Aircraft fuselage column assembly and fuselage lower structure with the column assembly

Abstract

The present invention relates to an aircraft fuselage column assembly and a fuselage lower structure with the column assembly, belonging to the technical field of aircraft structures, comprising a corrugated C-shaped column, the corrugated C-shaped column comprising a corrugated telescopic section and straight sections arranged at both ends of the corrugated telescopic section, the straight section and the web and edge strip of the corrugated telescopic section are integrally formed, two corner pieces are respectively connected to the inner sides of the straight section, the corner piece is provided with an upper web of the corner piece, and the upper web of the corner piece is connected to the edge strips on both sides of the straight section. The present invention can make the corrugated telescopic section of the corrugated C-shaped column undergo telescopic deformation when the corrugated C-shaped column is under pressure, and at the same time, the upper web of the corner piece on the corner piece can pull the edge strips on both sides of the corrugated C-shaped column to prevent the corrugated C-shaped column from opening outwards when under pressure, thereby ensuring the stability of the corrugated C-shaped column when under pressure, so that the column assembly can stably absorb the impact energy generated by a crash, thereby improving the crashworthiness of the aircraft and the protection effect on the occupants during a crash.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft structures, and in particular relates to an aircraft fuselage column assembly and a fuselage lower structure with the column assembly. Background Art

[0002] Crashworthiness refers to the ability to protect the occupants to the greatest extent possible, minimize casualties, and enable the occupants to successfully evacuate the aircraft in the event of an aircraft crash or other emergency landing.

[0003] Based on civil aircraft crash accidents combined with typical fuselage frame crash tests and full aircraft crash tests conducted at home and abroad, the results show that when the lower fuselage structure collides with the ground during a crash, the lower fuselage structure is deformed and damaged to absorb the impact energy generated by the collision, thereby protecting the safety of the passengers. Civil aircraft crash accidents are inevitable, and at the same time, more and more passengers are transported on civil aircraft. In order to ensure that civil aircraft can absorb impact energy and protect the safety of passengers in the event of a collision, higher requirements are placed on the crashworthiness of civil aircraft fuselage structures. In the prior art, a column structure is provided between the fuselage bulkhead and the floor beam, and the deformation of the column structure is used to fully absorb the impact energy generated by the collision during the crash, thereby improving the crashworthiness of the aircraft.

[0004] Most of the fuselage structures of existing aircraft adopt open thin-walled structures, which reduce the weight of the aircraft while having high strength. Among them, the existing column structure is a C-type column structure, which is generally composed of a thin-walled structure of composite materials or aluminum alloys. However, when the C-type column structure is deformed during a crash, it is easy for local areas to buckle or suddenly break. When the local area of ​​the column structure buckles or breaks, the column structure will almost lose its bearing capacity and no longer have the effect of absorbing the impact energy of the crash, resulting in poor energy absorption stability of the column structure, thereby reducing the crashworthiness of the aircraft and the protection of the occupants during a crash. Summary of the invention

[0005] In view of this, the present invention provides an aircraft fuselage column assembly and a fuselage lower structure with the column assembly, which can stably absorb the impact energy generated by a crash, improve the crashworthiness of the aircraft and the protection effect on the occupants during a crash, so as to solve the deficiencies in the prior art.

[0006] The technical solution of the present invention is: an aircraft fuselage column assembly is configured and connected between a bulkhead and a floor beam of a lower structure of an aircraft fuselage, the column assembly includes a corrugated C-shaped column, the corrugated C-shaped column includes a corrugated telescopic section and straight sections arranged at both ends of the corrugated telescopic section, the straight section and the web and edge strip of the corrugated telescopic section are integrally formed, the corrugations of the corrugated telescopic section are arranged along the direction in which the length extends, and when the two ends of the corrugated C-shaped column are compressed, the corrugated telescopic section undergoes telescopic deformation along the length direction, two corner pieces are respectively connected to the inner side of the straight section, the corner piece is provided with an upper web of the corner piece, and the upper web of the corner piece is connected to the edge strips on both sides of the straight section.

