Miniature aircraft skin with energy collection and multispectral stealth functions

Abstract

The invention provides a miniature aircraft skin with energy collection and multispectral stealth functions, and belongs to the technical field of energy collection and spectral stealth, the miniature aircraft skin is composed of a periodic Al2O3-W multi-layer structure, and the multi-layer structure is formed by stacking a top oxidation film layer and N unit layers; each unit layer comprises a W layer and an Al2O3 layer, energy collection and multispectral camouflage are combined, the skin not only shows efficient photothermal conversion performance, but also meets visible light, laser and infrared compatible camouflage requirements, and the performance of a miniature aircraft in a complex environment is effectively improved; the problems that energy supply of a micro aircraft is limited and unstable, and a traditional camouflage structure is difficult to be compatible with visible light, infrared camouflage and laser camouflage multispectral stealth requirements are solved, and the manufacturing cost is reduced.

Description

Technical Field

[0001] This invention belongs to the field of energy harvesting and spectral stealth technology, specifically, it relates to a skin for a micro aircraft that combines energy harvesting and multispectral stealth. Background Technology

[0002] Traditional aircraft are widely used in transportation, reconnaissance, and detection. However, in confined and complex environments, conventional aircraft often struggle to enter or operate flexibly due to their large size and insufficient maneuverability, potentially even posing a collision risk. To overcome these limitations, micro-air vehicles (MAVs) have emerged. Leveraging their core advantages of small size and light weight, MAVs can penetrate confined, narrow, or dangerous spaces inaccessible to traditional aircraft and even humans, performing diverse missions and demonstrating enormous application potential.

[0003] When performing complex missions, the performance of micro-aircraft is severely constrained by two key bottlenecks: insufficient energy supply and difficulties in multispectral camouflage. Regarding energy, existing solutions have significant drawbacks: reliance on batteries is limited by their finite energy density and the strict size and weight constraints of micro-aircraft, resulting in excessively short flight endurance; while using laser-based remote power supply can replenish energy, it is highly susceptible to environmental interference, such as obstacles along the flight path or changes in atmospheric conditions, which can lead to energy interruptions and cause the micro-aircraft to fail due to loss of power. Therefore, developing a solution that can continuously, stably, and autonomously harvest environmental energy is crucial.

[0004] Meanwhile, achieving effective multispectral compatible camouflage presents another significant challenge. In battlefield or complex environments, MAVs need to evade multiple detection methods simultaneously: in the visible light band, their surface reflectance spectrum must be precisely modulated to blend into the background; in the mid-infrared and long-infrared bands, the skin must have extremely low emissivity to reduce the risk of detection by thermal imagers; furthermore, against laser detection, it must exhibit extremely low reflectivity for specific laser wavelengths to avoid generating strong echo signals. Traditional single-spectral camouflage structures are insufficient to meet these multi-dimensional stealth requirements. Summary of the Invention

[0005] To address the shortcomings of existing technologies, this invention proposes a skin (appearance) for a micro-aircraft that combines energy harvesting and multispectral stealth. This solves the problems of limited and unstable energy supply for micro-aircraft, the difficulty of traditional camouflage structures in achieving multispectral stealth capabilities including visible light, infrared camouflage, and laser camouflage, and reduces manufacturing costs.

[0006] This invention is achieved through the following technical solution: a skin for a micro-aircraft that combines energy harvesting and multispectral stealth: The skin of the micro-aircraft is composed of a periodic Al2O3-W multilayer structure, which is composed of a top oxide film layer and N unit layers stacked together. The oxide film thickness is h 0, each unit layer contains a W layer and an Al2O3 layer, with thicknesses of respectively. d i and h i ( i =1,2… N ).

[0007] Furthermore, the thickness of the top oxide film h 0 is adjustable, and color change is achieved through Brie-Perot (FP) resonance. h When the value is increased to 0, the structural color transitions from warm to cool colors on the CIE 1931 chromaticity diagram, adapting to various environmental backgrounds.

