Variable-structure satellite structure based on shape memory material

Abstract

The invention provides a variable-structure satellite structure based on a shape memory material, and relates to the technical field of spaceflight satellites. The variable structure satellite structure comprises a variable structure regular pentagon module and a variable structure regular hexagon module which are made of shape memory materials, and the variable structure regular pentagon module and the variable structure regular hexagon module are connected to form a sphere-like polyhedral structure. The variable structure regular pentagon modules and the variable structure regular hexagon modules are used for synchronously contracting or synchronously extending through temperature changes. Structural optimization is carried out through material-structure collaborative design, the characteristic that a multistable structure can still keep a stable geometric configuration after a load is removed is utilized, the configuration stability of a system is fundamentally improved, and dependence on the characteristic of a single material is reduced; even if the phase change of the shape memory polymer and the composite material thereof is incomplete due to temperature fluctuation, the system can still maintain the target configuration, and the reliability in an extreme space environment is remarkably improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace satellites, and more particularly, to a variable-configuration satellite structure based on shape memory materials. Background Art

[0002] Existing mechanically variable-configuration satellite structures generally rely on complex drive systems and sophisticated control algorithms, which not only significantly increase the system cost and weight but also introduce additional failure risk points. Current variable-configuration satellite systems based on shape memory polymers and their composites mainly rely on the shape memory effect of materials under a constant external environment. Although such systems exhibit good reliability under working conditions with stable environmental parameters, they still face many severe challenges in actual space applications. For example, there are drastic temperature fluctuations (-100°C to +100°C) and long-term vacuum conditions in the space environment, resulting in a decrease in the deformation accuracy of the shape memory performance. Moreover, the shape recovery rate of the material itself cannot achieve 100% deformation and recovery, reducing the deformation accuracy of the satellite in the space environment. Summary of the Invention

[0003] The problem solved by the present invention is: how to improve the deformation accuracy of a satellite in the space environment.

[0004] To solve the above problems, the present invention provides a variable-configuration satellite structure based on shape memory materials, including a variable-configuration regular pentagon module and a variable-configuration regular hexagon module made of shape memory materials. The variable-configuration regular pentagon module and the variable-configuration regular hexagon module are connected to form a quasi-spherical polyhedron structure. Both the variable-configuration regular pentagon module and the variable-configuration regular hexagon module are used to synchronously contract or synchronously extend by changing the temperature.

[0005] Optionally, the variable-configuration regular pentagon module and the variable-configuration regular hexagon module are connected by a quick-release structure.

[0006] Optionally, both the variable-configuration regular pentagon module and the variable-configuration regular hexagon module include a plurality of curved beam assemblies. The plurality of curved beam assemblies are sequentially connected in a circumferential direction to enclose the variable-configuration regular pentagon module or the variable-configuration regular hexagon module. Each curved beam assembly forms a side frame of the variable-configuration regular pentagon module or the variable-configuration regular hexagon module. Each curved beam assembly 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 that are parallel to each other, 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 surrounded 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 contracted steady state and an extended steady state by changing the temperature.

[0007] Optionally, the thickness of the second steady-state beam is used to be reduced by a change in temperature.

[0008] Optionally, first wedge surface structures for connecting to other first steady-state beams are provided at two ends of the first steady-state beam, and the first steady-state beams of multiple curved beam assemblies are connected through the first wedge surface structures to form the variable pentagon module or form the variable hexagon module; the second steady-state beam in each curved beam assembly is located on a side of the first steady-state beam away from the center of the variable pentagon module or the variable hexagon module; a second wedge surface structure is provided at one end of the second steady-state beam facing away from the first steady-state beam, the second wedge surface structure extends along the axis of the second steady-state beam, and the variable pentagon module and the variable hexagon module are connected through the second wedge surface structure to form the spherical polyhedron structure.

[0009] Optionally, the steady-state frame includes two opposite curved beams and two opposite connecting beams, the two curved beams and the two connecting beams are alternately connected to enclose a frame structure, the middle parts of the two curved beams are bent towards each other, the middle part of the first steady-state beam is connected to the middle part of one of the curved beams, the middle part of the second steady-state beam is connected to the middle part of the other curved beam, the two curved beams are used to achieve reverse buckling deformation by a change in temperature, and the steady-state connecting rod 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 curved rods, the two first curved rods and the two second connecting rods are alternately connected to enclose a closed structure, the two first connecting rods are respectively connected to the two connecting beams, the middle parts of the two first curved rods are bent away from each other, the two middle parts of the two first connecting rods are respectively connected to the middle parts of the two first curved rods, and the middle parts of the two curved rods are used to achieve reverse buckling deformation by a change in temperature.

