Anti-collision structure of spacecraft, and spacecraft

Abstract

The present invention provides a collision avoidance structure and a spacecraft, which relate to the field of aerospace technology and solve the technical problem that it is difficult for a spacecraft to effectively cope with collisions. The collision avoidance structure includes a beam and a metamaterial structure. The beam is arc-shaped as a whole and has a convex side and a concave side. The metamaterial structure is connected to the concave side of the beam. The metamaterial structure includes a plurality of first wall panels parallel to a first direction and a plurality of second wall panels parallel to a second direction. The plurality of first wall panels and the plurality of second wall panels intersect with each other to form a plurality of first cell structures arranged in an array. The first direction is perpendicular to the second direction, and the first wall panels and the second wall panels intersect to form a plurality of intersecting wall segments arranged in an array. The first cell structure is a square cylindrical structure. The metamaterial structure also includes a plurality of second cell structures, and the central axis of the second cell structure coincides with the central axis of the intersecting wall segments. The collision avoidance structure improves energy absorption on the basis of ensuring rigidity and can effectively cope with collisions.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to an anti-collision structure of a spacecraft and a spacecraft. Background Art

[0002] In space exploration, a major problem for spacecraft is the impact of high-speed micrometeorites. These tiny space debris fly at extremely high speeds and carry huge kinetic energy. When they hit a spacecraft, they may cause serious damage, including damage to the outer shell, structure, and internal systems. In serious cases, they may even affect the normal operation of the spacecraft and the safety of astronauts.

[0003] In related technologies, the anti-collision design of spacecraft requires a balance between structural rigidity and lightness. When a spacecraft is flying at high speed, it must not only withstand the huge impact force of external collisions, but also maintain structural stability and prevent excessive deformation. Therefore, it is urgent to develop an anti-collision structure that can cope with unknown collision threats in extreme aerospace environments and provide reliable protection for the long-term operation of spacecraft. Summary of the invention

[0004] The purpose of the present invention is to provide a collision avoidance structure of a spacecraft and a spacecraft, so as to solve the technical problem that the existing spacecraft is difficult to effectively cope with collisions.

[0005] In order to achieve the above object, the present invention provides the following technical solutions:

[0006] In a first aspect, the present invention provides an anti-collision structure of a spacecraft, comprising a beam and a metamaterial structure, wherein the beam is in an arc shape as a whole and has a convex side and a concave side, and the metamaterial structure is connected to the concave side of the beam;

[0007] The metamaterial structure comprises a plurality of first wall plates parallel to a first direction and a plurality of second wall plates parallel to a second direction, wherein the plurality of first wall plates and the plurality of second wall plates intersect with each other to form a plurality of first cell structures arranged in an array;

[0008] Wherein, the first direction is perpendicular to the second direction, the first wall plate and the second wall plate intersect to form a plurality of intersecting wall segments arranged in an array; the first cell structure is a square cylindrical structure;

[0009] The metamaterial structure further includes a plurality of second cell structures, wherein the second cell structures are square cylindrical structures, the central axis of the second cell structures coincides with the central axis of the intersecting wall segments, and the four third wall panels forming the second cell structures are at an angle of 45° with the first wall panels;

[0010] On the same second wall plate, the second cell structure is arranged at one of the two adjacent intersecting wall segments, and the second cell structure is not arranged at the other intersecting wall segment; on the same first wall plate, the second cell structure is arranged at one of the two adjacent intersecting wall segments, and the second cell structure is not arranged at the other intersecting wall segment;

[0011] Along the direction away from the beam, the thickness of the first wall plate gradually increases, the side length of the second cell structure increases, and the thickness of the third wall plate of the second cell structure increases;

[0012] The beam member includes a plurality of third cell structures arranged in an array, wherein the third cell structure is a square cylindrical structure, and along a direction from the convex side to the concave side, the thickness of four fourth wall plates forming the third cell structure gradually increases.

[0013] According to at least one embodiment of the present invention, the ratio of the thickness of the third wall plate of the second cell structure to the side length of the second cell structure is 10.

[0014] According to at least one embodiment of the present invention, the thickness of the first wall panel ranges from 1.2 mm to 2.2 mm; and / or,

[0015] The thickness of the fourth wall plate ranges from 1.2 mm to 2.2 mm.

[0016] According to at least one embodiment of the present invention, the side length of the second cell structure ranges from 5 mm to 12.5 mm.