[0008] Furthermore, the spectral absorption characteristics of the multilayer structure were calculated using the finite-difference time-domain method; the intensity and width of the Fabry-Perot (FP) resonance were adjusted by changing the film thickness. The thickness of the transparent layer is related to the resonant wavelength, which can be predicted by the following formula: (1) In the formula, k It is an odd number. n is the refractive index of the transparent layer.

[0009] Furthermore, the oxide film layer can enhance the absorption capacity of the micro-aircraft skin at high temperatures, and improve the photoelectric conversion efficiency (PCE) by optimizing the thickness of the W layer and Al2O3 layer in the unit layer.

[0010] Furthermore, the photothermal conversion efficiency (PCE) can be calculated using the following formula: (2) σ It is the Stefan-Boltzmann constant; T abs Operating temperature for the skin of micro-aircraft; T amb The ambient temperature; CF Represents the light-gathering factor; Q Solar radiative heat flux under AM 1.5 standard conditions; α abs and ε abs These are the total solar absorptivity and total emissivity, calculated using the following formulas: (3) (4) in I AM1.5 (λ) represents the spectral irradiance of solar radiation under AM 1.5 standard conditions; I BB (λ, T abs ( ) represents the radiation distribution of a Planck blackbody; α obj ( λ () represents the spectral absorbance; ε obj ( λ () represents the spectral emissivity, which is determined by Kirchhoff's law. ε obj ( λ ) = α obj ( λ ).

[0011] Furthermore, the variation pattern of photoelectric conversion efficiency (PCE) is similar to that of spectral absorption, and its value increases with... h 0 increases, then increases and then decreases; even the top oxide film h Despite manufacturing deviations, the photoelectric conversion efficiency (PCE) remains stable.

[0012] Furthermore, the multilayer structure satisfies the following wide-angle stability conditions within the incident angle range of 0°–60°: low reflectivity deviation in the visible light band, small CIE 1931 chromaticity coordinate offset, and stable wide-angle color camouflage.

[0013] Furthermore, the skin of the micro-aircraft meets the requirements for infrared camouflage over a wide temperature range; The target has a small temperature difference with the background radiation, and the signal attenuation rate is low in the mid-infrared and long-wave infrared bands.

[0014] Furthermore, the wide temperature range includes an operating temperature of 100–500℃ and an ambient temperature of -20–20℃.

[0015] Beneficial effects of the invention This invention proposes a novel skin for micro-aircraft that combines energy harvesting with multispectral camouflage, composed of a periodic Al2O3-W multilayer structure. This skin not only exhibits highly efficient photothermal conversion performance but also simultaneously meets the requirements for visible light, laser, and infrared compatible camouflage, effectively improving the performance of micro-aircraft in complex environments; it solves the following technical problems: 1. Existing technologies are constrained by strict size and weight limitations, and there is a need to develop sustainable and stable high-efficiency energy solutions. However, the current reliance on micro batteries results in a severe lack of endurance due to size constraints, while alternative laser power supply methods have significant drawbacks such as interruption of energy transmission due to obstacles between the transmitter and receiver. 2. The skin needs to overcome the key technical challenge of multispectral compatible camouflage, which means that it needs to coordinate the reflection spectrum modulation required for visible light background matching, the characteristics of effectively suppressing mid- and far-infrared thermal radiation, and maintaining extremely low reflectivity for specific laser wavelengths on a single structure. 3. To achieve efficient solar energy absorption and the aforementioned complex multispectral camouflage functions, it is necessary to use precious metals, metamaterial structures, or rely on precise micro-nano processing techniques, which inevitably and significantly increases the overall manufacturing cost of the skin. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the skin of the micro-aircraft of the present invention; Figure 2 This section compares the structural performance of structures with and without oxide films, where (a) shows a comparison of spectral absorbance in the visible-near-infrared bands and a solar / blackbody radiation reference spectrum. Figure 2 (b) shows the numerical distributions of TSA and PCE for the two structures; Figure 3 The PCE decay trend of structures with and without oxide film with increasing temperature is shown. Figure 4 The effect of oxide film thickness on absorption performance is shown in (a), where (b) is the periodic variation of spectral absorbance with thickness, (c) is the absorption spectrum distribution corresponding to different thicknesses, and (d) is the evolution of PCE with thickness. Figure 5 The graph shows the change in reflectance spectrum as the oxide film thickness increases; (a) is the transverse wave, (b) is the longitudinal wave, and (c) is the curve of incident angle versus photothermal conversion efficiency. Figure 6 (a) Reflectance spectra of micro-aircraft skin in the range of 0.38–0.78 μm under different oxide film thicknesses. Figure 6 (b) is the corresponding chromaticity diagram; Figure 7 (a) shows the reflection spectra at different incident angles within the visible wavelength range. Figure 7 (b) is the corresponding chromaticity diagram; Figure 8 The diagram illustrates the infrared camouflage performance. (a) shows the emissivity of the micro-aircraft skin with oxide film in the atmospheric window, mid-infrared, and far-infrared regions. (b) shows the reflectivity of the micro-aircraft skin with and without oxide film at 1.064 μm. Figure 9Thermal images at ambient temperatures of 20°C and -20°C; Figure 10 For the radiation intensity of the micro-aircraft skin in the 3-5 μm and 8-14 μm bands, (a) is the radiation intensity curve of the micro-aircraft skin in the MWIR and LWIR bands when the operating temperature rises from 100℃ to 500℃, and (b) is the radiation intensity curve of the MWIR and LWIR bands when the incident angle gradually increases from 0° to 60°. Detailed Implementation

