An aircraft cabin floor stand

Abstract

The application provides an aircraft passenger cabin floor stand column for supporting a large civil aircraft passenger cabin floor, and belongs to the technical field of anti-collision energy-absorbing structure manufacturing. The aircraft passenger cabin floor stand column is an I-shaped stand column with an I-shaped cross section, which comprises a web and flanges symmetrically arranged on both sides of the web; the length direction of the web and the flanges is parallel; the upper end of the I-shaped stand column is an upper connecting section, and the lower end is a lower connecting section; the part of the I-shaped stand column between the upper connecting section and the lower connecting section is an energy-absorbing section; the energy-absorbing section is designed by cutting. The web and the flanges of the energy-absorbing section of the I-shaped stand column are designed by cutting in different forms, which is more conducive to guiding the I-shaped stand column to gradually deform in stages under a crushing load, and can maximize the reduction of the structure weight and the use of aviation fuel while ensuring that the stand column structure deforms in stages and gradually absorbs a large amount of crash energy.

Description

Technical Field

[0001] This invention provides an aircraft cabin floor support column for supporting the cabin floor of a large civil aircraft, belonging to the field of anti-collision and energy-absorbing structure manufacturing technology. Background Technology

[0002] As a key component in aircraft, providing support and protection during crashes, the cabin floor pillars of large civil aircraft are typically connected to the cabin floor beams and fuselage frame via a fixed connection structure. During flight, the cabin floor pillars support the main weight of the cabin without increasing their own overall mass. During a crash, the cabin floor pillars absorb the main energy, converting the kinetic energy of the impact into localized plastic deformation energy, minimizing damage to people and property.

[0003] The structural design of large civil aircraft needs to address issues such as rapid landings and crashes, as these problems can seriously threaten personal safety and cause damage to cargo and property. The failure and energy absorption characteristics of the cabin floor pillars of large civil aircraft under impact conditions are key to a deeper understanding of the crashworthiness or crashworthiness of aircraft structures.

[0004] The following indicators are typically used to evaluate the design performance of the cabin pillars of large civil aircraft:

[0005] 1. Do not weaken the initial peak load to ensure that it can support the aircraft cabin floor during normal flight;

[0006] 2. Without increasing the overall mass of the column, to meet the overall lightweight design requirements of the aircraft;

[0007] 3. It has high energy absorption performance and stable deformation mode to ensure that the aircraft minimizes the damage to the human body when subjected to impact loads.

[0008] In addition to the above standards, practical requirements must also be met, such as a simple manufacturing process, no welding process, and the ability to ensure the stability of the structure.

[0009] The common structure of large civil aircraft cabin floor pillars is a metal pillar with a C-shaped or rolled C-shaped cross section. Its initial structure provides the necessary support for the aircraft cabin floor, and the pillar structure deforms during the impact process to absorb and dissipate the impact energy.

[0010] The current structure of traditional cabin floor pillars can meet the basic requirements of aircraft during normal flight, such as supporting the cabin floor and meeting the requirements of lightweight aircraft design. However, it is difficult to meet the energy absorption performance requirements of aircraft during crash impacts, for the following reasons:

[0011] Current aircraft cabin floor pillars have poor energy absorption and unstable deformation processes when subjected to impact, failing to provide reliable safety for the human body.

[0012] Since most existing passenger aircraft cabin floor supports are slender structures with C-shaped or rolled-edge C-shaped cross sections, although they can provide a certain degree of support strength for the cabin floor, they are extremely unstable under impact loads (because when the slender structure is subjected to pressure loads and the pressure load reaches a certain value, the slender structure will suddenly bend at a certain position, causing the overall structure to be destroyed), and have poor energy absorption effect, the actual demand for cabin floor supports is affected.

[0013] Therefore, it is necessary to propose a column structure that is highly designable, has a reasonable processing cost, and has good energy absorption performance. In addition to providing support for the cabin floor, it should be able to absorb more impact energy during the aircraft crash, thus ensuring the safety of people and property. Summary of the Invention

[0014] The purpose of this invention is to solve the problems existing in the prior art and provide an aircraft cabin floor support column for supporting the aircraft cabin floor. While reducing its own overall weight, it strengthens the support of the cabin floor and can significantly improve energy absorption performance, thus providing more reliable safety for large civil aircraft.