[0017] According to at least one embodiment of the present invention, the ratio of the side length of the cross section of the third cell structure to the side length of the cross section of the first cell structure is 5.

[0018] According to at least one embodiment of the present invention, on the same second wall plate, the side lengths of the second cell structures at a plurality of the intersecting wall segments are the same.

[0019] According to at least one embodiment of the present invention, the anti-collision structure comprises a first metal skin, wherein the first metal skin is coated on the outer sides of the plurality of third cell structures arranged in an array; and / or,

[0020] The anti-collision structure includes a second metal skin, which is coated on the outer sides of a plurality of the first cell structures arranged in an array.

[0021] According to at least one embodiment of the present invention, the first metal skin and the second metal skin are both made of aluminum alloy; and / or,

[0022] The first metal skin and the second metal skin are connected by welding.

[0023] According to at least one embodiment of the present invention, the metamaterial structure is an integrally formed part; and / or,

[0024] The material of the metamaterial structure includes one of a nickel-titanium shape memory alloy and an aluminum alloy.

[0025] In a second aspect, the present invention further provides a spacecraft, comprising the anti-collision structure described in the first aspect.

[0026] Among the one or more technical solutions provided in the exemplary embodiments of the present invention, at least one of the following beneficial effects can be achieved.

[0027] The anti-collision structure of a spacecraft in an exemplary embodiment of the present invention includes a beam and a metamaterial structure. The beam is in an arc shape as a whole and has a convex side and a concave side, and the metamaterial structure is connected to the concave side of the beam. The overall profile of the beam is in an arc shape, and the arc-shaped beam is formed by a plurality of third cell structures arranged in an array, and the third cell structure is a square cylindrical structure. At the same time, the thickness of the four fourth wall panels forming the third cell structure gradually increases along the direction from the convex side to the concave side. When the impactor hits the convex side of the beam, the arc-shaped beam further optimizes the force conduction path while ensuring the overall structural stiffness.

[0028] When part of the energy of the impact object is absorbed by the beam, the remaining energy will be effectively transferred to the metamaterial structure located on the concave side of the beam because the beam is an arc-shaped structure. The metamaterial structure is formed by a first cell structure arranged in a multi-row and multi-column array, and a second cell structure is arranged at the intersecting wall segment shared by adjacent first cell structures, wherein the first cell structure and the second cell structure are both square cylindrical structures. Specifically, the central axis of the second cell structure coincides with the central axis of the intersecting wall segment, and the two ends of the third wall plate of the second cell structure intersect with part of the first wall plate and part of the second wall plate of the same first cell structure, respectively, to form an angle of 45°. At the same time, the second cell structure is not arranged at all intersecting wall segments, but is arranged in a staggered arrangement, that is, whether in the first direction or the second direction, the second cell structure is arranged at every other intersecting wall segment. The metamaterial structure of this arrangement can not only evenly disperse the collision energy in multiple directions, but also further absorb the collision energy in the form of deformation, crack extension and local damage.

[0029] Furthermore, along the direction away from the beam, the thickness of the first wall plate gradually increases, the size (side length) of the second cell structure increases, and the thickness also increases; that is, the metamaterial structure improves the energy absorption capacity in different directions through the synergy between the gradient wall thickness of the first cell structure and the gradient enhancement of the second cell structure. Based on this, the anti-collision structure provided by the exemplary embodiment of the present invention introduces multiple types of gradient cell structures, and on the basis of ensuring the overall structural stiffness, the structure is simple, and the performance of lightweight and energy absorption is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] The accompanying drawings illustrate exemplary embodiments of the present invention and together with the description serve to explain the principles of the present invention, and these drawings are included to provide a further understanding of the present invention and are incorporated in and constitute a part of this specification;

[0031] Figure 1 is an isometric structural schematic diagram of an anti-collision structure according to an embodiment of the present invention;

[0032] Figure 2 is a schematic diagram of the front view of the anti-collision structure according to an embodiment of the present invention;

[0033] Figure 3 is a schematic diagram of an axonometric structure of a beam member according to an embodiment of the present invention;

[0034] Figure 4 is a schematic diagram of the main structure of a metamaterial structure according to an embodiment of the present invention;

[0035] Figure 5 4 is a diagram showing the energy absorption effect of the anti-collision structure according to an embodiment of the present invention.

