Foldable composite material as well as preparation method, application and use method thereof

Abstract

The invention belongs to the technical field of space structure and energy electronic integrated design, and particularly relates to a foldable composite material and a preparation method, application and use method thereof. The photoelectric conversion function and the communication radiation function are simultaneously borne on a single flexible structure, the high expansion area ratio and the high structural strength are achieved through paper folding geometry, and energy and communication resource collaboration and structure and function integrated design are achieved. According to the invention, co-fusion design of structure, energy and communication is realized, the area-mass ratio and the system integration degree are greatly improved, and the mass of the unfolding mechanism is reduced; the self-unfolding and self-locking capability is achieved, and the on-orbit reliability is improved; and the perovskite solar cell layer and the conductive antenna are cooperatively optimized, so that the comprehensive energy efficiency and the electromagnetic performance stability are improved.

Description

Technical Field

[0001] This invention belongs to the field of integrated design technology of spatial structure and energy electronics, specifically relating to a foldable composite material and its preparation, application and use methods. Background Technology

[0002] In spacecraft, solar panels and communication antenna systems are typically designed independently, leading to increased system size, complex deployment mechanisms, high component mass, poor assembly coupling, functional redundancy, and significant resource consumption. Origami structures have applications in deployable spacecraft systems, such as for mechanical deployment components, but a method for integrating energy functional elements with origami topology has yet to be developed. Perovskite solar cells possess high photoelectric conversion efficiency and flexible fabrication capabilities, but they are prone to degradation under the high radiation and temperature differences of space, and lack structural protection and integrated layout design strategies. Antenna integration design aims to achieve coplanar arrangement of array antennas and solar cells, but currently, a systematic approach to co-optimize electromagnetic radiation characteristics with origami deployment geometry is lacking. Summary of the Invention

[0003] The purpose of this invention is to provide a foldable composite material and its preparation, application, and use.

[0004] To achieve the above objectives, the present invention provides the following technical solution: The present invention provides a foldable composite material, including a foldable substrate and a perovskite solar cell layer located on one side of the foldable substrate, and a conductive antenna located on the other side of the foldable substrate.

[0005] Preferably, the material of the foldable substrate includes polyimide or polyethylene terephthalate; The thickness of the foldable substrate is 0.08~0.12mm.

[0006] Preferably, the folding form of the foldable base includes Miura folding, water wave folding, Kresling folding, umbrella folding, snake folding, zipper folding, pleated folding, hexagonal Miura folding, or star folding. The upper and lower surfaces of the foldable substrate are also provided with grooves and creases to correspond to different folding methods; the total thickness of the grooves and creases on the upper and lower surfaces does not exceed 60% of the thickness of the foldable substrate.

[0007] Preferably, the perovskite solar cell layer includes a conductive electrode layer, an electron transport layer, a perovskite absorber layer, and a hole transport layer stacked sequentially from bottom to top; the conductive electrode layer is in contact with the foldable substrate; The material of the conductive electrode layer includes at least one of indium tin oxide, fluorine-doped tin oxide, aluminum-doped zinc oxide, and indium-doped zinc oxide; the thickness of the conductive electrode layer is 120~180 nm. The electron transport layer is made of materials including titanium dioxide, zinc oxide, tin oxide, strontium titanate, fullerene, and [6,6]-phenyl-C. 61 At least one of methyl butyrate; the thickness of the electron transport layer is 40-60 nm; The material of the perovskite absorber layer includes lead iodine methylammonium iodide or lead bromide methylammonium iodide; the thickness of the perovskite absorber layer is 300~400 nm; The hole transport layer is made of at least one of Spiro-OMeTAD, poly(3-hexylthiophene), poly[N,N'-bis(4-butylphenyl)-N,N'-bis(phenyl)benzidine], carbazole derivatives, and copper phthalocyanine; the thickness of the hole transport layer is 80~120 nm.

[0008] Preferably, the material of the conductive antenna includes at least one selected from silver, copper, and gold; the thickness of the conductive antenna is 5~15μm. The conductive antenna is in the form of a rectangular patch.

[0009] Preferably, a driving component is also provided on the foldable substrate to realize the unfolding of the foldable composite material; The driving component includes an electric driving component, an elastic driving component, or a pneumatic driving component.

[0010] The present invention also provides a method for preparing the foldable composite material described in the above technical solution, comprising the following steps: According to the desired folding method, groove creases are formed on both sides of the base to obtain the foldable base; A perovskite solar cell layer is fabricated on one side of the foldable substrate, and a conductive antenna is fabricated on the other side to obtain the foldable composite material.

