Perovskite solar cell for space

Abstract

The present invention relates to a perovskite solar cell for space, which exhibits excellent radiation resistance and is capable of operating effectively under space conditions. The perovskite solar cell for space of the present invention comprises: a first electrode; a second electrode; a perovskite photoactive layer provided between the first electrode and the second electrode; a first protective layer provided between the first electrode and the photoactive layer; and a second protective layer provided between the second electrode and the photoactive layer, wherein the first protective layer and the second protective layer include a composition for forming a protective layer containing a radiation-resistant material.

Description

Perovskite solar cells for space

[0001] The present invention relates to a perovskite solar cell for space use.

[0002]

[0003] Solar cells are the core components of solar power generation that directly convert sunlight into electricity. They are currently used in a variety of fields, including homes, aviation, meteorology, and communications. Solar cars and solar air conditioners are also attracting attention.

[0004] These solar cells mainly use silicon semiconductors, but the high cost of power generation is a problem due to the high cost of raw materials for high-purity silicon semiconductors and the complexity of the solar cell manufacturing process using them. In other words, the cost of power generation is 3 to 10 times higher than that of conventional fossil fuel-based power generation, and thus the market growth is limited by government subsidies. For this reason, research and development of solar cells that do not use silicon has been active, and since the 1990s, dye-sensitized solar cells (DSSCs) using dyes, which are organic semiconductor materials, and polymer solar cells (Polymer Solar Cells) using conductive polymers have been studied in earnest. Despite the efforts of many academic and industrial circles, organic semiconductor-based solar cells such as DSSCs and polymer solar cells have not yet reached the commercialization stage. However, with the recent emergence of perovskite solar cells (PSCs), which combine the advantages of DSSCs and polymer solar cells, expectations for next-generation solar cells are growing.

[0005] Perovskite solar cells are a hybrid of conventional DSSCs and polymer solar cells. Unlike DSSCs, they do not use liquid electrolytes, resulting in improved reliability. The optical superiority of perovskite allows for high efficiency, and their efficiency has been steadily improving through recent process, material, and structural improvements. Meanwhile, the development of perovskite solar cells for use in space power supplies is currently underway.

[0006] Accordingly, there is a need to develop perovskite solar cells that can operate effectively even under space conditions.

[0007]

[0008] The present invention provides a space-use perovskite solar cell having excellent radiation resistance and capable of operating effectively under space conditions.

[0009] However, the problems to be solved by the present invention are not limited to the problems mentioned above, and other problems not mentioned will be clearly understood by those skilled in the art from the description below.

[0010]

[0011] One embodiment of the present invention provides a space-use perovskite solar cell, comprising: a first electrode; a second electrode; a perovskite photoactive layer provided between the first electrode and the second electrode; a first protective layer provided between the first electrode and the photoactive layer; and a second protective layer provided between the second electrode and the photoactive layer; wherein the first protective layer and the second protective layer include a composition for forming a protective layer including a radiation-resistant material.

[0012] According to one embodiment of the present invention, the photoactive layer may include a compound represented by the following chemical formula 1:

[0013] [Chemical Formula 1]

[0014] ABX3

[0015] In the above chemical formula 1, A includes at least one of an organic ammonium ion and an alkali metal, B includes at least one metal of Pb, Sn, Bi, and Sb, and X is a halogen anion.

[0016] According to one embodiment of the present invention, the radioactive material may include an ammonium iodide compound.

[0017] According to one embodiment of the present invention, the radioactive material may include a lanthanide metal ion.

[0018] According to one embodiment of the present invention, the space-use perovskite solar cell may further include: a substrate provided on one surface of the first electrode; an electron transport layer provided between the first electrode and the first protective layer; and a hole transport layer provided between the second electrode and the second protective layer.

[0019] According to one embodiment of the present invention, the space-use perovskite solar cell may further include: a substrate provided on one surface of the first electrode; a hole transport layer provided between the first electrode and the first protective layer; and an electron transport layer provided between the second electrode and the second protective layer.

[0020] According to one embodiment of the present invention, at least one of the substrate, the first electrode, the second electrode, the electron transport layer, and the hole transport layer may include a radiation-resistant material.

[0021]

[0022] A space-use perovskite solar cell according to one embodiment of the present invention has the advantage of being able to operate effectively under space conditions due to its excellent radiation resistance.

[0023] The effects of the present invention are not limited to the effects described above, and effects not mentioned will be clearly understood by those skilled in the art from the present specification and the attached drawings.

[0024]

[0025] FIG. 1 is a cross-sectional view of a space-use perovskite solar cell according to one embodiment of the present invention.

[0026] FIG. 2 is a cross-sectional view of a space-use perovskite solar cell according to another embodiment of the present invention.

[0027] FIG. 3 is a diagram showing the results of a solar cell performance evaluation before and after proton irradiation of a space-use perovskite solar cell manufactured in an embodiment of the present invention.

[0028] Figure 4 is a diagram showing the results of a solar cell performance evaluation before and after proton irradiation for a perovskite solar cell manufactured in a comparative example.

[0029]

[0030] Throughout this specification, whenever a part is said to "include" a component, this does not mean that it excludes other components, but rather that it may include other components, unless otherwise specifically stated.

