Energy-absorbing columns for aircraft

Abstract

An energy-absorbing column for aircraft significantly improves energy absorption performance and enhances resistance to defect sensitivity. The energy-absorbing column for aircraft of the present invention has a C-shaped projection along its height direction and includes a web extending along the height direction and flanges bending from both sides of the web along its width direction. Three or more web creases are formed on the web, spaced apart along the height direction and extending along the width direction. A flange crease is formed on each flange, extending linearly from near the end of the web crease closest to the side in the height direction toward the other side of the height direction and away from the web.

Description

Technical Field

[0001] This invention relates to the field of aircraft design and manufacturing, and in particular to energy-absorbing columns for aircraft. Background Technology

[0002] Columns are typically installed under the floor of an aircraft cargo hold. These columns absorb the kinetic energy of the crash by deforming their own structure during an aircraft crash, thus maximizing the protection of lives and minimizing economic losses. Therefore, their energy absorption performance has received widespread attention and is a key area of ​​research.

[0003] Traditional columns are typically made of C-shaped metal profiles, which have low energy absorption performance during aircraft crashes. In particular, when the column contains minor defects in the manufacturing, transportation, and installation processes, it will inevitably undergo overall buckling deformation, leading to a further significant reduction in energy absorption performance. Summary of the Invention

[0004] The present invention was made in view of the above-mentioned problems, and its purpose is to provide an energy-absorbing column for aircraft that helps to significantly improve energy absorption performance and improve resistance to defects.

[0005] To achieve the above objectives, the present invention provides an energy-absorbing column for an aircraft, the projection of the energy-absorbing column along the height direction being C-shaped, and including a web extending along the height direction and flanges bending from both sides of the web in the width direction of the energy-absorbing column, wherein three or more web creases are formed on the web, the multiple web creases are spaced apart along the height direction and extend along the width direction respectively, and a flange crease is formed on each of the flanges, the flange crease extending linearly from near the end of the web crease closest to the side in the height direction toward the other side in the height direction and away from the web.

[0006] According to the present invention, the energy-absorbing column for aircraft, when compressed in the height direction, forms an initial static plastic strand at the web crease and flange crease on the side closest to the height direction. Subsequently, it gradually expands towards the other side of the height direction through the remaining web creases to form a moving plastic hinge, ultimately forming a progressive deformation mode. Compared with the overall buckling deformation mode of conventional column configurations, this helps to significantly improve energy absorption performance. Furthermore, by arranging three or more web creases at intervals along the height direction, compared with conventional column configurations, it helps to stably guide the movement of the static plastic hinge, avoid interference from initial defects, and thus improve defect resistance sensitivity.

[0007] Furthermore, in the energy-absorbing column for aircraft of the present invention, it is preferable that the web crease and the flange crease are "V" shaped creases or "U" shaped creases.

[0008] The energy-absorbing column for aircraft according to the present invention can easily form web creases and flange creases, thereby reducing manufacturing costs.

[0009] Furthermore, in the energy-absorbing column for aircraft of the present invention, it is preferable that the end of the flange crease is close to the corner where the web intersects the flange, but spaced apart from that corner, and the end of the web crease is close to the corner where the web intersects the flange, but spaced apart from that corner.

[0010] The energy-absorbing column for aircraft according to the present invention can suppress the influence of flange creases and web creases on the structural bearing capacity while stabilizing and guiding the structure to generate initial static plastic hinge lines.

[0011] Furthermore, in the energy-absorbing column for aircraft of the present invention, it is preferable that the angle between the crease of the flange and the cross-section of the energy-absorbing column is less than or equal to 90°.

[0012] The energy-absorbing column for aircraft according to the present invention easily guides the structure to generate a plastic hinge line that deforms to one side in the height direction.

[0013] Furthermore, in the energy-absorbing column for aircraft of the present invention, it is preferable that the flange crease extends to the free edge of the flange on the side opposite to the web.

[0014] The energy-absorbing column for aircraft according to the present invention, similar to the one described above, readily guides the structure to generate a plastic hinge line that deforms to one side in the height direction.

[0015] Furthermore, in the energy-absorbing column for aircraft of the present invention, it is preferable to set the length of the static plastic hinge line when the energy-absorbing column deforms according to the principle of minimum energy as a, and set the distance between the web crease on the side closest to the height direction and the web crease on the side next to the height direction as b, then a≈b (i.e. b is approximately equal to a).

