Stanchion for aircraft structure
Composite struts with varying ply counts and pivotable connections improve energy dissipation and load distribution in aircraft floor structures, addressing structural weaknesses during high-load scenarios.
Patent Information
- Application Number
- JP2025088410
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2024-05-29
- Filing Date
- 2025-05-28
- Publication Date
- 2025-12-23
AI Technical Summary
Existing aircraft floor structures lack efficient energy dissipation during high-load scenarios, such as landing on the belly, and require improved load distribution and structural integrity.
The use of composite struts with varying ply counts in longitudinal segments and a bonded, mechanically fastened configuration, along with pivotable connections, to enhance energy dissipation and load distribution.
Enhances structural integrity and energy dissipation during high-load events, providing improved safety and performance in aircraft floor systems.
Smart Images
Figure 2025186185000001_ABST
Abstract
Description
[Technical Field]
[0001] FIELD OF THE DISCLOSURE
[0001] The present disclosure relates generally to aircraft structures, and more particularly to stanchions for supporting floor systems within aircraft. [Background technology]
[0002]
[0002] The body of an aircraft is generally formed from fuselage segments joined together. The fuselage segments may include a structural framework surrounded by an outer skin. A floor structure may extend across the body structure of the aircraft and define a portion of the cabin for the crew and passengers on one side and a cargo space on the other side. The floor structure may include floor beams spanning the width of the body of the aircraft and attached to the structural framework. Summary of the Invention
[0003]
[0003] A strut for an aircraft is disclosed herein. The strut includes a first composite body defining a first channel having a first web extending between a first pair of spaced flanges. The first composite body also includes a first number of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the first number of longitudinal segments. The strut also includes a second composite body defining a second channel having a second web extending between a second pair of flanges. The second composite body also includes a second number of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the second number of longitudinal segments. In this case, the first composite body is fixed relative to the second composite body.
[0004] In another aspect of the present disclosure, the number of plies in each of the first multiple longitudinal segments is symmetrical about a central longitudinal segment of the first multiple longitudinal segments.
[0005] In another aspect of the present disclosure, the number of plies in each of the second multiple longitudinal segments is symmetrical about a central longitudinal segment of the second multiple longitudinal segments.
[0006] In another aspect of the present disclosure, the post includes a plurality of fasteners extending through the first web and the second web.
[0007]
[0007] In another aspect of the present disclosure, the support includes a reinforcing plate attached to one of a first pair of spaced flanges using a first fastener and a reinforcing plate attached to a corresponding one of a second pair of flanges using a second fastener.
[0008] In another aspect of the present disclosure, the first composite body is longitudinally offset from the second composite body.
[0009] In another aspect of the present disclosure, the first web includes a first attachment surface facing away from the first channel.
[0010] In another aspect of the present disclosure, the second web includes a second attachment surface facing away from the second channel.
[0011]
[0011] In another aspect of the present disclosure, a strut includes a pivotable connection having a first pivotable attachment fixed to the first composite body and the second composite body at a distal end of the strut, and a second pivotable attachment pivotally mounted to the first pivotable attachment about a pivotable axis.
[0012]
[0012] In another aspect of the present disclosure, the first web and the first pair of spaced flanges are a unitary structure having a C-shaped cross-section, and the first web includes a first surface facing the first channel and a second surface that at least partially engages with the second composite body.
[0013]
[0013] In another aspect of the present disclosure, the second web and the second pair of spaced flanges are a unitary structure having a C-shaped cross-section, and the second web includes a first surface facing the second channel and a second surface that engages with the first composite body.
[0014] In another aspect of the present disclosure, a first composite body is bonded to a second composite body.
[0015]
[0015] Disclosed herein is a fuselage segment. The fuselage segment includes circumferentially extending ribs, longitudinally extending stringers engaging the ribs, floor beams extending laterally between corresponding segments of the ribs, and a strut extending between one of the floor beams and a corresponding one of the ribs. The strut includes a first composite body defining a first channel having a first web extending between a first pair of spaced-apart flanges. The first composite body also includes a first number of longitudinal segments, each longitudinal segment having a ply count that varies between adjacent longitudinal segments of the first number of longitudinal segments. The strut also includes a second composite body defining a second channel having a second web extending between a second pair of flanges. The second composite body also includes a second number of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the second number of longitudinal segments, wherein the first composite body is fixed relative to the second composite body.
