Bearing-thermal control-impact change resistance functional superstructure and preparation method thereof

Abstract

The invention discloses a bearing-thermal control-anti-impact function superstructure and a preparation method thereof, and relates to the technical field of spaceflight anti-impact protection, the bearing-thermal control-anti-impact function superstructure comprises a middle mixed core body, and the top and the bottom of the middle mixed core body are respectively provided with an upper panel and a lower panel; a through hole is formed in the upper panel; the middle mixed core body comprises a shell, a heat transfer core body arranged in the shell and a dot matrix core body arranged at the bottom of the heat transfer core body; the heat transfer core body is filled with a phase change material, and the dot matrix core body is filled with a heat insulation material. The technical problems that in the prior art, the preparation process is complex, and the function is single are solved.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace anti - impact protection, and particularly to a load - bearing - thermal control - anti - impact variable - function superstructure and a preparation method thereof. Background Art

[0002] With the rapid iteration of aerospace return technology, the time - varying loads of aerodynamic heat - landing impact have gradually become the key problems that need to be solved urgently for equipment during the return process. At the same time, during the revolution and rotation of the satellite cabin wall panel, it also needs to face the time - varying load environment of solar radiation heat - debris impact.

[0003] CN116766710A discloses an efficient heat - insulation and load - bearing integrated sandwich composite structure, which adopts a sandwich structure with metal upper and lower panels and orthogonal M - type rods in the middle, enabling it to have the functions of force transmission and strain isolation. At the same time, the use of phase - change materials to absorb the leakage heat of the struts effectively alleviates the problem of heat short - circuit, but it cannot effectively block heat transfer. CN118003708A discloses a heat - insulation - stealth - load - bearing integrated structure and a preparation method thereof. This structure is prepared by separately preparing a heat - resistant panel, an integrated insulation and stealth encapsulation layer, and a load - bearing layer, and each functional layer is mechanically connected together by metal bolts. Its preparation process is complex and not conducive to temperature control. CN117962417A provides a lightweight multi - functional thermal protection structure and a preparation method thereof. The structure is provided with a load - bearing layer and a heat - insulation layer in a laminated manner, and the functional layers are bonded by high - temperature glue. However, its preparation method is single and there is a problem of failure under extreme loads. In summary, the traditional multi - functional structures have low space utilization rate, and there are defects in the preparation methods. Once prepared, they simultaneously possess all functions and cannot adjust their own performance according to the change of the load field. Summary of the Invention

[0004] In order to solve the technical problems of complex preparation process and single function existing in the prior art, the embodiments of the present invention provide a load - bearing - thermal control - anti - impact variable - function superstructure and a preparation method thereof. The technical solution is as follows:

[0005] On the one hand, a load - bearing - thermal control - anti - impact variable - function superstructure is provided, including an intermediate hybrid core body, and an upper panel and a lower panel are respectively arranged at the top and bottom of the intermediate hybrid core body; through - holes are arranged on the upper panel; the intermediate hybrid core body includes a shell, a heat - transfer core body arranged inside the shell, and a lattice core body arranged at the bottom of the heat - transfer core body; the heat - transfer core body is filled with phase - change materials, and the lattice core body is filled with heat - insulation materials.

[0006] Optionally, the materials of the upper panel and the lower panel include at least one of the following: metal panel, non - metal panel, composite material panel.

[0007] Optionally, the shapes of the upper panel and the lower panel include any one of the following: square, circular, regular hexagon.

[0008] Optionally, the structure of the heat transfer core includes at least one of the following: square fin structure, triangular fin structure, spiral fin structure, triply periodic minimal surface structure, gradient hybrid triply periodic minimal surface structure.

[0009] Optionally, the structural materials of the heat transfer core include at least one of the following: metals such as titanium alloy and stainless steel, non-metals such as ceramics and resins.

[0010] Optionally, the outer shell includes a thin-walled circular tube or a thin-walled square tube.

[0011] Optionally, the phase change materials include at least one of the following: n-hexadecane, n-octadecane, paraffin wax, stearic acid, palmitic acid, polyethylene glycol, metallic copper, silver, Al-based alloy, Zn-based alloy.