[0031] Throughout this specification, when it is said that an element is "on" another element, this includes not only cases where the element is in contact with the other element, but also cases where another element exists between the two elements.

[0032] Throughout this specification, the unit “parts by weight” may mean the weight ratio between each component.

[0033] Throughout this specification, terms containing ordinal numbers, such as "first" and "second," are used to distinguish one component from another and are not limited by the ordinal numbers. For example, within the scope of the invention, the first component may also be referred to as the second component, and similarly, the second component may be referred to as the first component.

[0034]

[0035] Hereinafter, the present specification will be described in more detail.

[0036] Fig. 1 is a cross-sectional view of a space-use perovskite solar cell according to one embodiment of the present invention, and Fig. 2 is a cross-sectional view of a space-use perovskite solar cell according to another embodiment of the present invention. Specifically, Fig. 1 shows a cross-sectional view of a space-use perovskite solar cell having a regular architecture (nip) cell structure. Fig. 2 shows a cross-sectional view of a space-use perovskite solar cell having an inverted architecture (pin) cell structure.

[0037] One embodiment of the present invention provides a space-use perovskite solar cell, comprising: a first electrode; a second electrode; a perovskite photoactive layer provided between the first electrode and the second electrode; a first protective layer provided between the first electrode and the photoactive layer; and a second protective layer provided between the second electrode and the photoactive layer; wherein the first protective layer and the second protective layer include a composition for forming a protective layer including a radiation-resistant material.

[0038] One embodiment of the present invention provides a space-use perovskite solar cell having excellent radiation resistance and capable of effective operation under space conditions. Specifically, the space-use perovskite solar cell can effectively improve radiation resistance by providing a first protective layer and a second protective layer on one surface and the other surface of the perovskite photoactive layer, respectively. By providing the first protective layer and the second protective layer, when light is irradiated, decomposition of the perovskite included in the photoactive layer can be suppressed, thereby improving stability. In addition, by providing the first protective layer and the second protective layer on the one surface and the other surface of the photoactive layer, the charge extraction capability of the perovskite can be improved, and thus the performance of the space-use perovskite solar cell can be effectively improved.

[0039] In addition, the space-use perovskite solar cell can realize lightweight properties. That is, the space-use perovskite solar cell has an excellent power production per unit mass, which has the advantage of reducing the launch and operating costs of small satellites. In addition, the space-use perovskite solar cell can be manufactured under relatively low-temperature conditions, which reduces manufacturing costs and has the advantage of being usable as a flexible device.

[0040] Referring to FIGS. 1 and 2, the space-use perovskite solar cell (1) may include a first electrode (210), a second electrode (220), and a perovskite photoactive layer (300).

[0041] According to one embodiment of the present invention, the first electrode is a material for forming the first electrode, including indium tin oxide (ITO), fluorine-doped tin oxide (FTO), antimony tin oxide (ATO), gallium tin oxide (GTO), zinc tin oxide (ZTO), gallium-doped ZTO (ZTO: Ga), indium zinc oxide (IZO), aluminum zinc oxide (AZO), boron-doped zinc oxide (BZO), niobium titanium oxide (NTO), indium gallium zinc oxide (IGZO), and indium zinc tin oxide (Indium zinc tin oxide, It may include at least one of the IZTO).

[0042] According to one embodiment of the present invention, the second electrode may include an opaque electrode or a transparent electrode. The opaque electrode is a material for forming the second electrode, and may include at least one of silver (Ag), aluminum (Al), platinum (Pt), tungsten (W), copper (Cu), molybdenum (Mo), gold (Au), nickel (Ni), palladium (Pd), indium (In), ruthenium (Ru), lead (Pd), rhodium (Rh), iridium (Ir), osmium (Os), and carbon (C). In addition, the transparent electrode may include at least one of indium tin oxide (ITO), fluorine tin oxide (FTO), antimony tin oxide (ATO), gallium tin oxide (GTO), zinc tin oxide (ZTO), gallium-doped ZTO (ZTO: Ga), indium zinc oxide (IZO), aluminum zinc oxide (AZO), boron-doped zinc oxide (BZO), niobium titanium oxide (NTO), indium gallium zinc oxide (IGZO), and indium zinc tin oxide (IZTO) as a material for forming the second electrode.

[0043] According to one embodiment of the present invention, the perovskite photoactive layer may include a compound represented by the following chemical formula 1. The perovskite photoactive layer including the compound represented by the above chemical formula 1 can be easily applied to space solar cells because defects in the photoactive layer can be recovered when exposed to radiation energy due to the unique properties of perovskite.

[0044] [Chemical Formula 1]

[0045] ABX3

[0046] In the above chemical formula 1, A includes at least one of an organic ammonium ion and an alkali metal, B includes at least one metal of Pb, Sn, Bi, and Sb, and X is a halogen anion.

[0047] Specifically, in the above chemical formula 1, A may include an organic ammonium ion, and the organic ammonium ion may be a methyl ammonium ion (Methylammonium ion, MA). + ), formamidinium ion (Formamidiniumion, FA) + ), ethyl ammonium ion (EA) + ), and phenylammonium ion (PA + ) may include at least one of Cs, Rb, Na, K, and Li.