[0016]
[0016] In another aspect of the present disclosure, the number of plies in each of the first multiple longitudinal segments is symmetrical around a central longitudinal segment of the first multiple longitudinal segments, and the number of plies in each of the second multiple longitudinal segments is symmetrical around a central longitudinal segment of the second multiple longitudinal segments.
[0017]
[0017] In another aspect of the present disclosure, the support includes a reinforcing plate attached to one of a first pair of spaced flanges using a first fastener and a reinforcing plate attached to a corresponding one of a second pair of spaced flanges using a second fastener.
[0018]
[0018] In another aspect of the present disclosure, the struts include a pivotable connection having a first pivotable attachment fixed to a first composite body and a second composite body at the distal ends of the multiple struts, and a second pivotable attachment pivotally mounted to the first pivotable attachment about a pivotable axis.
[0019] In another aspect of the present disclosure, the first web and the first pair of spaced apart flanges are a unitary structure having a C-shaped cross-section, the first web including a first surface facing the first channel and a second surface that at least partially engages the second composite body. The second web and the second pair of spaced apart flanges are a unitary structure having a C-shaped cross-section, the second web including a first surface facing the second channel and a second surface that engages the first composite body.
[0020]
[0020] A floor assembly for an aircraft is disclosed herein. The floor assembly includes a floor panel, at least one floor beam supporting the floor panel, at least one rib supporting opposite ends of the floor panel, and at least one strut extending between the at least one floor beam and the at least one rib. The strut includes a first composite body defining a first channel having a first web extending between a first pair of spaced flanges. The first composite body also includes a first number of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the first number of longitudinal segments. The strut also includes a second composite body defining a second channel having a second web extending between a second pair of flanges. The second composite body also includes a second number of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the second number of longitudinal segments. In that case, the first composite body is fixed relative to the second composite body.
[0021]
[0021] In another aspect of the present disclosure, the number of plies in each of the first multiple longitudinal segments is symmetrical around a central longitudinal segment of the first multiple longitudinal segments, and the number of plies in each of the second multiple longitudinal segments is symmetrical around a central longitudinal segment of the second multiple longitudinal segments.
[0022] In another aspect of the present disclosure, the first web and the first pair of spaced apart flanges are a unitary structure having a C-shaped cross-section, the first web including a first surface facing the first channel and a second surface that at least partially engages the second composite body. The second web and the second pair of spaced apart flanges are a unitary structure having a C-shaped cross-section, the second web including a first surface facing the second channel and a second surface that engages the first composite body.
[0023]
[0023] The above summary is not intended to represent all possible embodiments or all aspects of the present disclosure. Rather, the foregoing summary is intended to illustrate some of the novel aspects and features disclosed herein. While the features, functions, and advantages of the present disclosure may be realized alone in various embodiments or may be combined in other embodiments, further details of these embodiments may be understood by reference to the following description and drawings. [Brief explanation of the drawings]
[0024] [Figure 1]
[0024] An exemplary fuselage segment having a structural framework for forming a portion of the body of an aircraft is shown. [Figure 2]
[0025] 2 illustrates an enlarged view of an exemplary support column of the structural framework of FIG. 1. [Figure 3]
[0026] 2 illustrates a perspective view of an exemplary support column of the structural framework of FIG. 1. [Figure 4]
[0027] 4 illustrates a cross-sectional view of an exemplary strut taken along line 4-4 of FIG. 2. [Figure 5]
[0028] 2 illustrates an enlarged view of another exemplary support column of the structural framework of FIG. 1. [Figure 6]
[0029] 6 illustrates a front perspective view of the exemplary support post of FIG. 5. [Figure 7]
[0030] 6 illustrates a rear perspective view of the exemplary support column of FIG. 5. DETAILED DESCRIPTION OF THE INVENTION
[0025]
[0031] The present disclosure may extend to modifications and alternative forms, with exemplary embodiments shown by way of example in the drawings and described in detail below. The inventive aspects of the present disclosure are not limited to the disclosed embodiments. Rather, the present disclosure is intended to cover alternatives that fall within the scope of the present disclosure as defined by the appended claims.