[0015] This invention is achieved through the following technical solution:

[0016] The present invention provides an aircraft cabin floor support column, wherein the aircraft cabin floor support column is an I-shaped support column with an I-shaped cross-section, comprising: a web and flanges symmetrically arranged on both sides of the web; the web and the flanges are parallel in length direction;

[0017] The upper end of the I-shaped column is the upper connecting section, and the lower end is the lower connecting section; the part of the I-shaped column located between the upper connecting section and the lower connecting section is the energy absorption section;

[0018] The energy absorption section has a cut-out design.

[0019] A further improvement of the present invention is that:

[0020] The portion of the web between the upper connecting section and the lower connecting section is the web energy absorption section.

[0021] The energy absorption section of the web plate has a cutting design, that is, weight reduction holes are opened in the energy absorption section of the web plate.

[0022] Preferably, the weight-reducing hole includes: an elongated hole, a narrow hole, a circular hole, or a rectangular hole.

[0023] A further improvement of the present invention is that:

[0024] The portion of each flange located between the upper connecting section and the lower connecting section is the flange energy absorption section;

[0025] There is a trimmed design on the energy absorption section of each flange, that is, a trimmed part is provided on the energy absorption section of each flange.

[0026] Preferably, the cutting section includes: a U-shaped cutting section, a stepped cutting section, a semi-circular cutting section, or a triangular cutting section.

[0027] A further improvement of the present invention is that:

[0028] Multiple elongated holes are opened in the upper part of the energy absorption section of the web plate, and elongated holes are opened in the lower part of the energy absorption section of the web plate.

[0029] A U-shaped cutout is provided on one side of the lower part of the energy absorption section of each flange, and a triangular cutout is provided on the other side;

[0030] The shape and size of the energy absorption sections of the two flanges are exactly the same, and the U-shaped cutouts on the two flanges are opposite to each other, as are the triangular cutouts on the two flanges.

[0031] A further improvement of the present invention is that:

[0032] A narrow hole is provided at the lower part of the energy absorption section of the web plate.

[0033] A stepped cutout is provided on one side of the lower part of the rim energy absorption section of each rim;

[0034] The shape and size of the energy absorption sections of the two flanges are exactly the same, and the stepped cut-out sections on the two flanges are opposite each other.

[0035] A further improvement of the present invention is that:

[0036] Multiple elongated holes are opened in the upper part of the energy absorption section of the web plate, and elongated holes are opened in the lower part of the energy absorption section of the web plate.

[0037] A triangular cutout is provided on one side of the lower part of the energy absorption section of each flange, and a semi-circular cutout is provided on the other side.

[0038] The shape and size of the energy absorption sections of the two flanges are exactly the same, and the triangular cutouts on the two flanges are opposite each other, as are the semi-circular cutouts on the two flanges.

[0039] Compared with the prior art, the beneficial effects of the present invention are:

[0040] This invention utilizes aerospace-grade metal materials to create an I-shaped column. Through rational design and optimization, the web of the energy-absorbing section of the I-shaped column is cut in different ways along with the flanges. This facilitates the gradual deformation of the I-shaped column under crushing loads, ensuring that the column structure undergoes gradual deformation and absorbs significant impact energy while minimizing structural weight and aviation fuel consumption. Furthermore, this invention eliminates the need for modifications to the existing cabin floor connection structure.

[0041] Attached figures and their descriptions

[0042] Figure 1 This is a schematic diagram of the structure connecting the aircraft cabin floor columns, the aircraft cabin floor beams, and the cabin fuselage frame according to the present invention.

[0043] Figure 2(a) is a schematic diagram of the structure of the I-shaped column after it has been formed according to Embodiment 1 of the present invention.

[0044] Figure 2(b) is a schematic diagram of the web of the I-shaped column in Embodiment 1 of the present invention.

[0045] Figure 2(c) is a schematic diagram of the structure of the two flanges in the I-shaped column of Embodiment 1 of the present invention.

[0046] Figure 2(d) is a top view of the I-shaped column of Embodiment 1 of the present invention.

[0047] Figure 3(a) is a schematic diagram of the structure of the I-shaped column after it has been formed according to Embodiment 2 of the present invention.

[0048] Figure 3(b) is a schematic diagram of the web of the I-shaped column in Embodiment 2 of the present invention.

