Energy-absorbing compression-resistant chiral superstructure, design method and application thereof

Abstract

This disclosure provides an energy-absorbing and compressive-resistant chiral superstructure, its design method, and its application. Relating to the field of energy-absorbing and compressive-resistant structure technology, the energy-absorbing and compressive-resistant chiral superstructure is constructed as an array of periodically arranged representative cells. Each representative cell has a nested double-hexagonal structure, including an outer hexagonal border and an inner hexagonal central body located inside the outer hexagonal border. A connecting ligament extends from each vertex of the inner hexagonal central body, with the other end of the ligament connected to the inner sidewall of the outer hexagonal border. The inner hexagonal central body, the connecting ligament, and the outer hexagonal border are integrally formed, and the inner hexagonal central body exhibits chiral geometric characteristics relative to the outer hexagonal border. This disclosure enables stable energy absorption throughout the entire load-bearing range from low to high loads, significantly improving the overall compressive strength and energy absorption efficiency of the superstructure.

Description

Technical Field

[0001] This specification relates to the field of energy-absorbing and pressure-resistant structural technology, and in particular to an energy-absorbing and pressure-resistant chiral superstructure, its design method, and its application. Background Technology

[0002] In the field of energy-absorbing and compressive strength structures, traditional aircraft design engineering often employs solid stiffened or simple triangular, quadrilateral, or honeycomb structures for the internal structure of wings. This type of design, based on traditional mechanical paradigms, relies on constructing rigid geometric constraints to achieve high specific stiffness and compressive strength. During the cruise phase of stable flight, these structures can rely on the material's yield limit and geometric symmetry to form a stable and reliable static force transmission path, exhibiting good overall stability under static loads. Current research on metamaterial topologies is maturing, providing a technological foundation for the synergistic optimization of lightweight and energy-absorbing performance in aircraft structures.

[0003] Real-world flight environments present complex dynamic loads. Traditional rigid structures can only passively resist instantaneous loads such as impacts and vibrations through elastic material deformation, lacking a macroscopic structural kinetic energy buffering and absorption mechanism. Impact loads cannot be uniformly attenuated, easily leading to stress concentration and brittle instability, threatening the structural safety of aircraft. Chiral structures, as asymmetric metamaterial topological configurations, cannot be superimposed on their mirror images. They consist of a central rigid node and extended flexible ligaments. Under external loads, the elastic bending of the ligaments drives the central node to rotate in tandem. Relying on the unique deformation mode of bending-rotation coupling, they possess large strain capacity and excellent fracture toughness, providing a new direction for energy absorption protection of aircraft. However, there are still significant shortcomings in applying chiral structures to macroscopic engineering: most chiral structure units do not have continuous array properties, resulting in poor mechanical connectivity after splicing, easy geometric interference at the junctions, and loads that cannot be uniformly transferred. This can easily lead to stress concentration at weak points in the connection, causing premature structural failure. Some chiral structures can only achieve energy absorption protection in one direction and do not have multi-directional load-bearing capacity. However, the aerodynamic loads borne by aircraft wings and control surfaces are mostly complex and multi-directional. Conditions such as lateral gusts and large-angle yaws place higher demands on multi-directional structural support, which existing structures cannot meet.

[0004] Therefore, there is an urgent need for a chiral superstructure that combines continuous array arrangement characteristics with multi-directional load-bearing and energy absorption capabilities to meet the engineering application requirements of complex working conditions such as aircraft rudders. Summary of the Invention

[0005] This specification provides an energy-absorbing and pressure-resistant chiral superstructure, its design method, and its application, which can solve the problems existing in related technologies.

[0006] In one aspect, this disclosure provides an energy-absorbing and pressure-resistant chiral superstructure, which is constructed as a periodically arranged array of multiple representative cells; The representative cell has a double hexagonal nested structure, including an outer hexagonal border and an inner hexagonal central body located inside the outer hexagonal border; A connecting ligament extends from each vertex of the inner hexagonal central body, and the other end of the connecting ligament is connected to the inner sidewall of the outer hexagonal frame. The inner hexagonal center, connecting ligaments, and outer hexagonal frame are integrally formed structures, with the inner hexagonal center exhibiting chiral geometric characteristics relative to the outer hexagonal frame.

[0007] The chiral double-nested hexagonal structure disclosed herein can provide controllable energy absorption and compressive strength characteristics. This structure adopts a topological layout in which an outer hexagonal frame nests an inner hexagonal central body, and with the connecting ligaments extending from the vertices of the inner hexagon to the inner side of the outer frame, it constructs a hierarchical force-bearing system that is different from traditional homogeneous superstructures.

[0008] The outer hexagonal frame, as the first load-bearing layer, can first undergo orderly elastic deformation to dissipate initial energy under in-plane / out-of-plane loads. As the load increases further, the connecting ligaments will gradually buckle and deform, and the inner hexagonal chiral center body can rotate and shift in a directional manner with the load direction. Through the multi-stage deformation process of large deformation of the ligaments and relative rotation of the center body, the impact energy is continuously absorbed, avoiding the problem of instantaneous overall instability of traditional structures. This achieves stable energy absorption throughout the entire process from low load to high load, significantly improving the overall compressive bearing capacity and energy absorption efficiency of the superstructure.

[0009] In some examples, both the inner hexagonal center and the outer hexagonal border are regular hexagons, and the ratio of the side length of the inner hexagonal center to the side length of the outer hexagonal border is 1:2.

[0010] With the above proportions, the annular gap between the inner hexagonal center and the outer hexagonal frame is uniform in width, which facilitates the filling of buffer materials, conductive media, or functional adhesive layers. This avoids the problem of excessively wide gaps leading to increased filling costs and exceeding the design threshold for overall structural weight, while also preventing excessively narrow gaps from increasing the difficulty of filling operations and causing uneven distribution of functional materials. The resulting combined structure achieves an optimal balance between rigidity and buffering performance, making it suitable for most mechanical splicing, decoration, and structural load-bearing scenarios.

[0011] In some examples, the inner hexagonal center volume is constructed as a proportionally scaled outer hexagonal border with the same orientation; or, The inner hexagonal center body is constructed as a proportionally scaled outer hexagonal border after being twisted at a preset angle.

[0012] The above structure, through two matching layouts of the inner hexagonal center and the outer hexagonal border, can adapt to different usage scenarios while ensuring the overall stability of the hexagonal structure, taking into account both structural strength and visual display effect, and effectively improving the adaptability and application flexibility of the hexagonal structure.

[0013] In some examples, the extension direction of the connecting ligament forms an angle of 15°-30° with the radial direction of the corresponding vertex of the inner hexagon. When subjected to force, it drives the central body of the inner hexagon to generate a cooperative rotation, and dissipates the impact energy through the bending deformation of the connecting ligament.

[0014] The aforementioned structure connects the ligaments at an angle of 15°-30° to the radial direction of the corresponding vertex of the inner hexagon. Under stress, this causes the central body of the inner hexagon to rotate in tandem, dissipating impact energy through the deformation of the connecting ligaments. Examples of suitable parameters for typical operating conditions of rudder wings are provided: 15°, 20°, 25°, 30° for low-speed general-purpose control surfaces; 16°, 19°, 22°, 26°, 28° for high-speed fighter control surfaces; 18°, 21°, 24°, 27° for large transport aircraft wings; 20°, 22.5°, 25°, 27.5° at the joints of folding rudder wings; and adjustable parameters for precision variable camber rudder wings: 15.2°, 17.8°, 21.3°, 24.6°, 28.9°. Specific parameters require adjustment based on actual conditions and are not limited to the examples mentioned above.

[0015] In some examples, the double hexagonal nested structure is formed by splicing multiple rods, with the inner hexagon having a side length of 10mm±2mm, the outer hexagon having a side length of 20mm±4mm, the connecting ligament having a length of 10mm±2mm, and all rods having a wall thickness of 0.5mm-3mm, representing the cell's out-of-plane stretching height adapting to the rudder core layer size. Under quasi-static compressive load, the energy-absorbing and compressive chiral superstructure is in the linear elastic stage before a displacement of 4 mm ± 1 mm. The displacement of the energy-absorbing and compressive chiral superstructure exceeds the linear elastic stage and reaches the yield point, entering the plateau period. During compression, the maximum principal stress is uniformly distributed in the internal pore network, with no local stress concentration.

[0016] The energy-absorbing and compressive-resistant chiral superstructure disclosed herein exhibits superior specific energy absorption and compressive stress resistance compared to traditional hexagonal honeycomb structures of the same relative density.

[0017] In some examples, the length of the connecting ligament is equal to the side length of the central body of the inner hexagon; One end of the ligament is connected to the vertex of the inner hexagonal center body, and the other end is connected to the vertex or midpoint of the outer hexagonal border.

[0018] The above structure sets the length of the connecting ligament to be equal to the side length of the inner hexagonal central body, while limiting one end of the connecting ligament to the vertex of the inner hexagonal central body and connecting the other end to the vertex or midpoint of the outer hexagonal border.

[0019] In some examples, in the representative cell, the connecting ligaments are distributed in a rotationally symmetric manner with the center of the inner hexagonal centrosome as the center of symmetry, and the extension direction of the connecting ligaments deviates from the radial direction of the inner hexagonal centrosome, forming a chiral topology with a rotational tendency.

[0020] The above can form a rotational chiral structure. When subjected to axial tensile and compressive loads, the radially distributed connecting ligaments will synchronously generate a rotational tendency, causing the cell as a whole to undergo controllable negative Poisson's ratio deformation. Compared with ordinary regular hexagonal cells, the stiffness can be continuously adjusted over a wider strain range, adapting to the stress requirements of different load levels in buffering and vibration reduction scenarios. At the same time, the elastic potential energy stored during rotation can form a multi-steady-state effect, which can spontaneously return to the initial shape after the load is removed, or switch to a preset deformation configuration as needed, improving the reconfigurability and cycle life of the structure.

[0021] In some examples, the energy-absorbing and pressure-resistant chiral superstructures are constructed using a macroscopic periodic array assembly method, with the outer hexagonal borders of adjacent representative cells overlapping to form a continuous two-dimensional planar filling structure.

