A modular piezoelectric torsional point lattice structure and method of making

Abstract

The application discloses a splicing and inserting type modular compression-torsion lattice structure and a manufacturing method thereof, a plurality of splicing and inserting type compression-torsion units, the compression-torsion unit comprising two square panels and a plurality of inclined rods, a pair of trapezoidal cross-section grooves and a pair of trapezoidal cross-section bosses being symmetrically distributed on four outer sides of the square panel, a star-shaped hole being arranged on a middle portion of the square panel, and a fixing groove being arranged at each vertex of the star-shaped hole; the two square panels are arranged in parallel, the two ends of the inclined rods are respectively inserted into the fixing grooves at corresponding positions of the star-shaped holes of the upper and lower square panels, and an annular structure is further assembled on an inner circle of the star-shaped hole, so that the two ends of the inclined rods are prevented from sliding out of the fixing grooves in the mode of the annular structure. The application is assembled in the mode of splicing and inserting, and the complex and difficult-to-machine compression-torsion lattice structure is discretized, so that each component in the structure can be mass-produced in the mode of machining. The application combines compression and torsion two deformation modes, and compared with a traditional lattice structure with single compression or single torsion, can absorb more energy. The multi-mode deformation can disperse impact load and improve the energy absorption efficiency of the structure.

Description

Technical Field

[0001] This invention relates to lightweight, high-performance structures, specifically to an interlocking modular press-twist lattice structure and its manufacturing method. Background Technology

[0002] Lightweight lattice structures, with their low relative density, high strength compared to steel, and excellent energy absorption, are ideal lightweight energy-absorbing structures with broad application prospects in fields such as energy absorption and smart structures. However, traditional lattice structures primarily absorb impact energy through collapse, resulting in a limited range of buffering and energy absorption methods.

[0003] Compression-torsion lattice structures combine both compression and torsion deformation modes, dispersing impact loads and improving energy absorption efficiency compared to traditional lattice structures with only compression or torsion. Patent application number 202111561756.X discloses a bistable structure with torsional deformation under tensile and compressive loads and its constituent multistable lattice structure. Similarly, patent application number 202210729389.8 discloses a composite material compression-torsion coupled chiral lattice sandwich structure and its fabrication method. The main problems with these technical solutions are: complex structural forms, making mass production difficult using traditional machining methods, while fabrication using 3D printing or composite material processing methods is inefficient and costly; and after design and fabrication, the macroscopic dimensions of the lattice structure cannot be changed by altering the number of compression-torsion units. Summary of the Invention

[0004] Purpose of the invention: The purpose of this invention is to address the shortcomings of existing technologies by providing an interlocking modular compression-torsion lattice structure and its manufacturing method. This structure assembles individual compression-torsion units through interlocking, combining both compression and torsion deformation modes. Compared to traditional lattice structures with only compression or torsion, it can absorb more energy and can be mass-produced through machining. This invention can disperse impact loads, improve the energy absorption efficiency of the structure, and has wide applications in vehicle lateral protection, intelligent structures, high-end instrument protection, and aerospace.

[0005] Technical Solution: The present invention provides a modular press-twist matrix structure, comprising several interlockable press-twist units. Each press-twist unit includes two square panels and several diagonal rods. Two adjacent sides of the four outer edges of the square panel have trapezoidal grooves, and two adjacent sides have trapezoidal bosses that match the grooves. The central portion of the square panel has a star-shaped hole, and each vertex of the star-shaped hole has a fixing groove. The two square panels are placed parallel to each other, and the two ends of the diagonal rods are respectively inserted into the fixing grooves at corresponding positions of the star-shaped holes in the upper and lower square panels. The ring is also equipped with an annular structure to prevent the ends of the diagonal rod from slipping out of the fixing groove. A certain number of compression-torsion units are assembled to form a compression-torsion lattice structure according to actual needs. During assembly, for two compression-torsion units in the same horizontal direction, the trapezoidal cross-section boss of one compression-torsion unit and the trapezoidal cross-section groove of the other compression-torsion unit are clearance-fitted to realize the connection between the compression-torsion units. During assembly, two compression-torsion units in the same vertical direction share the middle square panel. When the assembled compression-torsion lattice structure is subjected to compressive and tensile loads, the compression-torsion lattice structure will undergo axial torsional deformation while deforming axially.