[0012] Optionally, the structure of the lattice core includes at least one of the following: triply periodic minimal surface structure, honeycomb structure, grid structure.

[0013] Optionally, the structural materials of the lattice core include at least one of the following: metals such as titanium alloy and stainless steel, non-metals such as ceramics and resins.

[0014] Optionally, the thermal insulation materials include at least one of the following: glass fiber, asbestos, aerogel felt, aerogel paste, vacuum panel.

[0015] Optionally, the heat transfer core and the lattice core are connected by an intermediate partition.

[0016] Optionally, the intermediate partition is determined according to the shape of the outer thin-walled shell and includes at least one of the following: square, circular. And the material is the same as that of the heat transfer core, including at least one of the following: metals such as titanium alloy and stainless steel, non-metals such as ceramics and resins.

[0017] On the other hand, a preparation method of a load-thermal control-impact-resistant variable function superstructure is also provided, including: preparing by 3D printing in cooperation with physical filling of functional materials, or preparing by a hybrid method of machining and 3D printing in cooperation with physical filling of functional materials.

[0018] An embodiment of the present invention provides a load-bearing-thermal control-impact-resistant variable-function superstructure and a preparation method thereof. Considering the transformation effect of the thermal control-impact-resistant function in the time dimension under time-varying loads, a variable function is filled in the core structure to achieve the technical effect that the overall structure regulates its own performance by using the load. At the same time, in order to improve the temperature control and heat insulation performance of the structure, a load-bearing-insulation basic structure is also introduced. The present invention faces the protection requirements of time-varying excitation, realizes a lightweight and efficient structural design, effectively guarantees the service safety of the equipment, and alleviates the technical problems of complex preparation process and single function existing in the prior art. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0020] Figure 1 It is a three-dimensional schematic diagram of a cell of a load-bearing-thermal control-impact-resistant variable-function superstructure provided by an embodiment of the present invention;

[0021] Figure 2 It is a side view of a cell of a load-bearing-thermal control-impact-resistant variable-function superstructure provided by an embodiment of the present invention;

[0022] Figure 3 It is an application schematic diagram of a load-bearing-thermal control-impact-resistant variable-function superstructure provided by an embodiment of the present invention;

[0023] Figure 4 It is a schematic diagram of the shape of an upper panel provided by an embodiment of the present invention;

[0024] Figure 5 It is a schematic diagram of the shape of a lower panel provided by an embodiment of the present invention;

[0025] Figure 6 It is a schematic diagram of various combined structures of a heat transfer core and a housing provided by an embodiment of the present invention;

[0026] Figure 7 It is a schematic diagram of various cell configurations of a three-period minimal surface structure provided by an embodiment of the present invention;

[0027] Figure 8 It is a schematic diagram of various structures of a lattice core provided by an embodiment of the present invention;

[0028] Figure 9 It is a double Y-axis diagram of the temperature control and temperature equalization performance of a load-bearing-thermal control-impact-resistant variable-function superstructure provided by an embodiment of the present invention.

[0029] Illustration: 1. Upper panel, 2. Intermediate hybrid core, 21. Outer shell, 22. Heat transfer core, 23. Lattice core, 3. Functional filling material, 31. Phase change material, 32. Thermal insulation material, 4. Through hole, 5. Lower panel, 6. Intermediate partition. Detailed implementation mode

[0030] The following will describe the technical solutions in the present invention with reference to the accompanying drawings.

[0031] In the embodiments of the present invention, words such as "exemplarily" and "for example" are used to represent examples, illustrations or explanations. Any embodiment or design solution described as "example" in the present invention should not be construed as being more preferred or having more advantages than other embodiments or design solutions. Exactly speaking, the use of the word "example" is intended to present concepts in a specific way. In addition, in the embodiments of the present invention, the meaning expressed by "and / or" can be both, or either one of the two.

[0032] To make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following will be described in detail with reference to the accompanying drawings and specific embodiments.