[0007] Preferably, the corner piece also includes: a main web of the corner piece, and corner piece edge strips are respectively connected on both sides of the main web of the corner piece, the main web of the corner piece, the corner piece edge strip corresponds one by one to the web and edge strip of the straight section and are fixedly connected at corresponding positions, the upper web of the corner piece is located at one end of the main web of the corner piece and the corner piece edge strip, and one side of the upper web of the corner piece is fixedly connected to the main web of the corner piece and the corner piece edge strip.

[0008] Preferably, the upper web of the corner piece is connected to one end of the corner piece away from the corrugated telescopic section, a corrugated C-shaped column extends from one end of the corner piece close to the upper web of the corner piece, and the other side of the upper web of the corner piece is fixedly connected to the partition frame or floor beam.

[0009] Preferably, the strength of the corner piece is greater than the strength of the corrugated C-shaped column.

[0010] A lower structure of an aircraft fuselage includes a bulkhead, a floor beam horizontally arranged on the inner side of the bulkhead, and an aircraft fuselage column assembly. A plurality of aircraft fuselage column assemblies are symmetrically arranged on both sides of the central axis of the aircraft. One end of a corrugated C-shaped column of the aircraft fuselage column assembly is fixedly connected to the floor beam, and the other end is tilted downward and fixedly connected to the bulkhead.

[0011] Preferably, the angle between the corrugated C-shaped column and the central axis of the aircraft ranges from -20° to 20°.

[0012] Preferably, the partition frame includes: an upper partition frame, the upper partition frame is a major arc and opens downward, both ends of the opening of the upper partition frame are connected to the floor beam, a lower partition frame is arranged on the lower side of the floor beam, the lower partition frame is a minor arc and opens upward, both ends of the opening of the lower partition frame are connected to the floor beam, and the end of the corrugated C-shaped column away from the floor beam is fixedly connected to the lower partition frame.

[0013] Preferably, the web width of the lower bulkhead is smaller than the web width of the upper bulkhead.

[0014] Preferably, the floor beam and the upper bulkhead are integrally formed, and two bulkhead connecting plates are provided between the two ends of the lower bulkhead and the floor beam, and the bulkhead connecting plates are detachably fixedly connected to the lower bulkhead and the floor beam, respectively.

[0015] Preferably, the strength of the bulkhead connecting piece is greater than the strength of the upper bulkhead.

[0016] Compared with the prior art, the present invention provides an aircraft fuselage column assembly and a fuselage lower structure with the column assembly. By using a corrugated C-shaped column in combination with an angle piece, when the corrugated C-shaped column is under pressure, the corrugated telescopic section of the corrugated C-shaped column undergoes telescopic deformation to absorb energy. At the same time, the angle plate upper web on the angle piece can pull the edge strips on both sides of the corrugated C-shaped column to avoid the corrugated C-shaped column from opening outwards when under pressure, preventing the fuselage column structure from becoming unstable, buckling or breaking, ensuring the stability of the corrugated C-shaped column when under pressure, and enabling the column assembly to stably absorb the impact energy generated by a crash, thereby improving the crashworthiness of the aircraft and the protection effect on the occupants during a crash. The column assembly of the present invention has good buffering effect, high safety, strong practicality, and is worthy of promotion. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a perspective view of a column assembly of the present invention;

[0018] Figure 2 is a three-dimensional diagram of a connector of the present invention;

[0019] Figure 3 is a three-dimensional diagram of a corrugated C-shaped column of the present invention;

[0020] Figure 4 is a stereoscopic diagram of the installation of the connector of the present invention;

[0021] Figure 5 is a perspective view of the lower structure of the fuselage of the present invention;

[0022] Figure 6 It is a schematic diagram of the connection between the column assembly of the present invention and the partition frame and floor beam;

[0023] Figure 7 is a rear view of the fuselage lower structure of the present invention;

[0024] Figure 8 It is an enlarged view of the bulkhead connecting piece of the present invention. DETAILED DESCRIPTION

[0025] The present invention provides an aircraft fuselage column assembly and a fuselage lower structure with the column assembly, Figures 1 to 8 The present invention is described with reference to the structural schematic diagram of FIG.