[0036] Figure numerals: 10, first cell structure; 11, first wall panel; 12, second wall panel; 13, intersecting wall segment; 20, second cell structure; 23, third wall panel; 30, third cell structure; 31, convex side; 32, concave side; 34, fourth wall panel. DETAILED DESCRIPTION

[0037] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0038] One of the most severe challenges facing spacecraft in space travel is high-speed micrometeorite collisions. When flying at high speed, spacecraft not only need to withstand the huge impact caused by external collisions, but also must maintain sufficient structural strength to prevent excessive deformation and ensure the stability of the spacecraft. The lightweight design of energy-absorbing structures is equally important because it directly affects the total mass of the spacecraft, thereby affecting the propulsion system and power efficiency of the spacecraft. Therefore, the relationship between stiffness, energy absorption capacity and lightweight must be weighed during design to ensure that the spacecraft can effectively absorb impact energy while maintaining high flight performance.

[0039] In view of the above problems, the collision avoidance structure of the spacecraft provided by the exemplary embodiment of the present invention uses various types of gradient cell structures, which can effectively absorb and disperse the collision energy through multi-directional plastic deformation and crack extension during the collision process. It is more advantageous in real collision situations and can better dissipate large collision energy without sacrificing structural stiffness.

[0040] Figure 1 is an isometric structural schematic diagram of an anti-collision structure according to an embodiment of the present invention; Figure 2 Schematic diagram of the front view of the anti-collision structure according to an embodiment of the present invention. Figure 1-Figure 2 As shown, the anti-collision structure of a spacecraft provided by an exemplary embodiment of the present invention includes a beam and a metamaterial structure. The beam is generally arc-shaped and has a convex side 31 and a concave side 32 , and the metamaterial structure is connected to the concave side 32 of the beam.

[0041] The beam is in a generally arc-shaped curved shape, and the metamaterial structure connected to the concave side 32 of the beam can be arranged on the body of the spacecraft, and the convex side 31 of the beam faces the outside of the body of the spacecraft to bear the huge impact caused by the external collision. It should be noted that there can be multiple metamaterial structures arranged on the concave side 32 of the beam, and the beam of the anti-collision structure can be designed according to the shape of the body of the spacecraft to serve as a barrier for the spacecraft to resist collision as much as possible.

[0042] Figure 3 Schematic diagram of the axonometric structure of a beam member according to an embodiment of the present invention. Figure 3 As shown, the beam member of an exemplary embodiment of the present invention includes a plurality of third cell structures 30 arranged in an array, the third cell structure 30 is a square cylindrical structure, and the thickness of the four fourth wall panels 34 forming the third cell structure 30 gradually increases along the direction from the convex side 31 to the concave side 32.

[0043] For example, multiple columns of third cellular structures 30 are distributed in an array along the arc length direction of the beam, and 2 rows or 1 row of third cellular structures 30 are distributed along the width direction of the beam. It should be noted that the number of third cellular structures 30 in the width direction of the beam can be increased or decreased according to actual needs, and the fourth wall panels 34 of adjacent third cellular structures 30 can be shared.

[0044] For example, the four fourth wall panels 34 are arranged to form a cylindrical structure with a square cross section, and the central axis direction is the radial direction of the beam. For example, the side length of the outer contour of the cross section of the third cell structure 30 is 50 mm. Along the direction from the convex side 31 to the concave side 32, the thickness of the four fourth wall panels 34 forming the third cell structure 30 gradually increases. Figure 3 As shown, the minimum thickness t of the fourth wall plate 34 min =1.2mm, maximum thickness t max =2.2mm.

[0045] As can be seen from the above, when the curved beam is hit by an external load, it can optimize the force conduction path, and then effectively transfer it to the metamaterial structure to further dissipate energy. At the same time, the evenly distributed square third cell structure 30 can make the overall structure of the beam have a certain rigidity. The thickness gradient design of the fourth wall plate 34 of the third cell structure 30 ensures a certain rigidity on the basis of effectively absorbing and dispersing energy, and is more lightweight.