[0049] Figure 3(c) is a schematic diagram of the structure of the two flanges in the I-shaped column of Embodiment 2 of the present invention.

[0050] Figure 3(d) is a top view of the I-shaped column of Embodiment 2 of the present invention.

[0051] Figure 4(a) is a schematic diagram of the structure of the I-shaped column after it has been formed according to Embodiment 3 of the present invention.

[0052] Figure 4(b) is a schematic diagram of the web of the I-shaped column in Embodiment 3 of the present invention.

[0053] Figure 4(c) is a schematic diagram of the structure of the two flanges in the I-shaped column of Embodiment 3 of the present invention.

[0054] Figure 4(d) is a top view of the I-shaped column of Embodiment 3 of the present invention.

[0055] Figure 5This is a schematic diagram comparing the load-displacement curves of the I-shaped column in Embodiment 1 of the present invention with those of a traditional cabin floor column structure.

[0056] Figure 6 This is a schematic diagram comparing the load-displacement curves of the I-shaped column in Embodiment 2 of the present invention with those of a traditional cabin floor column structure.

[0057] Figure 7 This is a schematic diagram comparing the load-displacement curves of the I-shaped column in Embodiment 3 of the present invention with those of a traditional cabin floor column structure. Detailed Implementation

[0058] The present invention will now be described in further detail with reference to the accompanying drawings:

[0059] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. In addition, the forms of the various structures described in the following embodiments are merely illustrative. The aircraft cabin floor support structure involved in the present invention is not limited to the structures described in the following embodiments. All other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0060] To better meet the requirements of large civil aircraft cabin floor pillars in aircraft design, and to improve the energy absorption capacity of aircraft cabin floor pillars without reducing the overall weight of the pillar structure or diminishing its supporting effect on the cabin floor, this invention provides an aircraft cabin floor pillar with high energy absorption performance and stable deformation process. The aircraft cabin floor pillar is an I-shaped pillar with an I-beam cross-section, comprising a web and two flanges symmetrically arranged on both sides of the web, with the web and flanges parallel in their length directions. The upper end of the I-shaped pillar is an upper connecting section 2, which can be connected to the aircraft cabin floor beam 1 by mechanical connection methods such as bolts or riveting. The lower end of the I-shaped pillar is a lower connecting section 3, which can be connected to the cabin fuselage frame 4 by mechanical connection methods such as bolts or riveting. The portion of the I-shaped pillar located between the upper connecting section 2 and the lower connecting section 3 is an energy absorption section 101, which has a tailored design.

[0061] Specifically, the portion of the web between the upper connecting section 2 and the lower connecting section 3 is the web energy-absorbing section, and the portion of the two flanges between the upper connecting section 2 and the lower connecting section 3 is the flange energy-absorbing section. Cutting designs are incorporated into both the web and flange energy-absorbing sections. These cutting designs refer to the presence of weight-reducing holes in the web energy-absorbing sections and different shaped and sized cut-out portions in the flange energy-absorbing sections of each flange. For example, weight-reducing holes of different shapes, such as elongated holes, slender holes, circular holes, and rectangular holes, can be introduced at different locations in the web energy-absorbing sections. Cut-out portions of different shapes, such as U-shaped cut-out portions, stepped cut-out portions, and semi-circular and triangular cut-out portions, can be introduced at different locations in the two flange energy-absorbing sections.

[0062] The portions of the two flanges and the web located at the upper connecting section 2 and the lower connecting section 3 serve only as connections and are not subject to trimming design. The specific shape of these portions can be designed according to actual needs. In the embodiments shown in Figures 2 to 4, the portions of the two flanges located at the upper connecting section 2 are triangular in shape, and the portions of the web located at the upper connecting section 2 are rectangular in shape. The portions of the two flanges located at the lower connecting section 3 are triangular in shape, and the portions of the web located at the lower connecting section 3 are trapezoidal in shape.

[0063] This invention creates column structures of different shapes by cutting and designing the two flanges and web of the column. This reduces the mass of the cabin floor column while still providing support for the cabin floor, and ensures that the column structure can undergo stable and gradual deformation and absorb more energy under crushing load.

[0064] The specific embodiments of the present invention are described in detail below with reference to the technical solutions and accompanying drawings.