[0006] Furthermore, the number of the inclined rods is the same as the number of vertices of the star-shaped hole; the annular structure and the star-shaped hole have the same shape and height, the annular structure coincides with the central axis of the star-shaped hole, and are in clearance fit.

[0007] The number of vertices in the star-shaped hole can be adjusted. For example, a hexagonal star-shaped hole structure can be used, with right angles constructed at each vertex of the regular hexagonal star-shaped hole to serve as fixing slots, which are then connected sequentially. The right-angle fixing slots facilitate the splicing of the half-I-beams at both ends of the diagonal bar. In addition to hexagonal star-shaped holes, star-shaped holes with other numbers of vertices can also be used, such as new types of triangular interlocking modular pressure-twist lattice structures, new types of quadrilateral interlocking modular pressure-twist lattice structures, new types of pentagonal interlocking modular pressure-twist lattice structures, new types of heptagonal interlocking modular pressure-twist lattice structures, new types of octagonal interlocking modular pressure-twist lattice structures, and new types of polygonal interlocking modular pressure-twist lattice structures.

[0008] Furthermore, the ends of the diagonal brace adopt a semi-I-beam structure, which is inserted into the fixing groove at the apex of the star-shaped hole. The shape of the end cross-section of the diagonal brace includes, but is not limited to, any shape among rectangles, circles, ellipses, etc.

[0009] Furthermore, each of the inclined rods in the same compression unit is inclined at the same angle and inserted into the fixing slot of the square panel through a clearance fit. The angle of inclination here refers to the angle between the inclined rod and the square panel. For example, assuming that the star-shaped hole of the square panel has 6 vertices and is a hexagonal star-shaped hole; fix the upper square panel, and then sequentially insert the semi-I-beam structures at the upper ends of the six inclined rods into the fixing slot of the star-shaped hole in the middle of the upper panel, and then assemble the ring structure into the star-shaped hole; then insert the semi-I-beam structures at the lower ends of the six inclined rods into the fixing slot of the star-shaped hole in the middle of the lower square panel, and fix the ring structure. Furthermore, the trapezoidal cross-section protrusions all have their upper bases attached to the outer edges of the square panel, and their lower bases extend from the upper bases to the side, and the length of the lower base is greater than the length of the upper base; the length of the lower base of the trapezoidal cross-section groove is greater than the length of the upper base, and the lower base is recessed into the square panel; the two pairs of trapezoidal cross-section protrusions and trapezoidal cross-section grooves of the same square panel are distributed opposite each other so as to be connected to the adjacent square panels. This structural design facilitates the assembly of square panels, achieving the minimum material requirements and maximum utilization of interlocking in terms of functional design, and allowing for arbitrary adjustment of different numbers and orientations of pressure and torsion units.

[0010] This invention also discloses a method for manufacturing an interlocking modular press-twist lattice structure, comprising the following steps:

[0011] Step 1: Make a single square panel. Each square panel includes four sub-panels, namely sub-panel a-1, sub-panel a-2, sub-panel b-1 and sub-panel b-2. The four sub-panels have the same shape and size, and have the same star-shaped holes.

[0012] Sub-panels a-1 and a-2 are combined to form panel a. The grooves at the vertices of the star-shaped holes on sub-panel a-1 and the grooves at the vertices of the star-shaped holes on sub-panel a-2 are combined to form a fixing groove. Sub-panels b-1 and b-2 are combined to form panel b. The grooves at the vertices of the star-shaped holes on sub-panel b-1 and the grooves at the vertices of the star-shaped holes on sub-panel b-2 are combined to form a fixing groove. Sub-panels b-1 and a-2 are centrally symmetrical about the bottom axis of sub-panel a-2 and have the same geometric parameters. Sub-panels b-2 and a-1 are centrally symmetrical about the bottom axis of sub-panel a-2 and have the same geometric parameters. Sub-panels a-1, a-2, b-1, and b-2 are stacked and spliced ​​from top to bottom to form a square panel.

