A morphing satellite structure based on shape memory material

Abstract

The application provides a shape memory material-based metamorphic satellite structure and relates to the technical field of space satellites. The metamorphic satellite structure comprises a variable-configuration regular pentagon module and a variable-configuration regular hexagon module made of shape memory material, the variable-configuration regular pentagon module is connected with the variable-configuration regular hexagon module to form a spherical polyhedral structure, and the variable-configuration regular pentagon module and the variable-configuration regular hexagon module are both used for synchronous contraction or synchronous expansion by temperature change. The structure is optimized through material-structure collaborative design, the characteristics of the multi-stable structure that can still maintain a stable geometric configuration after load removal are utilized, the configuration stability of the system is fundamentally improved, and the dependence on single material characteristics is reduced; even when the shape memory polymer and the composite material thereof cause incomplete phase change due to temperature fluctuation, the system can still maintain a target configuration, and the reliability in an extreme space environment is significantly improved.

Description

Technical Field

[0001] This invention relates to the field of aerospace satellite technology, and more specifically, to a variable satellite structure based on shape memory materials. Background Technology

[0002] Existing mechanically variable-structure satellite structures generally rely on complex drive systems and sophisticated control algorithms, which not only significantly increases system cost and weight but also introduces additional potential failure points. Current variable-structure satellite systems based on shape memory polymers and their composites primarily rely on the shape memory effect of the material under constant external conditions for deformation. While these systems exhibit good reliability under stable environmental parameters, they still face numerous severe challenges in practical space applications. For example, the space environment presents drastic temperature fluctuations (-100℃ to +100℃) and long-term vacuum conditions, leading to reduced deformation accuracy of the shape memory performance. Furthermore, the material's shape recovery rate cannot achieve 100% deformation and recovery, further reducing the satellite's deformation accuracy in the space environment. Summary of the Invention

[0003] The problem this invention addresses is: how to improve the deformation accuracy of satellites in the space environment.

[0004] To address the aforementioned problems, this invention provides a variable-structure satellite structure based on shape memory materials, comprising a variable-structure regular pentagonal module and a variable-structure regular hexagonal module made of shape memory materials. The variable-structure regular pentagonal module and the variable-structure regular hexagonal module are connected to form a spherical polyhedron structure. Both the variable-structure regular pentagonal module and the variable-structure regular hexagonal module are used to synchronously shrink or synchronously expand through temperature changes.

[0005] Optionally, the variable pentagonal module and the variable hexagonal module are connected by a quick-release structure.

[0006] Optionally, both the variable pentagonal module and the variable hexagonal module include multiple curved beam components, which are connected sequentially along the circumference to form the variable pentagonal module or the variable hexagonal module. Each curved beam component constitutes a border of the variable pentagonal module or the variable hexagonal module. Each curved beam component includes a double beam frame and a steady-state link. The double beam frame includes a first steady-state beam, a second steady-state beam, and a steady-state frame connected between the first steady-state beam and the second steady-state beam. The steady-state link is located within the area enclosed by the steady-state frame and is connected to the steady-state frame. The steady-state link and the steady-state frame are used to switch between a contraction steady-state state and an extension steady-state state by changing the temperature.

[0007] Optionally, the thickness of the second steady-state beam is reduced by changing the temperature.

[0008] Optionally, the two ends of the first stable beam are provided with a first wedge-shaped surface structure that connects to other first stable beams. The first stable beams of the plurality of curved beam assemblies are connected through the first wedge-shaped surface structure to form the variable pentagonal module or the variable hexagonal module. The second stable beam in each curved beam assembly is located on the side of the first stable beam away from the center of the variable pentagonal module or the variable hexagonal module. The end of the second stable beam away from the first stable beam is provided with a second wedge-shaped surface structure, which extends along the axis of the second stable beam. The variable pentagonal module and the variable hexagonal module are connected through the second wedge-shaped surface structure to form the spherical polyhedron structure.