[0033] Figure 1 is a three-dimensional schematic diagram of a cell of a load-bearing-thermal control-impact-resistant variable-function superstructure provided according to an embodiment of the present invention. Figure 2 is a side view of a cell of a load-bearing-thermal control-impact-resistant variable-function superstructure provided according to an embodiment of the present invention. As Figure 1 and Figure 2 shown, it includes an intermediate hybrid core 2. The upper and lower parts of the intermediate hybrid core 2 are respectively provided with an upper panel 1 and a lower panel 5, and the intermediate hybrid core 2 is internally filled with a functional filling material 3.

[0034] Specifically, through holes 4 are provided on the upper panel 1; the intermediate hybrid core 2 includes an outer shell 21, a heat transfer core 22 arranged inside the outer shell 21, and a lattice core 23 arranged at the bottom of the heat transfer core 22; the heat transfer core 22 is internally filled with a phase change material 31, and the lattice core 23 is internally filled with a thermal insulation material 32.

[0035] Figure 3 is an application schematic diagram of a load-bearing-thermal control-impact-resistant variable-function superstructure provided according to an embodiment of the present invention. As Figure 3 shown, the load-bearing-thermal control-impact-resistant variable-function superstructure provided by the embodiments of the present invention forms a periodic close-packed structure on a plane, constituting the panel of the load-bearing-thermal control-impact-resistant variable-function superstructure.

[0036] The variable-function superstructure provided by the embodiments of the present invention is composed of a thermal control-impact-resistant variable-function hybrid core body formed by an upper shell 21, a heat transfer core body 22, and a filled phase change material 31, and a load-bearing-insulation multi-function core body formed by a lower lattice core body 23 and a filled heat insulation material 32. Among them, the thermal control-impact-resistant variable-function hybrid core body is used to achieve thermal-mechanical time-varying excitation protection, and the load-bearing-insulation multi-function core body is used to achieve dynamic regulation of temperature control performance and impact performance, as well as to suppress heat conduction and heat radiation.

[0037] Specifically, the phase change material 31 is a high-temperature phase change material, and the heat insulation material 32 is a high-temperature heat insulation material. The phase change material 31 is filled in the heat transfer core body 22 by using through holes 4. Therefore, the upper shell 21, the heat transfer core body 22, and the phase change material 31 can exert a temperature control effect under heat loading. When the heat loading is transformed into impact loading, the internal liquid phase change material 31 and the upper shell 21 and the heat transfer core body 22 form a liquid-inclusion structure, thus having impact resistance. In addition, by matching different heat transfer core bodies 22 and phase change materials 31, dynamic regulation of temperature control performance and impact resistance can be achieved.

[0038] Specifically, in the load-bearing-insulation multi-function core body provided by the present invention, the lattice core body 23 realizes changes in load-bearing performance by matching different lattice structures, and the heat insulation material 32 is formed into a single layer or filled in the structure as a whole. The purpose is to suppress heat conduction and heat radiation, thereby reducing the heat transferred to the upper core body and the backplane, and finally achieving the structural heat insulation effect.

[0039] Optionally, the materials of the upper panel 1 and the lower panel 5 include at least one of the following: metal panel, non-metal panel, composite material panel.

[0040] For example, the metal panel includes titanium alloy and stainless steel; the non-metal panel includes resin and ceramic; the composite material includes aramid fiber and carbon fiber reinforced phenolic resin.

[0041] Figure 4 is a schematic diagram of the shape of an upper panel provided by an embodiment of the present invention. Figure 5 is a schematic diagram of the shape of a lower panel provided by an embodiment of the present invention. As Figure 4 and Figure 5 shown, the shapes of the upper panel 1 and the lower panel 5 include any one of the following: square, circular, regular hexagon. Among them, a plurality of through holes 4 are provided at the center of the upper panel 1. For example, two through holes 4 are provided.

[0042] Optionally, the heat transfer core body 22 is made of one or more of metals such as titanium alloy and stainless steel, or non-metals such as resin and ceramic.