[0048] According to one embodiment of the present invention, the photoactive layer can be formed using a perovskite precursor solution. The perovskite precursor solution can include a precursor material and a solvent for forming the compound represented by the above chemical formula 1. The precursor material can be used without limitation as one used in the art to prepare the compound represented by the above chemical formula 1. For example, the precursor material can include cesium iodide (CsI), ammonium iodide formate (FAI), and lead iodide (PbI2).

[0049] In addition, the solvent may be one used in the art, and for example, the solvent may include at least one of dimethylformamide (DMF), dimethyl sulfoxide (DMSO), γ-butyrolactone (GBL), dimethylacetamide (N,N-dimethylacetamide, DMA), methylpyrrolidone (N-Methyl-2-Pyrrolidone, NMP), 1,3-dimethyl-2-imidazolidinone (DMI), dimethylacetamide (DMA), 2-mercaptoethanol (2ME), hexamethylphosphoramide (HMPA), acetonitrile, and methylamine. However, the types of the solvents are not limited to those described above.

[0050] Referring to FIGS. 1 and 2, the space-use perovskite solar cell (1) may include a first protective layer (410) and a second protective layer (420). The first protective layer (410) may be provided between the first electrode (210) and the perovskite photoactive layer (300), and the second protective layer (420) may be provided between the second electrode (220) and the perovskite photoactive layer (300). The first protective layer (410) and the second protective layer (420) each include a radiation-resistant material, thereby improving the radiation resistance of the space-use perovskite solar cell (1), thereby enhancing stability against not only UV but also cosmic radiation.

[0051] According to one embodiment of the present invention, the radiation-resistant material may include an ammonium iodide compound. By using an ammonium iodide compound as the radiation-resistant material, the radiation resistance of the first protective layer and the second protective layer can be effectively enhanced. The ammonium iodide compound may include an aromatic ring or a cyclic alkyl. The ammonium iodide compound including an aromatic ring or a cyclic alkyl can improve the radiation resistance of the first protective layer and the second protective layer.

[0052] Specifically, the ammonium iodide compound may include a compound represented by the following chemical formula 2.

[0053] [Chemical Formula 2]

[0054]

[0055] In the above chemical formula 2, R1 is a straight or branched chain alkylene having 1 to 5 carbon atoms, and R2 may be a substituted or unsubstituted aromatic ring having 6 to 30 carbon atoms, or a substituted or unsubstituted cyclic alkyl having 5 to 10 carbon atoms. At this time, the substituted aromatic ring may be substituted with at least one halogen ion. In addition, the substituted cyclic alkyl may be substituted with at least one halogen ion. The aromatic ring may be a benzene ring, and the cyclic alkyl may be cyclohexyl.

[0056] The above ammonium iodide compound may include at least one of Phenethylammonium iodide (PEAI), Cyclohexylethylammonium iodide (CEAI), F-rich pentafluorophenylethylammonium iodide (FEAI), and Benzenebutanammonium iodide (PBAI).

[0057] According to one embodiment of the present invention, the radioactive material may include a lanthanide metal ion. Specifically, the radioactive material may include a cerium ion (Ce 3+ ), europium ion (Eu 3+ ), neodymium ion (Nd 3+ ), samarium ion (Sm 3+ ) and ytterbium ion (Yb 3+ ) may include at least one of the following. By using a lanthanide metal ion as a radiation-resistant material, the radiation resistance of the first protective layer and the second protective layer can be effectively enhanced.

[0058] According to one embodiment of the present invention, the content of the radiation-resistant material included in the first protective layer may be greater than the content of the radiation-resistant material included in the second protective layer. Specifically, the concentration of the lanthanide metal ion included in the first protective layer may be greater than the concentration of the lanthanide metal ion included in the second protective layer. Referring to FIGS. 1 and 2, by making the concentration of the lanthanide metal ion included in the first protective layer provided in the direction in which light (L) is irradiated greater than the concentration of the second protective layer, the residual radiation that is preferentially blocked by the first protective layer and then transmitted is additionally blocked by the second protective layer, thereby maximizing the radiation resistance effect for the photoactive layer. However, by manufacturing the first protective layer by controlling the concentration within a level that does not affect the refractive index and transparency, the overall thickness and weight of the space-use perovskite solar cell can be effectively reduced.

[0059] According to one embodiment of the present invention, the thickness ratio of the perovskite photoactive layer and the first protective layer may be 1:0.004 to 1:0.07, 1:0.005 to 1:0.07, 1:0.01 to 1:0.07, 1:0.03 to 1:0.07, or 1:0.05 to 1:0.07. When the thickness ratio of the perovskite photoactive layer and the first protective layer is within the above-mentioned range, the radiation resistance effect of the photoactive layer can be maximized, and the overall thickness and weight of the space-use perovskite solar cell can be effectively reduced.

[0060] According to one embodiment of the present invention, the thickness ratio of the perovskite photoactive layer and the second protective layer may be 1:0.004 to 1:0.07, 1:0.005 to 1:0.06, 1:0.01 to 1:0.06, 1:0.03 to 1:0.06, or 1:0.05 to 1:0.06. When the thickness ratio of the perovskite photoactive layer and the second protective layer is within the above-mentioned range, the radiation resistance effect of the photoactive layer can be maximized, and the overall thickness and weight of the space-use perovskite solar cell can be effectively reduced.