[0009] Optionally, the steady-state frame includes two opposing curved beams and two opposing connecting beams, which are alternately connected to form a frame structure. The middle portions of the two curved beams bend towards each other. The middle portion of the first steady-state beam is connected to the middle portion of one of the curved beams, and the middle portion of the second steady-state beam is connected to the middle portion of the other curved beam. The two curved beams are used to achieve reverse buckling deformation through temperature changes. The steady-state linkage is connected between the two connecting beams.

[0010] Optionally, the steady-state connecting rod includes two first connecting rods, two second connecting rods, and two first bending rods. The two first bending rods and the two second connecting rods are alternately connected to form a closed structure. The two first connecting rods are respectively connected to the two connecting beams. The middle parts of the two first bending rods are bent in opposite directions. The two middle parts of the two first connecting rods are respectively connected to the middle parts of the two first bending rods. The middle parts of the two bending rods are used to achieve reverse buckling deformation through temperature changes.

[0011] Optionally, the curved beam assembly further includes a temperature control module, which is installed on the curved beam assembly and is used to adjust the heating temperature of the curved beam assembly.

[0012] Optionally, the curved beam assembly is provided with an anti-radiation layer and a self-cleaning coating.

[0013] Optionally, the shape memory material is at least one of polylactic acid, styrene-butadiene copolymer, epoxy resin, or cyanate ester.

[0014] Compared with related technologies, the shape memory material-based variable satellite structure of this invention utilizes variable-shape regular pentagonal and hexagonal modules made of shape memory materials. The shapes of these modules can be changed by temperature variations, allowing for multi-stable state switching through localized actuation of the shape memory polymer and its composite materials. This reduces system weight and energy consumption, and minimizes the use of traditional drive components (such as motors and hydraulic systems). Furthermore, the variable-shape regular pentagonal and hexagonal modules are connected to form a spherical polyhedral structure. Both modules are used for synchronous reception based on temperature changes. The ability to shrink or extend synchronously allows the variable-configuration regular pentagonal module and variable-configuration regular hexagonal module to maintain their target shape stably even without external energy input, thanks to the strong self-locking capability of the spherical polyhedral structure. This significantly reduces the dependence on continuous actuation. Even when the phase transition of shape memory polymers and their composites is incomplete due to temperature fluctuations, the system can still maintain the target configuration, significantly improving reliability in extreme space environments. Furthermore, it integrates the active actuation characteristics of shape memory smart materials with the configuration stability characteristics of multi-stable mechanical metamaterials, improving the problem that the accuracy of shape memory deployment structures mainly depends on the material itself, thereby improving the deformation accuracy of the satellite in the space environment. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the curved beam assembly in the initial contracted state according to an embodiment of the present invention.

[0016] Figure 2 This is a schematic diagram of the structure of the steady-state connecting rod and the second steady-state beam after deformation in an embodiment of the present invention;

[0017] Figure 3 This is a schematic diagram of the structure of a bent beam after deformation in an embodiment of the present invention;

[0018] Figure 4 This is a schematic diagram of the curved beam assembly in its final extended state after deformation of another curved beam in an embodiment of the present invention;

[0019] Figure 5 This is a schematic diagram of the steady-state connecting rod in its initial state according to an embodiment of the present invention;

[0020] Figure 6 This is a schematic diagram of the steady-state connecting rod in its final state according to an embodiment of the present invention;

[0021] Figure 7 This is a schematic diagram of the variable pentagonal module in its initial state in an embodiment of the present invention.

[0022] Figure 8 This is a schematic diagram of the variable pentagonal module in its final state in an embodiment of the present invention.

[0023] Figure 9 This is a schematic diagram of the variable hexagonal module in its initial state in an embodiment of the present invention.

[0024] Figure 10 This is a schematic diagram of the variable hexagonal module in its final state in an embodiment of the present invention.

[0025] Figure 11 This is a schematic diagram of the initial state of the shape memory material-based modified satellite structure in an embodiment of the present invention;

[0026] Figure 12 This is a schematic diagram of the final state of the shape memory material-based modified satellite structure in an embodiment of the present invention.

