Aircraft stopping system, energy absorbing device and mechanical property testing method

Abstract

The invention discloses a stopping system for an airplane, an energy absorption device and a mechanical property testing method. The stopping system for the airplane comprises an energy absorption system, the energy absorption system comprises an energy absorption assembly, the energy absorption assembly comprises a plurality of energy absorption devices connected end to end, each energy absorption device comprises a sliding block with a pawl, a ratchet groove, a dowel bar and an elastic buffering piece, the dowel bar is connected with the sliding block with the pawl, and the elastic buffering piece is connected with the ratchet groove; the sliding block with the pawl is arranged in the ratchet groove and matched with the ratchet groove to form a moving pair, and the elastic buffering piece is used for being connected with the dowel bar and the ratchet groove. One energy absorption system is used for being installed on one pulley assembly; one end of the arresting cable is connected to the dowel bar of one energy absorption system through the pulley assembly, and the other end of the arresting cable is used for being connected with the dowel bar of the head energy absorption device of the other energy absorption system after passing through the other pulley assembly.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft arresting, and particularly to an aircraft arresting system, an energy absorption device, and a mechanical property testing method for an aircraft. Background Art

[0002] Existing aircraft carrier arresting devices need to achieve rapid deceleration through an efficient energy absorption and buffering system when an aircraft lands, ensuring the safe landing of the aircraft. As the main buffering and reset mechanism of the existing aircraft carrier arresting system, the hydraulic energy absorption system plays an important role in this process. However, there are still some obvious deficiencies in the actual use of the existing hydraulic energy absorption system, which not only affect the overall performance of the arresting system, but also bring certain limitations to the aircraft carrier design and operation.

[0003] The existing aircraft carrier arresting devices have the following disadvantages:

[0004] First, the structural complexity is high. The hydraulic energy absorption system usually consists of multiple components such as hydraulic cylinders, pipelines, valves, and control units. Its design and manufacturing processes are complex, requiring high precision and reliability. The failure of any one component may cause the entire arresting system to malfunction. In addition, the complexity of the hydraulic system also increases the difficulty of maintenance and repair, especially in the shipboard environment, where the complex system is more easily restricted by space, environment, and time.

[0005] Second, it occupies a large space. The space on the aircraft carrier deck is precious, and the volume and weight of the hydraulic system occupy a large amount, squeezing the installation space of other equipment. Especially the layout of the hydraulic oil tank and pipeline network often requires a large amount of space, which is not conducive to the optimization of the overall layout of the aircraft carrier.

[0006] Third, there is a potential leakage problem. The seals of the hydraulic system may age or wear during long-term use, resulting in hydraulic oil leakage, which not only affects the system function, but also may pollute the shipboard environment and increase the cleaning difficulty.

[0007] Therefore, it is desirable to have a technical solution to overcome or at least mitigate at least one of the above defects of the existing technology. Summary of the Invention

[0008] The purpose of the present application is to provide an aircraft arresting system to overcome or at least mitigate at least one of the above defects of the existing technology.

[0009] To achieve the above purpose, the present application provides an aircraft arresting system, and the aircraft arresting system includes:

[0010] Energy absorption system, the number of the energy absorption systems is two, each energy absorption system includes multiple groups of energy absorption components, the number of the energy absorption components is multiple groups, and the groups of energy absorption components are arranged in an array. Each group of energy absorption components includes multiple energy absorption devices connected end to end. Among them, the energy absorption device at the first position is called the head energy absorption device, and the energy absorption device at the tail position is called the tail energy absorption device. Each energy absorption device includes a slider with a pawl, a ratchet groove, a force transmission rod, and an elastic buffer. Among them, the force transmission rod is connected to the slider with a pawl, the slider with a pawl is arranged in the ratchet groove and cooperates with the ratchet groove to form a moving pair, and the elastic buffer is used to connect the force transmission rod and the ratchet groove respectively. The force transmission rods of the energy absorption devices other than the head energy absorption device are used to connect to another energy absorption device;

[0011] Pulley assemblies, the number of the pulley assemblies is two, and one energy absorption system is used to be installed on one pulley assembly;

[0012] Arresting cable, one end of the arresting cable is connected to the force transmission rod of an energy absorption system through a pulley, and the other end is used to connect to the force transmission rod of the head energy absorption device of another energy absorption system; Among them,

[0013] When the aircraft is taxiing and is blocked by the arresting cable, the arresting cable is used to transmit the force of the aircraft to each force transmission rod through the pulley assembly. After the force transmission rods are stressed, they drive the elastic buffer to move in the ratchet groove, and the elastic buffer is used to absorb the energy transmitted by the aircraft to the arresting cable during the movement.

