Energy absorption stand column and airplane

Abstract

The utility model relates to an energy absorption stand column and an airplane, and the energy absorption stand column comprises a base plate and two side plates which are oppositely arranged. The substrate extends along a first direction. The two opposite side plates are connected with the two sides, in the second direction, of the base plate respectively, the side plates extend in the first direction, and the first direction intersects with the second direction. The side plate is provided with an energy absorption notch penetrating through the thickness of the side plate. According to the energy-absorbing stand column, the energy-absorbing notches penetrating through the thickness of the side plates are formed in the side plates, and when the energy-absorbing stand column is subjected to impact loads during falling and collision, the energy-absorbing notches of the side plates can be deformed or damaged firstly, and part of impact energy is consumed. Afterwards, deformation expands to other areas, so that the whole energy absorption stand column deforms step by step, impact energy is absorbed in a staged mode, and the energy absorption efficiency is improved.

Description

Technical Field

[0001] This application relates to the field of fuselage frames, and more particularly to an energy-absorbing column and an aircraft. Background Technology

[0002] During an aircraft crash, the substructure of the cargo hold floor is the first to impact the ground. The columns in this substructure are connected at one end to the cargo hold floor beams and at the other end to the fuselage frame. They not only effectively support the cargo hold floor but also serve as crucial energy-absorbing structural elements during the crash. Therefore, their energy-absorbing capacity is particularly important in aircraft crashworthiness design.

[0003] The existing aircraft cargo hold floor under-floor pillar structure generally uses metal C-shaped pillars. Existing metal C-shaped pillars have the advantages of simple manufacturing and assembly. However, the crush failure mode of this type of pillar is uncontrollable, it cannot achieve effective progressive crushing, the energy absorption effect is poor, and it cannot provide reliable safety for passengers. Utility Model Content

[0004] This application provides an energy-absorbing column and an aircraft, aiming to improve the energy absorption effect of the energy-absorbing column during a crash.

[0005] To achieve the above objectives, according to a first aspect of this application, an energy-absorbing column is provided, comprising:

[0006] The substrate extends along a first direction;

[0007] Two side plates are arranged opposite each other and are respectively connected to the two sides of the substrate in the second direction. Each side plate extends along the first direction and the first direction and the second direction intersect.

[0008] The side plate has an energy-absorbing notch that extends through the thickness of the side plate.

[0009] Optionally, each side plate is provided with an energy-absorbing notch, and the energy-absorbing notches on different side plates are arranged opposite each other.

[0010] Optionally, the energy-absorbing notch is located at the edge of the side plate away from the substrate.

[0011] Optionally, in the first direction, the distance between the edge of the energy-absorbing notch and the edge of one end of the substrate in the first direction is 70 mm.

[0012] Optionally, the substrate and the side plate are integrally formed. The substrate has a first region, and the side plate has a second region. The second region is located on both sides of the first region in a second direction. Both the first region and the second region are provided with crease lines.

[0013] Optionally, the first region and the second region have multiple crease lines, which are combined to form multiple trapezoidal folded surfaces, which are arranged in an array along the circumference and first direction of the energy-absorbing column.

[0014] Optionally, both the substrate and the side plate have a core layer and a cover layer, with the cover layer enclosing the core layer. The core layer has a carbon fiber structure, and the cover layer has a metal structure.

[0015] Optionally, weight-reduction holes are also provided on the substrate.

[0016] Optionally, at least one weight-reducing hole is located between two opposing energy-absorbing notches.

[0017] According to a second aspect of this application, an aircraft is provided that includes an energy-absorbing column of any of the above disclosures.

[0018] The energy-absorbing column disclosed in this application has an energy-absorbing notch extending through the thickness of the side plate. When the energy-absorbing column is subjected to an impact load during a fall, the energy-absorbing notch in the side plate will deform or break first, thereby consuming some of the impact energy. Subsequently, the deformation will extend to other areas, causing the entire energy-absorbing column to gradually deform, thereby absorbing impact energy in stages and improving energy absorption efficiency.

[0019] Other features and advantages of this application will be described in detail in the following detailed description section. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] To gain a more complete understanding of this application and its beneficial effects, the following description will be provided in conjunction with the accompanying drawings, wherein the same reference numerals in the following description denote the same parts.