[0046] Figure 4 Schematic diagram of the main structure of the metamaterial structure according to an embodiment of the present invention. Figure 4 As shown, the metamaterial structure of an exemplary embodiment of the present invention includes a plurality of first wall panels 11 parallel to the first direction and a plurality of second wall panels 12 parallel to the second direction, and the plurality of first wall panels 11 and the plurality of second wall panels 12 intersect with each other to form a plurality of first cell structures 10 arranged in an array; wherein the first direction is perpendicular to the second direction, and the first wall panels 11 and the second wall panels 12 intersect to form a plurality of intersecting wall segments 13 arranged in an array; the first cell structure 10 is a square cylindrical structure; the metamaterial structure also includes a plurality of second cell structures 20, and the second cell structure 20 is a square cylindrical structure, and the central axis of the second cell structure 20 coincides with the central axis of the intersecting wall segment 13, and the four third wall panels 23 forming the second cell structure 20 are at an angle of 45° with the first wall panel 11.

[0047] Exemplarily, on the same second wall panel 12, a second cellular structure 20 is set at one of the two adjacent intersecting wall segments 13, and the second cellular structure 20 is not set at the other intersecting wall segment 13; on the same first wall panel 11, a second cellular structure 20 is set at one of the two adjacent intersecting wall segments 13, and the second cellular structure 20 is not set at the other intersecting wall segment.

[0048] Exemplarily, along the direction away from the beam, the thickness of the first wall plate 11 gradually increases, and the side length of the second cell structure 20 increases, and the thickness of the third wall plate 23 of the second cell structure 20 increases.

[0049] The first cell structure 10 and the second cell structure 20 are both square cylindrical structures, and the central axis directions of the cylindrical structures of the two are parallel to the width direction of the beam, that is, the lengths of the cylindrical structures of the two are the same as the widths of the beam.

[0050] The plurality of first wall panels 11 and the plurality of second wall panels 12 are arranged in an equidistant manner along the first direction and the second direction perpendicular to each other, and a plurality of rows and columns of intersecting wall segments 13 are formed at the intersection of the two. On the other hand, the intersecting wall segment 13 can be regarded as a corner line segment shared by four adjacent first cell structures 10.

[0051] like Figure 4 As shown, the metamaterial structure is formed by an array of first cell structures 10 in 9 rows and 10 columns, and the side length of the square outer contour of each first cell structure 10 is 10 mm. The first wall plate 11 parallel to the first direction is substantially perpendicular to the extension direction of the beam, and the thickness of the first wall plate 11 gradually increases in the direction away from the beam. For example, the thickness t of the first wall plate 11 is x The thickness increases linearly from 1.2mm to 2.2mm.

[0052] In some embodiments, the side length of the square outer contour of the second cellular structure 20 of the metamaterial structure of the exemplary embodiment of the present invention is a, in mm, satisfying a=-0.08f+15.25, and f is the center axis of the second cellular structure 20 and the distance between it and the second wall panel 12 of the metamaterial structure farthest from the beam body.

[0053] For example, the thickness of the third wall plate 23 of the second cell structure 20 is t z =0.1a.

[0054] Specifically, the side length of the second cellular structure 20 ranges from 5 mm to 12.5 mm, that is, along the direction away from the beam, the side length of the second cellular structure 20 increases from 5 mm to a final 12.5 mm, and the thickness increases from 0.5 mm to a final 1.25 mm.

[0055] Exemplarily, the second cell structures 20 at multiple intersecting wall segments 13 on the same second wall plate 12 have the same side lengths, that is, the square side lengths of the second cell structures 20 in the same row are the same, while the square side lengths of the second cell structures 20 in the same column increase.

[0056] Since the second cell structures 20 are staggeredly arranged at the intersecting wall segments 13 of the metamaterial structure, that is, in the same row, the second cell structure 20 is arranged at every other intersecting wall segment 13; in the same column, the second cell structure 20 is arranged at every other intersecting wall segment 13. Therefore, the four third wall panels 23 of the second cell structure 20 can be regarded as the reinforcement structure of the first cell structure 10 at the corner position, and the third wall panel 23 and the first wall panel 11 form an angle of 45°, that is, the third wall panel 23 and the second wall panel 12 also form an angle of 45°.

[0057] Based on this, by introducing a staggered second cellular structure 20 into the first cellular structure 10 arranged in an array, and the first wall panel 11 of the first cellular structure 10 is set in a gradient, the wall thickness and the square side length of the second cellular structure 20 are also set in a gradient. When hit by an external force, it can not only evenly disperse the collision energy in multiple directions, but also further absorb the collision energy through complex changes such as deformation, crack extension and local damage, thereby reducing the impact force transmitted to the spacecraft, thereby achieving efficient energy absorption.