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

[0012] Optionally, a radiation-resistant layer and a self-cleaning coating are provided on the curved beam assembly.

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

[0014] Compared with the related technologies, the allosteric satellite structure based on shape memory materials of the present invention utilizes variable-configuration regular pentagon modules and variable-configuration regular hexagon modules made of shape memory materials, and can achieve changes in the shapes of the variable-configuration regular pentagon modules and the variable-configuration regular hexagon modules through temperature changes. Thus, the state switching of the multi-stable structure can be realized through the local driving of shape memory polymers and their composites, reducing the system weight and energy consumption; the use of traditional driving components (such as motors and hydraulic systems) is reduced. Then, by connecting the variable-configuration regular pentagon modules and the variable-configuration regular hexagon modules to form a quasi-spherical polyhedron structure, both the variable-configuration regular pentagon modules and the variable-configuration regular hexagon modules are used to synchronously contract or synchronously extend through temperature changes. During the synchronous contraction or synchronous extension of the variable-configuration regular pentagon modules and the variable-configuration regular hexagon modules, due to the strong self-locking ability of the quasi-spherical polyhedron structure, the target shape can be stably maintained without external energy input, significantly reducing the dependence on continuous driving; even when the phase change of the shape memory polymer and its composites is incomplete due to temperature fluctuations, the system can still maintain the target configuration, significantly improving the reliability in extreme space environments; furthermore, the active driving characteristics of shape memory intelligent materials and the configuration stability characteristics of multi-stable mechanical metamaterials are integrated, improving the problem that the accuracy of the shape memory deployment structure mainly depends on the material itself, thereby improving the deformation accuracy of the satellite in the space environment. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 FIG. is a schematic structural diagram of the curved beam assembly in the initial contraction state in the embodiment of the present invention; Figure 2 FIG. is a schematic structural diagram of the steady-state connecting rod and the second steady-state beam after deformation in the embodiment of the present invention; Figure 3 FIG. is a schematic structural diagram of a curved beam after deformation in the embodiment of the present invention; Figure 4 FIG. is a schematic structural diagram of the curved beam assembly in the final extended state after deformation of another curved beam in the embodiment of the present invention; Figure 5 FIG. is a schematic structural diagram of the steady-state connecting rod in the initial state in the embodiment of the present invention; Figure 6 FIG. is a schematic structural diagram of the steady-state connecting rod in the final state in the embodiment of the present invention; Figure 7 FIG. is a schematic diagram of the variable-configuration regular pentagon module in the initial state in the embodiment of the present invention; Figure 8 FIG. is a schematic diagram of the variable-configuration regular pentagon module in the final state in the embodiment of the present invention; Figure 9Schematic diagram of the variable - configuration regular hexagon module in the initial state in the embodiments of the present invention; Figure 10 Schematic diagram of the variable - configuration regular hexagon module in the final state in the embodiments of the present invention; Figure 11 Schematic diagram of the initial state of the variable - configuration satellite structure based on shape - memory material in the embodiments of the present invention; Figure 12 Schematic diagram of the final state of the variable - configuration satellite structure based on shape - memory material in the embodiments of the present invention.

[0016] Explanation of reference numerals: 1 - Variable - configuration regular pentagon module; 2 - Variable - configuration regular hexagon module; 3 - Spherical - like polyhedron structure; 4 - Curved beam assembly; 5 - Double - beam frame; 51 - First steady - state beam; 52 - Second steady - state beam; 53 - Steady - state frame; 531 - Curved 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 curved rod. Detailed implementation manners

[0017] To make the above - mentioned objects, features, and advantages of the present invention more obvious and understandable, the following describes the specific embodiments of the present invention in detail with reference to the drawings.

[0018] In the drawings, the X - axis represents the horizontal position, and the positive direction of the X - axis (i.e., the arrow direction of the X - axis) represents the right side, and the negative direction of the X - axis (i.e., the direction opposite to the positive direction of the X - axis) represents the left side; the Y - axis represents the front - rear position, and the positive direction of the Y - axis (i.e., the arrow direction of the Y - axis) represents the front side, and the negative direction of the Y - axis (i.e., the direction opposite to the positive direction of the Y - axis) represents the rear side; the Z - axis represents the up - down position, and the positive direction of the Z - axis (i.e., the arrow direction of the Z - axis) represents the upper side, and the negative direction of the Z - axis (i.e., the direction opposite to the positive direction of the Z - axis) represents the lower side. At the same time, it should be noted that the above - mentioned representation meanings of the X - axis, Y - axis, and Z - axis are only for facilitating the description of the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be understood as a limitation to the present invention.