[0017] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] Unless otherwise specified, the experimental methods used in the following examples are conventional methods. The materials, reagents, methods, and instruments used, unless otherwise specified, are all conventional materials, reagents, methods, and instruments in the art, and can be obtained commercially by those skilled in the art.

[0019] This invention proposes a novel micro-aircraft skin that combines energy harvesting and multispectral camouflage functions, such as... Figure 1 As shown. Focusing on solar radiation to achieve energy harvesting, its energy is mainly concentrated in the 0.3-2.5 μm range.

[0020] Multispectral camouflage includes the visible light band (0.3-0.78 μm), the Nd:YAG laser band (1.064 μm), and the infrared band (3-4 μm and 8-14 μm).

[0021] For visible light camouflage, the reflection spectrum must closely match the background to produce similar colors; for Nd:YAG laser band, the micro-aircraft skin must have extremely low reflectivity at 1.064 μm to reduce reflected signals; since the atmosphere is relatively transparent in the MWIR and LWIR regions, and most thermal imagers operate in this region, infrared camouflage requires the micro-aircraft skin to have low emissivity.

[0022] The proposed micro-aircraft skin consists of a periodic Al₂O₃-W multilayer structure. The main geometric parameters are defined as follows: oxide film thickness is... h 0, no. i Units ( i =1,2… N The thicknesses of W and Al2O3 in the sample are respectivelyd i and h i .

[0023] The spectral absorption characteristics of the multilayer structure were calculated using the finite-difference time-domain (FDTD) method. Typically, the intensity and width of the Fabry-Perot (FP) resonance can be adjusted by changing the film thickness. The thickness of the transparent layer is related to the resonant wavelength, which can be predicted using the following formula: (1) In the formula, k It is an odd number. n The refractive index of the transparent layer is given. The wavelength range for solar energy collection is 0.3–2.5 micrometers. Furthermore, it is assumed that the FP resonant wavelength is 1.875 micrometers, and the refractive index of aluminum oxide (Al₂O₃) at this wavelength is 1.75. According to formula (1), when… k When the coefficient of performance (COP) is 1, the thickness of the alumina layer is 0.2 micrometers. To obtain the optimal photoelectric conversion efficiency (PCE), the monolayer periodic structure is further optimized. Furthermore, the thickness of each layer is adjusted to a specific range for optimization. h 0 represents 0.01 - 1 micrometer. d 1 represents 0.01 - 1 micrometer. h 1 represents 0.01 - 1 micrometer. With the maximum photoelectric conversion efficiency as the optimization objective, the optimized structural parameters are as follows: h 0 = 0.08 micrometers d 1 = 0.01 micrometers h 1 = 0.07 micrometers, at which point the maximum photoelectric conversion efficiency is 0.876.