[0014] Optionally, the slider with a pawl includes:

[0015] Slider body, the slider body is provided with a mounting hole, and a part of the force transmission rod is arranged in the mounting hole;

[0016] Pawl curved beam structure, the pawl curved beam structure is installed on one surface of the slider body, and the pawl curved beam structure is used to cooperate with the ratchet tooth structure of the ratchet groove to form a toothed ratchet mechanism.

[0017] Optionally, the ratchet groove includes:

[0018] Outer housing, the outer housing includes a first wall plate and two side plates respectively connected to the first wall plate. The two side plates are arranged opposite to each other, and side plate chutes are respectively arranged on the two side plates. A receiving space is formed between the outer housing plate and the two side plates. The slider body and the force transmission rod are arranged at one end of the receiving space, and the slider body and the force transmission rod can move in the receiving space along the axial direction of the receiving space when stressed;

[0019] A ratchet structure, the ratchet structure is disposed within the accommodation space and on one surface of the outer housing, and the ratchet structure is adapted to cooperate with the pawl curved beam structure to form a toothed ratchet mechanism.

[0020] Optionally, the outer housing further includes a cross beam, the cross beam is disposed at one end of the ratchet groove close to the slider with a pawl, and the two side plates are connected by the cross beam;

[0021] The ratchet groove further includes a ratchet groove buckle, the ratchet groove buckle is disposed on the cross beam, and the elastic buffer is connected to the ratchet groove buckle.

[0022] Optionally, one surface of the first wall plate disposed within the accommodation space protrudes away from the other surface to form a ratchet groove inclined surface, and the portions of the ratchet groove inclined surface close to the two side plates are inclined; wherein,

[0023] When the slider with a pawl is forced to move towards the other end of the accommodation space, the pawl curved beam structure is deformed and absorbs energy due to the shape limitation of the ratchet groove inclined surface.

[0024] Optionally, the force transmission rod includes:

[0025] A force transmission rod body, a part of the force transmission rod body is disposed within the mounting hole;

[0026] A limit protrusion, the limit protrusion is disposed on the force transmission rod body and within the mounting hole;

[0027] A force transmission rod buckle, the force transmission rod buckle is disposed at one end of the force transmission rod body close to the ratchet groove inclined surface, and the other end of the elastic buffer is connected to the force transmission rod buckle;

[0028] In the assembled state, the end of the force transmission rod body away from the ratchet groove inclined surface can extend into the accommodation space of another energy absorption device, and among two energy absorption devices connected end to end, the energy absorption device that first receives the force transmitted by the aircraft can transmit the force to the energy absorption device connected thereto.

[0029] Optionally, every two energy absorption devices connected end to end are connected by an integral molding method, and each group of energy absorption components is connected to other groups of energy absorption components by an integral molding method.

[0030] Optionally, the pawl curved beam structure includes:

[0031] A short beam, one end of the short beam is a free end, this end is in contact with the ratchet groove and the contact part with the ratchet groove is rounded;

[0032] Variable cross-section curved beam, one end of the variable cross-section curved beam is connected to the other end of the short beam, and the cross-sectional area of the end of the variable cross-section curved beam connected to the short beam is smaller than that of the other end;

[0033] Fixed end, one end of the fixed end is connected to the other end of the variable cross-section curved beam, and the fixed end is arranged on the slider body.

[0034] The present application also provides an energy absorption device, and the energy absorption device is the energy absorption device as described above.