[0022] The above-mentioned assembly method with overlapping edges completely eliminates the gaps between cells, achieving greater utilization of the planar space of the chiral superstructure (even 100% utilization). Compared with discrete assembly structures with non-overlapping edges, more energy-absorbing cells can be arranged on the same area of ​​the substrate, resulting in a larger overall load-bearing area, more uniform stress distribution, and the ability to avoid premature structural failure caused by local stress concentration, thereby improving the overall ultimate load-bearing capacity of the superstructure.

[0023] In some examples, the representative cells have a uniform height along a direction perpendicular to the two-dimensional plane, forming a three-dimensional skeletal structure.

[0024] The uniform height design ensures the consistency of mechanical properties of each section of the three-dimensional structure, avoiding load shift and local instability caused by uneven height. When subjected to impact loads perpendicular to the plane, all cells can undergo controllable plastic deformation synchronously, giving full play to the chiral energy absorption characteristics of each cell. The total energy absorption is increased by more than 30% compared to the two-dimensional planar structure, resulting in better buffering and impact resistance performance.

[0025] Secondly, this disclosure also provides a design method for an energy-absorbing and compressive-resistant chiral superstructure, applied to the aforementioned energy-absorbing and compressive-resistant chiral superstructure. The design method includes the following steps: The basic six-ligament chiral ring structure is set up, which consists of a central geometry and an extended connecting ligament; The basic six-ligament chiral ring structures are arranged in an alternating manner and interconnected in a two-dimensional plane to form a complex chiral superstructure network with regular pore arrangement. Using regular hexagons as boundaries, the representative cell of the bihexagonal nested structure is obtained by cutting and defining the shape from the complex chiral superstructure network; Using the representative cell as the basic unit, the cells are arranged in a common-edge translational manner in all directions within a two-dimensional space to assemble a macroscopic continuous superstructure array.

[0026] The above design method, through its progressive steps from core unit construction to overall network formation, and then to standardized cell shaping and macroscopic array assembly, gradually constructs a chiral superstructure that combines lightweight characteristics with excellent energy absorption and compressive strength. Each step sequentially realizes the construction of core energy-absorbing units, the construction of a globally interconnected energy-absorbing network, the shaping of standardized load-bearing cells, and the assembly of macroscopically controllable structures. This fully leverages the nonlinear deformation and progressive energy absorption characteristics of chiral structures while also taking into account the feasibility of macroscopic structural design and fabrication. Ultimately, it yields an energy-absorbing and compressive-resistant chiral superstructure with stable energy absorption, excellent compressive strength, and adaptability to different application scenarios.

[0027] Thirdly, this disclosure also provides a rudder structure, the inner core of which is filled with the energy-absorbing and pressure-resistant chiral superstructure as described above. The energy-absorbing and pressure-resistant chiral superstructure serves as a load-bearing skeleton to support the rudder skin and withstand aerodynamic loads. It maintains stable energy-absorbing and pressure-resistant performance under both positive vertical loads and lateral transverse loads, without local stress concentration.

[0028] The chiral superstructure rudder disclosed herein can dissipate energy step by step through the rotational deformation of chiral micro-elements. Under extreme dynamic load impacts such as bird strikes and airflow disturbances, its energy absorption efficiency is improved by more than 30% compared with traditional structures. It can effectively avoid local pitting, cracking or even fracture damage to the rudder skin and significantly improve the impact fatigue life of the rudder.

[0029] Fourthly, this disclosure also provides an aircraft equipped with the aforementioned rudder structure. The rudder structure achieves synergistic optimization of lightweighting and load-bearing performance through an internal energy-absorbing and pressure-resistant chiral superstructure, reducing the overall energy consumption of the aircraft while improving flight safety under sudden aerodynamic impact conditions.

[0030] The energy-absorbing and pressure-resistant chiral superstructure disclosed herein can evenly distribute the aerodynamic load borne by the rudder through the rotational deformation of the internal chiral units, avoid structural cracking caused by local stress concentration, and significantly improve the fatigue service life of the rudder. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of this specification, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this specification. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0032] Figure 1 A schematic diagram of a representative cell in an energy-absorbing, pressure-resistant chiral superstructure provided according to an embodiment of the present disclosure is shown.

[0033] Figure 2 This illustration shows another structural schematic of a representative cell in an energy-absorbing, pressure-resistant chiral superstructure provided according to an embodiment of the present disclosure.

[0034] Figure 3 A schematic diagram of the structure following a periodically arranged array of representative cells according to an embodiment of the present disclosure is shown.

[0035] Figure 4 A schematic diagram illustrating the transformation process during the formation of an energy-absorbing, pressure-resistant chiral superstructure according to an embodiment of the present disclosure is shown.

[0036] Figure 5 and Figure 6 The quasi-static compressive mechanical properties quantification curves of an energy-absorbing, compressive-resistant chiral superstructure provided according to an embodiment of the present disclosure are shown.

[0037] Figure 7 The diagram shows a finite element stress cloud diagram of a macroscopic array structure of an energy-absorbing and compressive chiral superstructure provided according to an embodiment of the present disclosure under compression conditions.

[0038] Figure 8 and Figure 9 An engineering assembly model of an energy-absorbing and pressure-resistant chiral superstructure infill, such as the NACA0012 standard rudder wing, is shown.

[0039] Figure label: 100, representing a cell; 110, outer hexagonal border; 120, inner hexagonal center body; 130, connecting ligament; 200, rudder structure. Detailed Implementation

[0040] The following description provides specific application scenarios and requirements for this specification, intended to enable those skilled in the art to make and use the contents of this specification. Various partial modifications to the disclosed embodiments will be apparent to those skilled in the art, and the general principles defined herein can be applied to other embodiments and applications without departing from the spirit and scope of this specification. Therefore, this specification is not limited to the embodiments shown, but rather to the widest scope consistent with the claims.

[0041] The terminology used herein is for the purpose of describing particular exemplary embodiments only and is not restrictive. For example, unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “the” used herein may also include the plural forms. When used in this specification, the terms “comprising,” “including,” and / or “containing” mean that the associated feature, integer, step, operation, element, and / or component is present, but do not preclude the presence of one or more other features, integers, steps, operations, elements, components, and / or groups, or that other features, integers, steps, operations, elements, components, and / or groups may be added to the system / method.

[0042] Considering the following description, these and other features of this specification, as well as the operation and function of the related components of the structure, and the economy of assembly and manufacture of the parts, can be significantly improved. All of these form part of this specification with reference to the accompanying drawings. However, it should be clearly understood that the drawings are for illustrative and descriptive purposes only and are not intended to limit the scope of this specification. It should also be understood that the drawings are not drawn to scale.

[0043] The flowcharts used in this specification illustrate operations implemented according to some embodiments of this specification. It should be clearly understood that the operations in the flowcharts may not be implemented in a sequential order. Instead, the operations may be implemented in reverse order or simultaneously. Furthermore, one or more additional operations may be added to the flowcharts. One or more operations may be removed from the flowcharts.

[0044] In this specification, "X includes at least one of A, B, or C" means that X includes at least A, or X includes at least B, or X includes at least C. That is, X can include only one of A, B, and C, or any combination of A, B, and C, as well as other possible content / elements. Any combination of A, B, and C can be A, B, C, AB, AC, BC, or ABC.

[0045] In this specification, unless explicitly stated otherwise, the relationships between structures can be direct or indirect, complete or partial. For example, when describing "A is connected to B," unless explicitly stated that A and B are directly connected, it should be understood that A can be directly connected to B or indirectly connected to B. Similarly, when describing "A is above B," unless explicitly stated that A is directly above B (AB is adjacent and A is above B), it should be understood that A can be directly above B or indirectly above B (AB is separated by other elements, and A is above B). Furthermore, when describing "A is inside B," unless explicitly stated that A is entirely inside B, it should be understood that A can be entirely inside B or partially inside B. And so on.

[0046] The energy-absorbing and pressure-resistant chiral superstructure disclosed herein, its design method, and its application belong to the field of lightweight and impact-resistant protection technology for aerospace structures. It mainly addresses the structural optimization needs of key load-bearing components such as aircraft rudders and wings, and can significantly improve the dynamic impact energy dissipation capability while ensuring the specific stiffness of the structure, thereby reducing the risk of structural failure under extreme conditions.

[0047] In actual aircraft service, structures such as control wings not only need to withstand stable aerodynamic loads during the cruise phase, but also need to cope with sudden strong impact conditions such as gusts, high-angle maneuvers, and bird strikes. Traditional honeycomb and stiffened structures are limited by a single rigid load-bearing mode, and are prone to stress concentration and brittle fracture under multi-directional complex loads, making it difficult to meet the requirements of lightweighting and multi-condition load-bearing. Chiral metamaterials, with their unique bending-rotation coupling deformation mechanism, provide a new technical path to solve this contradiction. However, existing chiral structures generally have defects such as discontinuous array splicing and insufficient unidirectional load-bearing capacity, which limit their large-scale engineering applications in the aerospace field.

[0048] This disclosure provides an energy-absorbing and pressure-resistant chiral superstructure, its design method, and its application. Through a double hexagonal nested topological configuration design, a seamless common-edge array arrangement of chiral unit cells is achieved, which takes into account both in-plane quasi-isotropic load-bearing capacity and efficient impact energy dissipation characteristics. It can be directly used as a core layer to fill the interior of aircraft rudder wings, providing a feasible solution for the synergistic optimization of lightweight and safety in aerospace structures.

[0049] To facilitate the description of the design principles and mechanical properties of the energy-absorbing and compressive chiral superstructure, the geometric parameters, load directions, and other descriptions in this specification are based on the regular hexagonal coordinate system of the representative cell. The structural performance is quantitatively explained in conjunction with the results of finite element simulation and mechanical tests. The technical solution of this disclosure is explained in detail below with reference to the accompanying drawings.

[0050] Reference Figures 1 to 4 In one aspect, this disclosure provides an energy-absorbing and pressure-resistant chiral superstructure, which is constructed as an array of multiple periodically arranged representative cells 100; The cell 100 has a double hexagonal nested structure, including an outer hexagonal border 110 and an inner hexagonal central body 120 located inside the outer hexagonal border 110; A connecting ligament 130 extends from each vertex of the inner hexagonal central body 120, and the other end of the connecting ligament 130 is connected to the inner sidewall of the outer hexagonal frame 110. The inner hexagonal center body 120, the connecting ligament 130, and the outer hexagonal frame 110 are integrally formed structures, and the inner hexagonal center body 120 has chiral geometric characteristics relative to the outer hexagonal frame 110.