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

[0028] 1-Variable pentagonal module; 2-Variable hexagonal module; 3-Spherical polyhedral structure; 4-Curved beam assembly; 5-Double beam frame; 51-First steady-state beam; 52-Second steady-state beam; 53-Steady-state frame; 531-Bending beam; 532-Connecting beam; 54-First wedge-shaped surface structure; 55-Second wedge-shaped surface structure; 6-Steady-state connecting rod; 61-First connecting rod; 62-Second connecting rod; 63-First bending rod. Detailed Implementation

[0029] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0030] In the attached figures, the X-axis represents the horizontal position, with the positive direction of the X-axis (where the arrow points) indicating the right side and the negative direction (opposite to the positive direction) indicating the left side. The Y-axis represents the front-to-back position, with the positive direction of the Y-axis (where the arrow points) indicating the front and the negative direction (opposite to the positive direction) indicating the rear. The Z-axis represents the vertical position, with the positive direction of the Z-axis (where the arrow points) indicating the top and the negative direction (opposite to the positive direction) indicating the bottom. It should be noted that the aforementioned representations of the X, Y, and Z axes are for ease of description and simplification of the invention, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention.

[0031] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in sequences other than those illustrated or described herein.

[0032] Combination Figure 1 As shown, this embodiment of the invention provides a variable satellite structure based on shape memory material, including a variable regular pentagonal module 1 and a variable regular hexagonal module 2 made of shape memory material. The variable regular pentagonal module 1 and the variable regular hexagonal module 2 are connected to form a spherical polyhedron structure 3. Both the variable regular pentagonal module 1 and the variable regular hexagonal module 2 are used to synchronously shrink or synchronously expand by changing temperature.

[0033] Specifically, the shape of the variable-structure regular pentagonal module 1 is as follows: Figure 7 As shown, the shape of the variable-structure regular hexagonal module 2 is as follows: Figure 9 As shown, the variable-structure satellite structure in this embodiment of the invention may specifically include 12 variable-structure regular pentagonal modules 1 and 20 variable-structure hexagonal modules 2. Five variable-structure hexagonal modules 2 are connected to the outside of each variable-structure regular pentagonal module 1, and each variable-structure regular hexagonal module 2 is connected to the outside of each variable-structure regular pentagonal module 1 and other variable-structure regular hexagonal modules 2. The variable-structure regular pentagonal modules 1 and variable-structure regular hexagonal modules 2 are connected by a snap-locking structure, magnetic connection, or tenon and mortise joint, etc. After assembly, the 12 variable-structure regular pentagonal modules 1 and the 20 variable-structure hexagonal modules 2 form a spherical polyhedral structure 3, such as... Figure 11 As shown, 12 variable-structure regular pentagonal modules 1 and 20 variable-structure hexagonal modules 2 form an "Archimedean solid" (e.g., a soccer ball). Initially, as shown... Figure 11 As shown, the spherical polyhedral structure 3 in this embodiment of the invention is in its initial state, which can also be understood as a contracted state. After the 12 variable-structure regular pentagonal modules 1 and the 20 variable-structure hexagonal modules 2 are heated, the 12 variable-structure regular pentagonal modules 1 and the 20 variable-structure hexagonal modules 2 deform synchronously, as shown... Figure 12 As shown, the spherical polyhedral structure 3 in this embodiment of the invention is in an extended state. Before and after the extension, the specific angle combination of the variable pentagonal module 1 and the variable hexagonal module 2 can naturally close into a sphere without additional forced deformation. The variable pentagonal module 1 and the variable hexagonal module 2 are subjected to uniform forces in all directions, which can avoid local stress concentration. The spherical polyhedral structure 3 can be used to improve the structural stability of the variable satellite. In the process of satellite confrontation, the satellite shape can be changed by modification to disrupt the enemy's judgment and obtain greater benefits at a lower cost.