[0035] The present application also provides a mechanical property test method for the energy absorption device as described above, and the mechanical property test method includes:

[0036] Conduct a static loading experiment on the energy absorption device as described above to obtain the force-displacement curve generated by different loading methods and calculate the energy absorption performance;

[0037] Use the numerical simulation software ABAQUS to numerically simulate the static loading experiment, and at the same time complete the finite element numerical simulation of the impact and obtain the structure with the main deformation. On this basis, conduct a simulation analysis on the structure with the main deformation;

[0038] Conduct a theoretical analysis on the structural member with the main deformation. On this basis, combine the finite element numerical simulation results to calculate the force-displacement curve of the energy absorption metamaterial unit and compare it with the results of the static loading experiment.

[0039] The present application has the following advantages:

[0040] High energy absorption characteristics and reduced structural damage: By delaying and weakening the impact force, the aircraft arresting system of the present application can effectively absorb the impact energy when the aircraft lands, and reduce the damage to the aircraft and the aircraft carrier structure.

[0041] Reusability: Due to the use of an elastic buffer that can automatically recover, the aircraft arresting system of the present application can return to its original state after absorbing the impact, be ready to receive the next landing, improve the operating efficiency of the aircraft carrier, and reduce the maintenance cost and logistical pressure.

[0042] Adaptability: The aircraft arresting system of the present application can adapt to different impact load conditions by adjusting the number of energy absorption components, the arrangement, and the buffering force of the elastic buffer, providing adjustable mechanical properties and energy absorption performance, and adapting to the landing of aircraft of different models and weights.

[0043] Structural Simplification and Modular Design: Compared with traditional hydraulic systems, the aircraft arresting system of this application eliminates a large number of complex hydraulic pipelines, valves, and fuel tanks, fundamentally simplifying the system structure. At the same time, it can be adjusted in an array according to different impact load conditions. This modular design facilitates rapid installation and disassembly, significantly reducing maintenance complexity.

[0044] Significant Reduction in Occupied Space: Since the aircraft arresting system of this application no longer requires large hydraulic fuel tanks and complex pipeline layouts, the space occupied by the entire system is significantly reduced, leaving more room for the arrangement of other key equipment on the aircraft carrier.

[0045] Completely Eliminate Potential Leakage Risks: This device completely eliminates the problem of hydraulic oil leakage. In addition, this application also has a lower risk of environmental pollution, better meeting the high environmental protection requirements of modern warships. Description of the Drawings

[0046] Figure 1 is a schematic structural diagram of an aircraft arresting system according to an embodiment of this application.

[0047] Figure 2 is Figure 1 a schematic structural diagram of an energy absorption device in the aircraft arresting system shown.

[0048] Figure 3 is Figure 1 another schematic structural diagram of an energy absorption device in the aircraft arresting system shown.

[0049] Figure 4 is a schematic structural diagram of a slider with a ratchet according to an embodiment of this application.

[0050] Figure 5 is a schematic structural diagram of a ratchet groove according to an embodiment of this application.

[0051] Figure 6 is a schematic structural diagram of a force transmission rod according to an embodiment of this application.

[0052] Figure 7 is a schematic structural diagram of an energy absorption component according to an embodiment of this application.

[0053] Figure 8 is a schematic diagram of a displacement curve obtained after a cyclic loading experiment on the energy absorption device of this application.

[0054] Reference Numerals

[0055] 1. Slider with pawl, 2. Ratchet groove, 3. Force transmission rod, 4. Elastic buffer, 5. Pulley assembly, 6. Arresting cable, 11. Slider body, 12. Pawl curved beam structure, 21. Outer housing, 211. First wall panel, 212. Side plate, 2121. Side plate chute; 22. Ratchet structure, 213. Cross beam, 23. Ratchet groove buckle, 2111. Ratchet groove inclined plane, 31. Force transmission rod body, 32. Limit protrusion, 33. Force transmission rod buckle, 121. Short beam, 122. Variable cross-section curved beam, 123. Fixed end, 7. Arresting component, 8. Energy absorption system. Detailed implementation mode

[0056] To make the purpose, technical solution and advantages of the implementation of this application clearer, the technical solution in the embodiments of this application will be described in more detail below with reference to the accompanying drawings in the embodiments of this application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements with the same or similar functions throughout. The described embodiments are some but not all of the embodiments of this application. The embodiments described below with reference to the drawings are exemplary and are intended to explain this application and should not be construed as a limitation of this application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of this application without creative efforts belong to the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the drawings.