[0061] According to one embodiment of the present invention, the thickness of the perovskite photoactive layer may be 100 nm or more and 1,000 nm or less, 200 nm or more and 800 nm or less, 300 nm or more and 600 nm or less, 500 nm or more and 1,000 nm or less, or 600 nm or more and 800 nm or less. When the thickness of the photoactive layer is within the above-mentioned range, the performance of the space-use perovskite solar cell is excellent, and the overall thickness and weight of the solar cell can be effectively reduced.

[0062] According to one embodiment of the present invention, the thickness of the first protective layer may be 2 nm or more and 50 nm or less, 5 nm or more and 50 nm or less, 10 nm or more and 50 nm or less, 20 nm or more and 50 nm or less, 30 nm or more and 50 nm or less, or 40 nm or more and 50 nm or less. When the thickness of the first protective layer is within the above-mentioned range, the first protective layer can implement excellent radiation resistance properties.

[0063] According to one embodiment of the present invention, the thickness of the second protective layer may be 2 nm or more and 50 nm or less, 5 nm or more and 50 nm or less, 10 nm or more and 50 nm or less, 20 nm or more and 50 nm or less, 30 nm or more and 50 nm or less, or 40 nm or more and 50 nm or less. When the thickness of the first protective layer is within the above-mentioned range, the second protective layer can implement excellent radiation resistance properties.

[0064] According to one embodiment of the present invention, the thickness of the first protective layer may be greater than the thickness of the second protective layer. Specifically, the ratio of the thickness of the second protective layer to the thickness of the first protective layer may be 1:1.1 to 1:2.5, 1:1.2 to 1:2, 1:1.3 to 1:1.8, 1:1.1 to 1:1.5, or 1:1.7 to 1:2.5. Referring to FIGS. 1 and 2, by making the thickness of the first protective layer provided in the direction in which light (L) is irradiated greater than the thickness of the second protective layer, the residual radiation transmitted after being preferentially blocked by the first protective layer is additionally blocked by the second protective layer, thereby maximizing the radiation resistance effect for the photoactive layer. In addition, by adjusting the ratio of the thickness of the second protective layer to the thickness of the first protective layer within the aforementioned range, the overall thickness and weight of the space-use perovskite solar cell can be effectively reduced.

[0065] According to one embodiment of the present invention, the first protective layer can be formed using a lanthanide metal ion precursor. For example, the lanthanide metal ion precursor can include at least one of CeX3, EuX3, NdX3, SmX3, and YbX3. Here, X is a halogen anion, and Cl - , Br - , or I - It can be. Specifically, the lanthanide metal ion precursor can include at least one of CeCl3, EuCl3, NdCl3, SmCl3, and YbCl3. By using the lanthanide metal ion precursor, a space-use perovskite solar cell that can maintain excellent electrochemical properties even after exposure to proton rays can be effectively implemented.

[0066] According to one embodiment of the present invention, the second protective layer can be formed using a lanthanide metal ion precursor. For example, the lanthanide metal ion precursor can include at least one of CeX3, EuX3, NdX3, SmX3, and YbX3. Here, X is a halogen anion, and Cl - , Br - , or I - It can be. Specifically, the lanthanide metal ion precursor can include at least one of CeCl3, EuCl3, NdCl3, SmCl3, and YbCl3. By using the lanthanide metal ion precursor, a space-use perovskite solar cell that can maintain excellent electrochemical properties even after exposure to proton rays can be effectively implemented.

[0067] At this time, the types of the lanthanide metal ion precursor for forming the first protective layer and the lanthanide metal ion precursor for forming the second protective layer may be the same or different.

[0068] According to one embodiment of the present invention, the space-use perovskite solar cell may further include: a substrate provided on one surface of the first electrode; an electron transport layer provided between the first electrode and the first protective layer; and a hole transport layer provided between the second electrode and the second protective layer.

[0069] Referring to FIG. 1, the space-use perovskite solar cell (1) may have a structure in which a substrate (100), a first electrode (210), an electron transport layer (500), a first protective layer (410), a perovskite photoactive layer (300), a second protective layer (420), a hole transport layer (600), and a second electrode (220) are sequentially laminated.

[0070] According to one embodiment of the present invention, the substrate may be any substrate used in solar cells in the art without limitation. Specifically, a high-strength and heat-resistant c-plane sapphire substrate, a transparent heat-resistant substrate capable of transmitting sunlight, a flexible substrate, and the like may be used.For example, as a material for forming the substrate, glass, polyethylene terephthalate (PET), polyethersulfone (PES), polyethylene naphthalate (PEN), polycarbonate (PC), polymethyl methacrylate (PMMA), polyimide (PI), ethylene vinyl acetate (EVA), amorphous polyethylene terephthalate (APET), polypropylene terephthalate (PPT), polyethylene terephthalate glycol (PETG), polycyclohexylene dimethylene terephthalate glycol-modified (PCTG), It may include at least one of modified triacetylcellulose (TAC), cycloolefin polymer (COP), cycloolefin copolymer (COC), dicyclopentadiene (DCPD), cyclopentadiene (CPD), polyarylate (PAR), polyetherimide (PEI), polydimethylsiloxane (PDMS), silicone resin, fluororesin, and modified epoxy resin.