[0043] Optionally, the structure of the heat transfer core 22 includes at least one of the following: square fin structure, triangular fin structure, spiral fin structure, triply periodic minimal surface (TPMS) structure, gradient hybrid triply periodic minimal surface structure.

[0044] Optionally, the outer shell 21 includes a thin-walled circular tube or a thin-walled square tube.

[0045] Specifically, as Figure 2 shown, the heat transfer core 22 and the lattice core 23 are connected by an intermediate partition 6. Among them, the shape of the intermediate partition 6 matches the shape of the outer shell 21. For example, when the outer shell 21 is a thin-walled circular tube, the intermediate partition 6 is circular; when the outer shell 21 is a thin-walled square tube, the intermediate partition 6 is square.

[0046] Optionally, the material of the intermediate partition 6 is the same as that of the heat transfer core 22, and is one or more of metals such as titanium alloy and stainless steel, or non-metals such as resin and ceramic.

[0047] Optionally, the connection method between the heat transfer core 22 and the lattice core 23 and the intermediate partition 6 includes any one of the following: bonding, welding, and integrated printing.

[0048] Figure 6 is a schematic diagram of various combined structures of the heat transfer core and the outer shell provided according to an embodiment of the present invention. As Figure 6 shown, the combined structure of the heat transfer core 22 and the outer shell 21 includes any one of the following: intermediate partition + thin-walled circular tube (as shown in Figure 6 Figure (a) therein), intermediate partition + thin-walled circular tube + triangular fin structure (as shown in Figure 6 Figure (b) therein), intermediate partition + thin-walled circular tube + square fin structure (as shown in Figure 6 Figure (c) therein), intermediate partition + thin-walled circular tube + spiral fin structure (as shown in Figure 6 Figure (d) therein).

[0049] Figure 7 is a schematic diagram of various cell configurations of the triply periodic minimal surface structure provided according to an embodiment of the present invention. As Figure 7 shown, the heat transfer core 22 includes any one of the following cell configurations of the triply periodic minimal surface structure: shell-shaped Gyroid cell (as shown in Figure 7 Figure (a) therein), shell-shaped Diamond cell (as shown in Figure 7 Figure (b) therein), shell-shaped Diamond+Gyroid hybrid cell (as shown in Figure 7 Figure (c) therein), shell-shaped Schwarz cell (as shown in Figure 7 Figure (d) therein).

[0050] Specifically, the outer shell 21 completely wraps the heat transfer core 22, and the heat transfer core 22 is attached to the inner wall of the outer shell 21. The material of the outer shell 21 is the same as that of the heat transfer core 22.

[0051] Optionally, the attachment method of the heat transfer core 22 on the inner wall of the outer shell 21 includes any one of bonding, welding, or integrated printing.

[0052] Optionally, the phase change material 31 includes at least one of the following: n-hexadecane, n-octadecane, paraffin wax, stearic acid, palmitic acid, polyethylene glycol, metallic copper, silver, Al-based alloy, Zn-based alloy. For example, the phase change material 31 can be any one of the above materials, or a combination of any multiple of them.

[0053] Optionally, the lattice core 23 is made of one or more of metals such as titanium alloy and stainless steel, or non-metals such as resin and ceramic.

[0054] Optionally, the structure of the lattice core 23 includes at least one of the following: triply periodic minimal surface structure, honeycomb structure, grid structure.

[0055] Figure 8 are schematic diagrams of various structures of the lattice core provided according to an embodiment of the present invention. As Figure 8 shown, the structure of the lattice core 23 includes any one of the following: Octet grid structure (as shown in FIG. (a) in Figure 8 ), Fluorites grid structure (as shown in FIG. (b) in Figure 8 ), hexagonal honeycomb structure (as shown in FIG. (c) in Figure 8 ), square honeycomb structure (as shown in FIG. (d) in Figure 8 ).

[0056] Optionally, as shown in FIG. (e) in Figure 8 , the structure of the lattice core 23 further includes a corrugated channel structure.

[0057] Optionally, the thermal insulation material 32 includes at least one of the following: glass fiber, asbestos, aerogel felt, aerogel paste, vacuum panel.