[0065] Example 1:

[0066] like Figures 2(a) to 2(d) As shown, the aircraft cabin floor support column provided in this embodiment includes: a web plate 5 and flanges 6 symmetrically arranged on both sides of the web plate 5. Multiple elongated holes 501 are opened in the upper part of the energy absorption section of the web plate 5 of the I-shaped column, and elongated holes 502 are opened in the lower part of the energy absorption section of the web plate 5. Both the elongated holes 501 and the elongated holes 502 are weight reduction holes, and the width of the elongated holes is smaller than the width of the elongated holes. At the same time, a U-shaped cutting part 601 is provided on one side of the lower part of the energy absorption section of each flange 6, and a triangular cutting part 602 is provided on the other side. That is, material is removed from both sides of the lower part of the energy absorption section of each flange 6, thereby cutting out a U-shaped notch and a triangular notch.

[0067] Figure 2(b) shows the shape after elongated holes and strip holes are opened on the energy absorption section of the web 5. Figure 2(c) shows the shape after introducing U-shaped and triangular cut-out sections on the energy absorption sections of the two flanges. The size, position, and shape of the U-shaped and triangular cut-out sections on the two flanges are kept the same, that is, the shape and size of the energy absorption sections of the two flanges after the cut-out design are completely identical. When the two flanges are symmetrically arranged on both sides of the web, the U-shaped cut-out sections on the two flanges are opposite each other, and the triangular cut-out sections on the two flanges are opposite each other. Figure 2(d) shows a top view of the aircraft cabin floor pillar. In actual production, the two flanges and the web with the cut-out design can be processed into the aircraft cabin floor pillar shown in Figure 2(a) by forging and other processing techniques.

[0068] Example 2:

[0069] like Figures 3(a) to 3(d) As shown, the aircraft cabin floor support column provided in this embodiment includes: a web 7 and flanges 8 symmetrically arranged on both sides of the web 7. An elongated hole 701 is formed in the lower part of the web energy-absorbing section of the web 7. Simultaneously, a stepped cut section 801 is provided on one side of the lower part of the flange energy-absorbing section of each flange 8. That is, material is removed from one side of the lower part of the flange energy-absorbing section of each flange 8, thereby cutting out a stepped notch. The size, position, and shape of the stepped cut sections on the two flanges are kept identical, meaning that the shape and size of the flange energy-absorbing sections of the two flanges are completely identical after the introduction of the cut design. When the two flanges are symmetrically arranged on both sides of the web, the stepped cut sections on the two flanges face each other.

[0070] This embodiment employs a forging process, meaning the column structure is integrally formed from the trimmed flanges and web. The I-beam column adopts an integrated design concept, incorporating different geometric trimming designs in the two flanges and web. Figure 3(b) shows an elongated hole 701 in the lower part of the web 7. Figure 3(c) shows a stepped trimming section 801 formed after material removal from one side of the lower part of the two flanges. The dimensions and shape of the stepped trimming section 801 on the two flanges do not need to be identical. Figure 3(d) shows a top view of the aircraft cabin floor column. The aircraft cabin floor column shown in Figure 3(a) can be formed by integrally molding the trimmed flanges and web.

[0071] Example 3:

[0072] like Figures 4(a) to 4(d)As shown, the aircraft cabin floor support column provided in this embodiment includes: a web plate 9 and flanges 10 symmetrically arranged on both sides of the web plate 9. Multiple elongated holes 901 are formed in the upper part of the web plate energy absorption section of the web plate 9, and elongated holes 902 are formed in the lower part of the web plate energy absorption section of the web plate 9. Simultaneously, a triangular cutting portion 1001 is provided on one side of the lower part of the flange energy absorption section of the two flanges 10, and a semi-circular cutting portion 1002 is provided on the other side. That is, material is removed from both sides of the lower part of the flange energy absorption section of each flange 6, thereby cutting out a triangular notch and a semi-circular notch.

[0073] Figure 4(b) shows the shape of the web after incorporating the elongated and slender hole cut-out design. Figure 4(c) shows the shape of the two flanges after incorporating the triangular and semi-circular cut-out design. The dimensions, positions, and shapes of the triangular and semi-circular cut-out portions on the two flanges remain identical; that is, the shape and dimensions of the flange energy-absorbing sections of the two flanges are completely identical after incorporating the cut-out design. When the two flanges are symmetrically arranged on both sides of the web, the triangular cut-out portions on the two flanges face each other, and the semi-circular cut-out portions on the two flanges face each other. Figure 4(d) shows a top view of the aircraft cabin floor pillar. The aircraft cabin floor pillar shown in Figure 4(a) can be formed by integrally molding the two flanges and web after the cut-out design.