[0071] According to one embodiment of the present invention, the electron transport layer may include an oxide of at least one metal selected from the group consisting of Ti, Sn, Zn, W, Zr, Ga, In, Y, Nb, Ta, and V, as a material for forming the electron transport layer. In addition, the electron transport layer is a material for forming an electron transport layer, and is selected from among 6,6-phenyl-C61-butylic acid methyl ester (PCBM(C61)), PCBM(C60), PCBM(C70), PCBM(C71), PCBM(C76), PCBM(C80), PCBM(C82), indene-C60 bisadduct (ICBA) and 6,6-phenyl-C61-butylic acid cholesteryl ester (PCBCR), polybenzimidazole, perylene, poly[[N,N'-bis(2-octyldodecyl)-napthalene-1,4,5,8-bis(dicarboximide)-2,6-diyl]-alt-5,5'-(2,2'-bithiophene)](NDI2OD-T2), naphthalene. diimide(NDI)-selenophene copolymer(PNDIS-HD), poly[(E)-2,7-bis(2-decyltetradecyl)-4-methyl-9-(5-(2-(5-methylthiophen-2-yl)vinyl)thiophen-2-yl)benzo[lmn][3,8] phenanthroline-1,3,6,8(2H,7H)-tetraone] (PNDI-TVT), poly[[N,N′-bis(2-hexyldecyl)naphthalene-1,4,5,8-bis(dicarboximide)-2,6-diyl]-alt-5,5′-thiophene] (PNDI2HD-T), NiOx, BCP(Bathocuproine), and a P-type oxide semiconductor.

[0072] According to one embodiment of the present invention, the hole transport layer is a material forming a hole transport layer, MeO-2PACz((2-(3,6-Dimethoxy-9H-carbazol-9-yl)ethyl)phosphonic acid), Spiro-OMeTAD(2,2',7,7'-tetrakis(N,Np-dimethoxyphenylamino)-9,9'-spirobifluorene), P3HT(poly[3-hexylthiophene]), PCPDTBT(Poly[2,6-(4,4-bis-(2-ethylhexyl)-4H-cyclopenta [2,1-b;3,4-b′]dithiophene)-alt-4,7(2,1,3-benzothiadiazole)]), PCDTBT (Poly[N-9′-heptadecanyl-2,7-carbazole-alt-5,5-(4′,7′-di-2-thienyl-2′,1′,3′-benzothiadiazole)]), PTAA (poly[bis(4-phenyl)(2,4,6-trimethylphenyl)amine]), poly[bis(4-phenyl)(2,4,6-trimethylphenyl)amine]), PEDOT:PSS (poly(3,4-ethylenedioxythiophene) poly(styrenesulfonate), benzothiadiazole, diketopyrrolopyrrole, benzodithiophene, carbazole, fluorene, PS-PAA (polystyrenepolyacrylic acid block copolymer), poly-TPD (Poly(4-butylphenyl-diphenyl-amine)), PPV (polypheylene vinylene), It may include at least one of PVP (polyvinylpyrrolidone), NiOx, and a P-type oxide semiconductor.

[0073] According to one embodiment of the present invention, the space-use perovskite solar cell may further include: a substrate provided on one surface of the first electrode; a hole transport layer provided between the first electrode and the first protective layer; and an electron transport layer provided between the second electrode and the second protective layer.

[0074] Referring to FIG. 2, the space-use perovskite solar cell (1) may have a structure in which a substrate (100), a first electrode (210), a hole transport layer (600), a first protective layer (410), a perovskite photoactive layer (300), a second protective layer (420), an electron transport layer (500), and a second electrode (220) are sequentially laminated. At this time, the substrate (100), the first electrode (210), the hole transport layer (600), the first protective layer (410), the perovskite photoactive layer (300), the second protective layer (420), the electron transport layer (500), and the second electrode (220) may be the same as those described above.

[0075] According to one embodiment of the present invention, at least one of the substrate, the first electrode, the second electrode, the electron transport layer, and the hole transport layer may include a radiation-resistant material.

[0076] According to one embodiment of the present invention, the substrate may include the radiation-resistant material. By including the radiation-resistant material in the substrate, a darkening phenomenon of the substrate can be effectively prevented. Specifically, the substrate may include a composition for forming a substrate. The composition for forming a substrate may include a material for forming a substrate and the radiation-resistant material. That is, the composition for forming a substrate may include at least one of the ammonium iodide-based compound and the lanthanide metal ion precursor as the radiation-resistant material. The content of the radiation-resistant material may be 0.5 parts by weight or more and 3 parts by weight or less, based on 100 parts by weight of the composition for forming a substrate. When the content of the radiation-resistant material is within the above-mentioned range, a darkening phenomenon of the substrate can be effectively prevented while suppressing deterioration of the physical properties of the substrate.