[0026]
[0032] Several embodiments of the present disclosure are described herein. However, it should be understood that the disclosed several embodiments are illustrative examples, and that other several embodiments may take various alternative forms. The drawings are not necessarily drawn to scale and may be schematic. Some features may be exaggerated or minimized to show details of particular components. Therefore, the specific structural and functional details disclosed herein should not be construed as limiting, but merely as representative principles for teaching those skilled in the art how to utilize the present disclosure in various ways.
[0027]
[0033] 1 shows a perspective view of an exemplary fuselage segment 20. Multiple fuselage segments 20 may be joined together to form the body of an aircraft. In the illustrated example, the fuselage segment 20 includes a structural framework 22 surrounded by skin panels 24 that form the outer surface of the fuselage segment 20. The structural framework 22 includes a plurality of circumferentially extending ribs 26 that are longitudinally spaced from one another relative to a longitudinal axis A of the fuselage segment 20. Stringers 28 are circumferentially disposed around the fuselage segment 20 and extend longitudinally to engage the ribs 26 of the fuselage segment 20.
[0028]
[0034] Floor beams 30 extend laterally across the fuselage segments 20 between corresponding ribs 26 to support a floor system 32 (FIG. 2). In the illustrated example, pairs of struts 34 each engage a floor beam 30 and a corresponding one of the ribs 26 that is longitudinally aligned with a corresponding one of the floor beams 30. In this disclosure, axial, radial, and longitudinal are relative to the axis A of the fuselage segments 20.
[0029]
[0035] 2 shows an enlarged view of one of the struts 34 extending between one of the floor beams 30 and one of the ribs 26. In the illustrated example, the strut 34 is secured directly to the floor beam 30 at a first end with fastener 40 and directly to the rib 26 at a second end with fastener 42. While the strut 34 is shown directly engaging the floor beam 30 and the rib 26, the strut 34 may engage additional structure, such as a stringer 28 or a swivel connection (FIG. 5). The floor panels 36 are supported by the floor beams 30 with brackets 38, which form at least a portion of the floor system 32. The floor panels 36 at least partially separate the passenger cabin from the cargo hold on the aircraft.
[0030]
[0036] As shown in Figures 2-4, each of the struts 34 is formed from a first channel 50A attached in a back-to-back configuration with a second channel 50B. In the illustrated example, the first channel 50A and the second channel 50B are comprised of a composite material formed from multiple plies or layers of fibrous material, such as a woven carbon fiber material supported in a resin. The first channel 50A and the second channel 50B thereby form a first composite body and a second composite body, respectively. Each of the first channel 50A and the second channel 50B may be formed in a mold having a variable number of plies along its length, as described in more detail below.
[0031]
[0037] The first channel 50A and the second channel 50B extend longitudinally between first ends 52A and 52B and second ends 54A and 54B, respectively. The first channel 50A and the second channel 50B are longitudinally offset from one another, such that the first end 52A of the first channel 50A and the first end 52B of the second channel 50B do not overlap. Similarly, the second end 54A of the first channel 50A and the second end 54B of the second channel 50B also do not overlap. This therefore forms a central region of the strut 34 having a double wall defined by the first channel 50A and the second channel 50B. In one embodiment, the first channel 50A and the second channel 50B are mirror images of each other.
[0032]
[0038] Each of the first and second channels 50A, 50B includes a first web 60A and a second web 60b extending between a first pair 62A and a second pair 62B of spaced flanges, respectively, as a unitary structure. Each of the first and second channels 50A, 50B includes a first inner surface 64A and a second inner surface 64B facing the corresponding channel region, and a first outer surface 66A and a second outer surface 66B facing outward from the channel region and at least partially toward the other channel.
[0033]
[0039] When the first channels 50A and 50B are formed, each ply or layer of the composite structure extends continuously from the first web 60A and the second web 60B to the outer edges of the first and second pairs of spaced flanges 62A and 62B, respectively. Additionally, one or both of the outer surfaces 66A and 66B may include a bonding layer 39 within the molded-in regions of the first and second webs 60A and 60B, respectively, to aid in bonding the first and second channels 50A and 50B to one another. In one embodiment, the bonding layer 39 is activated via the application of heat and pressure to one or both of the first and second channels 50A and 50B. The bonding layer 39 may be comprised of a thermoplastic film.