[0034] Therefore, in this embodiment, the variable-form regular pentagonal module 1 and variable-form regular hexagonal module 2, made of shape memory material, can change their shapes through temperature variations. This allows for the localized switching of the multi-stable structure through the localized actuation of the shape memory polymer and its composite materials, reducing system weight and energy consumption. It also reduces the use of traditional drive components (such as motors and hydraulic systems). Furthermore, the variable-form regular pentagonal module 1 and variable-form regular hexagonal module 2 are connected to form a spherical polyhedral structure 3. Both the variable-form regular pentagonal module 1 and variable-form regular hexagonal module 2 are used to synchronously shrink or expand in response to temperature changes. This allows the system to maintain its target shape stably without external energy input during the synchronous contraction or extension of the variable pentagonal module 1 and the variable hexagonal module 2. The strong self-locking capability of the spherical polyhedral structure 3 further reduces reliance on continuous actuation. Even when the phase transition of shape memory polymers and their composites is incomplete due to temperature fluctuations, the system can still maintain the target configuration, significantly improving reliability in extreme space environments. Furthermore, it integrates the active actuation characteristics of shape memory smart materials with the configurational stability characteristics of multi-stable mechanical metamaterials, addressing the issue that the accuracy of shape memory deployment structures primarily depends on the material itself, thereby improving the deformation accuracy of the satellite in the space environment.

[0035] Optionally, the variable-configuration regular pentagonal module 1 and the variable-configuration regular hexagonal module 2 are connected by a quick-release structure.

[0036] Specifically, the quick-release structure can be connected in the following ways: Snap-on locking structure: Titanium alloy spring pins are used to achieve instant locking, with an unlocking force ≤5N; Magnetic connection: A combination of neodymium iron boron permanent magnets (N52 grade) and soft magnetic alloys, with an adsorption strength ≥0.3T; Mortise and tenon structure: An interference fit between a wedge tenon and a mortise, with a tolerance controlled within ±0.05mm.

[0037] Thus, by connecting the variable pentagonal module 1 and the variable hexagonal module 2 through a quick-release structure, a rapid connection between the two modules can be achieved, thereby improving installation efficiency.

[0038] Optionally, combined Figures 1 to 10As shown, both the variable pentagonal module 1 and the variable hexagonal module 2 include multiple curved beam components 4, which are connected sequentially along the circumference to form the variable pentagonal module 1 or the variable hexagonal module 2. Each curved beam component 4 constitutes a border of the variable pentagonal module 1 or the variable hexagonal module 2. Each curved beam component 4 includes a double beam frame 5 and a steady-state link 6. The double beam frame 5 includes a first steady-state beam 51 and a second steady-state beam 52 that are parallel to each other, and a steady-state frame 53 connecting the first steady-state beam 51 and the second steady-state beam 52. The steady-state link 6 is located within the area enclosed by the steady-state frame 53 and is connected to the steady-state frame 53. The steady-state link 6 and the steady-state frame 53 are used to switch between a contraction steady-state state and an extension steady-state state by changing the temperature.

[0039] Specifically, five curved beam components 4 form a variable pentagonal module 1, such as... Figure 7 and Figure 8 As shown, six curved beam components 4 form a variable hexagonal module 2, as... Figure 9 and Figure 10 As shown. In each curved beam assembly 4, as Figures 1 to 7 As shown, the curved beam assembly 4 includes a double-beam frame 5 and a steady-state connecting rod 6. The double-beam frame 5 includes a first steady-state beam 51, a second steady-state beam 52, and a steady-state frame 53 connecting the first steady-state beam 51 and the second steady-state beam 52. The first steady-state beam 51 is parallel to the second steady-state beam 52, and the steady-state frame 53 connects between the first steady-state beam 51 and the second steady-state beam 52. The steady-state connecting rod 6 is located within the area enclosed by the steady-state frame 53 and is connected to the steady-state frame 53. During the transformation, the steady-state connecting rod 6 of the variable-structure regular pentagonal module 1 and the variable-structure regular hexagonal module 2 are simultaneously heated to a temperature T1 (60℃~80℃), preferentially triggering the shrinkage deformation of the steady-state connecting rod 6, such as... Figure 6 As shown, the double-beam frame 5 is driven into a critical steady state; after a delay of 10~30s, the double-beam frame 5 is heated to T2 temperature (100℃~120℃). The T2 temperature of the double-beam frame 5 triggers its own phase transition, completing the shape switching between the variable pentagonal module 1 and the variable hexagonal module 2, as shown. Figure 8 and Figure 10 As shown, this completes the shape change of the modified satellite; the deformation process ensures reversibility through a shape memory recovery rate (≥95%), thereby changing the structure of the entire satellite. Optionally, the thickness of the second steady-state beam 52 is reduced by changing the temperature. In this way, the double beam frame 5 and the steady-state connecting rod 6 can be ensured to undergo stepped deformation based on their deformation temperatures, thereby improving the accuracy of the modification.