[0058] The present invention also provides a preparation method of a load-bearing-thermal control-impact-resistant variable function superstructure, including: preparing by 3D printing in cooperation with physical filling of functional materials, or preparing by a hybrid method of machining and 3D printing and in cooperation with physical filling of functional materials.

[0059] Specifically, the process of preparing by 3D printing in cooperation with physical filling of functional materials includes the following steps:

[0060] S1, the upper layer model of the integrated design load - thermal control - impact - resistant variable - function superstructure, input the model into a 3D printing device, and use one of the methods of SLM, SLS, SLA, and FDM to print and prepare the model.

[0061] S2, use the high - temperature negative - pressure drainage method or the immersion natural solidification method to fill the liquid phase - change material into the through - holes of the upper panel until the through - holes are about to overflow with the material or the sample is immersed in the liquid phase - change material, let it stand and wait for natural cooling, and finally seal the through - holes by using high - temperature glue or spot welding.

[0062] S3, prepare one of the glass fiber heat - insulating felt, asbestos, aerogel felt, and vacuum panel into the XY - plane size of the model, with a thickness of 7 mm to 15 mm.

[0063] S4, use high - temperature glue to bond the upper and lower sides of the heat - insulating material prepared in S3 to the bottom of the upper - layer structure model prepared in S1 and the lower panel, and wait for natural air - drying.

[0064] Specifically, another process of preparation by 3D printing combined with physical filling of functional materials includes the following steps:

[0065] S1, the overall model of the integrated design load - thermal control - impact - resistant variable - function superstructure, input the model into a 3D printing device, and use one of the methods of SLM, SLS, SLA, and FDM to print and prepare the model.

[0066] S2, use the high - temperature negative - pressure drainage method or the immersion natural solidification method to fill the liquid phase - change material into the through - holes of the upper panel until the through - holes are about to overflow with the material or the sample is immersed in the liquid phase - change material, let it stand and wait for natural cooling, and finally seal the through - holes by using high - temperature glue or spot welding.

[0067] S3, wrap the periphery of the lower - layer load - heat - insulating multi - functional core with adhesive tape or non - woven fabric, fill the aerogel paste into the structure through the reserved holes, remove the wrapping, and wait for natural air - drying to form.

[0068] Specifically, the process of preparation by the hybrid method of machining and 3D printing combined with physical filling of functional materials includes the following steps:

[0069] S1, design the upper and lower core models respectively, input the models into a 3D printing device, and use one of the methods of SLM, SLS, SLA, and FDM to prepare the models, or directly machine part of the core by machining methods.

[0070] S2, use machining methods to machine a solid cylinder or square block into a thin - walled circular tube or thin - walled square tube, and retain the bottom cover as the partition between the upper and lower cores. Finally, machine the conventional homogeneous panel into the upper and lower panels of the structure.

[0071] S3. Embed the upper enhanced heat transfer core into the thin-walled component, place the lower core on the other side of the partition, and connect the upper enhanced heat transfer core to the inner wall of the thin-walled component and the partition by spot welding or high-temperature glue. Connect the lower load-bearing core to the other side of the partition in the same way to complete the preparation of the metal matrix part of the sample.

[0072] S4. Use the negative pressure drainage method or the immersion natural solidification method to fill the through-holes in the upper panel with the liquid phase change material until the through-holes are about to overflow with the material or the sample is immersed in the liquid phase change material. Let it stand and wait for natural cooling, and then seal the through-holes by high-temperature glue or spot welding.

[0073] S5. Wrap the structure with adhesive tape or non-woven fabric, then squeeze the aerogel paste into the lower load-bearing core of the structure, remove the wrapping, and wait for natural air drying.

[0074] For example, some optional implementation manners provided by the embodiments of the present invention are as follows:

[0075] Implementation manner 1:

[0076] S1. Design an integrated model of a square upper panel + a cylinder + square fins and a square lower panel model, and then input the two models into a 3D printing device, and use the selective laser melting (SLM) method to print and prepare the models.