[0013] Step 2: Fabricate a single compression-torsion unit;

[0014] Take two square panels. First, insert one end of each diagonal rod into panel a of one square panel according to the order of the fixing slots. Then, insert the other end of each diagonal rod into panel b of the other square panel according to the order of the fixing slots. Fix a ring structure outside the star-shaped hole to prevent the diagonal rod from sliding outward. Finally, design trapezoidal grooves and trapezoidal bosses symmetrically on the four outer sides of the square panels.

[0015] Step 3: Based on actual needs, expand multiple individual compression and torsion units within space, using the following method:

[0016] In the same horizontal direction, each compression and torsion unit is connected by trapezoidal cross-section bosses and trapezoidal cross-section grooves, while two compression and torsion units in the same vertical direction can share the middle square panel.

[0017] Ultimately, a twisted lattice structure with an arbitrary number of rows and columns is formed.

[0018] Beneficial effects: Compared with the prior art, the present invention has the following advantages:

[0019] (1) The present invention discretizes the complex lattice structure into some parts with simple geometric configurations. These parts with simple geometric configurations can be produced by machining and then assembled into the target lattice structure, which satisfies mass production while reducing manufacturing costs.

[0020] (2) The present invention modularizes the pressure-torsion lattice structure, and then controls the scale and quantity of the lattice structure, including the number of layers and the size, by interlocking the concave and convex grooves.

[0021] (3) The compression-torsion lattice structure of the present invention combines both compression and torsion deformation modes, which can absorb more energy compared to traditional lattice structures with only compression or only torsion. Multi-mode deformation can disperse impact loads and improve the energy absorption efficiency of the structure. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0023] Figure 2 This is a schematic diagram of a single compression and torsion unit in this invention.

[0024] Figure 3 This is a schematic diagram of the square panel in this invention.

[0025] Figure 4 is a schematic diagram of the stacking of square panels according to the present invention, wherein Figure 4a This is a diagram showing the panel exploded; Figure 4b Sub-panel a-2 includes the bottom axis; Figure 4c The top view of the parts includes sub-panel a-1, sub-panel a-2, sub-panel b-1, and sub-panel b-2.

[0026] Figure 5 This is a schematic diagram of the ring structure in this invention.

[0027] Figure 6 This is a schematic diagram of the diagonal bar in this invention.

[0028] Figure 7 shows a new type of triangular interlocking modular press-twist dot matrix structure panel. Figure 7-1 ), a new type of quadrilateral interlocking modular press-twist dot matrix structure panel ( Figure 7-2 ), a new type of pentagonal interlocking modular press-twist dot matrix structure panel ( Figure 7-3 ), a new type of heptagonal interlocking modular press-twist dot matrix structure panel ( Figure 7-4 ), a new type of octagonal interlocking modular press-twist dot matrix structure panel ( Figure 7-5 And new types of standard unit components assembled from triangular shapes ( ). Figure 7-1-1 ), new type of quadrilateral interlocking standard unit ( Figure 7-2-1 ), new type of pentagonal interlocking standard unit ( Figure 7-3-1 ), new type of heptagonal interlocking standard unit ( Figure 7-4-1 ), new type of octagonal interlocking standard unit ( Figure 7-5-1 ).

[0029] Figure 8 This is a schematic diagram showing the arbitrary expansion of multiple compression and torsion units in space in the embodiment.

[0030] Figure 9 yes Figure 1 A schematic diagram showing the relationship between axial displacement and torsion angle of each layer when the interlocking modular compression-torsion lattice structure is subjected to compression and torsion under load.