[0051] The chiral double-nested hexagonal structure disclosed herein can provide controllable energy absorption and compressive strength characteristics. This structure adopts a topological layout in which an outer hexagonal frame 110 nests an inner hexagonal central body 120, and is combined with connecting ligaments 130 extending from the vertices of the inner hexagon to the inner side of the outer frame, thus constructing a hierarchical force system that is different from traditional homogeneous superstructures.

[0052] Among them, the outer hexagonal frame 110 serves as the first load-bearing layer, which can first undergo orderly elastic deformation to dissipate initial energy under in-plane / out-of-plane loads. When the load is further increased, the connecting ligament 130 will gradually buckle and deform, and the inner hexagonal chiral center body can rotate and shift in a directional manner with the load direction. Through the multi-stage deformation process of large deformation of the ligament and relative rotation of the center body, the impact energy is continuously absorbed, avoiding the problem of instantaneous overall instability of traditional structures. This achieves stable energy absorption in all stages from low load to high load, significantly improving the overall compressive bearing capacity and energy absorption efficiency of the superstructure.

[0053] The aforementioned periodic array layout allows for the uniform and customizable arrangement of multiple representative cells in a periodic array of 100, enabling the overall mechanical properties of the superstructure (short for energy-absorbing and compressive-resistant chiral superstructure) to exhibit uniform and stable characteristics in all directions, thus avoiding a sharp drop in overall load-bearing capacity caused by local structural defects. The cell size, the cross-sectional thickness and length of the connecting ligament 130, and the size ratio of the inner and outer hexagons can be adjusted according to the load requirements of the actual application scenario. This allows for convenient changes to the overall stiffness, yield strength, and energy absorption threshold of the superstructure, adapting to the compressive energy absorption requirements of different scenarios, and combining performance stability with design flexibility.

[0054] The one-piece molding structure can improve structural reliability and process applicability. The inner hexagonal center body 120, the connecting ligament 130 and the outer hexagonal frame 110 are integrally molded, eliminating the stress concentration defects at the splicing parts in the assembled structure, avoiding premature fracture failure of the connection parts during the stress process, and improving the overall service reliability of the structure. The above topology is suitable for various integrated processing technologies such as 3D printing and injection molding, without additional assembly processes, which can reduce processing costs and manufacturing errors, and facilitate large-scale industrial production.

[0055] The chiral geometry enhances energy dissipation capabilities. The chiral geometry design of the inner hexagonal center body 120 relative to the outer hexagonal frame 110 induces asymmetric deformation of the connecting ligaments 130 and continuous rotation of the inner center body when the structure is subjected to load. Compared with a symmetrical structure without chirality, an additional rotational deformation energy dissipation mechanism can be introduced. Under impact load, the energy dissipation process can be prolonged, increasing the energy absorption capacity per unit mass of the structure and exhibiting superior performance in lightweight energy-absorbing protection scenarios.

[0056] Specifically, the energy-absorbing and compressive-resistant chiral superstructure is a periodic array structure, formed by several identical representative cells 100 arranged repeatedly in a plane according to a fixed periodic pattern. It can be expanded into an overall structure of any size according to application requirements, ensuring that the mechanical properties remain consistent at any position.

[0057] The aforementioned single representative cell 100 has a double hexagonal nested structure: The outermost layer is an outer hexagonal border 110, which constitutes the outer bearing boundary of the unit cell. It is directly adjacent to or connected to the outer border of the adjacent cell, and together they form the overall bearing skeleton of the superstructure. An inner hexagonal central body 120 is set at the geometric center of the outer hexagonal border 110. The inner hexagon is a solid or thin-walled hollow central structure, which is concentrically arranged with the outer hexagon and has an offset angle relative to the outer hexagon to form chiral geometric features. Each of the six vertices of the inner hexagon extends outward with a connecting ligament 130. The outer end of each connecting ligament 130 is connected to the inner sidewall of the outer hexagonal frame 110, stably connecting the inner hexagonal central body 120 and the outer hexagonal frame 110 into a whole, forming a three-level force-bearing topology of "outer frame - force-transmitting ligament - central chiral body".

[0058] The integrated configuration means that the entire inner hexagonal central body 120, the six connecting ligaments 130, and the outer hexagonal frame 110, which represent cell 100, are a continuous structure formed as one piece. There are no splicing seams between the three. When the structure is under stress, the load can be smoothly transferred from the outer frame to the central body through the ligaments. There are no weak connection points, which ensures the continuity and stability of the structural deformation process.

[0059] The disclosed double-hexagonal nested chiral superstructure can significantly improve energy absorption performance and compressive load-bearing capacity. Compared with traditional hexagonal honeycomb structures and square chiral structures, under the same relative density conditions, the quasi-static compression ratio energy absorption of the energy-absorbing and compressive chiral superstructure is improved (e.g., by about 30%-45%), the plateau stress is improved (e.g., by about 20%-35%), and the energy absorption efficiency under low-velocity impact loads is improved (e.g., by about 28%). Due to its chiral geometry, the superstructure can achieve a smoother and more stable load response during compression by gradually buckling the connecting ligament 130 and rotating the inner hexagonal central body 120, thus avoiding the stress drop phenomenon that is prone to occur in traditional porous structures and significantly improving the stability of compressive deformation. The one-piece molded double nested structure gives the superstructure better resistance to damage. After multiple cycles of compression, the residual deformation is reduced compared to traditional honeycomb structures of the same density (for example, it can be reduced by about 20%-25%), and it has better durability in the fields of buffer protection and impact resistance.

[0060] When adjusting the structural parameters for different application scenarios, the above-mentioned energy-absorbing and pressure-resistant chiral superstructure can flexibly adjust the energy absorption range while maintaining its lightweight characteristics. It can be adapted to the buffer protection of small electronic devices, as well as meet the load-bearing and energy absorption requirements of large impact-resistant components in the fields of rail transit and aerospace.

[0061] Furthermore, referring to Figure 4 The flowchart illustrating the complete design and derivation process of the energy-absorbing superstructure is shown. (Attached) Figure 4 This paper fully demonstrates the four-step topology design process of the chiral superstructure disclosed in this paper, from biomimetic prototype to array arrangement, standard unit cell extraction, and macroscopic finished product, which solves the defects of discontinuous splicing and stress concentration in traditional chiral unit cell.

[0062] Figure 4 (a) can be a basic biomimetic chiral unit cell prototype, or it can be one of the implementations representing cell 100. This part can be derived from the microscopic chiral topology of nature, and is a six-ligament eccentric cantilever chiral ring; the geometric parameters are exemplarily: the inner hexagon side length is 10 mm, the ligament length is 10 mm, the wall thickness is 1 mm, and the height is 5 mm.

[0063] The mechanical mechanism representing cell 100: under pressure / load, the flexible ligament bends and the central hexagon rotates synchronously, relying on bending-torsional coupling deformation to absorb impact kinetic energy, which is the core basic configuration for energy absorption of this structure.

[0064] Figure 4 (b) Multi-cell staggered pre-arrangement network. This part is about... Figure 4 In section (a), basic chiral units are interlaced in two dimensions to form a disordered porous network with multiple colors; blue boxes mark the periodic hexagonal regions that can be extracted. If the units in this part are directly spliced, the mechanical connectivity is poor and geometric interference is easy, making mass production and finite element simulation impossible. Therefore, it is necessary to standardize and extract new cells.

[0065] Figure 4 (c) shows the improved and finalized double-hexagonal nested standard unit cell. This part is from... Figure 4 In the network (b), the hexagonal boundary is extracted and the standard cell of the double-layer hexagonal nested structure is reconstructed: the outer hexagon has a side length of 20mm, the inner hexagon has a side length of 10mm, and the link length is 10mm.

[0066] The improved representative cell 100 retains the chiral rotational energy absorption characteristics, while maintaining regular geometric boundaries, supporting seamless common-edge arrays, eliminating splicing stress concentration, and adapting to large-scale processing and mechanical calculations.

[0067] Figure 4 (d) Macroscopic periodic continuous superstructure array. Figure 4In the middle (c) standard unit cell, a two-dimensional omnidirectional common-edge translation array is formed, and the borders of adjacent unit cells are merged to form a whole porous skeleton without breaks and with continuous mechanical pathways.

[0068] The above structure distributes the overall load evenly and has multi-directional compressive strength in the plane. It can be directly cut and filled into the interior of the rudder wing structure 200.

[0069] In some examples, both the inner hexagonal center body 120 and the outer hexagonal border 110 are regular hexagons, and the ratio of the side length of the inner hexagonal center body 120 to the side length of the outer hexagonal border 110 is 1:2.

[0070] Under the above proportions, the width of the annular gap reserved between the inner hexagonal center body 120 and the outer hexagonal frame 110 is uniform, which facilitates the filling of buffer materials, conductive media or functional adhesive layers. It will not cause the filling cost to increase or the overall structural weight to exceed the design threshold due to the gap being too wide, nor will it cause the filling operation to become more difficult or the functional materials to be unevenly distributed due to the gap being too narrow. The final combined structure achieves the optimal balance between rigidity and buffer performance, which is suitable for the use needs of most mechanical splicing, decoration and structural load-bearing scenarios.

[0071] In other preferred examples, the ratio of the side length of the inner hexagonal center body 120 to the side length of the outer hexagonal border 110 can also be set to 1:1.5. Under this ratio, the width of the annular gap is smaller, the solid proportion of the overall structure is higher, which can provide stronger structural support strength, while the overall size will not increase excessively. This is suitable for lightweight structural scenarios with high load-bearing requirements and limited installation space, such as truss construction, outdoor camping equipment connectors, and drone frame honeycomb cores. Under the premise of controlling the overall weight, the structural bending and compressive performance can be improved, such as by 12%-18%.

[0072] When applied to scenarios requiring high buffering and energy absorption effects, the ratio of the side length of the inner hexagonal center body 120 to the side length of the outer hexagonal border 110 is preferably 1:2.5. With this ratio, the annular gap is wider, allowing for the filling of more highly elastic buffer material or energy-absorbing porous material. This effectively absorbs impact loads and disperses vibration energy, making it suitable as a honeycomb unit for anti-collision components and shock-absorbing pads. Compared to a 1:2 ratio structure, its energy absorption capacity can be increased by more than 25%, while still maintaining the advantages of uniform stress distribution and low stress concentration inherent in regular hexagonal structures.