[0040] Optionally, combined Figures 1 to 2 As shown, the thickness of the second steady-state beam 52 is reduced by changing the temperature.

[0041] Specifically, the steady-state connecting rod 6 of the variable pentagonal module 1 and the variable hexagonal module 2 are heated to a temperature T1 (60℃~80℃) simultaneously. While the steady-state connecting rod 6 is preferentially triggered to shrink and deform, the thickness of the second steady-state beam 52 is reduced to achieve the initial deformation of the double beam frame 5. After deformation, it reaches another stable state. In conjunction with the deformation of the steady-state connecting rod 6, the curved beam assembly 4 achieves a bistable structure, thereby improving the structural stability of the curved beam assembly 4.

[0042] Optionally, combined Figures 1 to 4 As shown, the two ends of the first stable beam 51 are provided with first wedge-shaped surface structures 54 that connect with other first stable beams 51. The first stable beams 51 of multiple curved beam assemblies 4 are connected through the first wedge-shaped surface structures 54 to form a variable pentagonal module 1 or a variable hexagonal module 2. The second stable beam 52 in each curved beam assembly 4 is located on the side of the first stable beam 51 away from the center of the variable pentagonal module 1 or the variable hexagonal module 2. The end of the second stable beam 52 away from the first stable beam 51 is provided with a second wedge-shaped surface structure 55. The second wedge-shaped surface structure 55 extends along the axis of the second stable beam 52. The variable pentagonal module 1 and the variable hexagonal module 2 are connected through the second wedge-shaped surface structure 55 to form a spherical polyhedron structure 3.

[0043] Specifically, the first wedge-shaped surface structure 54 is disposed at both ends of each first stable beam 51 along its length. Two first wedge-shaped surface structures 54 are inclined toward the middle of the first stable beam 51. Five first stable beams 51 can be sequentially connected through the first wedge-shaped surface structures 54 to form a variable-structure regular pentagonal module 1, and six first stable beams 51 can be sequentially connected through the first wedge-shaped surface structures 54 to form a variable-structure regular hexagonal module 2, ensuring that adjacent first stable beams 51 are tightly connected. The second wedge-shaped surface structure 55 is disposed at the end of the second stable beam 52 away from the first stable beam 51, that is, at the lower end of the second stable beam 52. The second wedge-shaped surface structure 55 extends along the axis of the second stable beam 52. The variable-structure regular pentagonal module 1 and the variable-structure regular hexagonal module 2 are connected through the second wedge-shaped surface structure 55 to form a spherical polyhedron structure 3. The second wedge-shaped surface structure 55 ensures that the variable-structure regular pentagonal module 1 and the variable-structure regular hexagonal module 2 are tightly connected. This ensures the structural connection stability of the formed spherical polyhedron structure 3.

[0044] Optionally, combined Figures 1 to 4As shown, the steady-state frame 53 includes two opposing bending beams 531 and two opposing connecting beams 532. The two bending beams 531 and the two connecting beams 532 are alternately connected to form a frame structure. The middle parts of the two bending beams 531 bend towards each other. The middle part of the first steady-state beam 51 is connected to the middle part of one of the bending beams 531, and the middle part of the second steady-state beam 52 is connected to the middle part of the other bending beam 531. The two bending beams 531 are used to achieve reverse buckling deformation through temperature changes. The steady-state connecting rod 6 is connected between the two connecting beams 532.