[0058] It can be seen that the metamaterial structure provided by the exemplary embodiment of the present invention achieves a balance between rigidity and flexibility, and can provide a more efficient energy absorption effect without sacrificing structural rigidity, thereby better dissipating the huge impact energy received by the spacecraft in the space environment.

[0059] In some embodiments, the anti-collision structure includes a first metal skin, which is coated on the outside of multiple third cellular structures 30 arranged in an array; the anti-collision structure includes a second metal skin, which is coated on the outside of multiple first cellular structures 10 arranged in an array.

[0060] Exemplarily, the first metal skin and the second metal skin are both made of aluminum alloy; the first metal skin and the second metal skin are welded to each other.

[0061] Since the first metal skin and the second metal skin are made of high-strength and lightweight aluminum alloy, the beam and the metamaterial structure have high bending resistance and can absorb part of the collision energy through plastic deformation. For example, when the convex side 31 of the first metal skin of the beam body is hit, the convex side 31 of the arc-shaped first metal skin first buckles and partially plastically deforms, thereby causing the third cell structure 30 with gradient thickness inside to deform accordingly, thereby absorbing part of the collision energy and transferring the remaining energy through the second metal skin into the metamaterial structure inside.

[0062] In some embodiments, the metamaterial structure is fixedly connected to the beam body through a high-strength welding process, which can ensure that the metamaterial structure will not break or fail during the process of transmitting the impact energy from the beam body to the metamaterial structure, thereby ensuring the energy absorption efficiency of the spacecraft. It should be noted that when the material of the metamaterial structure is an alloy, it can also be directly welded to the beam body without being covered with the second metal skin to form an integral anti-collision structure.

[0063] In some embodiments, the metamaterial structure is an integrally formed part; the material of the metamaterial structure includes one of a nickel-titanium shape memory alloy and an aluminum alloy.

[0064] The material of the metamaterial structure can be aluminum alloy or nickel-titanium shape memory alloy, and it can return to its original state after being deformed by impact.

[0065] The above metamaterial structure can be integrally printed by selective laser melting technology. The metal powder used is nickel-titanium shape memory alloy powder. The nickel-titanium shape memory alloy powder is selectively melted by high-power laser to form a 2D slice of the metamaterial structure. The metamaterial structure is formed by layer-by-layer printing. This integral molding process can make the metamaterial structure without weak links and improve its ability to absorb energy.

[0066] A specific embodiment is given below to further illustrate the energy absorption effect of the anti-collision structure of the spacecraft according to the exemplary embodiment of the present invention.

[0067] Example 1

[0068] like Figure 4 As shown, the material of the metamaterial structure is aluminum alloy, and the geometric parameters of the metamaterial structure are: the side length a of the second cell structure 20 increases from 5 mm to the final 12.5 mm; the thickness of the third wall plate 23 is t z =0.1a.

[0069] The side length of the square outer contour of the first cell structure 10 is 10 mm, and the thickness t of the first wall plate 11 is x The thickness increases linearly from 1.2mm to 2.2mm.

[0070] The beam is made of aluminum alloy. The side length of the outer contour of the cross section of the third cellular structure 30 is 50 mm. The thickness of the fourth wall plate 34 increases linearly from 1.2 mm to 2.2 mm.

[0071] Comparative Example 1

[0072] The difference between this comparative example and the embodiment is that the thickness t of the first wall plate 11 of the first cell structure 10 is x The value is constant at 1.7 mm.

[0073] Comparative Example 2

[0074] The only difference between the comparative example and the embodiment is that the side length a of the second cell structure 20 is a constant value of 9 mm.

[0075] Figure 5 : is an energy absorption effect diagram of the anti-collision structure according to an embodiment of the present invention. Figure 5 As shown, the anti-collision structures of Example 1 and Comparative Examples 1-2 are subjected to quasi-static compression simulation comparison, wherein the horizontal axis represents displacement and the vertical axis represents force. According to the definition of energy absorption, the larger the area enclosed by the force-displacement curve and the horizontal axis, the better the energy absorption effect.

[0076] like Figure 5 As shown, the energy absorption effect of Example 1 is significantly better than that of Comparative Example 2, while the energy absorption effect of Comparative Example 2 is better than that of Comparative Example 1. It can be seen that for the metamaterial structure, there is a synergistic effect between the thickness gradient change of the first wall plate and the gradient change of the side length of the second cell structure, so that Example 1 having both of the above-mentioned gradient changes has a more obvious energy absorption effect.