[0073] For special scenarios where the central body's function needs to be maximized and the border only serves a positioning and fixing function, the ratio of the side length of the inner hexagonal central body 120 to the side length of the outer hexagonal border 110 can be set to 1:1.2. With this ratio, the gap is extremely narrow, and only a small amount of adhesive material is needed to achieve a fixed connection between the central body and the border. The functional area ratio of the overall structure can reach more than 85%, which is suitable for use in scenarios with high requirements for functional area ratio, such as filter honeycomb and catalyst carrier honeycomb. It can improve the effective working area and reduce the performance loss caused by ineffective structure while ensuring structural stability.

[0074] If applied to modular scenarios that can be disassembled and spliced, the ratio of the side length of the inner hexagonal center body 120 to the side length of the outer hexagonal border 110 can also be set to 1:3. Under this ratio, the wide annular gap can reserve space for the installation of splicing buckles and connecting fasteners. Multiple hexagonal units can be quickly spliced ​​and fixed without additional damage to the center body or border. The assembled module has high overall flatness, and the splicing gap error can be controlled within 0.5mm. It is convenient to flexibly adjust the overall area and shape according to the usage requirements, and adapt to the usage requirements of modular display walls, reconfigurable outdoor flooring, and other scenarios.

[0075] The aforementioned range of proportions can be flexibly selected according to the performance requirements of different application scenarios. Compared with a single-proportion regular hexagonal honeycomb structure, it can adapt to more differentiated usage requirements such as load-bearing, buffering, functional carrier, and modular splicing. At the same time, it always maintains the advantages of the regular hexagonal structure, such as uniform stress, resistance to deformation, and high splicing fit. While improving structural adaptability, it does not add extra processing complexity. Common CNC cutting, injection molding, and 3D printing processes can all be directly adapted to different proportion processing needs, resulting in low production costs and strong versatility.

[0076] In some examples, the inner hexagonal center 120 is constructed as a proportionally scaled outer hexagonal border 110 with the same orientation; or, The inner hexagonal center body 120 is constructed as an outer hexagonal border 110 that is proportionally scaled after being twisted at a preset angle.

[0077] The above structure, through two matching layouts of the inner hexagonal center body 120 and the outer hexagonal border 110, can adapt to different usage scenarios while ensuring the overall stability of the hexagonal structure, taking into account both structural strength and visual display effect, and effectively improving the adaptability and application flexibility of the hexagonal structure.

[0078] When the inner hexagonal center body 120 is constructed as a proportionally scaled outer hexagonal border 110 with the same orientation, the contour edges of the inner and outer structures remain parallel and aligned. The stress of the entire hexagonal structure can be evenly distributed and transferred along the parallel edges, avoiding the problem of stress concentration and greatly improving the overall load-bearing capacity and deformation resistance of the structure. At the same time, the regular and aligned contours are also easy to process and manufacture, reducing the difficulty of mold development and production assembly, and are suitable for application scenarios such as load-bearing frames and mechanical connection bases with high structural strength requirements.

[0079] When the inner hexagonal center body 120 is constructed as an outer hexagonal border 110 and scaled proportionally after being twisted at a preset angle, the vertices and edges of the inner and outer hexagons are arranged in an alternating manner, forming multiple symmetrically distributed hollow partitions. This not only reduces the use of raw materials and lowers the overall weight and production cost while ensuring structural strength, but also creates a star-shaped symmetrical visual effect by utilizing the alternating contours. This is suitable for application scenarios that require aesthetic design, such as decorative components, display panels, and signage bases, and meets differentiated design and usage needs.

[0080] In some examples, the extension direction of the connecting ligament 130 forms an angle of 15°-30° with the radial direction of the corresponding vertex of the inner hexagon. When subjected to force, it drives the central body 120 of the inner hexagon to generate cooperative rotation, and dissipates the impact energy through the bending deformation of the connecting ligament 130.

[0081] The aforementioned connecting ligament 130 extends at an angle of 15°-30° to the radial direction of the corresponding vertex of the inner hexagon. Under stress, it drives the central body 120 of the inner hexagon to rotate in tandem, dissipating impact energy through the deformation of the connecting ligament 130. Examples of suitable parameters for typical operating conditions of rudder wings are provided: 15°, 20°, 25°, 30° for low-speed general-purpose control surfaces; 16°, 19°, 22°, 26°, 28° for high-speed fighter control surfaces; 18°, 21°, 24°, 27° for large transport aircraft wings; 20°, 22.5°, 25°, 27.5° at the joints of folding rudder wings; and adjustable parameters for precision variable camber rudder wings: 15.2°, 17.8°, 21.3°, 24.6°, 28.9°. Specific parameters require adjustment based on actual conditions and are not limited to the examples mentioned above.

[0082] Furthermore, when the extension direction of the connecting ligament 130 forms an angle of 30°-45° with the radial direction of the corresponding vertex of the inner hexagon, the bending deformation margin of the connecting ligament 130 is further expanded. During the stress process, the cooperative rotation stroke of the inner hexagonal central body 120 is longer, and the impact energy is gradually decomposed during the continuous deformation process, which is suitable for medium and high magnitude impact loads, while avoiding ligament stress concentration caused by excessive deformation amplitude. When the angle is in the range of 45°-60°, the force component of the connecting ligament 130 takes into account both deformation energy absorption and structural constraint. While driving the central body to rotate and dissipate energy, it can constrain the center through the lateral component force of the ligament. The offset of the body prevents irreversible displacement of the center position after impact, improving the structure's recovery capability; when the included angle is in the range of 60°-75°, the proportion of tangential force is further increased, and the rotation speed of the central body under impact load is faster, enabling energy dissipation to start in the early stage of impact contact, significantly reducing the initial peak value of impact, and adapting to the working scenario of instantaneous large impact; when the included angle is in the range of 75°-90°, the connecting ligament 130 is arranged almost tangentially, and after being stressed, almost all the load is converted into ligament bending deformation and central body rotation torque, and the energy dissipation efficiency reaches its peak. At this time, the stiffness of the structure is lower, which is suitable for the buffering and energy absorption requirements of low-frequency large deformation.

[0083] Multiple sets of ligaments 130 with different included angles can also be used in combination. By matching different ranges of included angles at different vertices of the inner hexagon, the structure can match the optimal energy absorption characteristics under impact from different directions. When facing impact loads from any direction, the deformation of the corresponding area of ​​the ligaments 130 and the directional rotation of the central body can achieve all-round impact energy dissipation, further expanding the applicable scenarios of the structure.

[0084] In some examples, the double hexagonal nested structure is formed by splicing multiple rods, with the inner hexagon having a side length of 10mm±2mm, the outer hexagon having a side length of 20mm±4mm, the connecting ligament 130 having a length of 10mm±2mm, and all rods having a wall thickness of 0.5mm-3mm, representing the cell 100 being stretched in the out-of-plane direction to adapt to the rudder core layer size. Under quasi-static compressive load, the energy-absorbing and compressive chiral superstructure is in the linear elastic stage before a displacement of 4 mm ± 1 mm. The displacement of the energy-absorbing and compressive chiral superstructure exceeds the linear elastic stage and reaches the yield point, entering the plateau period. During compression, the maximum principal stress is uniformly distributed in the internal pore network, with no local stress concentration.

[0085] Compared with traditional hexagonal honeycomb structures of the same relative density, the energy-absorbing and compressive plateau stress performance of this disclosed chiral superstructure is superior. The specific advantages and corresponding parameter ranges are illustrated below: The energy absorption performance of this structure is improved, reaching 12J / g-28J / g, which is 35%-75% higher than that of traditional hexagonal honeycomb structures at the same relative density. When the wall thickness of all members is in the range of 0.8mm-2mm, the side length of the inner hexagon is 8mm-12mm, and the side length of the outer hexagon is 16mm-24mm, the energy absorption can be stably maintained in the optimal range of 18J / g-25J / g, which is suitable for the energy absorption requirements of low-speed to medium-speed impact scenarios. If the wall thickness is less than 0.5mm, the members are prone to premature brittle fracture, and the energy absorption will drop to below 8J / g. If the wall thickness is greater than 3mm, the relative density of the structure is too high and the porosity is insufficient, and the energy absorption will also drop to below 10J / g, which cannot meet the requirements for lightweight energy absorption.

[0086] Uniform stress distribution and suppression of local failure: The double hexagonal nesting combined with the connecting ligament 130 in this structure results in a maximum principal stress variation coefficient of less than 0.18 throughout the compression cycle, far lower than the 0.35-0.45 of traditional hexagonal honeycomb structures, with no obvious local stress concentration. When the length of the connecting ligament 130 is in the range of 8mm-12mm, the stress uniformity is optimal, and the variation coefficient can be controlled in the range of 0.12-0.16. At this time, the structural yield failure is achieved by the successive buckling plastic deformation of the entire ligament, avoiding the sharp drop in overall load-bearing capacity caused by premature fracture of local members. If the length of the connecting ligament 130 exceeds the range of 8mm-12mm, excessive or insufficient ligament stiffness will lead to stress concentration at the inner hexagonal node, and the maximum principal stress variation coefficient will increase to above 0.25, significantly increasing the risk of premature local failure.

[0087] The controllable platform stress range adapts to the load-bearing requirements of the control wings. The platform stress of this structure is stable in the range of 1.2MPa-8.5MPa, and the platform strain range can reach 0.5-0.7, which is much larger than the 0.3-0.45 of traditional honeycomb structures, providing a longer stable energy-absorbing compression stroke. Specifically, when the wall thickness is increased from 0.5mm to 3mm, the platform stress can be linearly increased from 1.2MPa to 8.5MPa. The parameters can be adjusted according to the actual load-bearing requirements of the control wings: when applied to the control wings of small low-speed UAVs, a wall thickness of 0.5mm-1mm can be selected to obtain a low platform stress of 1.2MPa-3MPa, improving the buffering and vibration reduction performance of the control wings; when applied to the control wings of high-speed aircraft, a wall thickness of 1.5mm-3mm can be selected to obtain a high platform stress of 4MPa-8.5MPa, meeting the requirements for high-strength impact resistance.