[0077] S2. Prepare the upper temperature control structure. Use the negative pressure drainage method to fill the through-holes in the upper panel with the melted high-temperature phase change material until the through-holes are about to overflow with the material, and finally seal the through-holes by spot welding, and let it stand and wait for the high-temperature phase change material to solidify naturally.

[0078] S3. Prepare the lower heat insulation layer. Select aerogel felt as the heat insulation layer of the sandwich structure, cut the aerogel felt into the XY plane size of the sandwich structure, and the thickness is 7 mm to 15 mm.

[0079] S4. Assemble the upper and lower structures. Use high-temperature resistant glue to bond the two sides of the heat insulation layer to the bottom of the upper temperature control structure and the square lower panel, and wait for natural air drying.

[0080] Implementation manner 2:

[0081] S1. Design an integrated sandwich model of a square upper panel + a cylindrical inner shell Gyroid structure (upper layer) + corrugated channels (upper layer) + a square lower panel, and then input the model into a 3D printing device, and use the selective laser melting (SLM) method to print and prepare the model.

[0082] S2. Place the sample in the melted high-temperature phase change material using the immersion natural solidification method, wait for natural solidification, finally take out the sample, and seal the through holes by spot welding, then let it stand still and wait for the high-temperature phase change material to naturally solidify.

[0083] S3. Select aerogel paste as the thermal insulation layer of the sandwich structure, seal the periphery of the overall structure with non-woven fabric and retain the injection port, and at the same time inject aerogel paste until it is full, then remove the non-woven fabric, and finally let it stand still and wait for natural drying and curing.

[0084] Embodiment 3:

[0085] S1. Design an integrated sandwich model of a square upper panel + a cylindrical inner embedded spiral fin structure (upper layer) + an Octet grid structure (lower layer) + a square lower panel, and then input the model into a 3D printing device and prepare the model by selective laser melting (SLM) method.

[0086] S2. Place the sample in the melted high-temperature phase change material using the immersion natural solidification method, wait for natural solidification, finally take out the sample, and seal the through holes by spot welding, then let it stand still and wait for the high-temperature phase change material to naturally solidify.

[0087] S3. Seal the periphery of the overall structure with non-woven fabric and retain the injection port, then directly squeeze aerogel paste into the structure until it is full, finally remove the non-woven fabric, and let it stand still and wait for natural drying and curing.

[0088] Embodiment 4:

[0089] S1. Design the upper and lower plates and the square fin model, and use mechanical processing technology to obtain the structure by wire cutting the metal sheet according to the model size.

[0090] S2. Design the corrugated channel model, and place the metal sheet in the mold according to the model size, and obtain the corrugated channel structure under the reciprocating stamping of the press.

[0091] S3. Design the cylindrical model with a bottom cover, and fix the solid cylindrical bar on the lathe according to the model size, and obtain the cylindrical with a bottom cover by removing materials from the solid metal cylinder using turning method.

[0092] S4. Carry out structure assembly, using spot welding method, first fix the directional fins on the inside of the cylinder one by one by spot welding, weld the square upper panel of the structure to the upper side of the cylinder by spot welding, and finally spot weld the upper and lower sides of the corrugated channel to the bottom of the cylinder and the lower panel respectively.

[0093] S5. Use the negative pressure drainage method to fill the through holes in the upper panel with the melted high-temperature phase change material until the through holes are about to overflow with materials, and finally seal the through holes by spot welding, then let it stand still and wait for the high-temperature phase change material to naturally solidify.

[0094] S6. Seal the periphery of the overall structure with non-woven fabric and leave the injection port. Inject the aerogel paste until it is full, then remove the non-woven fabric, and finally let it stand still and wait for natural drying and curing.

[0095] Embodiment 5:

[0096] S1. Design a square upper panel + cylinder + shell-type Schwarz integrated model, input the integrated model into a 3D printing device, and use the selective laser melting (SLM) method to prepare the model by printing.

[0097] S2. Design a corrugated channel model. According to the model size, place the metal sheet into the mold and obtain the corrugated channel structure under the reciprocating stamping of the press.