[0074] This embodiment is produced using a forging process, meaning that the column structure is integrally formed from the flanges and webs after the design shape has been cut.

[0075] In actual production, the cutting design can be introduced into the two flanges and the web through machining, or the aircraft cabin floor pillars can be integrally formed through additive manufacturing, as detailed below:

[0076] In terms of manufacturing process, the aircraft cabin floor pillars of this invention mainly utilize integral forging technology. First, forging dies with different cutting designs are manufactured. Then, an extrusion molding process is used to obtain aircraft cabin floor pillar structures with corresponding cutting designs. In industrial production, this method is low-cost, highly efficient, suitable for mass production, and produces structures with stable performance.

[0077] Based on its strong design flexibility, the second processing method for the aircraft cabin floor pillars of this invention is as follows: using CNC machining, different shapes are introduced for cutting and processing according to the designed structure of the aircraft cabin floor pillars, and finally formed.

[0078] The third processing method for the aircraft cabin floor pillars of this invention is to use a more advanced additive manufacturing technology to lay up metal powder. However, this technology is not mature enough at present, and the cost is high and the time required is long.

[0079] The fourth processing method for the aircraft cabin floor pillar of this invention is as follows: The web and two flanges of the aircraft cabin floor pillar are respectively subjected to different cutting designs using machining processes. The web, after being processed with the cutting design shapes, is then welded to the two flanges to finally obtain the desired aircraft cabin floor pillar. It should be noted that while the aircraft cabin floor pillar of this invention can be obtained through welding, welding is currently not used in the aviation field due to its poor processing stability.

[0080] Figure 5 , Figure 6 , Figure 7 Performance comparison charts are provided for the aircraft cabin floor supports in Examples 1, 2, and 3, and for traditional aircraft cabin floor supports. From... Figure 5 , Figure 6 , Figure 7 It can be seen that the peak load of the aircraft cabin floor support column after the introduction of the trimmed design is slightly higher or almost unchanged than that of the traditional cabin floor support column, indicating that the supporting effect of the cabin floor after the introduction of the trimmed design is not weakened. In addition, the average load of the aircraft cabin floor support column after the introduction of the trimmed design during the failure process is significantly increased compared with the traditional cabin floor support column. Therefore, the present invention greatly improves the energy absorption effect of the traditional cabin floor support column during the failure process.

[0081] For a more intuitive understanding, Table 1 presents a comparison of the peak force, energy absorption level, and mass of Embodiments 1 to 3 after incorporating a tailored design, without altering the overall structural mass, with those of traditional cabin floor columns.

[0082]

[0083] Table 1

[0084] As can be seen from the peak forces in Table 1, the peak forces of the column structures in the three embodiments of the present invention are slightly higher than those of the traditional cabin floor column structures, or almost the same as those of the initial cabin floor column. As can be seen from the energy absorption in Table 1, the column structures in the three embodiments of the present invention have a significantly higher energy absorption rate than the traditional cabin floor column structures, with the maximum energy absorption level being 9 times higher. Furthermore, as can be seen from the mass in Table 1, the overall mass of the column structure of the present invention does not change significantly and remains consistent with the mass of a traditional column.

[0085] When subjected to load, the present invention initiates progressive crushing deformation from the introduction position of the cut-out portion on both flanges. During the progressive crushing deformation process, the device of the present invention can generate more plastic deformation in the deformation location area, absorb more energy, and thus greatly improve the energy absorption performance.