[0077] According to one embodiment of the present invention, the first electrode may include the radiation-resistant material. By including the radiation-resistant material in the first electrode, the radiation resistance of the space-use perovskite solar cell may be improved. Specifically, the first electrode may include a composition for forming a first electrode. The composition for forming the first electrode may include a material for forming the first electrode and the radiation-resistant material. That is, the composition for forming the first electrode may include at least one of the ammonium iodide-based compound and the lanthanide metal ion precursor as the radiation-resistant material. The content of the radiation-resistant material may be 0.5 parts by weight or more and 5 parts by weight or less, based on 100 parts by weight of the first electrode-forming composition. When the content of the radiation-resistant material is within the above-mentioned range, the radiation resistance of the space-use perovskite solar cell may be effectively improved.

[0078] According to one embodiment of the present invention, the second electrode may include the radiation-resistant material. By including the radiation-resistant material in the second electrode, the radiation resistance of the space-use perovskite solar cell may be improved. Specifically, the second electrode may include a composition for forming a second electrode. The composition for forming the second electrode may include a material for forming the second electrode and the radiation-resistant material. That is, the composition for forming the second electrode may include at least one of the ammonium iodide-based compound and the lanthanide metal ion precursor as the radiation-resistant material. The content of the radiation-resistant material may be 0.2 parts by weight or more and 10 parts by weight or less, based on 100 parts by weight of the second electrode-forming composition. When the content of the radiation-resistant material is within the above-mentioned range, the radiation resistance of the space-use perovskite solar cell may be effectively improved.

[0079] According to one embodiment of the present invention, the electron transport layer may include the radiation-resistant material. By including the radiation-resistant material in the electron transport layer, the decomposition of the perovskite included in the photoactive layer can be suppressed when light is irradiated, thereby improving stability. In addition, the charge dissociation ability of the perovskite can be improved, and thus the performance of the space-use perovskite solar cell can be effectively improved.

[0080] Specifically, the electron transport layer may include a composition for forming an electron transport layer. The composition for forming an electron transport layer may include a material for forming an electron transport layer and the radiation-resistant material. That is, the composition for forming an electron transport layer may include at least one of the ammonium iodide-based compound and the lanthanide metal ion precursor as the radiation-resistant material. Based on 100 parts by weight of the composition for forming an electron transport layer, the content of the radiation-resistant material may be 0.03 parts by weight or more and 0.2 parts by weight or less. When the content of the radiation-resistant material is within the above-mentioned range, the stability and charge dissociation ability of the photoactive layer may be improved.

[0081] According to one embodiment of the present invention, the hole transport layer may include the radiation-resistant material. By including the radiation-resistant material in the hole transport layer, the decomposition of the perovskite included in the photoactive layer can be suppressed when light is irradiated, thereby improving stability. In addition, the charge dissociation ability of the perovskite can be improved, and thus the performance of the space-use perovskite solar cell can be effectively improved.

[0082] Specifically, the hole transport layer may include a composition for forming a hole transport layer. The composition for forming a hole transport layer may include a material for forming a hole transport layer and the radiation-resistant material. That is, the composition for forming a hole transport layer may include at least one of the ammonium iodide-based compound and the lanthanide metal ion precursor as the radiation-resistant material. Based on 100 parts by weight of the hole transport layer-forming composition, the content of the radiation-resistant material may be 0.03 parts by weight or more and 0.2 parts by weight or less. When the content of the radiation-resistant material is within the above-mentioned range, the stability and charge dissociation ability of the photoactive layer may be improved.

[0083]

[0084] One embodiment of the present invention provides a method for manufacturing the space-use perovskite solar cell.

[0085] According to one embodiment of the present invention, a method for manufacturing the space-use perovskite solar cell may include the steps of: preparing a substrate; forming a first electrode on the substrate; forming an electron transport layer on the first electrode; forming a first protective layer on the electron transport layer; forming a perovskite photoactive layer on the first protective layer; forming a second protective layer on the perovskite photoactive layer; forming a hole transport layer on the second protective layer; and forming a second electrode on the hole transport layer.

[0086] That is, the method for manufacturing the above space-use perovskite solar cell can manufacture a solar cell with a regular structure.

[0087] According to one embodiment of the present invention, the step of preparing the substrate may include a step of cleaning the substrate. For example, the substrate may be cleaned using an ultrasonic cleaning method using a solvent such as isopropyl alcohol (IPA), acetone, or ethyl alcohol.

[0088] According to one embodiment of the present invention, the step of preparing the substrate may include a step of manufacturing the substrate using the substrate-forming composition. Through this, a substrate containing the radiation-resistant material can be prepared.

[0089] According to one embodiment of the present invention, the step of forming a first electrode on the substrate may include forming the first electrode through at least one method among sputtering, e-beam, and vacuum thermal evaporation.

[0090] According to one embodiment of the present invention, the step of forming the electron transport layer on the first electrode may include forming the electron transport layer through at least one of a CBD (chemical bath deposition) method, an aerosol spray pyrolysis method, a solution process method, and a vacuum thermal deposition method. At this time, SnO2, TiO2, etc. may be used as a material for forming the electron transport layer. In addition, the electron transport layer may include the radiation-resistant material.

[0091] According to one embodiment of the present invention, the step of forming a first protective layer on the electron transport layer may include forming the first protective layer through at least one of a solution process method and a vacuum thermal deposition method.