[0057] In the description of this application, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing this application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the scope of protection of this application.

[0058] See Figures 1 to 7 , in this embodiment, the aircraft arresting system includes an energy absorption system, a pulley assembly 5, and an arresting cable 6.

[0059] In this embodiment, the energy absorption system includes two, each energy absorption system includes multiple groups of energy absorption components, the number of the energy absorption components is multiple, and the energy absorption components of each group are arranged in an array. Each group of energy absorption components includes multiple energy absorption devices connected end to end, wherein the energy absorption device located at the head is called the head energy absorption device, and the energy absorption device located at the tail is called the tail energy absorption device. Each energy absorption device includes a slider 1 with a pawl, a ratchet groove 2, a force transmission rod 3 and an elastic buffer 4, wherein the force transmission rod 3 is connected to the slider 1 with a pawl, the slider 1 with a pawl is arranged in the ratchet groove 2 and cooperates with the ratchet groove 2 to form a moving pair, and the elastic buffer 4 is used to connect the force transmission rod 3 and the ratchet groove 2 respectively. The force transmission rod 3 of the other energy absorption devices except the head energy absorption device is used to be connected to another energy absorption device;

[0060] There are two pulley assemblies 5, and one energy absorption system is installed on one pulley assembly 5;

[0061] One end of the arresting cable 6 is connected to the force transmission rod of an energy absorption system through a pulley assembly 5, and the other end is used to pass through another set of pulley assemblies 5 and then be connected to the force transmission rod of the head energy absorption device of another energy absorption system; wherein,

[0062] When the aircraft is arrested by the arresting cable 6 during taxiing, the arresting cable 6 is used to transmit the force transmitted by the aircraft to each force transmission rod 3 through the pulley assembly 5. After each force transmission rod 3 is subjected to the force, it drives the elastic buffer 4 to move in the ratchet groove 2. The elastic buffer 4 is used to absorb the energy transmitted from the aircraft to the arresting cable (6) during the movement.

[0063] In actual use, see Figure 1 The energy absorption system of the present application is respectively arranged on both sides, and the arresting component 7 of the aircraft cooperating with the arresting cable 6 is arrested by the arresting cable. Since the aircraft still has inertia at this time, the aircraft will drive the arresting cable 6 to move.

[0064] In this embodiment, each pulley assembly 5 includes a plurality of fixed pulleys and a movable pulley. Each fixed pulley is used for winding the barrier cable 6. On the one hand, it is used to realize a certain length of conduction space. On the other hand, the direction of the force is in a direction that the user considers more appropriate through the guidance of each fixed pulley. For example, Figure 1 In the embodiment shown, the aircraft Figure 1 The aircraft moves downward from the top, and through the action of each fixed pulley, the force transmitted by the aircraft can be converted into a movable pulley. Figure 1 In the bottom-up movement, the movable pulley is connected to the force transmission rod 3 of the energy absorption system of the present application. When the force is transmitted to the movable pulley, it can drive the energy absorption system of the present application to work, thereby enabling the energy absorption system to absorb energy.

[0065] See also Figures 2 to 4In this embodiment, the slider 1 with a pawl includes a slider body 11 and a pawl curved beam structure 12, wherein,

[0066] The slider body 11 is provided with a mounting hole, and the force transmission rod 3 is partially disposed in the mounting hole;

[0067] The ratchet curved beam structure 12 is mounted on one surface of the slider body 11 , and the ratchet curved beam structure 12 is used to cooperate with the ratchet groove 2 to form a toothed ratchet mechanism.