[0088] The linear elastic stage performance adapts to the daily operating requirements of the rudder. Before a displacement of 4mm±1mm, the structure is in the linear elastic stage, corresponding to a nominal compressive strain range of 8%-13%. This range just covers the elastic deformation range caused by aerodynamic loads during daily flight of the rudder. The elastic modulus in the linear elastic stage is in the range of 50MPa-320MPa. The stiffness of the rudder shell can be matched by adjusting the wall thickness parameters to avoid interface debonding caused by stiffness mismatch, thus ensuring the integrity of the overall rudder structure and the stability of the aerodynamic shape.

[0089] The connecting ligament 130 can also be called an eccentric cantilever ligament. Because the eccentrically arranged ligament can generate additional rotational torque when subjected to force, it drives the central body to rotate and absorb energy. Unlike the traditional radially connected ligament structure, it can convert more impact energy into deformation energy rather than elastic strain energy, which greatly improves energy dissipation efficiency.

[0090] In some specific preparation embodiments, this energy-absorbing and compression-resistant chiral superstructure was fabricated using photosensitive resin via 3D printing. The representative cell 100 parameters are: inner hexagonal side length 10mm, outer hexagonal side length 20mm, inner hexagonal torsional offset angle relative to the outer hexagon 30°, connecting ligament 130 extension direction with corresponding vertex radial angle 25°, all member wall thickness 1.2mm, and overall relative density 0.18. A quasi-static compression test was conducted on the sample of this embodiment. The test results showed that its plateau stress was 1.62MPa and its specific energy absorption was 21.3J / g. In comparison, the plateau stress of a traditional regular hexagonal honeycomb sample with the same relative density was 1.18MPa and its specific energy absorption was 13.6J / g. The structure of this embodiment showed an increase in plateau stress of approximately 37.3% and an increase in specific energy absorption of approximately 56.6%, meeting the expected performance improvement.

[0091] In another specific embodiment, this energy-absorbing and pressure-resistant chiral superstructure is fabricated from aluminum alloy using CNC cutting. The representative cell 100 parameters are: inner hexagonal side length 9mm, outer hexagonal side length 22.5mm, ratio 1:2.5, inner hexagonal offset angle relative to outer hexagon 15°, connecting ligament 130 extension direction radial angle with corresponding vertex radial angle 40°, all members wall thickness 2mm, and polyurethane foam cushioning material filling the annular gaps. The overall relative density is 0.22. After a drop-weight impact test, the energy absorption efficiency of this embodiment reaches 0.82, with a residual deformation of 3.2%. Under the same conditions, the energy absorption efficiency of a traditional aluminum alloy honeycomb sample of the same density is 0.65, with a residual deformation of 4.1%. This embodiment shows an approximately 26% improvement in energy absorption efficiency and a approximately 22% reduction in residual deformation, significantly improving cushioning durability.

[0092] In some examples, the length of the connecting ligament 130 is equal to the side length of the inner hexagonal central body 120; One end of the connecting ligament 130 is connected to the vertex of the inner hexagonal central body 120, and the other end is connected to the vertex or the midpoint of the edge of the outer hexagonal border 110.

[0093] The above structure, by setting the length of the connecting ligament 130 to be equal to the side length of the inner hexagonal central body 120, and by limiting one end of the connecting ligament 130 to the vertex of the inner hexagonal central body 120 and the other end to the vertex or midpoint of the outer hexagonal border 110, can achieve the following beneficial effects: Ensuring uniform and stable stress distribution: Based on the geometric characteristics of a regular hexagon, the connecting ligaments 130 of equal length allow the stress transmitted from the inner hexagonal center body 120 to the outer hexagonal frame 110 to be evenly distributed, avoiding local stress concentration caused by inconsistent ligament lengths, preventing local structural fatigue fracture during long-term use, and improving the overall load-bearing capacity and structural stability of the structure.

[0094] Simplified production process: The uniform length of the connecting ligament 130 reduces the difficulty of dimensional calibration during processing. Manufacturers do not need to customize ligament parts of different lengths for different positions. They only need to process connecting components of the same specification to fit all installation positions. This reduces the variety of parts specifications and the probability of assembly errors, effectively improving production efficiency and reducing manufacturing costs.

[0095] To adapt to different stiffness requirements: By setting the outer ends of the connecting ligaments 130 at the vertices or midpoints of the outer hexagonal frame 110, the structural stiffness adjustment requirements in different scenarios can be met: When the outer ends of the connecting ligaments are set at the vertices, the overall structural support stiffness is stronger, which is suitable for load-bearing scenarios that require high stability; when the outer ends of the connecting ligaments are set at the midpoints of the edges, the ligament span is smaller and the structural toughness is higher, which is suitable for elastic scenarios that require buffering and energy absorption. Performance adaptation can be achieved by simply adjusting the connection points without changing the overall structural framework, making the adaptation more flexible.

[0096] Maintaining geometric symmetry: The above connection method perfectly matches the symmetrical structural characteristics of the inner and outer hexagons, which can ensure that the mechanical properties of the structure are consistent in all directions, avoid the force bias caused by structural asymmetry, and make the deformation and load-bearing capacity of the hexagonal structure uniform in all directions, thereby improving the reliability of the structure.

[0097] Chirality and symmetry in this disclosure are not contradictory; they are different dimensions describing structural features, and are both related and can coexist. The core can be understood from the following perspectives: Chirality is defined as the property that a molecule / structure cannot be superimposed on its mirror image. The core criterion for determining chirality is precisely the rule of symmetry: a structure will exhibit chirality if it lacks a second type of symmetry element (symmetry plane, symmetry center, inversion axis); conversely, if the above symmetry elements are present, the structure can be superimposed on its mirror image and is achiral. In other words, chirality is not "the absence of symmetry," but rather the lack of a specific type of symmetry; it can still possess other types of symmetry characteristics, and the two are not contradictory.

[0098] Chiral structures can also maintain complete geometric symmetry characteristics. For example, a chiral hexagonal honeycomb structure can still conform to the symmetrical structural characteristics of inner and outer hexagons. The arrangement of chiral units fully meets the requirements of overall rotational symmetry and translational symmetry. It not only retains the chiral characteristics, but also ensures that the mechanical properties of the structure are consistent in all directions. It will not cause force bias due to asymmetry, so that the deformation and load-bearing capacity of the chiral hexagonal structure are uniform in all directions, which can also improve the reliability of the structure.

[0099] In some examples, in cell 100, the connecting ligaments 130 are rotate symmetrically distributed with the center of the inner hexagonal centroid 120 as the center of symmetry, and the extension direction of the connecting ligaments 130 deviates from the radial direction of the inner hexagonal centroid 120, forming a chiral topology with a rotational tendency.

[0100] The above can form a rotational chiral structure. When subjected to axial tensile and compressive loads, the radially distributed connecting ligaments 130 will simultaneously generate a rotational tendency, causing the cell as a whole to undergo controllable negative Poisson's ratio deformation. Compared with ordinary regular hexagonal cells, the stiffness can be continuously adjusted over a wider strain range, adapting to the stress requirements of different load levels in buffering and vibration reduction scenarios. At the same time, the elastic potential energy stored during rotation can form a multi-steady-state effect, which can spontaneously return to the initial shape after the load is removed, or switch to a preset deformation configuration as needed, improving the reconfigurability and cycle life of the structure.

[0101] The rotational deformation process of chiral structures can gradually dissipate impact energy through ligament bending and overall rotation, avoiding local structural failure caused by stress concentration. Under the same surface density, the energy absorption of this structure can be increased by more than 30% compared with ordinary symmetrical ligament structures, making it suitable for applications in protective equipment, automotive collision energy absorption boxes, and other fields.

[0102] Chiral topology has natural bandgap control characteristics. The rotationally symmetric chiral arrangement can produce a blocking effect on elastic waves of a specific frequency. By adjusting the deflection angle of the connecting ligament 130, the bandgap range can also be flexibly adjusted, which can be used to design lightweight acoustic vibration isolation structures.

[0103] Cells are the basic building blocks of metamaterials / lattice structures. Macroscopic lattice structures are obtained by repeatedly splicing and arranging a large number of similar cells in space. The topological structure and mechanical properties of cells directly determine the performance of the entire macroscopic structure.

[0104] The inner hexagonal central body 120 can be a rigid hexagonal core structure located at the center of a single cell in a chiral lattice structure. It is the force support center of the entire cell, and all connecting ligaments 130 are connected and fixed to the vertices of the central body.

[0105] Rotationally symmetric distribution refers to a distribution form in which a graphic can completely coincide with the initial graphic after being rotated around the center by a certain angle (such as 60° or 120°). This distribution ensures the uniformity of force in all directions of the cell.

[0106] The radial direction can be a straight line from the center of the inner hexagonal central body 120 to the vertex of the central body, which is the conventional extension direction of the ligament 130 connecting the ordinary hexagonal lattice structure.

[0107] Chiral topology can be a topological configuration that cannot be superimposed on its own mirror image through translation, rotation or other operations. In this structure, the connecting ligaments 130 are uniformly deviated from the radial direction to form a rotational tendency. The whole structure has chiral characteristics and can produce special mechanical and physical properties that ordinary non-chiral structures do not have.

[0108] Negative Poisson's ratio refers to a special mechanical property of materials. Ordinary materials will contract laterally when under tension, while materials with negative Poisson's ratio will expand laterally when under tension. The rotational chirality design of this structure can naturally realize the negative Poisson's ratio effect, and it has higher shear resistance and energy absorption capacity compared with ordinary materials.

[0109] This disclosure relates to a structure, and the simulation material can be Nimonic 90, a material commonly used in the aerospace field, with a density of 8180 kg / m³, Young's modulus of 219 GPa, Poisson's ratio of 0.28, initial yield stress of 800 MPa, and isotropic tangent modulus of 10 GPa. The above parameters are only exemplary parameters, and specific settings should be made according to specific circumstances.

[0110] The materials for the energy-absorbing and pressure-resistant chiral superstructure can also be titanium alloy, aluminum alloy or carbon fiber reinforced composite materials, and can be adapted to the weight reduction and temperature resistance requirements of different application scenarios of the rudder.

[0111] The beneficial effects produced by different compatible materials vary significantly, and the energy absorption and pressure resistance characteristics of the superstructure can be fully utilized for different application scenarios.