[0034]
[0040] In one embodiment, channels 50A and 50B are composite structures formed from multiple layers of material formed into a C-shaped configuration through the application of heat and pressure by a mold during a molding or stamping process. Channels 50A and 50B each include a set of multiple plies that extend continuously between first ends 52A and 52B and second ends 54A and 54B, respectively.
[0035]
[0041] Although the channels 50A and 50B include a continuous set of plies as described above, each channel 50A and 50B may include longitudinal segments extending lengthwise relative to the first end 52A and 52B and the second end 54A and 54B. In this case, the number of plies may vary. For example, additional plies may be added to specific longitudinal segments of the first channel 50A and the second channel 50B in a predetermined pattern of ply thicknesses. In the illustrated example, each of the channels 50A and 50B includes longitudinal segments S-E at opposite ends that include a minimum number of plies extending between the first end 52A and 52B and the second end 54A and 54B, respectively. The first channel 50A and the second channel 50B also include longitudinal segments S-1, S-2, and S-3. In this case, the number of plies may vary between adjacent longitudinal segments. In the present disclosure, the number of plies is determined by the number of layers or plies of material stacked on top of each other when forming channels 50A and 50B. The illustrated example includes longitudinal segments S-E, S-1, S-2, and S-3, however, fewer longitudinal segments, such as three longitudinal segments, or more longitudinal segments, such as five longitudinal segments, may be utilized in the present disclosure based on a given application and the length of strut 34.
[0036]
[0042] 3, longitudinal segments S-E, S-1, and S-2 are symmetrically disposed about longitudinal segment S-3. Accordingly, longitudinal segment S-3 in the illustrated example is the central longitudinal segment of strut 34. Accordingly, longitudinal segment S-3 includes an equal number of longitudinal segments between first ends 52A and 52B and second ends 54A and 54B. Furthermore, in one embodiment, at least a portion of the central longitudinal segment is disposed at a midpoint equidistant from first ends 52A and 52B and second ends 54A and 54B.
[0037]
[0043] In the illustrated example, longitudinal segment S-1 includes a first number of plies, longitudinal segment S-2 includes a second number of plies, and longitudinal segment S-3 includes a third number of plies. Furthermore, one of inner longitudinal segments S-2 or S-3 may include the same number of plies as end longitudinal segment S-E. For example, longitudinal segments S-E and S-2 may each include eight plies, longitudinal segment S-1 may include ten plies, and section S-3 may include twelve plies. One advantage of having a variable number of plies among the longitudinal segments is the ability to control energy dissipation within strut 34 during high-load scenarios. One exemplary high-load scenario may include landing an aircraft on its belly during a failure of one or more of the aircraft's landing gear.
[0038]
[0044] 2-4, the first channel 50A and the second channel 50B may be secured to one another using mechanical fasteners in addition to the bond provided between the first channel 50A and the second channel 50B. In one embodiment, mechanical fasteners 70, such as bolts, may extend through the first web 60A and the second web 60B and apply a compressive force to the first channel 50A and the second channel 50B. Furthermore, the mechanical fasteners 70 may limit longitudinal movement of the first channel 50A and the second channel 50B relative to one another.
[0039]
[0045] As shown in FIG. 4 , a reinforcing plate 72 can be used to secure the first channel 50A and the second channel 50B relative to one another to improve load distribution. In the illustrated example, the reinforcing plate 72 is planar and constructed from a metallic or composite material. In one embodiment, the reinforcing plate 72 is attached to a corresponding one of each pair of spaced apart webs 62A and 62B. The reinforcing plate 72 is attached to the first channel 50A and the second channel 50B using mechanical fasteners 74, such as bolts. The reinforcing plate 72 can be further secured to the first channel 50A and the second channel 50B using adhesive members 76 disposed between the reinforcing plate 72 and a corresponding one of each pair of spaced apart flanges 62A and 62B. The adhesive members 76 can be used in addition to or in place of the fasteners 74.
[0040]
[0046] 5-7 show an exemplary support post 134 that is similar to support post 34 but differs in ways that will be described below or shown in the drawings. Similar or like components may be designated by the addition of a leading "1."