[0016] The energy-absorbing column for aircraft according to the present invention helps to guide the generation of static plastic hinge lines more stably.

[0017] Furthermore, in the energy-absorbing column for aircraft of the present invention, it is preferable that the length of the web crease is greater than or equal to half the width of the web and less than or equal to 0.9 times the width of the web.

[0018] The energy-absorbing column for aircraft according to the present invention can improve energy absorption performance while taking into account structural load-bearing capacity.

[0019] Furthermore, in the energy-absorbing column for aircraft of the present invention, preferably, in two adjacent web creases in the height direction, the height of the web crease on the side in the height direction is greater than or equal to the length of the web crease on the other side in the height direction.

[0020] The energy-absorbing column for aircraft according to the present invention helps guide the structure to deform gradually along a plurality of web creases arranged sequentially along the height direction, thereby causing the plastic hinge line to move from one side of the height direction to the other side of the height direction.

[0021] Furthermore, in the energy-absorbing column for aircraft of the present invention, preferably, in two adjacent web creases in the height direction, the depth of the web crease on one side in the height direction is greater than the depth of the web crease on the other side in the height direction.

[0022] The energy-absorbing column for aircraft according to the invention, similar to the one described above, helps to guide the structure to gradually deform along a plurality of web creases arranged sequentially along the height direction, thereby causing the plastic hinge line to move from one side of the height direction to the other side of the height direction.

[0023] Furthermore, in the energy-absorbing column for aircraft of the present invention, it is preferable that the depth of the web crease on the side closest to the height direction is greater than or equal to three times the structural form deviation, and the depth of the web crease with the smallest depth is greater than the structural form deviation.

[0024] The energy-absorbing column for aircraft according to the present invention helps to stably guide the structure to gradually deform along a plurality of web creases arranged sequentially along the height direction, thereby causing the plastic hinge line to move stably from one side of the height direction to the other side of the height direction.

[0025] Furthermore, in the energy-absorbing column for aircraft of the present invention, it is preferable that the width of the web crease and the flange crease is greater than or equal to half the depth of the web crease on the side closest to the height direction, and less than or equal to twice the depth of the web crease on the side closest to the height direction.

[0026] The energy-absorbing column for aircraft according to the present invention helps to prevent manufacturing damage and guidance failure.

[0027] Furthermore, in the energy-absorbing column for aircraft of the present invention, preferably, in two adjacent web creases in the height direction, the width of the web crease on one side in the height direction is less than or equal to the width of the web crease on the other side in the height direction.

[0028] The energy-absorbing column for aircraft according to the invention, similar to the one described above, helps to stably guide the structure to gradually deform along a plurality of web creases arranged sequentially along the height direction, thereby causing the plastic hinge line to move stably from one side of the height direction to the other side of the height direction.

[0029] Furthermore, in the energy-absorbing column for aircraft of the present invention, it is preferable that the spacing between adjacent web creases in the height direction is less than the height of the static plastic hinge line when the energy-absorbing column for aircraft deforms according to the principle of minimum energy, and greater than twice the width of the web crease.

[0030] The energy-absorbing column for aircraft according to the present invention, similar to the one described above, helps to prevent manufacturing damage and guidance failure.

[0031] Furthermore, in the energy-absorbing column for aircraft of the present invention, the multiple web creases may be arranged at equal intervals in the height direction or at unequal intervals in the height direction.

[0032] Furthermore, in the energy-absorbing column for aircraft of the present invention, preferably at least a portion of the plurality of web creases are located on one side of the height direction than the middle position of the web in the height direction.

[0033] Furthermore, in the energy-absorbing column for aircraft of the present invention, preferably the projections of the flange crease on one side of the width direction and the flange crease on the other side of the width direction overlap each other in the width direction.

[0034] (Invention Effects)

[0035] According to the present invention, when an energy-absorbing column for an aircraft is compressed in the height direction, an initial static plastic strand is formed at the web crease and flange crease on the side closest to the height direction. Subsequently, it gradually expands towards the other side in the height direction through the remaining web creases to form a moving plastic hinge, ultimately forming a progressive deformation mode. Compared with the overall buckling deformation mode of the conventional column configuration, this helps to significantly improve the energy absorption performance. Furthermore, by arranging three or more web creases at intervals along the height direction, compared with the conventional column configuration, it helps to stably guide the movement of the static plastic hinge, avoid interference from initial defects, and thus improve the defect resistance sensitivity. Attached Figure Description

[0036] Figure 1 This is a perspective view schematically illustrating an energy-absorbing column for an aircraft according to an embodiment of the present invention.