[0011] Preferably, the method for forming the groove crease is laser etching; The process of preparing the perovskite solar cell layer includes: sequentially preparing a conductive electrode layer, an electron transport layer, a perovskite absorber layer, and a hole transport layer on the surface of the foldable substrate. The conductive antenna was fabricated using inkjet printing.

[0012] The present invention also provides the application of the foldable composite material described in the above technical solution or the foldable composite material prepared by the preparation method described in the above technical solution as a solar sail in spacecraft.

[0013] The present invention also provides a method for using the foldable composite material described in the above technical solution or the foldable composite material prepared by the preparation method described in the above technical solution, comprising the following steps: The foldable composite material, which is in a folded state, is unfolded, and the perovskite solar cell layer is used to provide power to the spacecraft. The conductive antenna is used to receive and transmit communication signals.

[0014] The present invention provides a foldable composite material, including a foldable substrate and a perovskite solar cell layer located on one side of the foldable substrate, and a conductive antenna located on the other side of the foldable substrate.

[0015] This invention simultaneously supports photoelectric conversion and communication radiation functions on a single flexible structure. Utilizing origami geometry, it achieves a high unfolded area ratio and high structural strength, realizing synergistic energy and communication resource integration and a unified design of structure and function. This invention achieves a harmonious design of structure, energy, and communication, significantly improving the area-to-mass ratio and system integration, while reducing the mass of the unfolding mechanism. It possesses self-unfolding and self-locking capabilities, enhancing on-orbit reliability. The perovskite solar cell functional layer and the antenna conductive network layer are synergistically optimized, improving overall energy efficiency and electromagnetic performance stability. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of the foldable composite material provided by the present invention; Figure 2 This is a schematic diagram of the structure corresponding to the Miura fold; Figure 3 This is a schematic diagram of the perovskite solar cell layer in Example 1; Figure 4 This is a schematic diagram of the conductive antenna in this invention. Detailed Implementation

[0017] The present invention provides a foldable composite material, including a foldable substrate and a perovskite solar cell layer located on one side of the foldable substrate, and a conductive antenna located on the other side of the foldable substrate.

[0018] In this invention, the material of the foldable substrate preferably includes polyimide or polyethylene terephthalate; the thickness of the foldable substrate is preferably 0.08~0.12mm, specifically 0.08mm, 0.09mm, 0.10mm, 0.11mm, or 0.12mm.

[0019] In this invention, the folding form of the foldable substrate preferably includes Miura folding, water ripple folding, Kresling folding, umbrella folding, snake folding, zipper folding, pleated folding, hexagonal Miura folding, or star folding. In this invention, the parameters of the Miura folding preferably include: composed of identical rhomboid units, a fold angle of 65°, a fold line length of 50 mm, and a surface unit thickness of 0.15 mm.

[0020] In this invention, the upper and lower surfaces of the foldable substrate are preferably provided with grooves and creases to correspond to different folding methods; the total thickness of the grooves and creases on the upper and lower surfaces is preferably no more than 60% of the thickness of the foldable substrate; by controlling the thickness of the creases, it can be ensured that the substrate forms an effective flexible hinge.

[0021] In this invention, the perovskite solar cell layer preferably includes a conductive electrode layer, an electron transport layer, a perovskite absorption layer, and a hole transport layer stacked sequentially from bottom to top; the conductive electrode layer preferably is in contact with the foldable substrate.

[0022] In this invention, the material of the conductive electrode layer preferably includes at least one of indium tin oxide, fluorine-doped tin oxide, aluminum-doped zinc oxide, and indium-doped zinc oxide; the thickness of the conductive electrode layer is preferably 120~180nm, specifically 120nm, 130nm, 140nm, 150nm, 160nm, 170nm, and 180nm.

[0023] In this invention, the materials of the electron transport layer preferably include titanium dioxide, zinc oxide, tin oxide, strontium titanate, fullerene, and [6,6]-phenyl-C 61 At least one of methyl butyrate; the thickness of the electron transport layer is preferably 40-60 nm, specifically 40 nm, 50 nm, or 60 nm.

[0024] In this invention, the material of the perovskite absorber layer preferably includes lead iodine methylammonium or lead bromide methylammonium; the thickness of the perovskite absorber layer is preferably 300~400nm, specifically 300nm, 310nm, 320nm, 330nm, 340nm, 350nm, 360nm, 370nm, 380nm, 390nm, or 400nm.