[0031] Figure 10 yes Figure 1 A schematic diagram showing the relationship between axial displacement and the magnitude of the load when the interlocking modular compression-torsion lattice structure is subjected to compression and torsion.

[0032] Figure 11 yes Figure 1 A schematic diagram showing the relationship between axial displacement and the amount of energy absorbed when a modular compression-torsion lattice structure is subjected to compression and torsion under load. Detailed Implementation

[0033] The technical solution of the present invention will be described in detail below, but the scope of protection of the present invention is not limited to the embodiments described.

[0034] like Figure 1 and Figure 2As shown, the present invention discloses a modular press-twist lattice structure comprising several interlockable press-twist units. Each press-twist unit includes two square panels 1 and several diagonal rods 3. Two adjacent sides 7 of the four outer edges 7 of the square panel 1 are provided with trapezoidal cross-section grooves 8, and two adjacent sides are provided with trapezoidal cross-section protrusions 6 adapted to the trapezoidal cross-section grooves 8. A star-shaped hole 2 is opened in the middle portion of the square panel 1, and each vertex of the star-shaped hole 2 is provided with a fixing groove 4. The two square panels 1 are placed parallel to each other vertically, and the two ends of the diagonal rods 3 are respectively inserted into the fixing grooves 4 at the corresponding positions of the star-shaped holes 2 of the upper and lower square panels 1. The inner ring of hole 2 is also equipped with an annular structure 5, which prevents the ends of the diagonal rod 3 from sliding out of the fixing groove 4. A certain number of pressure-torsion units are assembled to form a pressure-torsion lattice structure according to actual needs. During assembly, for two pressure-torsion units in the same horizontal direction, the trapezoidal cross-section boss 6 of one pressure-torsion unit and the trapezoidal cross-section groove 8 of the other pressure-torsion unit are clearance-fitted to realize the connection between the pressure-torsion units. During assembly, two pressure-torsion units in the same vertical direction share the middle square panel 1. When the assembled pressure-torsion lattice structure is subjected to compressive and tensile loads, the pressure-torsion lattice structure will undergo axial torsional deformation while deforming axially.

[0035] In this embodiment, as Figure 3 As shown in Figure 4, the square panel 1 is designed as a cuboid structure with a side length of 40mm and a thickness of 6mm. The four sub-panels all have a side length of 40mm. Sub-panels a-1 and b-2 have a thickness of 1mm, and sub-panels a-2 and b-1 have a thickness of 2mm. A hexagonal star-shaped hole 2 with a side length of 20mm is cut out at the center. The bottom of the diagonal rod 3 has a square cross-section with a side length of 4mm and a cuboid structure with a thickness of 2mm. The inner diameter and height of the diagonal rod 3 are both 1mm, and its slope is 60°. Figure 6 As shown, the total height is equal to 28mm; the long side length and depth of the fixing groove 4 at the apex of the star-shaped hole 2 are both 4mm, and the short side length is equal to the inner diameter of the diagonal rod 3, which is 1mm; the annular structure 5 has the same shape as the star-shaped hole 2, with a width of 2mm and a thickness of 3mm. Furthermore, the annular structure 5 and the star-shaped hole 2 have the same shape and height, their central axes coincide, and they are in a clearance fit. Figure 5 As shown.

[0036] Figure 6 The ends of the diagonal brace are constructed using a semi-I-beam structure 9, which is inserted into a fixing groove 4 at the apex of the star-shaped hole. The end cross-section of the diagonal brace can be any shape, such as rectangle, circle, or ellipse, in addition to the square cross-section mentioned above. During compression and torsion, a ring structure 5 prevents the ends of the diagonal brace from slipping out of the fixing groove.