[0037] Figure 2 This is an enlarged perspective view illustrating the crease structure of an energy-absorbing column for an aircraft according to an embodiment of the present invention.

[0038] Figure 3A This is an explanatory diagram illustrating the deformation of an energy-absorbing column (including manufacturing and transportation defects) for an aircraft under pressure in the vertical direction according to an embodiment of the present invention.

[0039] Figure 3B It is an illustration showing the deformation of a traditional column (including manufacturing and transportation defects) under pressure in the height direction.

[0040] Figure 4 This is a comparative chart illustrating the relationship between displacement and load when an energy-absorbing column for aircraft (including manufacturing and transportation defects) and a conventional column (including manufacturing and transportation defects) are subjected to compression deformation in the height direction according to an embodiment of the present invention.

[0041] Figure 5 This is a perspective view illustrating an example of an application scenario of an energy-absorbing column for an aircraft according to an embodiment of the present invention.

[0042] (Symbol Explanation)

[0043] 1 Energy-absorbing column

[0044] 11. Web

[0045] 111 Web crease

[0046] 1111 First-level crease

[0047] 1112 Secondary crease

[0048] 1113 Level 3 crease

[0049] 1114 Level 4 crease

[0050] 1115 Level 5 crease

[0051] 12 Edges

[0052] 121 Folds on the edge

[0053] KJ fuselage frame

[0054] DB Cargo Floor Detailed Implementation

[0055] Below, in conjunction with Figures 1 to 4 An energy-absorbing column for an aircraft according to an embodiment of the present invention will be described.

[0056] For ease of explanation, the three mutually orthogonal directions are designated as X, Y, and Z. One side of the X direction is designated as X1, and the other side as X2. One side of the Y direction is designated as Y1, and the other side as Y2. One side of the Z direction is designated as Z1, and the other side as Z2.

[0057] like Figure 1 As shown, the energy-absorbing column 1 for the aircraft is formed in a C-shape in projection along the height direction (which is aligned with the Z direction in the illustrated example). It includes a web 11 extending along the height direction of the energy-absorbing column 1 and flanges 12 that bend from both sides of the web 11 in the width direction (which is aligned with the X direction in the illustrated example) (bending towards the Y2 direction in the illustrated example). More than three web creases 111 are formed on the web 11. These web creases 111 are spaced apart along the height direction of the energy-absorbing column 1 and are respectively positioned along the energy-absorbing... The column 1 extends in the width direction (which is consistent with the X direction in the illustrated example), and a flange crease 121 is formed on each flange 12. The flange crease 121 extends in a straight line from the web crease (i.e., the first-order crease 1111) on the side closest to the height direction of the energy-absorbing column 1 (the Z2 direction side in the illustrated example, but usually the lower side, i.e. the gravity direction side in actual use) toward the other side of the height direction of the energy-absorbing column 1 (the Z1 direction side in the illustrated example, but usually the upper side, i.e. the opposite side of the gravity direction in actual use) and away from the web 11.

[0058] Here, as Figure 1 As shown, the energy-absorbing column 1 is formed in a manner that is approximately symmetrical about the YZ plane.

[0059] In addition, such as Figure 1 As shown, at least a portion of the multiple web creases 111 are formed on one side of the web 11 in the height direction (in the illustrated example, the multiple web creases 111 are all formed at a position lower than the middle of the web 11 in the height direction).

[0060] In addition, such as Figure 1 As shown, the web 11 is generally flat, and the flange 12 is also generally flat, forming from one end of the web 11 in the height direction to the other end of the web 11 in the height direction, and bending approximately perpendicular to the web 11.

[0061] In addition, such as Figure 1 As shown, the web crease 111 includes a first-level crease 1111, a second-level crease 1112, a third-level crease 1113, a fourth-level crease 1114, and a fifth-level crease 1115 arranged sequentially from one side to the other in the height direction of the energy-absorbing column 1.

[0062] In addition, such as Figure 2 As shown, the web crease 111 and the flange crease 121 are, for example, stamping indentations (in the illustrated example, they are recessed toward the inside of the space partially enclosed by the web 11 and the flange 12, but they can also be recessed toward the outside of that space). The web crease 111 and the flange crease 121 are formed in a "V" shape (i.e., the creases are approximately "V" shaped when viewed along their height).