[0112] Titanium alloys possess inherent characteristics such as high specific strength, excellent corrosion resistance, and outstanding fatigue resistance. Using titanium alloys to fabricate energy-absorbing and pressure-resistant chiral superstructures not only meets the corrosion resistance requirements for rudder wings used in deep-sea, high-humidity, and high-salt near-shore environments, but also significantly reduces the overall weight of the rudder wing while maintaining the overall pressure-absorbing capacity of the structure. This reduces the power consumption for driving the rudder wing deflection and improves the overall payload and endurance of the vehicle. Furthermore, titanium alloys can maintain stable mechanical properties over long periods in high-temperature environments of 300℃-500℃, making them suitable for rudder wing applications where high temperatures are generated by aerodynamic / hydraulic heating during high-speed navigation. They do not experience structural softening or decreased energy absorption efficiency due to temperature increases, resulting in stronger long-term service stability.

[0113] Aluminum alloys possess advantages such as low density, good machinability, and low cost. When used to fabricate energy-absorbing and pressure-resistant chiral superstructures, they enable integrated molding of the superstructure, reducing the processing difficulty and manufacturing cost of complex chiral topologies. At the same time, they can meet the lightweight and low-cost requirements of rudder wings for small and medium-sized aircraft. Aluminum alloys have high specific stiffness, which can ensure that the overall structure does not become unstable and fracture when the chiral superstructure deforms under impact. They can fully absorb impact energy through the orderly deformation of chiral units, providing reliable protection for the drive and sensing structures inside the rudder wings. Under normal operating conditions of low- and medium-speed navigation, their overall cost-effectiveness is far superior to other materials.

[0114] Carbon fiber reinforced composites possess the characteristics of high designability, higher specific strength and specific modulus than metal materials, and excellent corrosion resistance and fatigue resistance. By adjusting the fiber layup direction, they can be specifically adapted to the stress requirements of different directions of the rudder, further enhancing the directional energy absorption and compressive strength of the chiral superstructure. Compared with metal materials, the structural weight can be further reduced by 20%-40%, with an extremely outstanding weight reduction effect. At the same time, the material has a low coefficient of thermal expansion and will not exhibit significant structural deformation under large temperature difference environments. It can meet the temperature resistance and weight reduction requirements of high-speed aircraft rudders in the aerospace field, and can also meet the requirements of long-term corrosion resistance for the rudders of long-endurance underwater vehicles.

[0115] In addition to the three materials mentioned above, other materials can be selected to suit specific application scenarios: High-temperature alloys: For the control wings of hypersonic aircraft above Mach 5, nickel-based or titanium-aluminum-based high-temperature alloys can be used to prepare chiral superstructures. These materials can maintain stable mechanical strength in high-temperature aerodynamic heating environments of 800℃-1200℃, ensuring that the chiral superstructure can still play an energy absorption and pressure resistance role in extreme high-temperature environments, resist the loads caused by airflow disturbances and aerodynamic impacts during high-speed flight, and improve the adaptability of the control wings to extreme working conditions.

[0116] Thermoplastic elastomer composites: For the flexible rudder requirements of underwater unmanned vehicles and small biomimetic vehicles, chiral superstructures can be prepared using thermoplastic elastomer composites filled with hard nanoparticles. This material combines elastic deformation capability with structural strength, allowing the rudder to actively deform and adjust its camber according to the navigation conditions. At the same time, the chiral superstructure can absorb the vibration energy brought by water flow pulsation, improving the stealth performance and navigation stability of the vehicle. Furthermore, the material's own damping properties can further enhance the energy absorption and noise reduction effect.

[0117] Biomimetic porous hydroxyapatite composite material: For the application scenario of artificial fish fin rudders in biomimetic underwater vehicles, a chiral superstructure can be prepared by using porous hydroxyapatite composite material doped with polymer phase. The density of this material is close to that of biological skeleton, which can accurately simulate the mechanical properties of natural biological fins. At the same time, the energy absorption properties of the chiral superstructure can buffer the alternating load during swimming, improve the fatigue life of artificial fin rudders, and meet the needs of long-term biomimetic navigation.

[0118] In some examples, the energy-absorbing and pressure-resistant chiral superstructure is constructed using a macroscopic periodic array assembly method, with the outer hexagonal borders 110 of adjacent representative cells 100 sharing the same edge to form a continuous two-dimensional planar filling structure.

[0119] The above-mentioned assembly method with overlapping edges completely eliminates the gaps between cells, achieving greater utilization of the planar space of the chiral superstructure (even 100% utilization). Compared with discrete assembly structures with non-overlapping edges, more energy-absorbing cells can be arranged on the same area of ​​the substrate, resulting in a larger overall load-bearing area, more uniform stress distribution, and the ability to avoid premature structural failure caused by local stress concentration, thereby improving the overall ultimate load-bearing capacity of the superstructure.

[0120] The macroscopic periodic array arrangement ensures consistent mechanical properties at any position of the superstructure, preventing sudden changes in mechanical properties due to local assembly deviations, thus enhancing controllability and predictability. At the same time, the hexagon itself possesses natural geometric stability, and the continuous two-dimensional network formed after connecting common edges can quickly disperse impact loads across the entire structural plane, avoiding single-point impact penetration and significantly improving the uniformity of energy absorption in the planar direction.

[0121] The above assembly method is simple and can be completed by standardized cutting and splicing. It does not require the addition of too many connecting fasteners, which reduces processing costs and assembly complexity. It is suitable for the large-scale production of large-size planar energy-absorbing components (such as protective wall panels and buffer pads).

[0122] In other examples, cell 100 has a uniform height along a direction perpendicular to the two-dimensional plane, forming a three-dimensional skeletal structure.

[0123] The uniform height design ensures the consistency of mechanical properties of each section of the three-dimensional structure, avoiding load shift and local instability caused by uneven height. When subjected to impact loads perpendicular to the plane, all cells can undergo controllable plastic deformation synchronously, giving full play to the chiral energy absorption characteristics of each cell. The total energy absorption is increased by more than 30% compared to the two-dimensional planar structure, resulting in better buffering and impact resistance performance.

[0124] The three-dimensional skeleton forms a continuous porous force transmission path, which not only retains the characteristic of chiral structures that can be designed with Poisson's ratio, but also allows for flexible adaptation to protection requirements of different thicknesses by adjusting the height parameter: when the height is set to a lower level, it can be used to manufacture thin mobile phone back panels and vehicle body buffer layers, while when the height is set to a higher level, it can be used to manufacture explosion-proof and vibration-isolation bearings and engineering protection piles, thus adapting to a wider range of scenarios.

[0125] The uniform three-dimensional skeleton contains continuous void channels. During the energy absorption and compression process, the voids can expel air to further buffer the impact force. At the same time, it has the advantage of being lightweight, reducing the weight by more than 40% compared to solid structures under the same load-bearing capacity. It meets the dual requirements of lightweight and high energy absorption of protective structures in aerospace, transportation and other fields.

[0126] The superstructure is a thin-walled structure with uniform wall thickness. Compared with traditional homogeneous energy-absorbing structures, this thin-walled uniform wall thickness design ensures that the stress distribution is more uniform when the superstructure is subjected to axial and lateral multi-directional loads. This avoids the problem of stress concentration and premature failure caused by local wall thickness differences, effectively extending the service life of the structure. On the other hand, the uniform thin-walled configuration can reduce the overall weight of the superstructure while meeting the structural compressive load requirements, achieving the goal of lightweight design and adapting to the stringent requirements of aerospace and high-speed rail transportation for lightweight load-bearing components.

[0127] The energy-absorbing and pressure-resistant chiral superstructure is made of an isotropic metallic material, specifically Nimonic 90 high-temperature alloy. Using Nimonic 90 as the material fully leverages its excellent high-temperature mechanical properties and creep resistance. This allows the energy-absorbing and pressure-resistant chiral superstructure to maintain stable energy absorption and pressure resistance under normal operating conditions at room temperature. Furthermore, under extreme conditions of high temperature and prolonged static loads, it avoids the strength degradation and creep deformation problems common in traditional metal energy-absorbing structures, maintaining stable chiral topological deformation characteristics and ensuring no deterioration in energy absorption and pressure resistance. Simultaneously, as an isotropic material, Nimonic 90 exhibits no directional difference in mechanical properties, matching the multi-directional energy absorption design requirements of the chiral superstructure. This avoids the significant fluctuations in energy absorption performance caused by changes in loading direction in anisotropic materials, improving the stability and reliability of the superstructure's energy absorption and pressure resistance. In addition, this alloy possesses excellent resistance to oxidation and corrosion, allowing the superstructure to be used long-term in high-humidity, high-temperature, and corrosive industrial environments, further expanding the application scenarios of this energy-absorbing chiral superstructure.

[0128] Secondly, this disclosure also provides a design method for an energy-absorbing and compressive-resistant chiral superstructure, applied to the aforementioned energy-absorbing and compressive-resistant chiral superstructure. The design method includes the following steps: Step S100: Set up a basic six-ligament chiral ring structure, which consists of a central geometry and an extended connecting ligament 130; The above steps establish a core unit capable of energy absorption and compressive strength from the source of the structure: the connecting ligament 130 itself is a flexible load-bearing component, which can dissipate impact energy through its large deformation when subjected to external load impact, providing basic deformation energy absorption space for the superstructure; the central geometry, as the core of structural support, can ensure that the unit skeleton will not directly undergo brittle fracture under load, maintaining the basic integrity of the overall structure. At the same time, the eccentric setting breaks the uniformity of stress of traditional symmetrical ligaments, which can trigger multi-level nonlinear deformation, providing a structural foundation for subsequent gradual energy absorption.

[0129] Step S200: Arrange and connect the basic six-ligament chiral ring structures in a staggered manner in a two-dimensional plane to form a complex chiral superstructure network with regular pore arrangement; In the above steps, the staggered arrangement creates a force linkage between the cantilever ligaments of adjacent units: under external loads, the deformation of a single unit is transmitted to the surrounding adjacent units through the connection, mobilizing the entire structure to participate in deformation and energy absorption, thus avoiding premature failure due to local stress. At the same time, the retention of regular pores provides sufficient compression space for structural deformation, preventing premature compaction and extending the load plateau range of the energy absorption process. On the other hand, it can reduce the overall density of the superstructure and meet the requirements of lightweight load-bearing.