[0045] Specifically, one of the two curved beams 531 is located above and the other below, and the two curved beams 531 are parallel to each other. The connecting beam 532 is roughly C-shaped, with the openings of the two connecting beams 532 facing away from each other, and includes a vertical segment in the vertical direction. The two curved beams 531 and the two connecting beams 532 are alternately connected, as shown... Figure 1 As shown, a polygonal variable frame structure is formed, with the middle sections of two curved beams 531 bending towards each other. The middle section of the first stable beam 51 is connected to the middle section of the upper curved beam 531, and the middle section of the second stable beam 52 is connected to the middle section of the lower curved beam 531. A stable connecting rod 6 connects the two vertical segments of the two connecting beams 532. Figure 1 Initially, the double-beam frame 5 and the steady-state connecting rod 6 are in an undeformed state. Simultaneous heating of the double-beam frame 5 and the steady-state connecting rod 6 causes the steady-state connecting rod 6 to contract and deform along the Y-axis, bringing the two vertical segments of the two connecting beams 532 closer together. Simultaneously, the second steady-state beam 52 thins, and the curved beam assembly 4 reaches a steady-state structure. Upon further heating, firstly, the middle section of the upper curved beam 531 bends upwards, at which point the curved beam assembly 4 reaches a steady-state structure. Upon further heating, the middle section of the lower curved beam 531 bends downwards, ultimately achieving another steady-state structure, which is the final deformed structure of the curved beam assembly 4. Thus, the deformation of the curved beam assembly 4 can be triggered stepwise by the phase change temperature gradient, improving the deformation flexibility of the curved beam assembly 4.

[0046] Optionally, combined Figure 1 , Figure 5 and Figure 6 As shown, the steady-state connecting rod 6 includes two first connecting rods 61, two second connecting rods 62, and two first bending rods 63. The two first bending rods 63 and the two second connecting rods 62 are alternately connected to form a closed structure. The two first connecting rods 61 are respectively connected to two connecting beams 532. The middle parts of the two first bending rods 63 are bent in opposite directions. The two middle parts of the two first connecting rods 61 are respectively connected to the middle parts of the two first bending rods 63. The middle parts of the two bending rods 63 are used to achieve reverse buckling deformation by changing the temperature.

[0047] Specifically, during heating, the middle sections of the two first bending rods 63 move towards each other under the connection of the two second connecting rods 62, causing the two first connecting rods 61 to move towards each other, thereby realizing the movement of the two connecting beams 532 towards each other. The deformation of the steady-state connecting rod 6 realizes the deformation of the steady-state frame 53, so that the curved beam assembly 4 reaches a stable state. In this way, the curved beam assembly 4 has multiple stable states, and each stable state can be precisely adjusted by the temperature change of the shape memory material and the fusion of the structure, thereby reducing the dependence on the temperature change of the shape memory material.

[0048] Optionally, the curved beam assembly 4 also includes a temperature control module, which is installed on the curved beam assembly 4 and is used to adjust the heating temperature of the curved beam assembly 4.

[0049] Specifically, the temperature control module consists of micro heating elements or a variable resistance layer, which is used to precisely control the phase transition temperature of the shape memory polymer locally to achieve step-by-step deformation. The temperature control module adopts PID closed-loop control logic, combined with feedback from external temperature sensors, to automatically adjust the heating power, reduce energy consumption and improve the deformation accuracy of the curved beam assembly 4.

[0050] Optionally, the curved beam assembly 4 is provided with an anti-radiation layer and a self-cleaning coating.

[0051] Specifically, the radiation-resistant layer can be a polyimide film, and the self-cleaning coating can be a titanium dioxide photocatalytic material, thereby enhancing the adaptability to the space environment.

[0052] Optionally, the shape memory material is at least one of polylactic acid, styrene-butadiene copolymer, epoxy resin, or cyanate ester. This expands the range of shape memory materials, reducing manufacturing difficulty and cost.

[0053] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.