[0026] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the technical solutions of the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0027] Crashworthiness refers to the ability to protect the occupants to the greatest extent possible, minimize casualties, and enable the occupants to successfully evacuate the aircraft in the event of an aircraft crash or other emergency landing.

[0028] Based on civil aircraft crash accidents combined with typical fuselage frame crash tests and full aircraft crash tests conducted at home and abroad, the results show that when the lower fuselage structure collides with the ground during a crash, the lower fuselage structure is deformed and damaged to absorb the impact energy generated by the collision, thereby protecting the safety of the passengers. Civil aircraft crash accidents are inevitable, and at the same time, more and more passengers are transported on civil aircraft. In order to ensure that civil aircraft can absorb impact energy and protect the safety of passengers in the event of a collision, higher requirements are placed on the crashworthiness of civil aircraft fuselage structures. In the prior art, a column structure is provided between the fuselage bulkhead and the floor beam, and the deformation of the column structure is used to fully absorb the impact energy generated by the collision during the crash, thereby improving the crashworthiness of the aircraft.

[0029] Most of the fuselage structures of existing aircraft adopt open thin-walled structures, which reduce the weight of the aircraft while having high strength. Among them, the existing column structure is a C-type column structure, which is generally composed of a thin-walled structure of composite materials or aluminum alloys. However, when the C-type column structure is deformed during a crash, it is easy for local areas to buckle or suddenly break. When the local area of ​​the column structure buckles or breaks, the column structure will almost lose its bearing capacity and no longer have the effect of absorbing the impact energy of the crash, resulting in poor energy absorption stability of the column structure, thereby reducing the crashworthiness of the aircraft and the protection of the occupants during a crash.

[0030] Based on the above problems, an embodiment of the present invention provides an aircraft fuselage column assembly and a lower fuselage structure with the column assembly. Through the use of a corrugated C-shaped column in conjunction with an angle piece, when the corrugated C-shaped column is under pressure, the corrugated telescopic section of the corrugated C-shaped column undergoes telescopic deformation to absorb energy. At the same time, the upper web of the angle piece on the angle piece can pull the edge strips on both sides of the corrugated C-shaped column to avoid the corrugated C-shaped column from opening outward when under pressure, preventing the fuselage column structure from becoming unstable, buckling or breaking, and ensuring the stability of the corrugated C-shaped column when under pressure, so that the column assembly can stably absorb the impact energy generated by a crash, thereby improving the crashworthiness of the aircraft and the protection effect on the occupants during a crash.

[0031] As shown in the figure, Figure 1 : is a three-dimensional diagram of the column assembly of this embodiment, an aircraft fuselage column assembly, configured and connected between the bulkhead 1 and the floor beam 2 of the aircraft fuselage lower structure, the column assembly includes a corrugated C-shaped column 3, the corrugated C-shaped column 3 includes a corrugated telescopic section 31 and straight sections 32 arranged at both ends of the corrugated telescopic section 31, the corrugated telescopic section 31 and the straight section 32 are on a straight line, the straight section 32 and the web and edge strip of the corrugated telescopic section 31 are integrally formed, and the corrugated The corrugations of the corrugated telescopic section 31 are arranged along the direction of its length extension. When the two ends of the corrugated C-shaped column 3 are compressed, the corrugated telescopic section 31 undergoes telescopic deformation along its length direction. The two corner pieces 4 are respectively connected to the inner sides of the straight section 32. The corner piece 4 has an upper web 41, which is connected to the edge strips on both sides of the straight section 32. The upper web 41 is used to pull the edge strips on both sides of the corrugated C-shaped column 3 to avoid the corrugated C-shaped column 3 from opening and deforming when it is compressed.

[0032] The corrugated C-shaped column in this embodiment absorbs energy by means of telescoping deformation, making full use of most areas of the column assembly for energy absorption, ensuring that the column assembly maintains a certain load-bearing capacity after telescoping, with higher energy absorption efficiency and more stable effect. At the same time, the corner piece 4 can pull and fix the edge strip of the corrugated C-shaped column to prevent the corrugated C-shaped column from opening outward when loaded, causing the column assembly structure to become unstable and bend.