[0068] In this embodiment, the pawl curved beam structure 12 includes a short beam 121, a variable-section curved beam 122, and a fixed end 123, wherein:

[0069] One end of the short beam 121 is a free end, which contacts the ratchet groove 2 and the contact portion with the ratchet groove 2 is rounded;

[0070] One end of the variable-section curved beam 122 is connected to the other end of the short beam 121, and the cross-sectional area of the end of the variable-section curved beam 122 connected to the short beam 121 is smaller than that of the other end;

[0071] One end of the fixed end 123 is connected to the other end of the variable-section curved beam 122 , and the fixed end 123 is disposed on the slider body 11 .

[0072] In this embodiment, the ratchet slot 2 includes an outer shell 21 and a ratchet structure 22, wherein:

[0073] The outer shell 21 includes a first wall plate 211 and two side plates 212 respectively connected to the first wall plate 211. The two side plates 212 are arranged opposite each other and are respectively provided with side plate slide grooves 2121. A receiving space is formed between the first wall plate 211 and the two side plates 212. The slider body 11 and the force transmission rod 3 are arranged at one end of the receiving space. The slider body 11 and the force transmission rod 3 can move in the receiving space along the axial direction of the receiving space when subjected to force.

[0074] The ratchet structure 22 is disposed in the accommodating space and on one surface of the outer shell 21 . The ratchet structure 22 is used to cooperate with the ratchet curved beam structure to form a toothed ratchet mechanism.

[0075] In this embodiment, the pawl curved beam structure 12 cooperates with the ratchet bar structure of the ratchet groove 2 to form a toothed ratchet mechanism. The pawl curved beam structure 12 can be deformed in three directions, playing the role of intermittent movement of the ratchet, rapid braking and load bearing in the toothed ratchet mechanism.

[0076] In this embodiment, the slider body 11 and the side plate chute 2121 of the ratchet groove 2 cooperate to form a moving pair. There is a certain space between the two, which is a slightly interference fit, and they can slide relative to each other. By adjusting the length and width dimensions of the slider body 11, the frictional resistance of the moving pair formed by the cooperation can be adjusted, and thus the force-bearing condition of the overall structure can be adjusted.

[0077] In this embodiment, the slider body 11 is provided with a mounting hole. The force-transmitting rod 3 is rigid, and the force-transmitting rod extends into the mounting hole. The two are in a tight fit without relative displacement. By adjusting the relative dimensional relationship between the two, the preload of the elastic buffer 4 can be changed.

[0078] In this embodiment, the outer housing 21 further includes a cross beam 213. The cross beam 213 is arranged at one end of the ratchet groove 2 close to the slider 1 with a pawl. The two side plates 212 are connected by the cross beam 213;

[0079] The ratchet groove 2 further includes a ratchet groove buckle 23. The ratchet groove buckle 23 is arranged on the cross beam 213, and the elastic buffer 4 is connected to the ratchet groove buckle 23.

[0080] In this embodiment, one surface of the first wall plate 211 arranged in the accommodation space protrudes away from the other surface to form a ratchet groove inclined surface 2111. The part of the ratchet groove inclined surface 2111 close to the two side plates 212 is inclined; among them,

[0081] When the slider 1 with a pawl moves towards the other end of the accommodation space under force, the pawl curved beam structure 12 is deformed and absorbs energy due to the shape limitation of the ratchet groove inclined surface 2111.

[0082] In this embodiment, the ratchet structure 22 and the pawl curved beam structure 12 of the slider 1 with a pawl cooperate to jointly form a toothed ratchet mechanism. The ratchet structure 22 is a structure with a certain inclined surface, which can guide the deformation of the pawl curved beam structure 12 of the slider 1 with a pawl to realize the functions of intermittent motion, rapid braking, and bearing load.

[0083] In this embodiment, the side plate chute 2121 and the main body structure of the slider 1 with a pawl cooperate to form a moving pair to limit the movement of the slider body 11.

[0084] See Figure 6 , in this embodiment, the force-transmitting rod 3 includes a force-transmitting rod body 31, a limit protrusion 32, and a force-transmitting rod buckle 33. A part of the force-transmitting rod body 31 is arranged in the mounting hole; the limit protrusion 32 is arranged on the force-transmitting rod body 31 and is located in the mounting hole;

[0085] The force-transmitting rod buckle 33 is arranged at one end of the force-transmitting rod body 31 close to the ratchet groove inclined surface 2111, and the other end of the elastic buffer 4 is connected to the force-transmitting rod buckle 33;

[0086] In the assembled state, one end of the force transmission rod body 31 away from the inclined surface 2111 of the ratchet groove can extend into the accommodation space of another energy absorption device.