[0041]
[0047] 5 , struts 134 extend between ribs 26 of fuselage 20 and floor beams 30. The connection between struts 134 and ribs 26 is identical to the connection between struts 34 and ribs 26, except that the connection between struts 134 and floor beams 30 includes a pivotable connection 190. Pivotable connection 190 includes a first pivotable attachment 192 secured to struts 134 with fasteners 40 and a second pivotable attachment 194 secured to floor beams 30 with fasteners 40. In the illustrated example, first pivotable attachment 192 and second pivotable attachment 194 are joined together about pivot axis P via pivots, such as pins, that extend through first pivotable attachment 192 and second pivotable attachment 194.
[0042]
[0048] One feature of first pivotable attachment 192 is that it is secured to the double thickness of strut 134 using fasteners 40 that extend through both first channel 150A and second channel 150B. Furthermore, in the illustrated example, first channel 150A and second channel 150B are not mirror images of each other like first channel 50A and second channel 50B of strut 34. Rather, first channel 150A is shorter in length than second channel 150B, allowing second channel 150B to be attached to rib 26 using fasteners 42.
[0043]
[0049] As shown in FIGS. 6-7 , channels 150A and 150B include a continuous set of plies extending between opposing first and second ends 152A and 152B and 154A and 154B. Each of first and second channels 150A and 150B also includes a first web 160A and a second web 160B extending between first and second pairs 162A and 162B of spaced flanges, respectively, as a single unit. Each channel 150A and 150B may also include longitudinal segments, such as segments S-E, S-1, S-2, and S-3, that have a varying number of plies. The number of plies may be varied by adding additional plies to the base number of plies extending between the first and second ends 154A and 154B of channels 150A and 150B.
[0044]
[0050] 5-7, the first channel 150A and the second channel 150B may be secured to one another using mechanical fasteners in addition to the bond provided between the first channel 150A and the second channel 150B. In one embodiment, mechanical fasteners 70, such as bolts, may extend through the first web 160A and the second web 160B, as in the case of the strut 34. The first channel 150A and the second channel 150B may be secured to one another using a reinforcing plate 72 and fasteners 74, as described above with respect to the strut 34.
[0045]
[0051] The following provisions provide several exemplary configurations of the struts 34, 134 as shown in the drawings.
[0046]
[0052] Article 1. 1. An aircraft strut comprising: a first composite body defining a first channel having a first web extending between a first pair of spaced-apart flanges, the first composite body including a first plurality of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the first plurality of longitudinal segments; and a second composite body defining a second channel having a second web extending between a second pair of flanges, the second composite body including a second plurality of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the second plurality of longitudinal segments, the first composite body being fixed relative to the second composite body.
[0047]
[0053] Article 2. 2. The support column of claim 1, wherein the number of plies in each of the first plurality of longitudinal segments is symmetrical about a central longitudinal segment of the first plurality of longitudinal segments.
[0048]
[0054] Article 3. 3. The strut of claim 1 or 2, wherein the number of plies in each of the second plurality of longitudinal segments is symmetrical about a central longitudinal segment of the second plurality of longitudinal segments.
[0049]
[0055] Article 4. The strut of any one of clauses 1 to 3, including a plurality of fasteners extending through the first web and the second web.
[0050]
[0056] Article 5. A support column as described in any one of clauses 1 to 4, including a reinforcing plate attached to one of a first pair of the spaced apart flanges using a first fastener and a reinforcing plate attached to a corresponding one of a second pair of the spaced apart flanges using a second fastener.
[0051]
[0057] Article 6. 6. The strut of any one of clauses 1 to 5, wherein the first composite body is longitudinally offset from the second composite body.
[0052]
[0058]
[0059] Article 7. 7. The support of any one of clauses 1 to 6, wherein the first web includes a first mounting surface facing away from the first channel.
[0053]
[0060] Article 8. The support of any one of clauses 1 to 7, wherein the second web includes a second mounting surface facing away from the second channel.
[0054]
[0061] Article 9. 9. A strut as described in any one of clauses 1 to 8, including a pivotable connection having a first pivotable attachment fixed relative to the first composite body and the second composite body at a distal end of the strut, and a second pivotable attachment pivotally mounted to the first pivotable attachment about a pivotable axis.