[0077] By introducing various types of gradient cell structures in the beam body and the metamaterial structure, on the basis of maintaining a certain rigidity and light weight, the collision energy can be effectively absorbed and dispersed through multi-directional plastic deformation and crack expansion during the collision process, and the dissipation of large collision energy in the space environment can be better met. At the same time, the anti-collision structure of the exemplary embodiment of the present invention uses a more simplified design of gradient cells, which can reduce production costs.

[0078] An exemplary embodiment of the present invention further provides a spacecraft, comprising the anti-collision structure of the spacecraft in the above-mentioned embodiment.

[0079] The technical advantages of the above-mentioned spacecraft over the prior art are the same as the technical advantages of the anti-collision structure of the spacecraft in the above-mentioned embodiment, which will not be repeated here.

[0080] It should be understood by those skilled in the art that the above embodiments are only for the purpose of clearly illustrating the present invention, and are not intended to limit the scope of the present invention. For those skilled in the art, other changes or modifications may be made based on the above disclosure, and these changes or modifications are still within the scope of the present invention.

Claims

1. A collision avoidance structure of a spacecraft, characterized in that: It comprises a beam and a metamaterial structure, wherein the beam is in an arc shape as a whole and has a convex side and a concave side, and the metamaterial structure is connected to the concave side of the beam; The metamaterial structure comprises a plurality of first wall plates parallel to a first direction and a plurality of second wall plates parallel to a second direction, wherein the plurality of first wall plates and the plurality of second wall plates intersect with each other to form a plurality of first cell structures arranged in an array; Wherein, the first direction is perpendicular to the second direction, the first wall plate and the second wall plate intersect to form a plurality of intersecting wall segments arranged in an array; the first cell structure is a square cylindrical structure; The metamaterial structure further includes a plurality of second cell structures, wherein the second cell structures are square cylindrical structures, the central axis of the second cell structures coincides with the central axis of the intersecting wall segments, and the four third wall panels forming the second cell structures are in contact with the first wall panel and the second wall panel and are at an angle of 45°; On the same second wall plate, the second cell structure is arranged at one of the two adjacent intersecting wall segments, and the second cell structure is not arranged at the other intersecting wall segment; on the same first wall plate, the second cell structure is arranged at one of the two adjacent intersecting wall segments, and the second cell structure is not arranged at the other intersecting wall segment; Along the direction away from the beam, the thickness of the first wall plate gradually increases, and the side length of the second cell structure increases, and the thickness of the third wall plate of the second cell structure increases.

2. The anti-collision structure according to claim 1, characterized in that: The beam member includes a plurality of third cell structures arranged in an array, the third cell structure is a square cylindrical structure, and the thickness of the four fourth wall plates forming the third cell structure gradually increases along the direction from the convex side to the concave side; and / or, The ratio of the thickness of the third wall plate of the second cell structure to the side length of the second cell structure is 0.

1.

3. The anti-collision structure according to claim 2, characterized in that: The thickness of the first wall plate ranges from 1.2 mm to 2.2 mm; and / or, The thickness of the fourth wall plate ranges from 1.2 mm to 2.2 mm.

4. The anti-collision structure according to claim 1, characterized in that: The side length of the second cell structure ranges from 5 mm to 12.5 mm.

5. The anti-collision structure according to claim 2, characterized in that: The ratio of the side length of the third cell structure to the side length of the first cell structure is 5.

6. The anti-collision structure according to any one of claims 1 to 5, characterized in that: On the same second wall plate, the side lengths of the second cell structures at a plurality of the intersecting wall segments are the same.

7. The anti-collision structure according to claim 2, characterized in that: The anti-collision structure comprises a first metal skin, wherein the first metal skin is coated on the outer sides of a plurality of the third cell structures arranged in an array; and / or, The anti-collision structure includes a second metal skin, which is coated on the outer sides of a plurality of the first cell structures arranged in an array.

8. The anti-collision structure according to claim 7, characterized in that: The first metal skin and the second metal skin are both made of aluminum alloy; and / or, The first metal skin and the second metal skin are connected by welding.

9. The anti-collision structure according to claim 7, characterized in that: The metamaterial structure is an integrally formed part; and / or, The material of the metamaterial structure includes one of a nickel-titanium shape memory alloy and an aluminum alloy.

10. A spacecraft, characterized in that: The anti-collision structure comprises the anti-collision structure according to any one of claims 1 to 9.

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