[0019] It should be noted that the terms "first", "second", etc. in the description and claims of the present invention and the above - mentioned drawings are used to distinguish similar objects, and do not necessarily need to describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances so that the embodiments of the present invention described here can be implemented in an order different from those illustrated or described here.

[0020] Combined with Figure 1As shown in the figure, an embodiment of the present invention provides a variable-structure satellite structure based on shape memory materials, which includes a variable-structure regular pentagon module 1 and a variable-structure regular hexagon module 2 made of shape memory materials. The variable-structure regular pentagon module 1 and the variable-structure regular hexagon module 2 are connected to form a quasi-spherical polyhedron structure 3. Both the variable-structure regular pentagon module 1 and the variable-structure regular hexagon module 2 are used to synchronously contract or synchronously extend by changing the temperature.

[0021] Specifically, the shape of the variable-structure regular pentagon module 1 is as Figure 7 shown, and the shape of the variable-structure regular hexagon module 2 is as Figure 9 shown. The variable-structure satellite structure in the embodiment of the present invention may specifically include 12 variable-structure regular pentagon modules 1 and 20 variable-structure hexagon modules 2. Five variable-structure hexagon modules 2 are connected to the outside of one variable-structure regular pentagon module 1. One variable-structure regular hexagon module 2 is connected to the variable-structure regular pentagon module 1 and other variable-structure regular hexagon modules 2 on the outside. The variable-structure regular pentagon module 1 and the variable-structure regular hexagon module 2 are connected by means of a snap-lock structure, magnetic attraction connection or mortise and tenon, etc. After assembly, 12 variable-structure regular pentagon modules 1 and 20 variable-structure hexagon modules 2 form a quasi-spherical polyhedron structure 3, as Figure 11 shown. 12 variable-structure regular pentagon modules 1 and 20 variable-structure hexagon modules 2 form an "Archimedean solid" (for example, a football). Initially, as Figure 11 shown, the quasi-spherical polyhedron structure 3 in the embodiment of the present invention is in an initial state, which can also be understood as a contracted state. After the 12 variable-structure regular pentagon modules 1 and 20 variable-structure hexagon modules 2 are heated, the 12 variable-structure regular pentagon modules 1 and 20 variable-structure hexagon modules 2 deform synchronously, as Figure 12 shown, so that the quasi-spherical polyhedron structure 3 in the embodiment of the present invention is in an extended state. Before and after the extension, the specific angle combinations of the variable-structure regular pentagon module 1 and the variable-structure regular hexagon module 2 can naturally close into a sphere without additional forced deformation. The variable-structure regular pentagon module 1 and the variable-structure regular hexagon module 2 are uniformly stressed in all directions, which can avoid local stress concentration, so as to improve the structural stability of the variable-structure satellite by using the quasi-spherical polyhedron structure 3. Furthermore, in the process of satellite confrontation, the satellite morphology can be changed by variable structure, so as to play a function of disturbing the judgment of the enemy and obtain greater benefits at a smaller cost.

[0022] Therefore, in this embodiment, by using the variable-configuration regular pentagon module 1 and the variable-configuration regular hexagon module 2 made of shape memory materials, the shape changes of the variable-configuration regular pentagon module 1 and the variable-configuration regular hexagon module 2 can be realized through temperature changes. Thus, the state switching of the multi-stable structure can be achieved through the local driving of shape memory polymers and their composites, reducing the system weight and energy consumption; the use of traditional driving components (such as motors and hydraulic systems) is reduced. Then, the variable-configuration regular pentagon module 1 and the variable-configuration regular hexagon module 2 are connected to form a quasi-spherical polyhedron structure 3. Both the variable-configuration regular pentagon module 1 and the variable-configuration regular hexagon module 2 are used to synchronously contract or synchronously extend through temperature changes. During the synchronous contraction or synchronous extension of the variable-configuration regular pentagon module 1 and the variable-configuration regular hexagon module 2, the quasi-spherical polyhedron structure 3 has a strong self-locking ability and can stably maintain the target shape without external energy input, significantly reducing the dependence on continuous driving; even when the phase change of the shape memory polymer and its composites is incomplete due to temperature fluctuations, the system can still maintain the target configuration, significantly improving the reliability in extreme space environments; furthermore, the active driving characteristics of shape memory intelligent materials are integrated 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 satellites in space environments.