[0098] S3. Design the lower panel. According to the model size, obtain the structure by wire-cutting the metal sheet.

[0099] S3. Conduct structural assembly. Using spot welding, weld the upper and lower sides of the corrugated channel to the bottom of the cylinder and the lower panel respectively.

[0100] S4. Use the negative pressure drainage method to fill the through holes in the upper panel with the melted high-temperature phase change material until the through holes are about to overflow with the material. Finally, use spot welding to seal the through holes and wait for natural air drying.

[0101] S5. Prepare the heat insulation structure. Seal the periphery of the overall structure with non-woven fabric and leave the injection port. Inject the aerogel paste until it is full, then remove the non-woven fabric, and let it stand still and wait for natural air drying.

[0102] Embodiment 6:

[0103] S1. Design the upper and lower panel models. Using machining technology, according to the model size, obtain the structure by wire-cutting the metal sheet.

[0104] S2. Design the shell-type Gyroid structure and hexagonal honeycomb structure models. Input the models into a 3D printing device and use the selective laser melting (SLM) method to prepare the models by printing respectively.

[0105] S3. Design a cylindrical model with a bottom cover. According to the model size, fix the solid cylindrical bar on the lathe and use the turning method to remove the material from the solid metal cylinder to obtain the cylindrical model with a bottom cover.

[0106] S4. Conduct local structural assembly. Using spot welding, first fix the shell-type Gyroid structure inside the cylinder by spot welding, and then weld the upper side and bottom of the cylinder to the upper panel and the hexagonal honeycomb structure respectively by spot welding.

[0107] S5. Use the negative pressure drainage method to fill the through-holes in the upper panel with the melted high-temperature phase change material until the through-holes are about to overflow with the material, and then use spot welding to seal the through-holes, and let it stand still to wait for the high-temperature phase change material to solidify naturally.

[0108] S6. Directly inject the aerogel paste into the hexagonal honeycomb structure, and finally let it stand still to wait for natural drying and curing.

[0109] S7. Weld the square lower panel of the structure to the lower side of the hexagonal honeycomb structure by spot welding to conduct structure enclosure and complete the preparation.

[0110] Figure 9 It is a double Y-axis diagram of the temperature control and temperature uniformity performance of the load-bearing-thermal control-impact-resistant variable function superstructure provided by the embodiment of the present invention. The working condition is a 10W heat source at the bottom panel, adiabatic on all sides, and convective boundary conditions at the top panel. The initial temperature is 293.15K. The abscissa is time (s), and the ordinates are the temperature (°C) on the left Y-axis and the temperature uniformity on the right Y-axis (the difference between the highest temperature and the lowest temperature at each moment of the back panel, unit: °C).

[0111] As Figure 9 Shown by the data on the left Y-axis, three indicators are investigated: the temperature-time curves at the center point (0, 0) of the top panel and the edge point (7.5, 7.5) of the top panel, and the change of the average temperature of the top panel over time; the overall trends of the temperature-time curves at the positions of the points (0, 0) and (7.5, 7.5) and the average temperature-time curve of the top panel are basically the same; within 1000s to 2500s, as the heating time increases, the temperature does not change significantly and is basically stable at 55°C to 60°C; during this stage, the high-temperature phase change material undergoes a phase change, changing from a solid state to a liquid state, absorbing heat but the temperature does not change significantly, showing a relatively obvious temperature plateau; the temperature control performance of the variable function superstructure is mainly reflected in this stage. By using different high-temperature phase change materials, the temperature control time and the stable platform temperature of the variable function superstructure can be adjusted to cope with different working conditions.

[0112] As Figure 9 Shown by the data on the right Y-axis, the change of the temperature uniformity of the top panel over time is investigated; within 1000s to 2500s, the numerical value of the temperature uniformity in the temperature control platform interval is basically stable at about 2.5°C, showing excellent temperature uniformity effect.