[0055]
[0062] Article 10. A support column described in any one of clauses 1 to 9, wherein the first web and the first pair of spaced flanges are an integral structure having a C-shaped cross-section, and the first web includes a first surface facing the first channel and a second surface that at least partially engages with the second composite body.
[0056]
[0063] Article 11. A support column according to any one of clauses 1 to 10, wherein the second web and the second pair of spaced flanges are a unitary structure having a C-shaped cross-section, and the second web includes a first surface facing the second channel and a second surface that engages with the first composite body.
[0057]
[0064] Article 12. 12. The strut of any one of clauses 1 to 11, wherein the first composite body is bonded to the second composite body.
[0058]
[0065] Article 13. a fuselage segment including a plurality of circumferentially extending ribs, a plurality of longitudinally extending stringers engaging the plurality of ribs, a plurality of floor beams extending laterally between corresponding segments of the plurality of ribs, and a plurality of struts extending between one of the plurality of floor beams and a corresponding one of the plurality of ribs, each of the plurality of struts defining a first channel having a first web extending between a first pair of spaced flanges; a first composite body including a first plurality of longitudinal segments, each longitudinal segment including a first plurality of longitudinal segments; a first composite body having a number of plies that varies between adjacent longitudinal segments of the plurality of longitudinal segments; and a second composite body defining a second channel having a second web extending between a second pair of flanges, the second composite body including a second plurality of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the second plurality of longitudinal segments, the first composite body being fixed relative to the second composite body.
[0059]
[0066] Article 14. 14. The fuselage segment of claim 13, wherein the number of plies in each of the first plurality of longitudinal segments is symmetrical about a central longitudinal segment of the first plurality of longitudinal segments, and the number of plies in each of the second plurality of longitudinal segments is symmetrical about a central longitudinal segment of the second plurality of longitudinal segments.
[0060]
[0067] Article 15. 15. The fuselage segment of clause 13 or 14, including a reinforcing plate attached to one of a first pair of the spaced apart flanges with a first fastener and attached to a corresponding one of a second pair of the spaced apart flanges with a second fastener.
[0061]
[0068] Article 16. 16. The fuselage segment of any one of clauses 13 to 15, including a pivotable connection having a first pivotable attachment fixed relative to the first composite body and the second composite body at the distal ends of the plurality of struts, and a second pivotable attachment pivotally mounted to the first pivotable attachment about a pivotable axis.
[0062]
[0069] Article 17. 17. The fuselage segment of any one of clauses 13 to 16, wherein the first web and the first pair of spaced apart flanges are a unitary structure having a C-shaped cross-section, the first web including a first surface facing the first channel and a second surface that at least partially engages the second composite body, and the second web and the second pair of spaced apart flanges are a unitary structure having a C-shaped cross-section, the second web including a first surface facing the second channel and a second surface that engages the first composite body.
[0063]
[0070] Article 18. A floor assembly for an aircraft, comprising: a floor panel; at least one floor beam supporting the floor panel; at least one rib supporting an opposite end of the floor panel; and at least one strut extending between the at least one floor beam and the at least one rib, the at least one strut comprising a first composite body defining a first channel having a first web extending between a first pair of spaced flanges, the first composite body comprising a first plurality of longitudinal segments, each longitudinal segment having a first plurality of longitudinal segments extending from the first plurality of longitudinal segments. 1. A floor assembly comprising: a first composite body having a number of plies that varies between adjacent longitudinal segments of a second plurality of longitudinal segments; and a second composite body defining a second channel having a second web extending between a second pair of flanges, the second composite body comprising a second plurality of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the second plurality of longitudinal segments, the first composite body being fixed relative to the second composite body.
[0064]
[0071] Article 19. 19. A floor assembly as described in clause 18, wherein the number of plies in each of the first plurality of longitudinal segments is symmetrical around a central longitudinal segment of the first plurality of longitudinal segments, and the number of plies in each of the second plurality of longitudinal segments is symmetrical around a central longitudinal segment of the second plurality of longitudinal segments.