[0024] In Figure 2(a), the red line represents the spectral absorbance of the oxide-coated structure in the 0.3–20 μm range, and the blue line represents the micro-aircraft skin without an oxide film. The orange area represents the normalized AM1.5 solar radiation spectrum, and the gray area represents the normalized blackbody radiation spectrum at 100°C. It is evident that in the visible-near-infrared region, the spectral absorbance of the oxide-coated micro-aircraft skin is higher than that of the oxide-free structure. Figure 2(b) shows that the TSA and PCE of the oxide-coated micro-aircraft skin are 0.876 and 0.901, respectively, while those of the oxide-free micro-aircraft skin are 0.688 and 0.713, respectively. Comparatively, the TSA and PCE of the oxide-coated micro-aircraft skin are increased by 26.14% and 27.3%, respectively, compared to the oxide-free structure. The maximum effective energy absorption of the oxide-coated micro-aircraft skin is calculated to be 788 W / m². 2 .

[0025] Photothermal conversion efficiency can be calculated using the following formula: (2) here σ It is the Stefan-Boltzmann constant; T abs Operating temperature for the skin of micro-aircraft; T amb The ambient temperature; CF Represents the light-gathering factor; Q The solar radiation heat flux is under AM 1.5 standard conditions. α abs and ε abs These are the total solar absorptivity and total emissivity, calculated using the following formulas: (3) (4) in I AM1.5 ( λ () represents the spectral irradiance of solar radiation under AM 1.5 standard conditions; I BB (λ, T abs ( ) represents the radiation distribution of a Planck blackbody; α obj ( λ () represents the spectral absorbance; ε obj ( λ () represents the spectral emissivity, which is determined by Kirchhoff's law. ε obj ( λ ) = α obj ( λ ).

[0026] To evaluate the photothermal conversion performance of oxide-coated micro-aircraft skin at high temperatures, the photothermal conversion efficiency (PCE) was calculated under different focusing factors and compared with that of the oxide-free structure. As shown in Figure 3, regardless of whether the structure has an oxide film, the PCE decreases with increasing temperature. Notably, the inhibitory effect of temperature changes on PCE significantly decreases with increasing focusing factor. Under the same focusing factor conditions, the photothermal conversion performance of the oxide-coated micro-aircraft skin is consistently superior to that of the oxide-free structure. This study indicates that the PCE of the oxide-coated micro-aircraft skin is higher than that of the oxide-free structure, demonstrating that the oxide film layer can effectively enhance the absorption capacity of the micro-aircraft skin at high temperatures. (This can be calculated using formulas 2 to 4.) As shown in Figure 4, the influence of oxide film thickness on the absorption characteristics of the micro-aircraft skin was further investigated. According to Figure 4(a), the spectral absorbance exhibits a periodic change with increasing thickness, and the period is closely related to the wavelength. This phenomenon is consistent with the absorption spectrum in the FP resonance mode. Four typical locations corresponding to the characteristic positions indicated by the white lines in Figure 4(a) were selected. h 0, and its corresponding complete absorption spectrum distribution is shown in Figure 4(b). As can be seen from Figure 4(b), with... h As the value increases from 0, the absorption of the micro-aircraft skin initially increases and then decreases. As shown in Figure 4(c), PCE exhibits a similar pattern of change to spectral absorption, with its value increasing with... h The coefficient initially increases and then decreases. Notably, even with a 50% manufacturing deviation in oxide film thickness, the micro-aircraft skin containing the oxide film still maintains a stable PCE of 0.769, demonstrating excellent process tolerance.