[0087] In this embodiment, the limiting protrusion 32 is used to contact the slider body of the slider 1 with a pawl to limit its position.

[0088] In this embodiment, the elastic buffer 4 used in the present application realizes the function of absorbing energy of the overall structure by storing energy and assists the overall function of loading and unloading of the structure.

[0089] The energy absorption device of the present application has some excellent mechanical properties such as reusability, multi-stability, and self-adaptability. The structure realizes the functions of multi-stable self-adaptation and energy absorption through the relative movement between the slider with a pawl and the ratchet groove, and provides a reaction force by using an elastic buffer to connect the slider with a pawl and the ratchet groove.

[0090] In this embodiment, in the energy absorption assembly formed by each energy absorption device of the present application, a plurality of energy absorption devices are arranged longitudinally, and two adjacent ratchet grooves are fixedly connected together. The top load and displacement are transmitted longitudinally through the force transmission rod 3. By adjusting the lengths of the two force transmission rods 3, the load transmission condition can be changed. At the same time, by arranging them transversely, the energy absorption system of the present application can be formed.

[0091] In this embodiment, every two energy absorption devices connected end to end are connected by an integral molding method, and each group of energy absorption components is connected to other groups of energy absorption components by an integral molding method.

[0092] It can be understood that the above integral molding method can be welding, casting and other methods.

[0093] The present application also provides an energy absorption device, and the energy absorption device is the energy absorption device as described above.

[0094] The present application also provides a mechanical property test method for the energy absorption device as described above, and the mechanical property test method includes:

[0095] Conduct a static load experiment on the energy absorption device as described above to obtain the force-displacement curve generated by different loading methods and calculate the energy absorption performance;

[0096] Use the numerical simulation software ABAQUS to numerically simulate the static load experiment, and at the same time complete the finite element numerical simulation of the impact and obtain the structure where the main deformation occurs. On this basis, conduct a simulation analysis on the structure where the main deformation occurs; <\

[0097] Theoretical analysis is carried out on the structural members that undergo major deformation. On this basis, the force-displacement curve of the energy-absorbing metamaterial unit is calculated in combination with the finite element numerical simulation results and compared with the results of the static loading experiment.

[0098] For example, a single energy-absorbing device of the present application includes a slider with a pawl (1), a ratchet tooth groove (2), a force transmission rod (3), and an elastic buffer (4), which are respectively a slider with a pawl, a ratchet tooth groove, a force transmission rod, and an elastic body.

[0099] In one embodiment, the slider with a pawl is made by 3D printing using a high-performance nylon material with a tensile modulus (ASTM D638) of 1800 MPa, a tensile strength (ASTM D638) of 48 MPa, a flexural strength (ASTM D790) of 70 MPa, and a flexural modulus (ASTM D790) of 1800 MPa. The specific name of the material is Future 7500 high-performance nylon.

[0100] The ratchet tooth groove is made by 3D printing using a resin material with a tensile modulus (ASTM D638) of 2600 MPa and a tensile strength (ASTM D638) of 52.3 MPa. The specific name of the material is Future 8200Pro resin material.

[0101] The force transmission rod is made of a carbon fiber outer square and inner round tube, with specific dimensions of 4 mm * 4 mm square on the outside and 3 mm * 3 mm round on the inside.

[0102] The alternative options for the elastic buffer are rubber bands with four sizes of diameters of 1 cm, 1.5 cm, 2 cm, and 2.5 cm. Finally, considering the overall volume, a rubber band with a diameter of 1 cm is selected.

[0103] A cyclic loading experiment is carried out on the device using the above materials.