[0092] According to one embodiment of the present invention, the perovskite photoactive layer can be manufactured using a precursor material capable of forming perovskite. In addition, the perovskite photoactive layer can be manufactured using a perovskite single crystal. For example, the photoactive layer can be formed by growing perovskite in the form of a single crystal, or the photoactive layer can be formed by melting a perovskite single crystal and using a solution process.

[0093] According to one embodiment of the present invention, the step of forming the perovskite photoactive layer may form the perovskite photoactive layer from the perovskite precursor solution using a solution process. For example, after performing spin coating, the perovskite photoactive layer may be formed by heating (annealing) at a temperature of 100°C or more and 150°C or less. The perovskite precursor solution may include a precursor material capable of forming perovskite.

[0094] According to one embodiment of the present invention, the step of forming a second protective layer on the photoactive layer may include forming the second protective layer through at least one of a solution process method and a vacuum thermal deposition method.

[0095] According to one embodiment of the present invention, the step of forming a hole transport layer on the second protective layer may include forming the hole transport layer through at least one of a solution process, sputtering, e-beam, and vacuum thermal evaporation. In this case, the hole transport layer may include the radiation-resistant material.

[0096] According to one embodiment of the present invention, the step of forming a second electrode on the hole transport layer may include forming the second electrode through a vacuum thermal deposition method.

[0097] According to one embodiment of the present invention, the solution process may include at least one of spin coating, dip coating, spray coating, Dr. blade coating, roll coating, bar coating, gravier coating, and slot-die coating.

[0098] According to one embodiment of the present invention, a method for manufacturing the space-use perovskite solar cell may include the steps of: preparing a substrate; forming a first electrode on the substrate; forming a hole transport layer on the first electrode; forming a first protective layer on the hole transport layer; forming a perovskite photoactive layer on the first protective layer; forming a second protective layer on the perovskite photoactive layer; forming an electron transport layer on the second protective layer; and forming a second electrode on the electron transport layer.

[0099] That is, the method for manufacturing the above space-use perovskite solar cell can manufacture a solar cell with an inverted structure.

[0100] In the method for manufacturing a space-use perovskite solar cell with an inverse structure according to the present embodiment, differences compared to the method for manufacturing a space-use perovskite solar cell with a regular structure according to the above-described embodiment will be explained with a focus on the parts.

[0101] According to one embodiment of the present invention, the step of forming a hole transport layer may include forming a hole transport layer from a composition for forming a hole transport layer through a solution process. At this time, MeO-2PACz, PTAA, etc. may be used as a material for forming the hole transport layer.

[0102] According to one embodiment of the present invention, the step of forming an electron transport layer may include forming the electron transport layer using at least one of a vacuum thermal evaporation method and a solution process method. In this case, materials for forming the electron transport layer may include C60, BCP (Bathocuproine), and the like.

[0103]

[0104] The present invention will be described in more detail through the following examples. These examples are provided for illustrative purposes only and are not intended to limit the present invention.

[0105]

[0106] Example: Perovskite solar cells for space use

[0107] A space-use perovskite solar cell having a structure of substrate / first electrode / hole transport layer / first protective layer / perovskite photoactive layer / second protective layer / electron transport layer / second electrode was manufactured using the following method.

[0108]

[0109] Preparation of substrate and first electrode

[0110] A glass substrate equipped with fluorine tin oxide (FTO) was prepared as a substrate equipped with a first electrode. The substrate was sequentially cleaned using isopropyl alcohol (IPA), acetone, and ethanol via ultrasonic cleaning, and the surface of the substrate was treated using a UV-Ozone dry cleaning method.

[0111]

[0112] Formation of hole transport layer

[0113] A hole transport layer precursor was prepared by dissolving MeO-2PACz, a material forming a hole transport layer, in ethanol at a concentration of 0.1 mg / mL. Thereafter, the precursor was coated on the first electrode (FTO) at a speed of 3000 rpm for 30 seconds, and then annealed at 100°C for 10 minutes to form a hole transport layer.

[0114]

[0115] Formation of the first protective layer

[0116] CeCl3 powder containing lanthanide metal ions was used as a radiation-resistant material. Afterwards, a first protective layer was formed on the hole transport layer through vacuum thermal evaporation. Specifically, vacuum thermal evaporation was performed using a thermal evaporator (KOREAKIYON LTD.,CO, KBEV - 150(2M2O)). At this time, the vacuum thermal evaporation process was 10 -6 It was performed under the conditions of a pressure of 10 Torr and a deposition rate of 0.2 Å / s, and the thickness of the first protective layer was 8 nm.

[0117]

[0118] Fabrication of perovskite photoactive layers

[0119] A perovskite precursor solution was prepared by dissolving a solute containing cesium iodide (CsI), ammonium formate (FAI), and lead iodide (PbI2) in a molar ratio of 0.15:0.85:1 in a solvent containing N,N-dimethylformamide (DMF) and dimethyl sulfoxide (DMSO) in a 4:1 ratio to a concentration of 1.8 M.

[0120] Thereafter, a perovskite precursor solution was applied onto the first protective layer, rotated at a speed of 5,000 rpm for 20 seconds, and heat-treated at 100°C for 10 minutes to finally manufacture a perovskite photoactive layer. At this time, the thickness of the perovskite photoactive layer was 600 nm.