[0025] In this invention, the material of the hole transport layer preferably includes at least one of Spiro-OMeTAD, poly(3-hexylthiophene) (P3HT), poly[N,N'-bis(4-butylphenyl)-N,N'-bis(phenyl)benzidine] (Poly-TPD), carbazole derivatives, and copper phthalocyanine; the thickness of the hole transport layer is preferably 80~120nm, specifically 80nm, 90nm, 100nm, 110nm, or 120nm.

[0026] In this invention, the material of the conductive antenna preferably includes at least one of silver, copper, and gold; the thickness of the conductive antenna is preferably 5~15μm, specifically 5μm, 6μm, 7μm, 8μm, 9μm, 10μm, 11μm, 12μm, 13μm, 14μm, or 15μm; the conductive antenna is preferably in the form of a rectangular patch; and the operating frequency of the rectangular patch conductive antenna is preferably 5.8GHz.

[0027] In this invention, a driving component is preferably provided on the foldable substrate to realize the unfolding of the foldable composite material; the driving component preferably includes an electric driving component, an elastic driving component, or a pneumatic driving component. In this invention, the electric driving component is preferably a shape memory alloy disposed at the edge of the foldable substrate; the shape memory alloy preferably does not contact the perovskite solar cell layer and the conductive antenna. In this invention, the shape memory alloy preferably includes a nickel-titanium-based shape memory alloy. In this invention, the foldable composite material is unfolded by applying a current to the electric driving component; the magnitude of the current is preferably 1.5A; the unfolding time is preferably 4s; for the elastic driving component, the elastic driving component deforms and stores energy through mechanical constraint during folding, and the elastic force drives the substrate to unfold along the crease after unlocking; for the pneumatic driving component, the folding structure is mainly pushed by gas pressure. This invention does not have a special limitation on the structure of the elastic driving component or the pneumatic driving component, and any structure well known to those skilled in the art can be used.

[0028] In this invention, the structural schematic diagram of the foldable composite material is as follows: Figure 1 As shown.

[0029] The present invention also provides a method for preparing the foldable composite material described in the above technical solution, comprising the following steps: According to the desired folding method, groove creases are formed on both sides of the base to obtain the foldable base; A perovskite solar cell layer is fabricated on one side of the foldable substrate, and a conductive antenna is fabricated on the other side to obtain the foldable composite material.

[0030] The present invention forms groove creases on both sides of the substrate according to the desired folding method to obtain the foldable substrate.

[0031] In this invention, the preferred method for forming the groove crease is laser etching; this invention does not impose any special limitations on the laser etching process, and any process well known to those skilled in the art can be used.

[0032] After obtaining the foldable substrate, the present invention prepares a perovskite solar cell layer on one side of the foldable substrate and prepares a conductive antenna on the other side to obtain the foldable composite material.

[0033] In this invention, the process of preparing the perovskite solar cell layer preferably includes: sequentially preparing a conductive electrode layer, an electron transport layer, a perovskite absorber layer, and a hole transport layer on the surface of the foldable substrate. In this invention, the conductive electrode layer is preferably prepared by magnetron sputtering; the electron transport layer, perovskite absorber layer, and hole transport layer are all preferably prepared by spin coating. This invention does not impose any particular limitation on the magnetron sputtering and spin coating processes; any process well-known to those skilled in the art can be used.

[0034] In this invention, the conductive antenna is preferably fabricated using inkjet printing. The raw materials for inkjet printing preferably include at least one selected from silver nanowires, copper nanowires, gold nanowires, conductive silver paste, and conductive copper paste. This invention does not impose any particular limitation on the inkjet printing process; any process well-known to those skilled in the art can be used.

[0035] The present invention does not impose any special limitations on the preparation process of the drive component; any process well known to those skilled in the art can be used.

[0036] The present invention also provides the application of the foldable composite material described in the above technical solution or the foldable composite material prepared by the preparation method described in the above technical solution as a solar sail in spacecraft.

[0037] The present invention also provides a method for using the foldable composite material described in the above technical solution or the foldable composite material prepared by the preparation method described in the above technical solution, comprising the following steps: The foldable composite material, which is in a folded state, is unfolded, and the perovskite solar cell layer is used to provide power to the spacecraft. The conductive antenna is used to receive and transmit communication signals.

[0038] In this invention, the dimensions of the foldable composite material in the folded state are preferably (10.8~13.2)cm×(7.2~8.8)cm×(13.5~16.5)cm, specifically 12cm×8cm×15cm; the dimensions of the unfolded foldable composite material are preferably (43.2~52.8)cm×(32.4~39.6)cm, specifically 48×36cm.