[0086] This invention utilizes aerospace-grade metal materials to create I-shaped columns. Through rational design and optimization, different forms of trimming are applied to the web and flanges in the non-connected areas of the aircraft cabin floor columns. This removes excess material, reducing the weight of the cabin floor columns while fulfilling their structural functions and meeting the requirements for support and high average force distribution. Furthermore, the trimming design of this invention facilitates cutting and processing. The entire structure can be formed by integral forging followed by cutting, simplifying the manufacturing process, significantly reducing processing costs, and improving processing precision. The aircraft cabin floor support column of this invention can meet the actual needs of large civil aircraft. In the event of a crash, the cut-out design on the aircraft cabin floor support column makes it easier to guide the column to undergo progressive deformation under crushing load, that is, it can undergo progressive crushing deformation with better energy absorption performance, rather than the buckling deformation of traditional aircraft cabin floor support columns. While ensuring that the column structure undergoes progressive deformation and absorbs a large amount of crash energy, it can minimize the structural weight and reduce the use of aviation fuel. Moreover, this invention is based on the existing aircraft cabin floor connection structure and is an improved design, so there is no need to modify the original cabin floor connection structure.

[0087] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0088] In the description of this invention, unless otherwise stated, the terms "upper," "lower," "left," "right," "inner," "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0089] The above technical solution is only one embodiment of the present invention. For those skilled in the art, based on the principles disclosed in the present invention, it is easy to make various types of improvements or modifications, and not limited to the technical solutions described in the specific embodiments of the present invention. Therefore, the foregoing description is only a preferred option and is not restrictive.

Claims

1. A type of aircraft cabin floor support column, characterized in that: The aircraft cabin floor support column is an I-shaped support column with an I-shaped cross-section, which includes: a web and flanges symmetrically arranged on both sides of the web; the web and flanges are parallel in length direction; The upper end of the I-shaped column is the upper connecting section, and the lower end is the lower connecting section; the part of the I-shaped column located between the upper connecting section and the lower connecting section is the energy absorption section; The energy absorption section has a trimmed design; The portion of the web plate located between the upper connecting section and the lower connecting section is the web plate energy absorption section; the web plate energy absorption section has a cutting design, that is, weight reduction holes are opened in the web plate energy absorption section; The portion of each flange located between the upper connecting section and the lower connecting section is the flange energy absorption section; Each flange has a trimmed design on its flange energy absorption section, that is, a trimmed part is provided on one side of the lower part of the flange energy absorption section of each flange, and a trimmed part is provided on the other side; the shape and size of the flange energy absorption sections of the two flanges are exactly the same, and the trimmed parts on one side of the two flanges are opposite to each other, and the trimmed parts on the other side are opposite to each other. The cutting design on the web energy absorption section and the flange energy absorption section is used to guide the I-shaped column to undergo gradual deformation under crushing load.

2. The aircraft cabin floor support column according to claim 1, characterized in that: The weight-reducing holes include: elongated holes or circular holes.

3. The aircraft cabin floor support column according to claim 1, characterized in that: The weight-reducing holes include elongated holes.

4. The aircraft cabin floor support column according to claim 1, characterized in that: The weight-reducing hole includes a rectangular hole.

5. The aircraft cabin floor support column according to claim 1, characterized in that: The cutting section includes: a U-shaped cutting section, a stepped cutting section, a semi-circular cutting section, or a triangular cutting section.

6. The aircraft cabin floor support column according to claim 1, characterized in that: Multiple elongated holes are opened in the upper part of the energy absorption section of the web plate, and elongated holes are opened in the lower part of the energy absorption section of the web plate. A U-shaped cutout is provided on one side of the lower part of the energy absorption section of each flange, and a triangular cutout is provided on the other side; The shape and size of the energy absorption sections of the two flanges are exactly the same, and the U-shaped cutouts on the two flanges are opposite to each other, as are the triangular cutouts on the two flanges.

7. The aircraft cabin floor support column according to claim 1, characterized in that: A narrow hole is provided at the lower part of the energy absorption section of the web plate. A stepped cutout is provided on one side of the lower part of the rim energy absorption section of each rim; The shape and size of the energy absorption sections of the two flanges are exactly the same, and the stepped cut-out sections on the two flanges are opposite each other.

8. The aircraft cabin floor support column according to claim 1, characterized in that: Multiple elongated holes are opened in the upper part of the energy absorption section of the web plate, and elongated holes are opened in the lower part of the energy absorption section of the web plate. A triangular cutout is provided on one side of the lower part of the energy absorption section of each flange, and a semi-circular cutout is provided on the other side. The shape and size of the energy absorption sections of the two flanges are exactly the same, and the triangular cutouts on the two flanges are opposite each other, as are the semi-circular cutouts on the two flanges.

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