[0027] Figure 5 The reflectance spectra of the micro-aircraft skin at 0.38–0.78 μm are shown for different oxide film thicknesses, indicating that the average reflectance increases with increasing oxide film thickness. The chromaticity coordinates for different oxide film thicknesses are calculated using formulas (4)–(9) and plotted on the CIE 1931 xy chromaticity diagram, as shown below. Figure 5 As shown in (b), the structure's color gradually transitions from yellow to orange, purple, and blue as the thickness of the top oxide film increases, exhibiting a significantly wider color gamut. This characteristic indicates that the structure is well-suited for color camouflage applications. By adjusting the oxide film thickness, the skin of this micro-aircraft can adapt to various environments, such as desert and marine environments.

[0028] Figure 6(a) shows the reflectance spectra of the micro-aircraft skin in the range of 0.38–0.78 μm with different oxide film thicknesses. The average reflectance increases with increasing oxide film thickness. The chromaticity coordinates for different oxide film thicknesses were calculated using formulas (5)–(10) and plotted on the CIE 1931 xy chromaticity diagram, as shown below. Figure 6 As shown in (b), it can be seen that as the thickness of the top oxide film increases, the structure's color gradually transitions from yellow to orange, purple, and blue, exhibiting a significantly wider color gamut. This characteristic indicates that the structure is very suitable for color camouflage applications. By adjusting the oxide film thickness, the skin of this micro-aircraft can adapt to various environments, such as desert and marine environments. The calculation formula is as follows: (5) (6) (7) (8) (9) (10) Among them, D 65 It is the most commonly used artificial daylight source, with a color temperature of 6500 K; , and Represents CIE standard color matching functions R ( λ ) represents structural reflection; δ It is a constant; the x and y positions of the structural colors are determined based on their coordinates in the CIE 1931 xy chromaticity diagram.

[0029] Figure 7(a) shows that within the visible wavelength range, reflectance exhibits only slight fluctuations with the incident angle. Substituting the reflectance spectrum into equations (5)-(10), different chromaticity coordinates are derived and plotted as a chromaticity diagram. Observation Figure 7 (b) When the incident angle increases from 0° to 60°, the skin color changes very little, indicating that the micro-aircraft skin maintains excellent color camouflage performance in a wide angle range of 0° to 60°, highlighting its excellent angle insensitivity in visible light camouflage scenarios.

[0030] As shown in Figure 8(a), the blue area represents the atmospheric window, and the orange shaded area represents the mid-infrared and far-infrared regions. In the infrared region, the emissivity of the micro-aircraft skin with oxide film is almost the same as that without oxide film. Figure 8 (b) The emissivity and reflectivity of the micro-aircraft skin with and without oxide film at 1.064 μm are shown. It is evident that the reflectivity of the micro-aircraft skin with oxide film (0.014) is 94.4% lower than that of the structure without oxide film (0.25). In the mid-infrared and far-infrared regions, the average emissivity of the micro-aircraft skin with oxide film is extremely low (0.038), only increasing by 0.001 compared to the structure without oxide film. This indicates that the oxide film has no significant impact on the infrared camouflage capability of the micro-aircraft skin, but significantly improves the camouflage capability of the micro-aircraft skin against Nd:YAG lasers.

[0031] To verify the environmental adaptability of the micro-aircraft skin camouflage in the MWIR and LWIR regions, thermal images were calculated at ambient temperatures of 20°C and -20°C, as shown in the figure. Figure 9As shown. The background temperature was 300°C, and five different operating temperatures were selected: 100°C, 200°C, 300°C, 400°C, and 500°C. It can be seen that when the ambient temperature is 20°C and -20°C, the background radiation temperatures are 84.91°C and 67.43°C, respectively. The small difference in radiation temperature between the target and the background object indicates excellent infrared stealth performance. In summary, the infrared camouflage characteristics of the oxide film-coated micro-aircraft skin have good adaptability within a certain ambient temperature range. The calculation formula is as follows: (11) in, ε IR Indicates the emissivity of the thermal imager; T IR Indicates the observation temperature of the thermal imager; T obj It is the actual temperature of the target object.