[0033] As a further optimization solution, in the embodiment of the present disclosure, Figure 2 It is a three-dimensional diagram of the corner piece 4 of the present embodiment. Preferably, the corner piece 4 also includes a corner piece positive web 42, and two sides of the corner piece positive web 42 are respectively connected with corner piece edge strips 43, the corner piece positive web 42 and the corner piece edge strips 43 correspond one by one to the webs and edge strips of the straight section 32 and are fixedly connected at corresponding positions, the corner piece upper web 41 is located at one end of the corner piece positive web 42 and the corner piece edge strip 43, and one side of the corner piece upper web 41 is fixedly connected to the corner piece positive web 42 and the corner piece edge strip 43.

[0034] In this embodiment, the corner piece positive web 42 and the corner piece edge strip 43 of the corner piece 4 can be abutted against the web and edge strip of the corrugated C-shaped column 3 one by one and the corresponding abutting positions are respectively fixedly connected, thereby further enhancing the yield strength of the corrugated C-shaped column 3. The edges of one end of the corner piece positive web 42 and the corner piece edge strip 43 are respectively fixedly connected to one side of the corner piece upper web 41. For example, the corner piece 4 and the corner piece upper web 41 are manufactured by integral molding.

[0035] As shown in the figure, Figure 3 This is a three-dimensional diagram of the corrugated C-shaped column 3 of this embodiment. The web and the edge strip of the straight section 32 are respectively provided with a third bolt hole 321 and a fourth bolt hole 322. Figure 4 This is a three-dimensional installation diagram of the corner piece 4 of this embodiment. Four first bolt holes 421 are opened on the corner piece's main web 42, and two second bolt holes 431 are opened on the corner piece's edge strip 43. The positions of the first bolt hole 421 and the third bolt hole 321, and the positions of the second bolt hole 431 and the fourth bolt hole 322 correspond one to one and are fixedly connected by bolts respectively.

[0036] As a further optimization scheme, in the disclosed embodiment, preferably, the corner piece upper web 41 is connected to the end of the corner piece 4 away from the corrugated telescopic section 31, a corrugated C-shaped column 3 extends from the end of the corner piece 4 close to the corner piece upper web 41, and the other side of the corner piece upper web 41 is fixedly connected to the partition frame 1 or the floor beam 2.

[0037] In this embodiment, the upper web 41 of the corner piece is fixedly connected to the partition frame 1 and the floor beam 2, which can further improve the effect of the corner piece 4 pulling the edge strips on both sides of the corrugated C-shaped column 3 and further prevent the corrugated C-shaped column 3 from opening and deforming.

[0038] As a further optimization solution, in the disclosed embodiment, preferably, the strength of the corner piece 4 is greater than the strength of the corrugated C-shaped column 3 .

[0039] In this embodiment, the strength of the corner piece 4 is greater than the strength of the corrugated C-shaped column 3, which can avoid the deformation of the corrugated C-shaped column 3 during the collision, resulting in failure of the connection between the corrugated C-shaped column 3 and the bulkhead 1 and the floor beam 2, thereby ensuring the stability of the column assembly connecting the bulkhead and the floor beam, and preventing the corrugated C-shaped column 3 from invading the cabin structure after the connection with the floor beam 2 takes effect.

[0040] As shown in the figure, Figure 5 This is a stereoscopic diagram of the lower fuselage structure of the present embodiment, which is an aircraft fuselage lower structure, including a bulkhead 1, a floor beam 2 horizontally arranged on the inner side of the bulkhead 1, and an aircraft fuselage column assembly, wherein a plurality of aircraft fuselage column assemblies are symmetrically arranged on both sides of the central axis of the aircraft, and a corrugated C-shaped column 3 of the aircraft fuselage column assembly is fixedly connected to the floor beam 2 at one end, and fixedly connected to the bulkhead 1 at the other end inclined downward.

[0041] As a further optimization solution, in the disclosed embodiment, preferably, the angle between the corrugated C-shaped column 3 and the central axis of the aircraft is in the range of -20° to 20°.