[0063] In addition, such as Figure 2 As shown, the projections of the crease 121 of the edge strip on one side (X1 direction side in the illustrated example) of the energy-absorbing column 1 and the crease 121 of the edge strip on the other side (X2 direction side in the illustrated example) of the energy-absorbing column 1 in the width direction of the energy-absorbing column 1 overlap with each other in the width direction of the energy-absorbing column 1.

[0064] In addition, such as Figure 2 As shown, the flange crease 121 extends in a straight line from the end of the web crease 111 on one side of the height direction closest to the energy-absorbing column 1 (the Z2 direction side in the illustrated example) toward the other side of the height direction of the energy-absorbing column 1 (the Z1 direction side in the illustrated example) and away from the web 11.

[0065] Furthermore, the end of the preferred flange crease 121 (in the illustrated example, the end on the Z2 direction side) is close to the corner (boundary line) where the web 11 intersects the flange 12, but is spaced apart from that corner (boundary line); similarly, the end of the web crease 111 is close to the corner (boundary line) where the web 11 intersects the flange 12, but is spaced apart from that corner (boundary line).

[0066] Furthermore, the preferred angle θ between the edge crease 121 and the cross-section of the energy-absorbing column 1 (refer to...) Figure 1 The angle is less than or equal to 90° (e.g., 50°, 60°, 70°, etc.). Furthermore, it is preferable that the crease 121 of the flange 12 extends to the free edge of the flange 12 on the side opposite to the web 11.

[0067] Furthermore, when the length of the static plastic hinge line (i.e., the plastic hinge line first formed when the energy-absorbing column 1 is compressed in the height direction of the energy-absorbing column 1, which is approximately C-shaped in the illustrated example) when the energy-absorbing column 1 deforms according to the principle of minimum energy (i.e., when the energy-absorbing column 1 is compressed in the height direction of the energy-absorbing column 1), which is the first-order fold line 1111, is the closest to the energy-absorbing column 1 in the height direction (in the illustrated example, the Z2 direction side), which is the second-order fold line 1112, which is the next closest to the energy-absorbing column 1 in the height direction, which is the second-order fold line 1112, is denoted as b, it is preferable that a ≈ b. Moreover, it is preferable that b is approximately 35 mm.

[0068] Furthermore, it is preferable that the length of the web crease 111 (in the illustrated example, the dimension in the X direction) is greater than or equal to half the width of the web 11 (in the illustrated example, the dimension in the X direction) and less than or equal to 0.9 times the width of the web 11.

[0069] Furthermore, among two adjacent web creases 111 along the height direction of the energy-absorbing column 1, it is preferable that the length of the web crease 111 on one side (the Z2 direction side in the illustrated example) along the height direction of the energy-absorbing column 1 is greater than or equal to the length of the web crease 111 on the other side (the Z1 direction side in the illustrated example) along the height direction of the energy-absorbing column 1. More preferably, the length of the web crease 111 on one side along the height direction of the energy-absorbing column 1 is greater than the length of the web crease 111 on the other side along the height direction of the energy-absorbing column 1.

[0070] Furthermore, among two adjacent web creases 111 in the height direction of the energy-absorbing column 1, the depth of the web crease 111 on the side closer to the height direction (in the illustrated example, the Z2 direction side) is preferably greater than the depth of the web crease 111 on the other side closer to the height direction (in the illustrated example, the Z1 direction side).

[0071] Furthermore, the depth (in the Y direction, the dimension) of the web crease 111 on the side closest to the energy-absorbing column 1 in the height direction is preferably greater than or equal to three times the structural form and position deviation (the maximum value generally does not exceed 5 mm), and the depth of the web crease 111 with the smallest depth is greater than the structural form and position deviation. Also, the width (in the Z direction, the dimension) of the web crease 111 and the flange crease 121 is greater than or equal to half the depth of the web crease 111 on the side closest to the energy-absorbing column 1 in the height direction, and less than or equal to twice the depth of the web crease 111 on the side closest to the energy-absorbing column 1 for the aircraft in the height direction.

[0072] Furthermore, among two adjacent web creases 111 in the height direction of the energy-absorbing column 1, the width of the web crease 111 on one side (in the illustrated example, the Z2 direction side) in the height direction of the energy-absorbing column 1 is preferably less than or equal to the width of the web crease 111 on the other side (in the illustrated example, the Z1 direction side) in the height direction of the energy-absorbing column 1.