[0037] In this embodiment, the trapezoidal cross-section protrusions 6 all have their upper bases attached to the outer edges 7 of the square panel 1, and their lower bases extend from the upper bases towards the edges, with the lower base length greater than the upper base length; the lower base length of the trapezoidal cross-section grooves 8 is greater than the upper base length, and the lower base is recessed into the square panel 1; the two pairs of trapezoidal cross-section protrusions 6 and trapezoidal cross-section grooves 8 of the same square panel 1 are distributed opposite each other to facilitate interlocking with adjacent square panels 1, such as... Figure 3 As shown.

[0038] like Figure 8 As shown, the compression-torsion lattice structure in this embodiment adopts a modular design and modular splicing method. By splicing the trapezoidal cross-section protrusions 6 and trapezoidal cross-section grooves 8 on the side of the square panel 1, the scale and quantity of the lattice structure, including the number of layers and its size, can be controlled. The compression-torsion lattice structure can be arbitrarily expanded in space by multiple unit modules. The compression-torsion lattice structure combines both compression and torsion deformation modes, and compared with traditional lattice structures with single compression or single torsion, it can absorb more energy. Multi-mode deformation can disperse impact loads and improve the energy absorption efficiency of the structure.

[0039] As shown in Figure 7, the number of vertices of the star-shaped hole 2 can be self-adjusted, such as in the form of a novel triangular interlocking modular pressure-twisting lattice structure, a novel quadrilateral interlocking modular pressure-twisting lattice structure, a novel pentagonal interlocking modular pressure-twisting lattice structure, a novel hexagonal interlocking modular pressure-twisting lattice structure, a novel heptagonal interlocking modular pressure-twisting lattice structure, and a novel octagonal interlocking modular pressure-twisting lattice structure, etc. The number of vertices of the star-shaped hole 2 depends on the number of diagonal rods 3. Correspondingly, the geometry of the star-shaped hole 2 also determines the geometry of the ring structure 5, such as... Figure 5 As shown. From a mechanical and geometric perspective, the more diagonal bars 3 there are, the more dispersed the force on the diagonal bars 3 will be when subjected to compressive and torsional loads, resulting in better energy absorption. From an economic and material perspective, too many diagonal bars 3 will cause inconvenience and complicated assembly. Therefore, when applied in fields such as automobiles, 6 to 8 vertices of the star-shaped hole 2 are sufficient. When applied in the protection of small high-end instruments, 3 to 5 vertices of the star-shaped hole 2 are sufficient.

[0040] The manufacturing method of the above-mentioned interlocking modular press-twist lattice structure includes the following steps:

[0041] Step 1: Create a single square panel 1. Each square panel 1 includes four sub-panels, namely sub-panel a-1, sub-panel a-2, sub-panel b-1, and sub-panel b-2. The four sub-panels have the same shape and size, and have the same star-shaped hole 2; as shown in Figure 4.

[0042] As shown in Figure 4a, sub-panels a-1 and a-2 are combined to form panel a. The grooves at the vertices of the star-shaped holes 2 on sub-panel a-1 and the grooves at the vertices of the star-shaped holes 2 on sub-panel a-2 are combined to form a fixing groove 4. Sub-panels b-1 and b-2 are combined to form panel b. The grooves at the vertices of the star-shaped holes 2 on sub-panel b-1 and the grooves at the vertices of the star-shaped holes 2 on sub-panel b-2 are combined to form a fixing groove 4. Sub-panels b-1 and a-2 are centrally symmetrical about the bottom axis of sub-panel a-2, as shown in Figure 4b and Figure 4c, and have the same geometric parameters. Sub-panels b-2 and a-1 are centrally symmetrical about the bottom axis of sub-panel a-2, and have the same geometric parameters. Sub-panels a-1, a-2, b-1, and b-2 are stacked and spliced ​​from top to bottom to form a square panel 1.

[0043] Panels a and b produced using this method have the same thickness, both being half the thickness of square panel 1. The positions of all fixing slots 4 on square panel 1 are... Figure 4b The axis shown is called central symmetry. Panels a and b in the same square panel 1 are centrally symmetric. The groove in panel a is "convex upward" and the groove in panel b is "convex downward". Then, panel a and panel b are arranged along the central axis of the "convex" groove shape.