[0130] Step S300: Using regular hexagons as boundaries, extract and define the shape from the complex chiral superstructure network to obtain the representative cell 100 of the double hexagonal nested structure; The above steps regularize the unit structure through boundary truncation. The resulting double hexagonal nested structure not only retains the chiral deformation characteristics of the original complex chiral network, but also forms a nested load-bearing relationship between the outer frame and the inner unit: the outer regular hexagonal boundary can improve the overall structural stability of the cell, while the inner chiral ring maintains the deformable energy absorption characteristics, achieving the load-bearing characteristics of "outer stability and inner flexibility"; at the same time, the regular hexagonal boundary provides a standardized basic unit for subsequent array assembly, avoiding structural misalignment and irregular pores during splicing, and reducing the error of subsequent processing and assembly.

[0131] Step S400: Using the representative cell 100 as the basic unit, perform common-edge translation in each direction in two-dimensional space to assemble a macroscopic continuous superstructure array.

[0132] In the above steps, the assembly method of translating and arranging adjacent cells ensures that a complete and firm force connection is formed between adjacent cells, without any splicing gaps. External loads can be evenly transferred to all cells of the entire macro array, allowing all units to participate in deformation and energy absorption in an orderly manner, and fully leveraging the energy absorption and compressive strength potential of each unit. At the same time, the standardized array assembly method greatly reduces the difficulty of setting up and processing macro superstructures. Macro structures of any size can be obtained simply by splicing repeated units, adapting to the application needs of different scenarios.

[0133] The above design method, through its progressive steps from core unit construction to overall network formation, and then to standardized cell shaping and macroscopic array assembly, gradually constructs a chiral superstructure that combines lightweight characteristics with excellent energy absorption and compressive strength. Each step sequentially realizes the construction of core energy-absorbing units, the construction of a globally interconnected energy-absorbing network, the shaping of standardized load-bearing cells, and the assembly of macroscopically controllable structures. This fully leverages the nonlinear deformation and progressive energy absorption characteristics of chiral structures while also taking into account the feasibility of macroscopic structural design and fabrication. Ultimately, it yields an energy-absorbing and compressive-resistant chiral superstructure with stable energy absorption, excellent compressive strength, and adaptability to different application scenarios.

[0134] The above steps are followed by verification and optimization steps: Step S500: Establish a three-dimensional model of the macroscopic continuous superstructure array; The above steps involve local mesh refinement for connecting nodes and thin-walled regions. This avoids the problem of a sharp increase in computational load and excessively long simulation time caused by an overly dense overall mesh. It also accurately captures the deformation details and stress distribution in stress concentration areas, solving the defects of insufficient overall coarse mesh accuracy and inability to accurately reflect the mechanical response of key load-bearing areas. This ensures a balance between the accuracy of simulation results and computational efficiency.

[0135] Step S600: Mesh the 3D model and perform local refinement processing on the connecting nodes and thin-walled regions; The above-mentioned numerical simulation of the deformation process, failure path and mechanical response of macroscopic continuous superstructure array under compressive load can be simulated in advance without the need to make physical samples for testing. This can significantly shorten the research and development cycle, save material and labor costs for sample preparation and mechanical testing, and at the same time obtain data such as internal stress distribution and local instantaneous deformation that are difficult to measure directly in physical tests, so as to more comprehensively reflect the mechanical change law during the structural bearing process.

[0136] Step S700: Set boundary conditions and perform finite element simulation analysis to simulate the mechanical response under compressive load and verify the energy absorption capacity and compressive strength of the structure.

[0137] The above-mentioned quantitative verification of the energy absorption capacity and compressive strength of the structure through simulation can quickly determine whether the performance of the current superstructure array meets the design requirements during the structural design stage. If the performance does not meet the requirements, the weak points of the structure can be located directly based on the stress distribution results obtained from the simulation. The unit size, node connection method or wall thickness parameters of the superstructure can be adjusted in a targeted manner to complete the optimization. This avoids the R&D process of repeatedly preparing physical objects through trial and error, effectively improves the design optimization efficiency of superstructure energy-absorbing and compressive strength components, and ensures that the final prepared structure can meet the load-bearing and energy absorption requirements of actual working conditions.

[0138] Reference Figures 5 to 7 Furthermore, the boundary conditions for the finite element simulation analysis are set as follows: one end face of the macroscopic continuous superstructure array is set as a completely fixed constraint, and the other end face is subjected to an axial compression displacement in the range of 0-30mm with a step size of 1mm to simulate the mechanical response under different compression degrees.

[0139] By setting the simulation displacement range to 0-30mm and using a uniform step size of 1mm, the above method can comprehensively cover the entire mechanical response process of the superstructure from initial elastic deformation and plastic yielding to later densification and compaction. This avoids the inability to obtain key data such as the ultimate bearing capacity and progressive failure characteristics under large deformation of the superstructure due to insufficient compression displacement range, while also taking into account the deformation gradient accuracy in both small and large deformation stages. In the initial elastic deformation stage, a step size of 1 mm can accurately capture the linear variation law of basic mechanical parameters such as the elastic modulus and initial Poisson's ratio of the superstructure, and capture the initial position and evolution trend of stress concentration in various parts in the early stage of deformation. After entering the elastoplastic transition and yielding stage, the uniform small step size setting can accurately track the occurrence nodes of nonlinear behaviors such as buckling, nodal failure, and local fracture of skeleton members, clearly restore the abrupt change process of mechanical response from linear to nonlinear, and avoid missing the stress and strain data of key failure nodes due to excessive step size. For gradient superstructures or multiphase composite superstructure arrays, this parameter setting can ensure consistent deformation increments at each stage in regional deformation analysis with different densities and configurations, facilitating comparison of deformation synergy and load-bearing contribution ratios in different regions.

[0140] The uniform 1mm step size mentioned above also provides uniformly distributed discrete sample points for subsequent stress-strain curve fitting and regression analysis of superstructure structure-property relationship, improving the accuracy of mechanical property parameter fitting. At the same time, this parameter setting matches the loading step size range of common universal testing machine compression tests, which facilitates direct comparison and verification between simulation results and experimentally measured mechanical responses, improving the comparability and credibility of simulation analysis.

[0141] Figure 5 and Figure 6 The quasi-static compressive mechanical properties quantification curves are shown. Among them, Figure 5 Load-displacement curve (horizontal axis: compressive displacement mm, vertical axis: load MN): 0-4mm: linear elastic stage, the load increases proportionally with the displacement, and the structure can fully recover after unloading; around 4mm, the yield critical point is reached, and the slope of the curve slows down and enters the plastic plateau stage; 30mm: the load continues to rise slowly throughout the entire range without a cliff-like drop, indicating that the structure will not collapse brittlely in an instant, can continuously buffer impacts, and has high safety redundancy.

[0142] Figure 6 The total energy absorption EA-displacement curve (horizontal axis: compression displacement mm, vertical axis: absorbed energy J) is a continuously rising convex curve. The greater the compression displacement, the more energy is absorbed per unit deformation. There is no energy absorption saturation inflection point, which proves that it can still dissipate impact kinetic energy under large deformation. Compared with traditional honeycomb structures, its resistance to sudden aerodynamic impact and vibration buffering ability are significantly improved.

[0143] Figure 7 The finite element stress cloud diagram of the macroscopic array structure under compression is shown. The specific simulation conditions include using Nimonic 90 aerospace-grade nickel-based alloy as the material, with the upper end completely fixed and the lower end subjected to 0-30mm axial compressive displacement. A tetrahedral mesh with finely densified nodes is used for the calculation of thin-walled regions. Color scale: The bottom color scale is in Pa, with blue representing low-stress areas and reddish-brown representing high-stress areas.

[0144] The stress is evenly distributed throughout the entire area. High stress is not only concentrated in the outer frame. The internal hexagons and connecting ligaments 130 synchronously share the load, with no local extreme stress concentration. When under pressure, the outer hexagons remain parallel and stable, while the inner chiral units undergo slight rotation, relying on bending and torsion to dissipate impact energy. The aforementioned verification structure combines high compressive stiffness with high energy absorption characteristics, and impact loads will not cause premature local fracture, making it suitable for rudder gusts and aerodynamic impact conditions.

[0145] Reference Figure 8 and Figure 9 Thirdly, this disclosure also provides a rudder structure 200, the internal core layer of which is filled with the energy-absorbing and pressure-resistant chiral superstructure as described above. The energy-absorbing and pressure-resistant chiral superstructure serves as a load-bearing skeleton to support the rudder skin and withstand aerodynamic loads. It maintains stable energy-absorbing and pressure-resistant performance under both positive vertical loads and lateral transverse loads, without local stress concentration.

[0146] This disclosed chiral superstructure control wing dissipates energy through the rotational deformation of chiral micro-elements. Under extreme dynamic loads such as bird strikes and sudden airflow disturbances, its energy absorption efficiency is more than 30% higher than that of traditional structures. It effectively prevents localized pitting, cracking, or even fracture damage to the control wing skin, significantly improving the control wing's impact fatigue life. Facing directional aerodynamic loads at different flight stages, this structure can adapt to the mechanical requirements of both positive lift loads and directional sideslip loads through the coordinated deformation of chiral units. It eliminates the need for separately designed reinforcing ribs for different load directions, ensuring the overall mechanical stability of the control wing while reducing its overall weight by approximately 12%, effectively contributing to aircraft weight and drag reduction and improving fuel economy. Furthermore, this energy-absorbing and pressure-resistant chiral superstructure can be integrally formed through additive manufacturing, eliminating the need for additional splicing and assembly. This reduces the number of connecting parts inside the control wing, lowering the risk of structural loosening and subsequent failures. It also allows for adjustments to the size and distribution parameters of the chiral units according to the aerodynamic requirements of different aircraft models and control wing positions, resulting in greater adaptability and shortening the research and development cycle of new control wing designs. After localized damage to the rudder, only the chiral units in the damaged area need to be repaired or replaced, resulting in lower maintenance costs and effectively reducing maintenance expenses throughout the aircraft's lifecycle.

[0147] Figure 8 and Figure 9 An engineering assembly model of a chiral superstructure filled with a standard rudder wing such as NACA0012 is shown. This section demonstrates the final engineering implementation of the chiral porous superstructure, proving its direct use as the internal core layer of the rudder wing structure 200.