[0121]

[0122] Manufacturing of the second protective layer

[0123] CeI3 powder containing lanthanide metal ions was used as a radiation-resistant material. Afterwards, a second protective layer was formed on the perovskite photoactive layer through vacuum thermal evaporation. At this time, the vacuum thermal evaporation process was performed for 10 -6 The process was performed under conditions of a pressure of 10 Torr and a deposition rate of 0.2 Å / s, and the thickness of the second protective layer was set to 6 nm.

[0124]

[0125] Manufacturing of electron transport layer

[0126] PCBM (C60) and Bathocuproine (BCP) were used as materials to form the electron transport layer. Vacuum thermal evaporation method (pressure: 10 -6 An electron transport layer was formed by sequentially coating C60 and BCP on the second protective layer using a deposition rate of 0.2 Å / s (10 Torr). At this time, the thickness of the C60 coating was 25 nm, and the thickness of the BCP coating was 6 nm.

[0127]

[0128] Manufacturing of the second electrode

[0129] Vacuum thermal evaporation (pressure: 10 -6 A second electrode was manufactured by coating silver (Ag) on ​​the electron transport layer using a deposition rate of 0.2 Å / s (10 Torr). At this time, the thickness of the second electrode was 80 nm.

[0130]

[0131] Comparative example: perovskite solar cells

[0132] In the above embodiment, a perovskite solar cell having a structure of substrate / first electrode / hole transport layer / perovskite photoactive layer / electron transport layer / second electrode was manufactured by performing the same method as in the above embodiment, except that the first protective layer and the second protective layer were not formed.

[0133]

[0134] Experimental example: Proton irradiation test under low-orbit space environment conditions

[0135] For the space-use perovskite solar cell manufactured in the above example and the perovskite solar cell manufactured in the comparative example, the solar cell performance was evaluated before and after proton irradiation using the following method.

[0136] 100 mW / cm under AM 1.5G conditions 2 A light source was formed using a solar simulator capable of irradiating the light of the century. Subsequently, changes in the photocurrent-voltage characteristics within the device due to proton irradiation were recorded using a Keithley 2400 source meter.

[0137] The proton irradiation conditions were selected as a representative value of 10 MeV, reflecting the fact that the energy range that can directly penetrate and affect the perovskite photoactive layer of a solar cell is 1 MeV to 10 MeV among the proton energy range of 100 keV to 200 MeV in a low Earth orbit environment, and the irradiation experiment was conducted.

[0138] FIG. 3 is a drawing showing the results of a solar cell performance evaluation before and after proton irradiation for a space-use perovskite solar cell manufactured in an example of the present invention, and FIG. 4 is a drawing showing the results of a solar cell performance evaluation before and after proton irradiation for a perovskite solar cell manufactured in a comparative example.

[0139] Referring to FIGS. 3 and 4, it was confirmed that the photocurrent-voltage characteristics of the space-use perovskite solar cell manufactured in the embodiment of the present invention were maintained even after 10 MeV proton irradiation. On the other hand, it was confirmed that the characteristics of the perovskite solar cell manufactured in the comparative example were significantly degraded after 10 MeV proton irradiation.

[0140] Therefore, it can be seen that the space-use perovskite solar cell according to one embodiment of the present invention can be effectively operated even under space conditions.

[0141]

[0142] [Explanation of symbols]

[0143] 1: Perovskite solar cells for space

[0144] 100: Substrate

[0145] 210: First electrode

[0146] 220: Second electrode

[0147] 300: Perovskite photoactive layer

[0148] 410: First protective layer

[0149] 420: Second protective layer

[0150] 500: Electron transport layer

[0151] 600: Hole transport layer

Claims

1. First electrode; Second electrode; A perovskite photoactive layer provided between the first electrode and the second electrode; A first protective layer provided between the first electrode and the photoactive layer; and A second protective layer provided between the second electrode and the photoactive layer; A space-use perovskite solar cell, wherein the first protective layer and the second protective layer include a composition for forming a protective layer including a radiation-resistant material.

2. In paragraph 1, A space-use perovskite solar cell, wherein the photoactive layer comprises a compound represented by the following chemical formula 1: [Chemical Formula 1] ABX3 In the above chemical formula 1, A contains at least one of an organic ammonium ion and an alkali metal, B contains at least one metal among Pb, Sn, Bi and Sb, X is a halogen anion.

3. In paragraph 1, A space-use perovskite solar cell wherein the above-mentioned radiation-resistant material comprises an ammonium iodide-based compound.

4. In paragraph 1, A space-use perovskite solar cell wherein the above-mentioned radiation-resistant material comprises a lanthanide metal ion.

5. In paragraph 1, A substrate provided on one surface of the first electrode; An electron transport layer provided between the first electrode and the first protective layer; and A space-use perovskite solar cell further comprising a hole transport layer provided between the second electrode and the second protective layer.

6. In paragraph 1, A substrate provided on one surface of the first electrode; A hole transport layer provided between the first electrode and the first protective layer; and A space-use perovskite solar cell further comprising an electron transport layer provided between the second electrode and the second protective layer.

7. In paragraph 5 or 6, A space-use perovskite solar cell, wherein at least one of the substrate, the first electrode, the second electrode, the electron transport layer, and the hole transport layer contains a radiation-resistant material.

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