[0044] Step 2: Fabricate a single compression-torsion unit;

[0045] Take two square panels 1. First, insert one end of each diagonal rod 3 into panel a of one square panel 1 according to the fixing groove 4. Then, insert the other end of the diagonal rod 3 into panel b of the other square panel 1 according to the fixing groove 4. Fix an annular structure 5 outside the star-shaped hole 2 to prevent the diagonal rod 3 from sliding outward. Finally, design trapezoidal grooves 8 and trapezoidal bosses 6 symmetrically on the four outer sides 7 of the square panel 1.

[0046] Step 3: Based on actual needs, expand multiple individual compression and torsion units within space, using the following method:

[0047] In the same horizontal direction, each pressing and twisting unit is connected by trapezoidal cross-section protrusions 6 and trapezoidal cross-section grooves 8, while two pressing and twisting units in the same vertical direction can share the middle square panel 1 (for example, the upper and lower pressing and twisting units share three square panels 1); finally forming a pressing and twisting dot matrix structure with any number of rows and columns.

[0048] To facilitate a further understanding of the performance of the technical solution of this invention, it is hereby described as follows: Figure 1For example, the selected processing material is PA12, and the resulting interlocking modular compression-torsion lattice structure has a geometric configuration of 3×3×3. When subjected to load, it is gradually and slowly compressed axially. According to the compression displacement and the magnitude of the load, it can be divided into three stages: strengthening, yielding, and strengthening.

[0049] As the axial compression displacement increases, the rotation angle of each layer gradually increases, with the torsional angle increasing layer by layer from top to bottom, such as... Figure 9 As shown. The load-displacement and energy-displacement curves are respectively shown in Figure 1. Figure 10 and Figure 11 As shown in the load curve, the compression-torsion lattice structure of this embodiment produces a significant plateau region under compressive load, which is beneficial for the structure to continuously and stably absorb energy. Moreover, the compression and torsional deformation modes of the compression-torsion lattice structure can disperse the impact load and reduce the initial peak load.

Claims

1. A modular, interlocking, press-and-twist dot matrix structure, characterized in that, It includes several interlocking compression and twisting units. Each compression and twisting unit includes two square panels and several diagonal rods. Two adjacent sides of the four outer sides of the square panel are provided with trapezoidal cross-section grooves, and two adjacent sides are provided with trapezoidal cross-section bosses that are adapted to the trapezoidal cross-section grooves. The two square panels are placed parallel to each other. The two ends of the diagonal rods are respectively inserted into the fixing grooves at the corresponding positions of the star-shaped holes of the upper and lower square panels. The inner ring of the star-shaped hole is also equipped with an annular structure to prevent the two ends of the diagonal rods from sliding out of the fixing grooves. Each square panel includes four sub-panels, namely the first sub-panel, the second sub-panel, the third sub-panel, and the fourth sub-panel; all four sub-panels have the same star-shaped holes; The first sub-panel and the second sub-panel are combined to form the first panel. The grooves at the vertices of the star-shaped holes on the first sub-panel and the grooves at the vertices of the star-shaped holes on the second sub-panel are combined to form a fixing groove. The third sub-panel and the fourth sub-panel are combined to form the second panel. The grooves at the vertices of the star-shaped holes on the third sub-panel and the grooves at the vertices of the star-shaped holes on the fourth sub-panel are combined to form a fixing groove. The third sub-panel and the second sub-panel are centrally symmetrical about the bottom axis of the second sub-panel and have the same geometric parameters. The fourth sub-panel is centrally symmetrical with the first sub-panel about the bottom axis of the second sub-panel and has the same geometric parameters. The first, second, third, and fourth sub-panels are stacked and spliced ​​sequentially from top to bottom to form a square panel. Each vertex of the star-shaped hole on the square panel is provided with a fixing groove. A certain number of pressure-torsion units are assembled according to actual needs to form a pressure-torsion dot matrix structure. During assembly, for two pressure-torsion units in the same horizontal direction, the trapezoidal cross-section boss of one pressure-torsion unit and the trapezoidal cross-section groove of the other pressure-torsion unit are clearance-fitted to realize the connection between the pressure-torsion units. During assembly, two pressure-torsion units in the same vertical direction share the middle square panel. When the assembled compression-torsion lattice structure is subjected to compressive and tensile loads, the compression-torsion lattice structure will undergo axial torsional deformation while deforming axially.