[0042] In this embodiment, the column assembly is installed at an angle of -20°~20° to the aircraft centerline or yaw axis, so that the column assembly is mainly subjected to axial loads under crash conditions, ensuring that each corrugation in the corrugated telescopic section is fully telescoped.

[0043] As a further optimization scheme, in the embodiment of the present disclosure, preferably, the partition frame 1 includes: an upper partition frame 11, the upper partition frame 11 is a major arc and opens downward, both ends of the opening of the upper partition frame 11 are connected to the floor beam 2, a lower partition frame 12 is provided on the lower side of the floor beam 2, the lower partition frame 12 is a minor arc and opens upward, both ends of the opening of the lower partition frame 12 are connected to the floor beam 2, and the end of the corrugated C-shaped column 3 away from the floor beam 2 is fixedly connected to the lower partition frame 12.

[0044] In this embodiment, the straight sections 32 at both ends of the corrugated C-shaped column 3 and the upper web 41 of the corner piece are connected to the floor beam 2 and the lower partition frame 12 respectively.

[0045] Specifically, as shown in the figure, Figure 6 Schematic diagram of the connection between the column assembly, the bulkhead and the floor beam of the present embodiment. The longitudinal cross-section of the upper bulkhead 11, the lower bulkhead 12 and the floor beam 2 along the length direction of the fuselage in the present embodiment is Z-shaped. A fifth bolt hole 411 is provided on the upper web 41 of the corner piece, and a sixth bolt hole 123 and a seventh bolt hole 23 are provided on the edge strips of the lower bulkhead 12 and the floor beam 2, respectively. The sixth bolt hole 123 and the seventh bolt hole 23 correspond to the fifth bolt hole 411 one by one and are fixedly connected by bolts.

[0046] The existing aircraft fuselage bulkhead structure is integrated, without dividing the upper and lower bulkhead structures. In this embodiment, the bulkhead structure above the floor beam is divided into the upper bulkhead structure, and the bulkhead structure below the floor beam is divided into the lower bulkhead structure. Therefore, the bulkhead is divided into two separate structures, and the structures are connected by the aircraft fuselage column assembly.

[0047] In addition, the outer sides of the upper bulkhead 11 and the lower bulkhead 12 are connected with long stringers 6, and the outer skin 7 of the aircraft fuselage is connected to the edge strips of the upper bulkhead 11 and the lower bulkhead 12 and the long stringers 6 respectively by using rivets.

[0048] As shown in the figure, Figure 7This is a rear view of the lower fuselage structure of the present embodiment. A plurality of eighth bolt holes 21 are respectively opened on the web of the floor beam 2, and a plurality of ninth bolt holes 121 are opened on the web of the lower bulkhead 12. The eighth bolt holes 21 and the ninth bolt holes 121 correspond one to one with the third bolt holes 321 on the web of the straight sections 32 at both ends of the corrugated C-shaped column 3 and the first bolt holes 421 on the positive web 42 of the corner piece, and are fixedly connected by bolts.

[0049] Existing C-shaped pillars are prone to buckling failure or sudden breakage during a crash, resulting in poor energy absorption. At the same time, floor beams are prone to breakage and severe warping, which may penetrate the floor and pose a potential threat to the safety of passengers.

[0050] To this end, this embodiment proposes a solution. Preferably, the web width of the lower bulkhead 12 is smaller than the web width of the upper bulkhead 11 .

[0051] The lower bulkhead 12 in this embodiment is made of the same material as the upper bulkhead 11 , and the web width of the lower bulkhead 12 is smaller than the web width of the upper bulkhead 11 , so that the structural strength of the lower bulkhead 12 is slightly weaker.

[0052] The aircraft fuselage lower structure provided in this embodiment is based on deformation energy absorption. By providing a relatively weak lower bulkhead 12 and an improved fuselage column assembly, the energy absorption efficiency of the fuselage bulkhead structure can be optimized.

