers, organic fibers, or a combination thereof; The polymer matrix comprises a thermosetting material or a thermoplastic material.

11. The frame beam member according to claim 10, wherein: The plurality of first undulations and the plurality of second undulations of the at least one wall of the tubular volume are formed on an outer surface of a mold, the mold being configured to be removed after manufacturing is completed.

12. The frame beam member according to claim 10, wherein: The tubular volume comprises a mold, the plurality of first undulations and the plurality of second undulations of the at least one wall of the tubular volume being molded on an outer surface of the mold.

13. The frame beam member according to claim 1, wherein: The frame beam member is made of a metal, an alloy, a metalloid, a non-metallic component, or a compound including at least one of a metal, an alloy, a metalloid, or a non-metallic component.

14. An aircraft seat frame with enhanced dynamic response, comprising: A plurality of frame beam members, each frame beam member of the plurality of frame beam members comprising: A tubular volume comprising at least one wall having a plurality of first undulations and a plurality of second undulations arranged in sequence and extending radially outward along at least a portion of the length of the tubular volume; the plurality of first undulations and the plurality of second undulations are configured to allow the tubular volume to absorb energy of a compressive load applied during a flight scenario by local bending of the plurality of first undulations and the plurality of second undulations, the plurality of first undulations being configured to have a first curvature when unloaded; the plurality of first undulations being configured to have a second curvature when a compressive load is applied, the second curvature being greater than the first curvature, the plurality of second undulations being configured to have a third curvature when unloaded, the first curvature being greater than the third curvature, whereby the plurality of first undulations are configured to deform before the plurality of second undulations; and A plurality of joints are configured to be coupled 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 is configured to be coupled to an aircraft body.

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