[0022] Figure 1 This is a schematic diagram of the structure of an energy-absorbing column provided in one embodiment of this application. Figure 1 ;

[0023] Figure 2 This is a schematic diagram of the structure of an energy-absorbing column provided in one embodiment of this application. Figure 2 ;

[0024] Figure 3 yes Figure 2 Cross-sectional view at point AA;

[0025] Figure 4This is a schematic diagram of the structure of an energy-absorbing column provided in another embodiment of this application;

[0026] Figure 5 This is a load-displacement curve of an energy-absorbing column according to an embodiment of this application.

[0027] Explanation of reference numerals in the attached figures:

[0028] 1. Substrate; 11. First region; 12. Weight reduction hole; 13. Fastener hole;

[0029] 2. Side panel; 21. Energy-absorbing notch; 22. Second zone;

[0030] 31. Crease line; 32. Trapezoidal folded surface;

[0031] 41. Kernel layer; 42. Overlay layer. Detailed Implementation

[0032] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the protection scope of this application.

[0033] To achieve the above objectives, according to the first aspect of this application, an energy-absorbing column is provided, such as... Figure 1 As shown, one embodiment of the energy-absorbing column includes a base plate 1 and two oppositely arranged side plates 2. The base plate 1 extends along a first direction, and the two side plates 2 are respectively connected to the two sides of the base plate 1 in a second direction. Each side plate 2 extends along the first direction, and the first and second directions intersect. An energy-absorbing notch 21 penetrating the thickness of the side plate 2 is also provided on the side plate 2.

[0034] This application utilizes an energy-absorbing notch 21 extending through the thickness of the side plate 2. When the energy-absorbing column is subjected to an impact load during a fall, the energy-absorbing notch 21 of the side plate 2 will first deform or break, consuming some of the impact energy. Subsequently, the deformation will extend to other areas, causing the entire energy-absorbing column to gradually deform, thereby absorbing impact energy in stages and improving energy absorption efficiency.

[0035] Specifically, continue to refer to Figure 1In this first embodiment, each of the two opposing side plates 2 has an energy-absorbing notch 21, and the energy-absorbing notches 21 on different side plates 2 are arranged opposite each other. When the energy-absorbing column is impacted, the oppositely arranged energy-absorbing notches 21 can ensure that the forces on the two side plates 2 are balanced, avoiding structural tilting or irregular deformation due to uneven distribution of energy-absorbing notches 21. Moreover, the oppositely arranged energy-absorbing notches 21 can guide the energy-absorbing column to deform along a preset path, so that the side plates 2 buckle or fold synchronously when subjected to force, thereby optimizing the energy absorption process. If the notch distribution is asymmetrical, it may cause one side to deform first, while the other side deforms later, thereby reducing energy absorption efficiency, or even causing structural tilting or local damage. In some other embodiments, multiple spaced energy-absorbing notches 21 can be opened on each of the two opposing side plates 2, and the energy-absorbing notches 21 on different side plates 2 correspond one-to-one, with the corresponding energy-absorbing notches 21 being arranged opposite each other.

[0036] Reference Figure 1 In Embodiment 1, the energy-absorbing notch 21 is located at the edge of the side plate 2 away from the substrate 1. When the energy-absorbing column is impacted, the edge of the side plate 2 is more likely to buckle or fold preferentially, causing deformation to gradually extend inward from the free edge of the side plate 2. Specifically, the connection between the substrate 1 and the side plate 2 is a stress concentration area of ​​the energy-absorbing column. If the energy-absorbing notch 21 is close to the substrate 1, it may cause excessive stress at the connection, increasing the risk of premature breakage. Placing the energy-absorbing notch 21 at the edge of the side plate 2 away from the substrate 1 helps to reduce the stress concentration effect at the connection, making the deformation process more stable and controllable, thereby improving the overall impact resistance of the energy-absorbing column. It is worth mentioning that, in order to reduce the stress concentration at the connection between the side plate 2 and the substrate 1 and improve the overall structural strength of the energy-absorbing column, in Embodiment 1, the connection between the substrate 1 and each side plate 2 is provided with rounded corners to achieve a smooth transition and optimize stress distribution. It should be noted that in Embodiment 1, the energy-absorbing notch 21 is a semi-circular notch with a radius of 15mm; in some other embodiments, the energy-absorbing notch 21 can be any of the following: U-shaped notch, circular notch, elliptical notch, and triangular notch. It should be noted that the two energy-absorbing notches 21 provided opposite each other are usually notches of the same shape and size, and the energy-absorbing notch 21 can be formed by cutting. The energy-absorbing notch 21 processed in this way can make the cut surface of the energy-absorbing notch 21 smooth, flat and burr-free.