[0113] As can be seen from the above description, a load-bearing-thermal control-impact-resistant variable function superstructure provided by the embodiment of the present invention has the following technical effects compared with the prior art:

[0114] 1. In the new protection scenario, under the action of thermal-shock excitation in sub-periods, the variable-function material and the enhanced heat transfer structure not only provide excellent thermal control performance, but when the shock excitation acts, the liquid paraffin and the metal matrix form a liquid-inclusion structure, thus possessing excellent impact resistance performance.

[0115] 2. By adjusting the shape of the panel, modular assembly can be achieved, which can meet the protection requirements of different sizes or special-shaped parts.

[0116] 3. By introducing heat-insulating materials and temperature-control materials, the structure has heat-insulating performance and also has the characteristic of stabilizing the temperature at a set value within a certain time, ensuring that the equipment is in a suitable working environment.

[0117] 4. By adjusting the proportion and type of the functional material, dynamic adjustment of the temperature-control time and the controlled temperature can be achieved, so as to adapt to more application scenarios. For example, paraffin at 40°C, paraffin at 59°C, silver, Al-based alloys, etc. can be used.

[0118] 5. By matching different types of cores, the mechanical properties and temperature-control properties of the structure can be dynamically adjusted to adapt to different service environments. For example, the upper temperature-control structure can adopt a TPMS structure, metal foam, fins to enhance the heat transfer efficiency and thus give full play to the best performance of the temperature-control material, and the lower structure can adopt an Octet or honeycomb structure to improve the mechanical properties of the structure.

[0119] The above is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily think of changes or substitutions, which should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claimed rights.

Claims

1. A load-bearing-thermal-control-impact-resistant variable-function superstructure, characterized in that: It comprises an intermediate hybrid core, wherein an upper panel and a lower panel are respectively arranged on the top and bottom of the intermediate hybrid core; a through hole is arranged on the upper panel; the intermediate hybrid core comprises an outer shell, a heat transfer core arranged inside the outer shell and a lattice core arranged at the bottom of the heat transfer core; the heat transfer core is filled with phase change material, and the lattice core is filled with heat insulation material.

2. The load-bearing-thermal-control-impact-resistant variable-function superstructure according to claim 1, characterized in that: The material of the upper panel and the lower panel includes at least one of the following: a metal panel, a non-metal panel, and a composite material panel.

3. The load-bearing-thermal-control-impact-resistant variable-function superstructure according to claim 1, characterized in that: The shapes of the upper panel and the lower panel include any one of the following: square, circle, and regular hexagon.

4. The load-bearing-thermal-control-impact-resistant variable-function superstructure according to claim 1, characterized in that: The structure of the heat transfer core includes at least one of the following: a square fin structure, a triangular fin structure, a spiral fin structure, a three-period minimal surface structure, and a gradient mixed three-period minimal surface structure.

5. The load-bearing-thermal-control-impact-resistant variable-function superstructure according to claim 1, characterized in that: The shell comprises a thin-walled round tube or a thin-walled square tube.

6. The load-bearing-thermal-control-impact-resistant variable-function superstructure according to claim 1, characterized in that: The phase change material includes at least one of the following: n-hexadecane, n-octadecane, paraffin, stearic acid, palmitic acid, polyethylene glycol, metallic copper, silver, Al-based alloy, and Zn-based alloy.

7. The load-bearing-thermal-control-impact-resistant variable-function superstructure according to claim 1, characterized in that: The structure of the lattice core includes at least one of the following: a three-periodic minimal surface structure, a honeycomb structure, and a grid structure.

8. The load-bearing-thermal-control-impact-resistant variable-function superstructure according to claim 1, characterized in that: The thermal insulation material comprises at least one of the following: glass fiber, asbestos, aerogel felt, aerogel paste, and vacuum board.

9. The load-bearing-thermal-control-impact-resistant variable-function superstructure according to claim 1, characterized in that: The heat transfer core and the lattice core are connected via a middle partition.

10. A method for preparing a load-bearing-thermal-control-impact-resistant variable-functional superstructure according to any one of claims 1 to 9, characterized in that: include: The preparation is carried out by 3D printing in combination with physical filling functional materials, or by a hybrid method of machining and 3D printing in combination with physical filling functional materials.

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