[0039] In this invention, the unfolding process preferably includes real-time monitoring of the structural stress state and unfolding angle by sensors to ensure a smooth and reliable unfolding process; after unfolding, it is also preferable to maintain a stable shape through a stress self-locking mechanism.

[0040] Unless otherwise specified, the materials and equipment used in this invention are all commercially available products in the field.

[0041] The technical solutions of this invention will be clearly and completely described below with reference to the embodiments thereof. Obviously, the described embodiments are only a part of the embodiments of this invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0042] Example 1 A 0.1 mm thick polyimide film was used as the substrate, and according to... Figure 2 The substrate was fabricated using the folding pattern shown: a Miura folding pattern was adopted, consisting of multiple rhomboid units with a fold angle of 65°, a fold line length of 50 mm, and a unit thickness of 0.15 mm. Grooves and creases were formed on the upper and lower surfaces of the substrate using a laser etching process, with the total depth of the creases on the upper and lower surfaces being 40% of the substrate thickness. A perovskite solar cell layer is fabricated on one side surface of a foldable substrate (structural schematic shown in figure). Figure 3 As shown): An indium tin oxide transparent conductive electrode layer with a thickness of 150 nm and a sheet resistance of 15 ohms per square meter was prepared by magnetron sputtering; a titanium dioxide electron transport layer with a thickness of 50 nm was prepared on the surface of the conductive electrode layer by spin coating; a lead ammonium iodide perovskite absorber layer with a thickness of 350 nm was prepared on the surface of the electron transport layer by spin coating and annealed at 85 °C for 30 min; a Spiro-OMeTAD hole transport layer with a thickness of 100 nm was prepared on the surface of the perovskite absorber layer by spin coating; the preparation temperature of each layer was controlled below 120 °C. Conductive antennas were fabricated on the other side of the foldable substrate: silver nanowires were deposited using inkjet printing to form a conductive pattern with a thickness of 8 μm; the antenna was designed as a rectangular patch (structural schematic shown in Figure 1). Figure 4 As shown), the operating frequency is 5.8GHz; A foldable composite material is obtained by wrapping shape memory alloy around the edges of a foldable substrate, without contacting the perovskite solar cell layer and the conductive antenna. Application of foldable composite materials: For foldable composite materials in a folded state, a current of 1.5A is applied to activate the shape memory alloy within them to unfold, which is completed within 4 seconds. The dimensions of the foldable composite material in the folded state are 12cm×8cm×15cm; the dimensions of the unfolded foldable composite material are 48×36cm. The perovskite solar cell layer is used to provide power to the spacecraft, and the conductive antenna is used to receive and transmit communication signals.

[0043] Performance testing The structural properties of the foldable composite material obtained in Example 1 were tested; the test results are shown in Tables 1 and 2. In contrast to the modular solar sail, the modular design specifically involves the solar panel and the communication antenna being two independent components, each equipped with its own dedicated support base, independent folding and storage structure, and drive system. The two components are fixed to the spacecraft cabin by mechanical assembly. In the folded state, they occupy independent storage space. The unfolding process is independently controlled by their respective drive mechanisms. After unfolding, they are spliced ​​together to form a functional coverage area. Table 1. Structural properties of the foldable composite material obtained in Example 1

[0044] As shown in Table 1, the surface-to-mass ratio is improved by 244%. The composite material provided by this invention adopts a substrate-sharing design, which reduces the redundancy of two independent support structures and reduces the mass of non-functional structures by 62%. The unfolding ratio is improved by 300%. The synergy of the origami topology reduces the space conflict of independent components and significantly improves folding efficiency. Under the same functional coverage, the total mass of this invention is reduced by 76.2% compared with the split design, which reduces the redundant support and assembly of the dual system. The deflection performance after unfolding is excellent. When a 10N uniform load is applied to the center, the deflection is 63.2% higher than that of the split design. The synergistic stress characteristics of the origami unit are better than those of independent component splicing, providing a reliable structural guarantee for the stable performance of on-orbit functions.