[0023] Optionally, the variable-configuration regular pentagon module 1 and the variable-configuration regular hexagon module 2 are connected through a quick-release structure.

[0024] Specifically, the specific connection methods of the quick-release structure can be: snap-lock structure: instant locking is achieved by using a titanium alloy spring pin, and the unlocking force ≤ 5N; magnetic attraction 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: interference fit between a wedge-shaped tenon and a mortise, with the tolerance controlled within ±0.05mm.

[0025] In this way, by connecting the variable-configuration regular pentagon module 1 and the variable-configuration regular hexagon module 2 through a quick-release structure, the quick connection of the variable-configuration regular pentagon module 1 and the variable-configuration regular hexagon module 2 can be realized to improve the installation efficiency.

[0026] Optionally, in combination with Figures 1 to 10As shown, the variable pentagon module 1 and the variable hexagon module 2 both include a plurality of curved beam components 4. The plurality of curved beam components 4 are sequentially connected in the circumferential direction to enclose the variable pentagon module 1 or the variable hexagon module 2. Each curved beam component 4 constitutes a side frame of the variable pentagon module 1 or the variable hexagon module 2; each curved beam component 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 that are parallel to each other, and a steady-state frame 53 connected 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. The steady-state connecting rod 6 and the steady-state frame 53 are used to switch between a contracted steady state and an extended steady state by changing the temperature.

[0027] Specifically, five curved beam components 4 form the variable pentagon module 1, as Figure 7 and Figure 8 shown. Six curved beam components 4 form the variable hexagon module 2, as Figure 9 and Figure 10 shown. In each curved beam component 4, as Figures 1 to 7 shown, the curved beam component 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 connected between 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. The steady-state frame 53 is connected 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 shape change, the steady-state connecting rods 6 of both the variable pentagon module 1 and the variable hexagon module 2 are heated to the temperature T1 (60°C - 80°C) simultaneously. The contraction deformation of the steady-state connecting rod 6 is preferentially triggered, as Figure 6 shown, driving the double-beam frame 5 into the critical steady state; after a delay of 10 - 30 s, the double-beam frame 5 is heated to the temperature T2 (100°C - 120°C). The temperature T2 of the double-beam frame 5 triggers its own phase change, completing the shape switching of the variable pentagon module 1 and the variable hexagon module 2, as Figure 8 and Figure 10 shown, and then completing the shape change of the variable-configuration satellite; the reversibility of the deformation process is ensured by the shape memory recovery rate (≥95%), thereby changing the structure of the entire satellite. Optionally, the thickness of the second steady-state beam 52 is used to decrease by changing the temperature. In this way, the stepped deformation of the double-beam frame 5 and the steady-state connecting rod 6 can be ensured according to the deformation temperatures of the double-beam frame 5 and the steady-state connecting rod 6, so as to improve the shape change accuracy.

[0028] Optionally, as combined with Figures 1 to 2 shown, the thickness of the second steady-state beam 52 is used to decrease by changing the temperature.

[0029] Specifically, while heating the steady-state link 6 of the variable pentagon module 1 and the variable hexagon module 2 to the temperature T1 (60 °C to 80 °C), and preferentially triggering the contraction deformation of the steady-state link 6, the thickness of the second steady-state beam 52 decreases to achieve the preliminary deformation of the double-beam frame 5, and reaches another stable state after deformation. In cooperation with the deformation of the steady-state link 6, the curved beam assembly 4 reaches a bistable structure, thereby improving the structural stability of the curved beam assembly 4.

[0030] Optionally, in combination with Figures 1 to 4 As shown, first wedge surface structures 54 connected to other first steady-state beams 51 are provided at both ends of the first steady-state beam 51. The first steady-state beams 51 of multiple curved beam assemblies 4 are connected through the first wedge surface structures 54 to form a variable pentagon module 1 or a variable hexagon module 2; the second steady-state beam 52 in each curved beam assembly 4 is located on one side of the first steady-state beam 51 away from the center of the variable pentagon module 1 or the variable hexagon module 2; a second wedge surface structure 55 is provided at one end of the second steady-state beam 52 facing away from the first steady-state beam 51, and the second wedge surface structure 55 extends along the axis of the second steady-state beam 52. The variable pentagon module 1 and the variable hexagon module 2 are connected through the second wedge surface structure 55 to form a spherical polyhedron structure 3.