Claims

1. A variable-structure satellite structure based on shape memory materials, characterized in that, Includes a variable-form regular pentagonal module (1) and a variable-form regular hexagonal module (2) made of shape memory material. The variable-form regular pentagonal module (1) and the variable-form regular hexagonal module (2) are connected to form a spherical polyhedral structure (3). Both the variable-form regular pentagonal module (1) and the variable-form regular hexagonal module (2) are used to synchronously shrink or synchronously expand by changing temperature. Both the variable-form regular pentagonal module (1) and the variable-form regular hexagonal module (2) include multiple curved beam components (4). The multiple curved beam components (4) are connected sequentially along the circumference to form the variable-form regular pentagonal module (1) or the variable-form regular hexagonal module (2). Each curved beam component ( 4) A frame that constitutes the variable pentagonal module (1) or the variable hexagonal module (2); each of the curved beam components (4) includes a double beam frame (5) and a steady link (6), the double beam frame (5) includes a first steady beam (51) and a second steady beam (52) that are parallel to each other and a steady frame (53) connected between the first steady beam (51) and the second steady beam (52), the steady link (6) is located in the area enclosed by the steady frame (53) and is connected to the steady frame (53), the steady link (6) and the steady frame (53) are used to switch between a contraction steady state and an extension steady state by changing the temperature.

2. The shape memory material-based modified satellite structure according to claim 1, characterized in that, The variable pentagonal module (1) and the variable hexagonal module (2) are connected by a quick-release structure.

3. The shape memory material-based modified satellite structure according to claim 2, characterized in that, The thickness of the second steady-state beam (52) is reduced by changing the temperature.

4. The shape memory material-based modified satellite structure according to claim 2, characterized in that, The first stable beam (51) has a first wedge-shaped surface structure (54) at both ends connected to other first stable beams (51). The first stable beams (51) of the multiple curved beam assemblies (4) are connected through the first wedge-shaped surface structure (54) to form the variable pentagonal module (1) or the variable hexagonal module (2). The second stable beam (52) in each curved beam assembly (4) is located on the side of the first stable beam (51) away from the center of the variable pentagonal module (1) or the variable hexagonal module (2). The second stable beam (52) is provided with a second wedge-shaped surface structure (55) at the end away from the first stable beam (51). The second wedge-shaped surface structure (55) extends along the axis of the second stable beam (52). The variable pentagonal module (1) and the variable hexagonal module (2) are connected through the second wedge-shaped surface structure (55) to form the spherical polyhedron structure (3).

5. The shape memory material-based modified satellite structure according to claim 2, characterized in that, The steady frame (53) includes two opposing curved beams (531) and two opposing connecting beams (532), which are alternately connected to form a frame structure. The middle parts of the two curved beams (531) are bent towards each other. The middle part of the first steady beam (51) is connected to the middle part of one of the curved beams (531), and the middle part of the second steady beam (52) is connected to the middle part of the other curved beam (531). The two curved beams (531) are used to achieve reverse buckling deformation by changing the temperature. The steady link (6) is connected between the two connecting beams (532).

6. The shape memory material-based modified satellite structure according to claim 5, characterized in that, The steady-state connecting rod (6) includes two first connecting rods (61), two second connecting rods (62), and two first bending rods (63). The two first bending rods (63) and the two second connecting rods (62) are alternately connected to form a closed structure. The two first connecting rods (61) are respectively connected to the two connecting beams (532). The middle parts of the two first bending rods (63) are bent in opposite directions. The two middle parts of the two first connecting rods (61) are respectively connected to the middle parts of the two first bending rods (63). The middle parts of the two bending rods (63) are used to achieve reverse buckling deformation by changing the temperature.

7. The shape memory material-based modified satellite structure according to claim 2, characterized in that, The curved beam assembly (4) also includes a temperature control module, which is installed on the curved beam assembly (4) and is used to adjust the heating temperature of the curved beam assembly (4).

8. The shape memory material-based modified satellite structure according to claim 2, characterized in that, The curved beam assembly (4) is provided with an anti-radiation layer and a self-cleaning coating.

9. The shape memory material-based modified satellite structure according to claim 1, characterized in that, The shape memory material is at least one of polylactic acid, styrene-butadiene copolymer, epoxy resin, or cyanate ester.

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