[0073] Furthermore, it is preferable that the spacing between adjacent web creases 111 in the height direction of the energy-absorbing column 1 is less than the length of the static plastic hinge line of the energy-absorbing column 1 and greater than twice the width of the web crease 111.

[0074] According to the energy-absorbing column 1 of this embodiment, such as Figure 3A and Figure 3BAs shown, when the energy-absorbing column 1 is compressed along its height, initial static plastic strands form at the web fold 111 and flange fold 121 on the side closest to the energy-absorbing column 1 in the height direction (the lower side in the illustrated example). These strands then gradually expand towards the other side of the energy-absorbing column 1 in the height direction (the upper side in the illustrated example) through the remaining web folds 111, forming moving plastic hinges. This ultimately results in a progressive deformation mode, which, compared to the overall buckling deformation mode of traditional column configurations, significantly improves energy absorption performance (approximately by 60%). Furthermore, as... Figure 3A , Figure 3B and Figure 4 As shown, by arranging more than three web creases 111 at intervals along the height direction of the energy-absorbing column 1, compared with the traditional column configuration, it helps to stably guide the movement of the static plastic hinge line, avoid interference from initial defects, and thus improve the defect resistance sensitivity.

[0075] Furthermore, according to the energy-absorbing column 1 for an aircraft of this embodiment, in two adjacent web creases 111 in the height direction of the energy-absorbing column 1, the length of the web crease 111 on one side (in the illustrated example, the Z2 direction side) in the height direction of the energy-absorbing column 1 is set to be greater than or equal to the length of the web crease 111 on the other side (in the illustrated example, the Z1 direction side) in the height direction of the energy-absorbing column 1, and the depth (in the illustrated example, the dimension in the Y direction) of the web crease 111 on one side (in the illustrated example, the Z2 direction side) in the height direction is set to be greater than or equal to the length of the web crease 111 on the other side (in the illustrated example, the Z1 direction side) in the height direction of the energy-absorbing column 1. The depth of the web crease 111 on the Z1 direction side is set such that the width of the web crease 111 on one side (Z2 direction side in the illustrated example) of the height direction of the energy-absorbing column 1 (the dimension in the Z direction in the illustrated example) is less than or equal to the width of the web crease 111 on the other side (Z1 direction side in the illustrated example) of the height direction of the energy-absorbing column 1. This helps to stably guide the structure to gradually deform according to the multiple web creases 111 arranged sequentially along the height direction of the energy-absorbing column 1, thereby allowing the plastic hinge line to move stably from one side of the height direction of the energy-absorbing column 1 to the other side of the height direction of the energy-absorbing column 1.

[0076] Furthermore, according to the energy-absorbing column 1 for aircraft of this embodiment, by setting the depth of the web crease 111 on the side closest to the height direction of the energy-absorbing column 1 (the Z2 direction side in the illustrated example) to be greater than or equal to 3 times the structural form deviation (the maximum value is generally no more than 5 mm), and setting the depth of the web crease 111 with the smallest depth to be greater than the structural form deviation, it is more conducive to stably guiding the structure to gradually deform according to the multiple web creases 111 arranged sequentially along the height direction of the energy-absorbing column 1, thereby making the plastic hinge line move stably from one side of the height direction of the energy-absorbing column 1 to the other side of the height direction of the energy-absorbing column 1.

[0077] The present invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited to the above embodiments.

[0078] For example, in the above embodiment, the flange 12 is bent approximately perpendicularly to the web 11, but it is not limited to this; the flange 12 may also be bent obliquely relative to the web 11.

[0079] Furthermore, in the above embodiment, the energy-absorbing column 1 has five web creases 111 formed on the web 11, but it is not limited to this. It may also have only three or four web creases 111, or it may have more than six web creases 111.

[0080] Furthermore, in the above embodiments, the web crease 111 and the flange crease 121 are formed as "V" shaped creases, but are not limited to this, and can also be formed as "U" shaped creases, or other shapes.

[0081] Furthermore, in the above embodiments, the multiple web plate creases 111 can be arranged at equal intervals in the height direction of the energy-absorbing column 1, or they can be arranged at unequal intervals in the height direction of the energy-absorbing column 1.

[0082] Furthermore, in the above embodiment, the lower end of the edge crease 121 and the first-level crease 1111 are approximately at the same position in the height direction of the energy-absorbing column 1, but it is not limited to this, and the two can also be slightly offset in the height direction of the energy-absorbing column 1.