[0037] The energy-absorbing column has two ends in the first direction. When the energy-absorbing column is installed on an aircraft, one end in the first direction is connected to the cargo hold floor beam via fasteners, and the other end is connected to the fuselage frame. In Embodiment 1, the energy-absorbing notch 21 is closer to the end of the base plate 1 used for connection to the fuselage frame. The distance between the edge of the energy-absorbing notch 21 and the edge of that end is 70mm. During an aircraft crash or severe impact, the energy-absorbing column needs to absorb energy to the maximum extent possible, preventing excessive impact from being transmitted to the fuselage frame and cargo hold floor beam. Placing the energy-absorbing notch 21 closer to the end of the fuselage frame can preferentially trigger controllable deformation at that end, ensuring that the impact energy is fully absorbed within a reasonable area and not directly transmitted to critical connection points. In some other embodiments, the energy-absorbing notch 21 can be located in the middle of the side plate 2 in the first direction, or closer to the end of the base plate 1 used for connection to the cargo hold floor beam.

[0038] It is worth mentioning that, to facilitate the installation of the energy-absorbing column, fastener holes 13 are provided at both ends of the base plate 1 in the first direction. When two rows of fastener holes 13 are provided at one end in the first direction, the distance between the center of the fastener hole 13 near the end edge and the end edge is 4D to 6D, where D is the diameter of the fastener hole 13. To facilitate the installation of the energy-absorbing column on the aircraft, the end faces of both ends of the base plate 1 and the side plate 2 in the first direction are inclined (see reference). Figure 2 ).

[0039] Continue to refer to Figure 1 In the first embodiment disclosed in this application, a weight-reducing hole 12 is also formed on the substrate 1. In some other embodiments, multiple weight-reducing holes 12 can be formed on the substrate 1 at intervals. Regardless of whether a single weight-reducing hole 12 or multiple weight-reducing holes 12 are formed, at least one weight-reducing hole 12 is located between two opposing energy-absorbing gaps 21. The main function of the energy-absorbing column is to undergo controlled collapse deformation during impact to absorb energy. Forming a weight-reducing hole 12 between two energy-absorbing gaps 21 can guide stress distribution, making the deformation more uniformly spread from the gap area to the surrounding area, thereby optimizing the overall energy absorption effect. In order to prevent the short edge distance problem (i.e., the distance between the center of the hole and the edge of the structure is too short, resulting in local stress concentration and increasing the risk of fracture or structural failure), the material around the hole will bear high stress, resulting in local stress concentration, thereby increasing the risk of fracture, tearing or structural failure. The distance between the center of the fastener hole 13 near the weight-reducing hole 12 and the edge of the weight-reducing hole 12 is 4D to 6D, where D is the diameter of the fastener hole 13. In some embodiments, the weight reduction hole 12 can be a round hole, a rectangular hole, an elliptical hole, a semi-circular hole, or a polygonal hole.

[0040] Reference Figure 2 and Figure 3The base plate 1 and side plate 2 are integrally formed and made of the same material. Specifically, both the base plate 1 and side plate 2 have a core layer 41 and a cover layer 42. The cover layer 42 wraps around the core layer 41. The core layer 41 is a composite material structure, which can be carbon fiber composite material. The cover layer 42 is a metal structure, which can be aluminum alloy material. Aluminum alloy material can reduce the weight of the column. The specific strength (strength / density) of carbon fiber composite material is much higher than that of metal, and its weight is about 1 / 3 that of aluminum alloy. Using carbon fiber composite material as the core layer 41 can significantly reduce the overall weight of the energy-absorbing column, which helps to reduce the total weight of the aircraft and ensures that the energy-absorbing column has sufficient load-bearing capacity under normal use. Aluminum alloy material has good plasticity and ductility. It can buckle and fold according to the designed deformation mode when subjected to impact, thereby effectively absorbing energy. Moreover, aluminum alloy can deform before fracture, which helps to control the energy absorption process, so that the energy-absorbing column deforms according to the predetermined mode and improves the energy absorption effect.