[0031] Specifically, the first wedge surface structures 54 are provided at both ends of each first steady-state beam 51 in the length direction, and the two first wedge surface structures 54 incline towards the middle of the first steady-state beam 51. Five first steady-state beams 51 can be sequentially connected into a variable pentagon module 1 through the first wedge surface structures 54, and six first steady-state beams 51 can be sequentially connected into a variable hexagon module 2 through the first wedge surface structures 54, ensuring that adjacent two first steady-state beams 51 are tightly connected. The second wedge surface structure 55 is provided at one end of the second steady-state beam 52 facing away from the first steady-state beam 51, that is, the lower end of the second steady-state beam 52, and the second wedge surface structure 55 extends along the axis of the second steady-state beam 52. The variable pentagon module 1 and the variable hexagon module 2 are connected through the second wedge surface structure 55 to form a spherical polyhedron structure 3, and the second wedge surface structure 55 ensures that the variable pentagon module 1 and the variable hexagon module 2 are tightly connected. In this way, the structural connection stability of the formed spherical polyhedron structure 3 is ensured.

[0032] Optionally, in combination with Figures 1 to 4As shown, the steady-state frame 53 includes two opposite curved beams 531 and two opposite connecting beams 532. The two curved beams 531 and the two connecting beams 532 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-state beam 51 is connected to the middle part of one of the curved beams 531, and the middle part of the second steady-state 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 through temperature change. The steady-state connecting rod 6 is connected between the two connecting beams 532.

[0033] Specifically, one of the two curved beams 531 is located above, and the other is located below. The two curved beams 531 are parallel to each other. The shape of the connecting beam 532 is roughly in a C shape. The openings of the two connecting beams 532 face away from each other and include vertical segments in the vertical direction. The two curved beams 531 and the two connecting beams 532 are alternately connected, as Figure 1 shown, to form a polygon variable structure frame. The middle parts of the two curved beams 531 are bent towards each other. The middle part of the first steady-state beam 51 is connected to the middle part of the upper curved beam 531, and the middle part of the second steady-state beam 52 is connected to the middle part of the lower curved beam 531. The steady-state connecting rod 6 is connected between the two vertical segments of the two connecting beams 532. As Figure 1 described, initially, the double-beam frame 5 and the steady-state connecting rod 6 are in an undeformed state. The double-beam frame 5 and the steady-state connecting rod 6 are heated synchronously. The steady-state connecting rod 6 contracts and deforms along the Y-axis, causing the two vertical segments of the two connecting beams 532 to approach each other. At the same time, the second steady-state beam 52 becomes thinner, and the curved beam assembly 4 reaches a steady-state structure. After continued heating, first, the middle part of the upper curved beam 531 bends upward. At this time, the curved beam assembly 4 reaches a steady-state structure. After further heating, the middle part of the lower curved beam 531 bends downward. Finally, the curved beam assembly 4 reaches another steady-state structure, that is, the final deformed structure of the curved beam assembly 4. In this way, the deformation of the curved beam assembly 4 can be triggered step by step through the phase change temperature gradient, improving the deformation flexibility of the curved beam assembly 4.

[0034] Optionally, as combined with Figure 1 、 Figure 5 and Figure 6 shown, the steady-state connecting rod 6 includes two first connecting rods 61, two second connecting rods 62, and two first curved rods 63. The two first curved 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 curved rods 63 are bent away from each other. The two middle parts of the two first connecting rods 61 are respectively connected to the middle parts of the two first curved rods 63. The middle parts of the two curved rods 63 are used to achieve reverse buckling deformation through temperature change.

[0035] Specifically, when heating up, under the connection of the two second connecting rods 62, the middle parts of the two first bending rods 63 move towards each other, driving the two first connecting rods 61 to move towards each other, thereby realizing the movement of the two connecting beams 532 towards each other. Through the deformation of the steady-state connecting rod 6, the deformation of the steady-state frame 53 is realized, 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 through the change of the temperature of the shape memory material and the integration of the structure, thereby reducing the dependence on the change of the temperature of the shape memory material.

[0036] Optionally, the curved beam assembly 4 further includes a temperature control module. The temperature control module is installed on the curved beam assembly 4 and is used to adjust the heating temperature of the curved beam assembly 4.