2. The interlocking modular press-twist dot matrix structure according to claim 1, characterized in that, The number of the inclined rods is the same as the number of vertices of the star-shaped hole; the annular structure and the star-shaped hole have the same shape and height, the annular structure coincides with the central axis of the star-shaped hole, and are in clearance fit.

3. The interlocking modular press-twist lattice structure according to claim 1, characterized in that, The two ends of the diagonal bar adopt a semi-I-beam structure, and the semi-I-beam is inserted into the fixing groove at the apex of the star-shaped hole.

4. The interlocking modular press-twist dot matrix structure according to claim 1, characterized in that, The end cross-section of the diagonal rod can be any shape among square, rectangle, circle, and ellipse.

5. The interlocking modular press-twist lattice structure according to claim 1 or 3, characterized in that, Each diagonal rod in the same compression and torsion unit is inclined at the same angle and inserted into the fixing groove of the square panel through a clearance fit.

6. The interlocking modular press-twist lattice structure according to claim 1 or 3, characterized in that, The trapezoidal cross-section protrusions all have their upper bases attached to the outer edge of the square panel, and their lower bases extend from the upper bases to the side, with the lower base length being greater than the upper base length; the lower base length of the trapezoidal cross-section grooves is greater than the upper base length, and the lower base is recessed into the square panel. Two pairs of trapezoidal cross-section bosses and trapezoidal cross-section grooves are distributed oppositely on the same square panel so that they can be interlocked with adjacent square panels.

7. A method for manufacturing a modular press-twist lattice structure according to any one of claims 1 to 6, characterized in that, Includes the following steps: Step 1: Create a single square panel. Each square panel includes four sub-panels, namely the first sub-panel, the second sub-panel, the third sub-panel, and the fourth sub-panel; all four sub-panels have the same star-shaped hole. The first sub-panel and the second sub-panel are combined to form the first panel. The grooves at the vertices of the star-shaped holes on the first sub-panel and the grooves at the vertices of the star-shaped holes on the second sub-panel are combined to form a fixing groove. The third sub-panel and the fourth sub-panel are combined to form the second panel. The grooves at the vertices of the star-shaped holes on the third sub-panel and the grooves at the vertices of the star-shaped holes on the fourth sub-panel are combined to form a fixing groove. The third sub-panel and the second sub-panel are centrally symmetrical about the bottom axis of the second sub-panel and have the same geometric parameters. The fourth sub-panel is centrally symmetrical with the first sub-panel about the bottom axis of the second sub-panel and has the same geometric parameters. The first sub-panel, the second sub-panel, the third sub-panel, and the fourth sub-panel are stacked and pieced together from top to bottom to form a square panel; Step 2: Fabricate a single compression-torsion unit; Take two square panels. First, insert one end of each diagonal rod into the first panel of one square panel according to the order of the fixing slots. Then, insert the other end of each diagonal rod into the second panel of the other square panel according to the order of the fixing slots. Fix a ring structure outside the star-shaped hole to prevent the diagonal rod from sliding outward. Finally, design trapezoidal grooves and trapezoidal bosses symmetrically on the four outer sides of the square panels. Step 3: Based on actual needs, expand multiple individual compression and torsion units within space, using the following method: In the same horizontal direction, each compression and torsion unit is connected by trapezoidal cross-section bosses and trapezoidal cross-section grooves, while two compression and torsion units in the same vertical direction can share the middle square panel. Ultimately, a twisted lattice structure with an arbitrary number of rows and columns is formed.

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