[0065]
[0072] Article 20. 20. A floor assembly as described in clause 18 or 19, wherein the first web and the first pair of spaced flanges are a unitary structure having a C-shaped cross-section, the first web including a first surface facing the first channel and a second surface that at least partially engages the second composite body, and the second web and the second pair of spaced flanges are a unitary structure having a C-shaped cross-section, the second web including a first surface facing the second channel and a second surface that engages the first composite body.
[0066]
[0073] The terms "comprising," "including," and "having" are inclusive and thus specify the presence of stated features, integers, steps, operations, elements, or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, or components. The order of steps, processes, and operations may be varied where possible, and additional or alternative steps may be employed. As used herein, the term "or" includes any combination of the associated listed items. The term "any of" is understood to include all possible combinations of the referenced items, including "any one of" the referenced items. The term "any of" is understood to include all possible combinations of the referenced claims, including "any one of" the referenced claims of the appended claims.
[0067]
[0074] For consistency and convenience, directional adjectives may be employed throughout this detailed description that correspond to the illustrated embodiments. Those skilled in the art will recognize that terms such as "upper," "lower," "upward," "downward," "top," "bottom," and the like may be used descriptively with respect to the figures without representing a limitation on the scope of the invention as defined by the claims.
Claims
1. A strut (34, 134) for an aircraft, comprising: a first composite body (150A, 150B, 50A, 50B) defining a first channel (150A, 150B, 50A, 50B) having a first web (160A, 160B, 60A, 60B) extending between a first pair of spaced flanges (162A, 162B, 62A, 62B), the first composite body including a first plurality of longitudinal segments S, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the first plurality of longitudinal segments; a second composite body (150A, 150B, 50A, 50B) defining a second channel (150A, 150B, 50A, 50B) having a second web (160A, 160B, 60A, 60B) extending between a second pair of flanges (162A, 162B, 62A, 62B), the second composite body including a second plurality of longitudinal segments S, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the second plurality of longitudinal segments, and the first composite body comprising a strut (34, 134) fixed relative to the second composite body.
2. The strut (34, 134) of claim 1, wherein the number of plies in each of the first plurality of longitudinal segments S is symmetrical about a central longitudinal segment of the first plurality of longitudinal segments.
3. The strut (34, 134) of claim 1, wherein the number of plies in each of the second plurality of longitudinal segments S is symmetrical about a central longitudinal segment of the second plurality of longitudinal segments S.
4. The strut (34, 134) of claim 1, including a plurality of fasteners (70) extending through said first web and said second web (160A, 160B, 60A, 60B).
5. 2. The support (34, 134) of claim 1, including a reinforcing plate (72) attached to one of the first pair of spaced apart walls with a first fastener and a reinforcing plate (72) attached to a corresponding one of the second pair of walls with a second fastener.
6. The strut (34, 134) of claim 1, wherein said first composite body is longitudinally offset from said second composite body.
7. The strut (34, 134) of claim 6, wherein the first web includes a first attachment surface facing away from the first channel (150A, 150B, 50A, 50B).
8. The strut (34, 134) of claim 6, wherein the second web (160A, 160B, 60A, 60B) includes a second attachment surface facing away from the second channel (150A, 150B, 50A, 50B).
9. 2. The strut (34, 134) of claim 1, comprising a pivotable connection (190) having a first pivotable attachment (192) fixed relative to the first composite body and the second composite body at a distal end of the strut (34, 134), and a second pivotable attachment (194) pivotally mounted to the first pivotable attachment (192) about a pivotable axis.
10. 2. The strut (34, 134) of claim 1, wherein the first web and the first pair of opposing walls are a unitary structure having a C-shaped cross-section, the first web including a first surface facing the first channel (150A, 150B, 50A, 50B) and a second surface at least partially engaging the second composite body.
11. 11. The strut (34, 134) of claim 10, wherein the second web (160A, 160B, 60A, 60B) and the second pair of opposite side walls are of a unitary structure having a C-shaped cross-section, the second web (160A, 160B, 60A, 60B) including a first surface facing the second channel (150A, 150B, 50A, 50B) and a second surface engaging the first composite body.