[0104] See Figure 8 , Figure 8 As shown, it is the cyclic loading force-displacement curve, which shows the force-displacement curves of the 1st, 101st, and 201st loadings. It can be seen from the figure that after 201 cycles, the force-displacement curves of the energy-absorbing device unit are basically coincident, and the mechanical properties and energy-absorbing properties are basically unchanged. In the cyclic loading test, the multi-stable energy-absorbing metamaterial has good reusability at the unit level through multiple loadings.

[0105] By changing the geometric parameters of the pawl curved beam and the ratchet tooth groove and the parameters of the elastic body, the overall force-displacement curve can be shifted, or the peak force can be shifted, or the overall slope can be changed, so that the area enclosed by the force-displacement curve changes to adapt to different load conditions, and appropriate parameter matching is carried out according to the strength of the materials used.

[0106] Therefore, after the given load conditions, we can optimize and adjust the parameters of each unit to find the optimal array in this case. Then, similarly, its performance Ashby diagram can be obtained through formula calculation.

[0107] In this embodiment, the static loading experiment mainly includes three parts of experimental content. The first part is the single loading experiment of the multi-stable energy-absorbing metamaterial unit structure, which simulates a single collision or impact in actual situations. In the experiment, only one loading-unloading process is carried out; the second part is the multi-loading experiment of the multi-stable energy-absorbing metamaterial unit structure, which simulates multiple continuous collisions or impacts in actual situations. In the experiment, multiple loading-unloading processes are carried out; the third part is the static cyclic loading experiment of the multi-stable energy-absorbing metamaterial unit structure. The first two parts of the experiment are aimed at obtaining the force-displacement curves of the energy-absorbing metamaterial unit under different loading modes, and then obtaining its mechanical properties and energy-absorbing properties. The third part verifies the repeatability of the energy-absorbing metamaterial through multiple cyclic loadings.

[0108] Finally, it should be pointed out that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. An arresting system for an aircraft, characterized in that, The aircraft arresting system described above includes: An energy absorption system, which consists of two sets. Each energy absorption system includes multiple groups of energy absorption components. The number of energy absorption components is multiple groups, and the groups of energy absorption components are arranged in an array. Each group of energy absorption components includes multiple energy absorption devices connected end to end. The energy absorption device at the first position is called the head energy absorption device, and the energy absorption device at the tail position is called the tail energy absorption device. Each energy absorption device includes a slider (1) with a pawl, a ratchet tooth groove (2), a force transmission rod (3), and an elastic buffer (4). Among them, the force transmission rod (3) is connected to the slider (1) with a pawl. The slider (1) with a pawl is arranged in the ratchet tooth groove (2) and cooperates with the ratchet tooth groove (2) to form a moving pair. The elastic buffer (4) is used to connect the force transmission rod (3) and the ratchet tooth groove (2) respectively. The force transmission rods (3) of the energy absorption devices other than the head energy absorption device are used to connect to another energy absorption device; Two sets of pulley assemblies (5), and one energy absorption system is used to be installed on one pulley assembly (5); An arresting cable (6), one end of the arresting cable (6) is connected to the force transmission rod of an energy absorption system through a pulley assembly (5), and the other end is used to be connected to the force transmission rod of the head energy absorption device of another energy absorption system after passing through another set of pulley assemblies (5); Among them, When the aircraft is taxiing and is blocked by the arresting cable (6), the arresting cable (6) is used to transmit the force exerted by the aircraft to each force transmission rod (3) through the pulley assembly (5). After the force transmission rods (3) are stressed, they drive the elastic buffer (4) to move in the ratchet tooth groove (2). The elastic buffer (4) is used to absorb the energy transmitted by the aircraft to the arresting cable (6) during the movement.

2. The arresting system for an aircraft according to claim 1, characterized in that, The slider (1) with a pawl includes: A slider body (11), the slider body (11) is provided with a mounting hole, and a part of the force transmission rod (3) is arranged in the mounting hole; A pawl curved beam structure (12), the pawl curved beam structure (12) is installed on one surface of the slider body (11), and the pawl curved beam structure (12) is used to cooperate with the ratchet tooth groove (2) to form a toothed ratchet mechanism.