[0148] Figure 8 The left side shows a 3D schematic diagram of the entire control wing. The standard NACA0012 airfoil control wing has a 3D shape, with the core load-bearing area filled with a porous core layer marked in red, visually distinguishing the skin from the internal skeleton. Figure 8 The right side of the middle section shows a magnified view of the core layer. This magnified view shows the continuous chiral array filling the interior of the rudder, which completely preserves the aforementioned periodic grid topology, proving that the porous structure can perfectly fit the interior space of the rudder surface.

[0149] Figure 9 This is a front view of the rudder section. It shows a section cut along the chord direction, fully revealing the rudder's entire chiral superstructure core layer from the leading edge to the trailing edge.

[0150] The above structure, while significantly reducing the overall weight of the rudder (lightweighting), can achieve multi-directional impact bearing in vertical and lateral directions, solving the problem of insufficient unidirectional mechanical performance of traditional honeycomb rudders under gusts and yaw loads.

[0151] Fourthly, this disclosure also provides an aircraft equipped with the aforementioned rudder structure 200. The rudder structure 200 achieves synergistic optimization of lightweight and load-bearing performance through an internal energy-absorbing and pressure-resistant chiral superstructure, reducing the overall energy consumption of the aircraft while improving flight safety under sudden aerodynamic impact conditions.

[0152] The energy-absorbing and pressure-resistant chiral superstructure disclosed herein can evenly distribute the aerodynamic load borne by the control wings through the rotational deformation of the internal chiral units, avoiding structural cracking caused by local stress concentration and significantly improving the fatigue service life of the control wings. When the aircraft encounters sudden impact loads such as strong airflow or bird strikes, the chiral superstructure can absorb more than 70% of the impact energy through controllable stepwise deformation, significantly reducing the damage to the control wing connection parts and the main fuselage structure. While achieving a control wing weight reduction of more than 32% compared to traditional solid structures, the structural ultimate load-bearing capacity is increased by 21%, effectively reducing the overall weight of the aircraft structure, directly reducing fuel consumption during takeoff and cruise, extending the aircraft's range, and reducing the operating costs of long-range flight missions.

[0153] The core structure of this aircraft consists of three parts: the fuselage, the power system, and the flight control system. The rudder structure 200, as the core component of the control system, includes three types of movable control surfaces: ailerons, elevators, and rudders. The rudder integrates an energy-absorbing and pressure-resistant chiral superstructure as a load-bearing core layer, and is covered with an aerospace composite skin. Depending on the application scenario, the power system can be equipped with turbofan engines, electric propellers, or other options. The flight control system adjusts the rudder deflection angle in real time to achieve stable flight attitude control.

[0154] This aircraft can be widely used in civil passenger and cargo aviation, and can also be adapted to military aviation scenarios such as long-endurance reconnaissance UAVs and large reconnaissance and strike UAVs. It is especially suitable for high-altitude long-endurance UAV models with lightweight fuselage and high flight safety requirements, and can improve flight reliability in complex airflow environments while reducing weight and increasing range.

[0155] In summary, after reading this detailed disclosure, those skilled in the art will understand that the foregoing detailed disclosure may be presented by way of example only and may not be restrictive. Although not explicitly stated herein, those skilled in the art will understand that the requirements of this disclosure encompass various reasonable changes, improvements, and modifications to the embodiments. These changes, improvements, and modifications are intended to be made by this disclosure and are within the spirit and scope of the exemplary embodiments of this disclosure.

[0156] Furthermore, certain terms used in this disclosure have been used to describe embodiments of this disclosure. For example, "an embodiment," "an embodiment," and / or "some embodiments" mean that a particular feature, structure, or characteristic described in connection with that embodiment may be included in at least one embodiment of this disclosure. Therefore, it is to be emphasized and understood that two or more references to "an embodiment" or "an embodiment" or "alternative embodiment" in various parts of this disclosure do not necessarily refer to the same embodiment. Moreover, specific features, structures, or characteristics may be suitably combined in one or more embodiments of this disclosure.

[0157] It should be understood that in the foregoing description of the embodiments of this disclosure, various features are combined in a single embodiment, drawing, or description for the purpose of simplifying the disclosure and aiding in the understanding of a feature. However, this does not mean that the combination of these features is necessary, and those skilled in the art, upon reading this disclosure, may readily identify some of the devices as separate embodiments. That is, the embodiments in this disclosure can also be understood as an integration of multiple secondary embodiments. It is also valid when each secondary embodiment contains fewer than all the features of a single foregoing disclosed embodiment.

[0158] Every patent, patent publication, publication of a patent publication, and other material, such as articles, books, specifications, publications, documents, and literature (excluding any related historical examination documents), cited in this disclosure is incorporated herein for all purposes, including, for example, in the specification and claims of this disclosure. However, in the event of any inconsistency or conflict between the descriptions, definitions, and / or terms used in the foregoing and those used in this disclosure, the descriptions, definitions, and / or terms used in this disclosure shall prevail.

[0159] Finally, it should be understood that the embodiments disclosed herein are illustrative of the principles of the embodiments of this disclosure. Other modified embodiments are also within the scope of this disclosure. Therefore, the embodiments disclosed herein are merely examples and not limitations. Those skilled in the art can adopt alternative configurations based on the embodiments in this disclosure to implement the disclosures herein. Therefore, the embodiments of this disclosure are not limited to the embodiments precisely described in the disclosure.

Claims

1. An energy-absorbing and pressure-resistant chiral superstructure, characterized in that, It consists of an array of multiple representative cells arranged in a periodic pattern; The representative cell has a double hexagonal nested structure, including an outer hexagonal border and an inner hexagonal center body located inside the outer hexagonal border; A connecting ligament extends from each vertex of the inner hexagonal central body, and the other end of the connecting ligament is connected to the inner sidewall of the outer hexagonal frame. The inner hexagonal center, the connecting ligament, and the outer hexagonal frame are integrally formed, and the inner hexagonal center has chiral geometric features relative to the outer hexagonal frame.

2. The energy-absorbing and compressive-resistant chiral superstructure according to claim 1, characterized in that, Both the inner hexagonal center and the outer hexagonal border are regular hexagons, and the ratio of the side length of the inner hexagonal center to the side length of the outer hexagonal border is 1:

2.

3. The energy-absorbing and compressive-resistant chiral superstructure according to claim 1, characterized in that, The inner hexagonal center is constructed as a proportionally scaled portion of the outer hexagonal border, with the same orientation; or... The inner hexagonal center body is constructed as a proportional scaling of the outer hexagonal border after being twisted by a preset angle.

4. The energy-absorbing and compressive-resistant chiral superstructure according to any one of claims 1 to 3, characterized in that, The extension direction of the connecting ligament forms an angle of 15°-30° with the radial direction of the corresponding vertex of the inner hexagon. When subjected to force, it drives the central body of the inner hexagon to rotate in tandem, and dissipates the impact energy through the bending deformation of the connecting ligament.

5. The energy-absorbing and compressive-resistant chiral superstructure according to claim 4, characterized in that, The double hexagonal nested structure is formed by splicing multiple rods. The side length of the inner hexagon is 10mm±2mm, the side length of the outer hexagon is 20mm±4mm, the length of the connecting ligament is 10mm±2mm, the wall thickness of all rods is 0.5mm-3mm, and the representative cell is stretched in the out-of-plane direction to adapt to the size of the rudder core layer. Under quasi-static compressive load, the energy-absorbing and compressive-resistant chiral superstructure is in the linear elastic stage before a displacement of 4mm±1mm. The displacement of the energy-absorbing and compressive-resistant chiral superstructure exceeds the linear elastic stage and reaches the yield point, entering the plateau period. During compression, the maximum principal stress is uniformly distributed in the internal pore network, with no local stress concentration.

6. The energy-absorbing and compressive-resistant chiral superstructure according to claim 1, characterized in that, The length of the connecting ligament is equal to the side length of the central body of the inner hexagon; One end of the connecting ligament is connected to the vertex of the inner hexagonal center body, and the other end is connected to the vertex or the midpoint of the edge of the outer hexagonal border.

7. The energy-absorbing and compressive-resistant chiral superstructure according to claim 1, characterized in that, In the representative cell, the connecting ligaments are distributed in a rotationally symmetrical manner with the center of the inner hexagonal centroid as the center of symmetry, and the extension direction of the connecting ligaments deviates from the radial direction of the inner hexagonal centroid, forming a chiral topology with a rotational tendency.

8. The energy-absorbing and compressive-resistant chiral superstructure according to claim 1, characterized in that, The energy-absorbing and pressure-resistant chiral superstructure is constructed using a macroscopic periodic array assembly method, with the outer hexagonal borders of adjacent representative cells sharing the same edge, forming a continuous two-dimensional planar filling structure; or, The representative cells have a uniform height along a direction perpendicular to the two-dimensional plane, forming a three-dimensional skeletal structure.

9. A design method for an energy-absorbing and compressive-resistant chiral superstructure, characterized in that, The design method applied to the energy-absorbing and compressive-resistant chiral superstructure according to any one of claims 1-8 includes the following steps: The basic six-ligament chiral ring structure is set up, which consists of a central geometry and an extended connecting ligament; The basic six-ligament chiral ring structures are arranged in an alternating pattern and interconnected in a two-dimensional plane to form a complex chiral superstructure network with regular pore arrangement. Using regular hexagons as boundaries, the representative cell of the bihexagonal nested structure is obtained by truncating and defining the complex chiral superstructure network; Using the representative cell as the basic unit, the cells are arranged in a common-edge translational manner in all directions within a two-dimensional space to assemble a macroscopic continuous superstructure array.

10. A rudder wing structure, characterized in that, The internal core layer of the rudder structure is filled with an energy-absorbing and pressure-resistant chiral superstructure as described in any one of claims 1-9. The energy-absorbing and pressure-resistant chiral superstructure serves as a load-bearing skeleton to support the rudder skin and withstand aerodynamic loads. It maintains stable energy-absorbing and pressure-resistant performance under both positive vertical loads and lateral transverse loads, without local stress concentration.

11. An aircraft, characterized in that, The aircraft is equipped with the rudder structure as described in claim 10. The rudder structure achieves synergistic optimization of lightweight and load-bearing performance through an internal energy-absorbing and pressure-resistant chiral superstructure, reducing the overall energy consumption of the aircraft while improving flight safety under sudden aerodynamic impact conditions.

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