[0053] During a crash, the impact load first acts on the lower skin of the fuselage, and is then transmitted to the long stringer and the lower bulkhead through the skin. The middle section of the lower bulkhead absorbs energy to form a plastic hinge and bends into the cabin. Then, under the guidance of the corner piece 4, the corrugated C-shaped column makes the web and edge strip of the corrugated C-shaped column evenly loaded, absorbing energy in a telescoping deformation manner. At the same time, the remaining load is transmitted to the upper structure of the fuselage along the bulkhead connecting piece 13 and the upper bulkhead 11.

[0054] Under the action of a crash impact load, the lower structure of the aircraft fuselage of the present invention can effectively transfer the load to the corrugated C-shaped column 3, causing the corrugated telescopic section of the corrugated C-shaped column 3 to undergo progressive telescopic deformation, effectively improving the energy absorption capacity of the corrugated C-shaped column 3, and thereby reducing the crash load transmitted along the fuselage bulkhead.

[0055] During an aircraft crash, the lower bulkhead with relatively low strength bends and deforms, squeezing the corrugated C-shaped column 3 with the floor beam with slightly higher strength. The corrugated C-shaped column 3 utilizes the corrugated telescopic section to gradually telescope, thereby better absorbing the crash impact energy.

[0056] The disclosed embodiment can make the lower bulkhead 12 with a slightly weaker structural strength bend and deform first when the aircraft crashes, and the webs and edges of the straight sections 32 at both ends of the corrugated C-shaped column 3 are pulled by the corner pieces 4, ensuring that the corrugated C-shaped column 3 is stably stressed and undergoes progressive telescopic deformation in the telescopic section. Compared with the traditional fuselage structure, the lower bulkhead 12 is prone to bending and deformation, and the corrugated C-shaped column 3 is prone to stable and progressive telescopic deformation, which can absorb the impact energy of the crash to the maximum extent and improve the overall crashworthiness of the aircraft.

[0057] The present invention can ensure that the lower bulkhead can effectively produce compression deformation under the action of a crash impact load, and squeeze the corrugated C-shaped column. The corner piece 4 pulls the edge strip of the corrugated C-shaped column to ensure the stability of the corrugated C-shaped column when under pressure, so that the corrugated telescopic section of the corrugated C-shaped column undergoes telescopic deformation to absorb energy, so that the lower column assembly of the cargo hold can absorb more crash impact energy, thereby improving the crashworthiness of the aircraft and the protection effect on the occupants during a crash.

[0058] As a further optimization solution, in the embodiment of the present disclosure, as shown in the figure, Figure 8 This is an enlarged view of the bulkhead connecting piece of the present embodiment. Preferably, the floor beam 2 and the upper bulkhead 11 are integrally formed, and two bulkhead connecting pieces 13 are provided between the two ends of the lower bulkhead 12 and the floor beam 2. The bulkhead connecting pieces 13 are respectively detachably fixedly connected to the lower bulkhead 12 and the floor beam 2, and the upper bulkhead 11 and the floor beam 12 are an integrated thin-walled structure.

[0059] In this embodiment, the floor beam 2 and the upper bulkhead 11 are integrally formed to further improve the stability of the floor beam, further prevent the floor beam from breaking and warping, and prevent the floor from penetrating and threatening the safety of the occupants.

[0060] In this embodiment, a plurality of tenth bolt holes 131 are provided on the bulkhead connecting plate 13, a plurality of eleventh bolt holes 22 are provided at both ends of the floor beam 2, and a plurality of twelfth bolt holes 122 are provided at both ends of the lower bulkhead 12. The tenth bolt holes 131 on the bulkhead connecting plate 13 correspond one-to-one with the eleventh bolt holes 22 and the twelfth bolt holes 122, respectively, and are fixedly connected by bolts.

[0061] As a further optimization solution, in the disclosed embodiment, preferably, the strength of the bulkhead connecting piece 13 is greater than the strength of the upper bulkhead 11 .

[0062] The disclosed embodiment utilizes the bulkhead connecting piece 13 to stably connect the two ends of the lower bulkhead to the floor beam 2. When the lower bulkhead is hit during a crash, the middle section of the lower bulkhead is recessed toward the interior of the cabin, so that a stable plastic hinge is formed in the lower bulkhead.