12. The strut (34, 134) of claim 1, wherein the first composite body is bonded to the second composite body.
13. A fuselage (20) segment, comprising: a plurality of circumferentially extending ribs (26); a plurality of stringers (28) extending longitudinally and engaging the plurality of ribs (26); a plurality of floor beams (30) extending laterally between corresponding segments of said plurality of ribs (26); a plurality of struts (34) extending between one of the plurality of floor beams (30) and a corresponding one of the plurality of ribs (26), each of the plurality of struts (34) comprising: a first composite body (150A, 150B, 50A, 50B) defining a first channel (150A, 150B, 50A, 50B) having a first web extending between a first pair of spaced flanges (162A, 162B, 62A, 62B), the first composite body including a first plurality of longitudinal segments S, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the first plurality of longitudinal segments; a second composite body (150A, 150B, 50A, 50B) defining a second channel (150A, 150B, 50A, 50B) having a second web (160A, 160B, 60A, 60B) extending between a second pair of flanges (162A, 162B, 62A, 62B), the second composite body including a second plurality of longitudinal segments S, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the second plurality of longitudinal segments, and the first composite body being fixed relative to the second composite body.
14. 14. The fuselage (20) segment of claim 13, wherein the number of plies in each of the first plurality of longitudinal segments S is symmetric about a central longitudinal segment of the first plurality of longitudinal segments, and the number of plies in each of the second plurality of longitudinal segments is symmetric about a central longitudinal segment of the second plurality of longitudinal segments.
15. 14. The fuselage (20) segment of claim 13, including a reinforcing plate (72) attached to one of the first pair of spaced apart walls with a first fastener and a reinforcing plate (72) attached to a corresponding one of the second pair of walls with a second fastener.
16. 14. The fuselage (20) segment of claim 13, including a pivotable connection (190) having a first pivotable attachment (192) fixed relative to the first composite body and the second composite body at a distal end of the plurality of struts (34), and a second pivotable attachment (194) pivotally mounted to the first pivotable attachment (192) about a pivotable axis.
17. the first web and the first pair of opposing walls are a unitary structure having a C-shaped cross section, the first web including a first surface facing the first channel (150A, 150B, 50A, 50B) and a second surface at least partially engaging the second composite body; 14. The fuselage (20) segment of claim 13, wherein the second web (160A, 160B, 60A, 60B) and the second pair of opposite side walls are of a unitary structure having a C-shaped cross-section, the second web (160A, 160B, 60A, 60B) including a first surface facing the second channel (150A, 150B, 50A, 50B) and a second surface engaging the first composite body.
18. 1. A floor assembly for an aircraft, comprising: a floor panel (36); At least one floor beam (30) supporting said floor panel; At least one rib (26) supporting both side edges of the floor panel; and at least one support column (34, 134) extending between the at least one floor beam (30) and the at least one rib (26), the at least one support column (34, 134) comprising: a first composite body (150A, 150B, 50A, 50B) defining a first channel (150A, 150B, 50A, 50B) having a first web extending between a first pair of spaced flanges (162A, 162B, 62A, 62B), the first composite body including a first plurality of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the first plurality of longitudinal segments; and 1. A floor assembly comprising: a second composite body (150A, 150B, 50A, 50B) defining a second channel (150A, 150B, 50A, 50B) having a second web (160A, 160B, 60A, 60B) extending between a second pair of flanges (162A, 162B, 62A, 62B), the second composite body including a second plurality of longitudinal segments, each longitudinal segment having a number of plies that varies between adjacent longitudinal segments of the second plurality of longitudinal segments, the first composite body being fixed relative to the second composite body.
19. 20. The floor assembly of claim 18, wherein the number of plies in each of the first plurality of longitudinal segments S is symmetrical about a central longitudinal segment of the first plurality of longitudinal segments, and the number of plies in each of the second plurality of longitudinal segments is symmetrical about a central longitudinal segment of the second plurality of longitudinal segments.
20. the first web and the first pair of opposing walls are a unitary structure having a C-shaped cross section, the first web including a first surface facing the first channel (150A, 150B, 50A, 50B) and a second surface at least partially engaging the second composite body; 19. The floor assembly of claim 18, wherein the second web (160A, 160B, 60A, 60B) and the second pair of opposite side walls are a unitary structure having a C-shaped cross-section, the second web (160A, 160B, 60A, 60B) including a first surface facing the second channel (150A, 150B, 50A, 50B) and a second surface engaging the first composite body.