[0041] Embodiment two disclosed in this application is as follows: Figure 4 As shown, unlike Embodiment 1, the substrate 1 has a first region 11, and the side plate 2 has a second region 22. The second region 22 is located on both sides of the first region 11 in the second direction. Both the first region 11 and the second region 22 are provided with crease lines 31. The first region 11 and the second region 22 have multiple crease lines 31, which are combined to form multiple trapezoidal folded surfaces 32. The multiple trapezoidal folded surfaces 32 are arranged in an array along the circumference and the first direction of the energy-absorbing column. The crease lines 31 can be formed by stamping. When the energy-absorbing column is impacted or dropped, the crease lines 31 provide a preset deformation path, so that the energy-absorbing column can deform in an orderly and gradual manner according to the designed trapezoidal folded surfaces 32 when subjected to force, avoiding random or disorderly destructive deformation.

[0042] Reference Figure 5 , Figure 5 This is a load-displacement curve diagram of an energy-absorbing column according to one embodiment of this application, specifically the load-displacement curve diagram of the energy-absorbing column disclosed in Embodiment 2 of this application. Figure 5 It is evident that under dynamic impact conditions, the energy-absorbing column undergoes progressive deformation, with a peak load of 45kN and a specific energy absorption of 0.339J / g. In Embodiment 2 of this application, the introduction of energy-absorbing notches, weight-reducing holes, and crease lines does not weaken the supporting function of the energy-absorbing column, and the deformation mode of the energy-absorbing column during failure is controllable, resulting in a significant increase in energy absorption level and greatly enhancing the energy absorption effect of the energy-absorbing column during impact.

[0043] According to a second aspect of this application, an aircraft is provided that includes an energy-absorbing column of any of the above disclosures.

[0044] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more features. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0045] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0046] The embodiments, implementation methods, and related technical features of this application can be combined and substituted for each other without conflict.

[0047] The above are merely preferred embodiments of this application and are not intended to limit this application in any way. Any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of this application without departing from the scope of the technical solution of this application shall still fall within the scope of the technical solution of this application.

Claims

1. An energy absorbing column, characterized by include: Substrate (1) extends along a first direction; Two opposing side plates (2) are respectively connected to the substrate (1) on both sides in the second direction, and each side plate (2) extends along the first direction, where the first direction and the second direction intersect. The side plate (2) has an energy-absorbing notch (21) that extends through the thickness of the side plate (2).

2. The energy absorbing column of claim 1, wherein, Each of the side plates (2) is provided with the energy absorption notch (21), and the energy absorption notches (21) located on different side plates (2) are arranged opposite each other.

3. The energy absorbing column of claim 1, wherein, The energy-absorbing notch (21) is located at the edge of the side plate (2) away from the substrate (1).

4. The energy absorbing column of claim 1, wherein, In the first direction, the distance between the edge of the energy-absorbing notch (21) and the edge of one end of the substrate (1) in the first direction is 70 mm.

5. The energy absorbing column of claim 1, wherein, The substrate (1) and the side plate (2) are integrally formed. The substrate (1) has a first region (11) and the side plate (2) has a second region (22). The second region (22) is located on both sides of the first region (11) in a second direction. Both the first region (11) and the second region (22) are provided with crease lines (31).

6. The energy absorbing column of claim 5, wherein, The first region (11) and the second region (22) have multiple crease lines (31), which are joined together to form multiple trapezoidal folded surfaces (32), which are arranged in an array along the circumference of the energy-absorbing column and the first direction.

7. The energy absorbing column of claim 1, wherein, Both the substrate (1) and the side plate (2) have a core layer (41) and a cover layer (42), the cover layer (42) wrapping the core layer (41), the core layer (41) being a carbon fiber structure, and the cover layer (42) being a metal structure.

8. The energy absorbing column of claim 2, wherein, The substrate (1) is also provided with weight reduction holes (12).

9. The energy absorbing column of claim 8, wherein, At least one of the weight-reducing holes (12) is located between two opposing energy-absorbing notches (21).

10. An aircraft characterized by, Includes the energy-absorbing column as described in any one of claims 1-9.

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