[0063] The above disclosure is only a preferred specific embodiment of the present invention, but the embodiments of the present invention are not limited thereto, and any changes that can be conceived by those skilled in the art should fall within the protection scope of the present invention.

Claims

1. An aircraft fuselage column assembly, arranged and connected between a bulkhead (1) and a floor beam (2) of a lower structure of an aircraft fuselage, characterized in that: The column assembly comprises: a corrugated C-shaped column (3); The corrugated C-shaped column (3) comprises a corrugated telescopic section (31) and straight sections (32) arranged at both ends of the corrugated telescopic section (31); the straight section (32) is integrally formed with the web and edge strip of the corrugated telescopic section (31); the corrugations of the corrugated telescopic section (31) are arranged along the direction in which the corrugations extend in length; when the two ends of the corrugated C-shaped column (3) are compressed, the corrugated telescopic section (31) undergoes telescopic deformation along the length direction; Two corner pieces (4) are respectively connected to the inner side of the straight section (32), the corner piece (4) having an upper corner piece web (41), and the upper corner piece web (41) is connected to the edge strips on both sides of the straight section (32); The corner piece (4) further comprises: a corner piece positive web (42), both sides of the corner piece positive web (42) are respectively connected to corner piece edge strips (43), the corner piece positive web (42) and the corner piece edge strip (43) correspond to the web and edge strip of the straight section (32) one by one and are respectively fixedly connected at corresponding positions, the corner piece upper web (41) is located at one end of the corner piece positive web (42) and the corner piece edge strip (43), and one side of the corner piece upper web (41) is fixedly connected to the corner piece positive web (42) and the corner piece edge strip (43); The corner piece upper web (41) is connected to an end of the corner piece (4) away from the corrugated telescopic section (31); an end of the corner piece (4) close to the corner piece upper web (41) extends out of the corrugated C-shaped column (3); and the other side of the corner piece upper web (41) is fixedly connected to the bulkhead (1) or the floor beam (2); The strength of the corner piece (4) is greater than the strength of the corrugated C-shaped column (3).

2. An aircraft fuselage lower structure, characterized in that: include: A bulkhead (1), a floor beam (2) horizontally arranged on the inner side of the bulkhead (1), and the aircraft fuselage column assembly as claimed in claim 1, wherein a plurality of the aircraft fuselage column assemblies are symmetrically arranged on both sides of the center axis of the aircraft, and a corrugated C-shaped column (3) of the aircraft fuselage column assembly has one end fixedly connected to the floor beam (2) and the other end tilted downwardly fixedly connected to the bulkhead (1).

3. The aircraft fuselage lower structure according to claim 2, characterized in that: The angle between the corrugated C-shaped column (3) and the central axis of the aircraft is in the range of -20° to 20°.

4. The aircraft fuselage lower structure according to claim 2, characterized in that: The partition frame (1) comprises: an upper partition frame (11), the upper partition frame (11) is a major arc and opens downward, and both ends of the opening of the upper partition frame (11) are connected to the floor beam (2); a lower partition frame (12) is arranged on the lower side of the floor beam (2), the lower partition frame (12) is a minor arc and opens upward, and both ends of the opening of the lower partition frame (12) are connected to the floor beam (2); and one end of the corrugated C-shaped column (3) away from the floor beam (2) is fixedly connected to the lower partition frame (12).

5. The aircraft fuselage lower structure according to claim 4, characterized in that: The web width of the lower bulkhead (12) is smaller than the web width of the upper bulkhead (11).

6. The aircraft fuselage lower structure according to claim 4, characterized in that: The floor beam (2) and the upper bulkhead (11) are integrally formed, and two bulkhead connecting pieces (13) are provided between the two ends of the lower bulkhead (12) and the floor beam (2), and the bulkhead connecting pieces (13) are respectively detachably fixedly connected to the lower bulkhead (12) and the floor beam (2).

7. The aircraft fuselage lower structure according to claim 6, characterized in that: The strength of the bulkhead connecting piece (13) is greater than the strength of the upper bulkhead (11).

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