[0037] Specifically, the temperature control module is composed of a micro-heating element or a variable resistance layer and is used to locally and precisely control the phase transition temperature of the shape memory polymer to achieve stepwise deformation. The temperature control module adopts a PID closed-loop control logic and, in combination with the feedback of an external temperature sensor, automatically adjusts the heating power, reduces energy consumption, and improves the deformation accuracy of the curved beam assembly 4.

[0038] Optionally, an anti-radiation layer and a self-cleaning coating are provided on the curved beam assembly 4.

[0039] Specifically, the anti-radiation layer can be a polyimide film, and the self-cleaning coating can be a titanium dioxide photocatalytic material to enhance the adaptability to the space environment.

[0040] Optionally, the shape memory material is at least one of polylactic acid, styrene-butadiene copolymer, epoxy resin, or cyanate ester. In this way, by expanding the range of shape memory materials, the manufacturing difficulty and cost are reduced.

[0041] Although the present invention is disclosed as above, the protection scope of the present invention 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 these changes and modifications will all fall within the protection scope of the present invention.

Claims

1. A shape - memory - material - based allosteric satellite structure, characterized in that, It includes a variable-configuration regular pentagon module (1) and a variable-configuration regular hexagon module (2) made of shape memory material. The variable-configuration regular pentagon module (1) is connected to the variable-configuration regular hexagon module (2) to form a quasi-spherical polyhedron structure (3). Both the variable-configuration regular pentagon module (1) and the variable-configuration regular hexagon module (2) are used to synchronously contract or synchronously extend by changing the temperature.

2. The allosteric satellite structure based on shape memory material according to claim 1, wherein The variable-configuration regular pentagon module (1) and the variable-configuration regular hexagon module (2) are connected by a quick-release structure.

3. The allosteric satellite structure based on shape memory material according to claim 1, characterized in that Both the variable-configuration regular pentagon module (1) and the variable-configuration regular hexagon module (2) include a plurality of curved beam assemblies (4). The plurality of curved beam assemblies (4) are sequentially connected in the circumferential direction to enclose the variable-configuration regular pentagon module (1) or the variable-configuration regular hexagon module (2). Each curved beam assembly (4) constitutes a side frame of the variable-configuration regular pentagon module (1) or the variable-configuration regular hexagon module (2). Each of the curved beam assemblies (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) that are parallel to each other, and a steady-state frame (53) connected 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 surrounded by the steady-state frame (53) and is connected to the steady-state frame (53). The steady-state connecting rod (6) and the steady-state frame (53) are used to switch between a contracted steady state and an extended steady state by changing the temperature.

4. The allosteric satellite structure based on shape memory material according to claim 2, wherein The thickness of the second steady-state beam (52) is used to decrease by changing the temperature.

5. The allosteric satellite structure based on shape memory material according to claim 2, characterized in that Two ends of the first steady-state beam (51) are provided with first wedge surface structures (54) connected to other first steady-state beams (51). The first steady-state beams (51) of the plurality of curved beam assemblies (4) are connected through the first wedge surface structures (54) to form the variable-configuration regular pentagon module (1) or to form the variable-configuration regular hexagon module (2). The second steady-state beam (52) in each of the curved beam assemblies (4) is located on a side of the first steady-state beam (51) away from the center of the variable-configuration regular pentagon module (1) or the variable-configuration regular hexagon module (2). One end of the second steady-state beam (52) facing away from the first steady-state beam (51) is provided with a second wedge surface structure (55). The second wedge surface structure (55) extends along the axis of the second steady-state beam (52). The variable-configuration regular pentagon module (1) and the variable-configuration regular hexagon module (2) are connected through the second wedge surface structures (55) to form the quasi-spherical polyhedron structure (3).

6. The allosteric satellite structure based on shape memory material according to claim 2, characterized in that, The steady-state frame (53) includes two opposite bending beams (531) and two opposite 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) are bent 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 configured to achieve reverse buckling deformation through temperature change. The steady-state link (6) is connected between the two connecting beams (532).

7. The allosteric satellite structure based on shape memory material according to claim 6, characterized in that, The steady-state link (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 away from each other. 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 configured to achieve reverse buckling deformation through temperature change.

8. The allosteric satellite structure based on shape memory material according to claim 2, wherein The curved beam assembly (4) further includes a temperature control module. The temperature control module is installed on the curved beam assembly (4), and the temperature control module is used to adjust the heating temperature of the curved beam assembly (4).

9. The allosteric satellite structure based on shape memory material according to claim 2, wherein An anti-radiation layer and a self-cleaning coating are provided on the curved beam assembly (4).

10. The allosteric satellite structure based on shape memory material 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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