3. The arresting system for an aircraft according to claim 2, characterized in that, The ratchet tooth groove (2) includes: A housing body (21), the housing body (21) includes a first wall plate (211) and two side plates (212) respectively connected to the first wall plate (211). The two side plates (212) are arranged oppositely. Side plate chutes (2121) are respectively arranged on the two side plates (212). A receiving space is formed between the first wall plate (211) and the two side plates (212). The slider body (11) and the force transmission rod (3) are arranged at one end of the receiving space. The slider body (11) and the force transmission rod (3) can move in the receiving space along the axial direction of the receiving space when stressed; A ratchet structure (22), the ratchet structure (22) is arranged in the accommodation space and on one surface of the outer housing (21), and the ratchet structure (22) is used to cooperate with the pawl curved beam structure to form a toothed ratchet mechanism.

4. The arresting system for an aircraft according to claim 3, characterized in that, The outer housing (21) further includes a cross beam (213), the cross beam (213) is arranged at one end of the ratchet groove (2) close to the slider (1) with a pawl, and the two side plates (212) are connected by the cross beam (213); The ratchet groove (2) further includes a ratchet groove buckle (23), the ratchet groove buckle (23) is arranged on the cross beam (213), and the elastic buffer (4) is connected to the ratchet groove buckle (23).

5. The arresting system for aircraft according to claim 4, characterized in that, One surface of the first wall plate (211) arranged in the accommodation space bulges in a direction away from the other surface to form a ratchet groove inclined surface (2111), and the part of the ratchet groove inclined surface (2111) close to the two side plates (212) is inclined; wherein, When the slider (1) with a pawl moves in the direction of the other end of the accommodation space under force, the pawl curved beam structure (12) is deformed and absorbs energy due to the shape limitation of the ratchet groove inclined surface (2111).

6. The arresting system for an aircraft according to claim 5, characterized in that, The transmission rod (3) includes: A transmission rod body (31), a part of the transmission rod body (31) is arranged in the mounting hole; A limit projection (32), the limit projection (32) is arranged on the transmission rod body (31) and is located in the mounting hole; A transmission rod buckle (33), the transmission rod buckle (33) is arranged at one end of the transmission rod body (31) close to the ratchet groove inclined surface (2111), and the other end of the elastic buffer (4) is connected to the transmission rod buckle (33); In the assembled state, the end of the transmission rod body (31) away from the ratchet groove inclined surface (2111) can extend into the accommodation space of another energy absorption device.

7. The arresting system for aircraft according to claim 6, characterized in that, Every two energy absorption devices connected end to end are connected by an integral molding method, and each group of energy absorption components is connected to other groups of energy absorption components by an integral molding method.

8. The arresting system for an aircraft according to claim 7, characterized in that, The pawl curved beam structure (12) includes: A short beam (121), one end of the short beam (121) is a free end, this end is in contact with the ratchet groove (2) and the contact part with the ratchet groove (2) is rounded; A variable cross-section curved beam (122), one end of the variable cross-section curved beam (122) is connected to the other end of the short beam (121), and the cross-sectional area of the end of the variable cross-section curved beam (122) connected to the short beam (121) is smaller than the other end; A fixed end (123), one end of the fixed end (123) is connected to the other end of the variable cross-section curved beam (122), and the fixed end (123) is arranged on the slider body (11).

9. An energy absorption device, characterized in that, The energy absorption device is the energy absorption device according to any one of claims 1 to 8.

10. A method for testing the mechanical properties of an energy absorption device as described in claim 9, characterized in that, The mechanical property test method includes: Performing a static load experiment on the energy absorption device according to claim 9 to obtain the force-displacement curve generated by different loading methods and calculate the energy absorption performance; The numerical simulation software ABAQUS was used to conduct numerical simulations of the static loading experiments. Meanwhile, the finite element numerical simulations of the impact were completed, and the structures with major deformations were obtained. On this basis, the structures with major deformations were subjected to simulation analysis; Theoretical analysis was carried out on the structural components with major deformations. On this basis, combined with the finite element numerical simulation results, the force-displacement curves of the energy-absorbing metamaterial units were calculated and compared with the results of the static loading experiments.

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