[0045] Table 2 Energy performance of the foldable composite material obtained in Example 1

[0046] Table 2 shows that the energy efficiency stability and high efficiency of the foldable composite material of this invention in complex space environments are significantly better than those of traditional split designs: after 1 MeV electron irradiation (dose 1×10⁻⁶), 15 e / cm 2After integration, the efficiency retention rate of the perovskite solar cell was improved by 19.8% compared to the split design. The synergistic buffer layer formed in the integrated structure also has a radiation shielding function, replacing the independent protective structure required by the split design and effectively mitigating the degradation effect of high space radiation on the cell. In the high and low temperature simulation test of 100 cycles from -40℃ to +85℃, the efficiency fluctuation was reduced by 63.8% compared to the split design. The flexible characteristics of the origami structure can effectively disperse thermal stress, and the shared substrate blocks the heat conduction path between the antenna and the cell layer, reducing the damage to the functional layer caused by thermal expansion differences. The power density was improved by 11.9% compared to the split design, achieving a synergistic effect of high areal density and high photoelectric conversion efficiency.

[0047] Although the above embodiments have provided a detailed description of the present invention, they are only some embodiments of the present invention, and not all embodiments. Other embodiments can be obtained based on these embodiments without creative effort, and these embodiments all fall within the protection scope of the present invention.

Claims

1. A foldable composite material, characterized in that, It includes a foldable substrate and a perovskite solar cell layer located on one side of the foldable substrate, and a conductive antenna located on the other side of the foldable substrate.

2. The foldable composite material according to claim 1, characterized in that, The material of the foldable substrate includes polyimide or polyethylene terephthalate; The thickness of the foldable substrate is 0.08~0.12mm.

3. The foldable composite material according to claim 1 or 2, characterized in that, The foldable base can be folded in the following ways: Miura fold, water ripple fold, Kresling fold, umbrella fold, snake fold, zipper fold, pleated fold, hexagonal Miura fold, or star fold. The upper and lower surfaces of the foldable substrate are also provided with grooves and creases to correspond to different folding methods; the total thickness of the grooves and creases on the upper and lower surfaces does not exceed 60% of the thickness of the foldable substrate.

4. The foldable composite material according to claim 1, characterized in that, The perovskite solar cell layer includes a conductive electrode layer, an electron transport layer, a perovskite absorber layer, and a hole transport layer stacked sequentially from bottom to top; the conductive electrode layer is in contact with the foldable substrate. The material of the conductive electrode layer includes at least one of indium tin oxide, fluorine-doped tin oxide, aluminum-doped zinc oxide, and indium-doped zinc oxide; the thickness of the conductive electrode layer is 120~180 nm. The electron transport layer is made of materials including titanium dioxide, zinc oxide, tin oxide, strontium titanate, fullerene, and [6,6]-phenyl-C. 61 At least one of methyl butyrate; the thickness of the electron transport layer is 40-60 nm; The material of the perovskite absorber layer includes lead iodine methylammonium iodide or lead bromide methylammonium iodide; the thickness of the perovskite absorber layer is 300~400 nm; The hole transport layer is made of at least one of Spiro-OMeTAD, poly(3-hexylthiophene), poly[N,N'-bis(4-butylphenyl)-N,N'-bis(phenyl)benzidine], carbazole derivatives, and copper phthalocyanine; the thickness of the hole transport layer is 80~120 nm.

5. The foldable composite material according to claim 1, characterized in that, The conductive antenna is made of at least one of silver, copper, and gold; the thickness of the conductive antenna is 5~15μm. The conductive antenna is in the form of a rectangular patch.

6. The foldable composite material according to claim 1, characterized in that, The foldable substrate is also provided with a driving component to realize the unfolding of the foldable composite material; The driving component includes an electric driving component, an elastic driving component, or a pneumatic driving component.

7. A method for preparing the foldable composite material according to any one of claims 1 to 6, characterized in that, Includes the following steps: According to the desired folding method, groove creases are formed on both sides of the base to obtain the foldable base; A perovskite solar cell layer is fabricated on one side of the foldable substrate, and a conductive antenna is fabricated on the other side to obtain the foldable composite material.

8. The preparation method according to claim 7, characterized in that, The method for forming the groove crease is laser etching; The process of preparing the perovskite solar cell layer includes: sequentially preparing a conductive electrode layer, an electron transport layer, a perovskite absorber layer, and a hole transport layer on the surface of the foldable substrate. The conductive antenna was fabricated using inkjet printing.

9. The application of the foldable composite material according to any one of claims 1 to 6 or the foldable composite material prepared by the preparation method according to claim 7 or 8 as a solar sail in spacecraft.

10. A method of using the foldable composite material according to any one of claims 1 to 6 or the foldable composite material prepared by the preparation method according to claim 7 or 8, characterized in that, Includes the following steps: The foldable composite material, which is in a folded state, is unfolded, and the perovskite solar cell layer is used to provide power to the spacecraft. The conductive antenna is used to receive and transmit communication signals.

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