[0083] Furthermore, in the above embodiment, the energy-absorbing column 1 can be applied to an aircraft. Specifically, such as... Figure 5As shown, the energy-absorbing column 1 can be installed under the cargo hold floor of the aircraft. One end of the energy-absorbing column 1 in the height direction is connected to the fuselage frame KJ (e.g., by bolts), and the other end of the energy-absorbing column 1 in the height direction is connected to the cargo hold floor DB (e.g., by bolts). Thus, in the event of an aircraft crash, the energy-absorbing column 1 can form a stable plastic hinge line from one end of the fuselage frame KJ and move upward, guiding the column structure to absorb a large amount of energy.

[0084] Furthermore, in the above embodiments, the web crease 111 and the flange crease 121 can also be formed by additive manufacturing.

[0085] It should be understood that within the scope of this invention, the various parts of the embodiments can be freely combined, or the various parts of the embodiments can be appropriately modified or omitted.

Claims

1. An energy-absorbing column for an aircraft, the projection of the energy-absorbing column along its height direction being C-shaped, and comprising a web extending along the height direction and flanges bending from both sides of the web in the width direction of the energy-absorbing column, characterized in that, More than three web creases are formed on the web. The plurality of web creases are spaced apart along the height direction and extend along the width direction, respectively. Each of the flanges has a flange crease formed on it. The flange crease extends in a straight line from near the end of the web crease on the lower side of the height direction toward the upper side of the height direction and away from the web.

2. The energy-absorbing column for aircraft as described in claim 1, characterized in that, The web crease and the flange crease are "V" shaped creases or "U" shaped creases.

3. The energy-absorbing column for aircraft as described in claim 1, characterized in that, The end of the crease of the flange is close to the corner where the web and the flange intersect, but is spaced apart from that corner. The end of the web crease is close to the corner where the web intersects the flange, but is spaced apart from that corner.

4. The energy-absorbing column for aircraft as described in claim 1, characterized in that, The angle between the crease of the edge strip and the cross-section of the energy-absorbing column is less than or equal to 90°.

5. The energy-absorbing column for aircraft as described in claim 1, characterized in that, The crease of the flange extends to the free edge of the flange on the side opposite to the web.

6. The energy-absorbing column for aircraft as described in claim 1, characterized in that, Let a be the length of the static plastic hinge line when the energy-absorbing column deforms according to the principle of minimum energy, and let b be the distance between the web crease on the lower side closest to the height direction and the web crease on the lower side next to the height direction, then a≈b is satisfied.

7. The energy-absorbing column for aircraft as described in claim 1, characterized in that, The length of the web crease is greater than or equal to half the width of the web and less than or equal to 0.9 times the width of the web.

8. The energy-absorbing column for aircraft as described in claim 1, characterized in that, In two adjacent web creases along the height direction, the length of the lower web crease along the height direction is greater than or equal to the length of the upper web crease along the height direction.

9. The energy-absorbing column for aircraft as described in claim 1, characterized in that, In two adjacent web creases along the height direction, the depth of the lower web crease along the height direction is greater than the depth of the upper web crease along the height direction.

10. The energy-absorbing column for aircraft as described in claim 1, characterized in that, The depth of the web crease on the lower side closest to the height direction is greater than or equal to three times the structural form and position deviation, and the depth of the web crease with the smallest depth is greater than the structural form and position deviation.

11. The energy-absorbing column for aircraft as described in claim 1, characterized in that, The width of the web crease and the flange crease is greater than or equal to half the depth of the web crease on the lower side closest to the height direction, and less than or equal to twice the depth of the web crease on the lower side closest to the height direction.

12. The energy-absorbing column for aircraft as described in claim 1, characterized in that, In two adjacent web creases along the height direction, the width of the lower web crease along the height direction is less than or equal to the width of the upper web crease along the height direction.

13. The energy-absorbing column for aircraft as described in claim 1, characterized in that, The spacing between adjacent web creases in the height direction is less than the length of the static plastic hinge line when the energy-absorbing column deforms according to the principle of minimum energy, and greater than twice the width of the web crease.

14. The energy-absorbing column for aircraft as described in claim 1, characterized in that, At least a portion of the plurality of web creases is located on the lower side of the web in the height direction than the middle position of the web in the height direction.

15. The energy-absorbing column for aircraft as described in claim 1, characterized in that, The projections of the crease on one side of the flange in the width direction and the crease on the other side of the flange in the width direction overlap each other.

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