[0032] The signal attenuation rate and radiation intensity in the mid-wave infrared (MWIR) and long-wave infrared (LWIR) bands were calculated, and the results are as follows: Figure 10 As shown in the figure, the signal attenuation rate exhibits a relatively stable trend with increasing temperature and angle. Particularly noteworthy is that when the operating temperature reaches 500℃, the signal attenuation rate in both bands exceeds 95%. Even at a large incident angle of 60°, the signal attenuation rate in the 3-5 μm band remains almost unchanged, while the signal attenuation rate in the 8-14 μm band is still maintained at around 85%. This clearly demonstrates that the skin of the micro-aircraft maintains excellent signal attenuation performance under both high temperature and large incident angle conditions.

[0033] The radiation intensity of the micro-aircraft skin in the 3-5 μm and 8-14 μm bands, such as Figure 10 As shown in (a), the radiation intensity of the micro-aircraft skin in the MWIR and LWIR bands gradually increases as the operating temperature rises from 100℃ to 500℃. When the operating temperature reaches 500℃, the radiation intensity in the MWIR band is 359.4 W / m. 2 The LWIR band value is 119.6 W / m. 2 . Figure 10 (b) shows that the radiation intensity in both the MWIR and LWIR bands increases as the incident angle gradually increases from 0° to 60°. At an incident angle of 60°, the MWIR radiation intensity is 26.2 W / m². 2 The radiation intensity of LWIR is 148.1 W / m². 2 The above results demonstrate that the skin of the micro-aircraft possesses excellent infrared stealth capabilities.

[0034] The formulas for calculating radiation intensity and signal attenuation rate are as follows: (12) (13) (14) in S Signal attenuation rate; E obj ( T abs ) is the target radiation intensity; E b ( T abs , θ ) represents the blackbody radiation intensity.

[0035] The foregoing has provided a detailed description of a micro-aircraft skin that combines energy harvesting and multispectral stealth, as proposed in this invention. The principles and implementation methods of this invention have been explained. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this invention. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1.A micro air vehicle skin with energy harvesting and multispectral stealth, characterized in that: The micro air vehicle skin is composed of a periodic Al2O3-W multilayer structure, which is stacked by a top oxide film layer and N unit layers; where the oxide film thickness is h 0, each unit layer comprises a W layer and an AI2O3 layer, the thicknesses of which are d i and h i ( i = 1, 2… N ). 2.The micro air vehicle skin according to claim 1, characterized in that: The thickness of the top oxide film h 0 adjustable, color change is achieved by a Fabry-Perot (FP) resonance, when h 0 increases, the structural color presents a transition from warm to cold on the CIE 1931 chromaticity diagram, adapting to various environmental backgrounds. 3.The micro air vehicle skin according to claim 2, characterized in that: The spectral absorption characteristics of the multilayer structure are calculated by the finite-difference time-domain method; the strength and width of the Fabry-Perot (FP) resonance are adjusted by adjusting the thickness of the film layer; The thickness of the transparent layer is related to the resonance wavelength, which can be predicted by the following formula: ,(1) wherein k is an odd number, n is the refractive index of the transparent layer. 4.The micro air vehicle skin according to claim 3, characterized in that: The oxide film layer can enhance the absorption capacity of the micro air vehicle skin at high temperature, and the photoelectric conversion efficiency (PCE) is improved by optimizing the thickness of the W layer and the Al2O3 layer in the unit layer. 5.The micro air vehicle skin according to claim 4, characterized in that: The photo-thermal conversion efficiency (PCE) can be calculated by the following formula: ,(2) σ is the Stefan-Boltzmann constant; T abs is the operating temperature of the micro air vehicle skin; T amb is the ambient temperature; CF represents the concentration factor; Q is the solar irradiance heat flux under AM 1.5 standard conditions; α abs and ε abs respectively, the total solar absorptance and the total emittance, and the calculation formula is as follows: ,(3) ,(4) wherein I AM1.5 (λ) is the spectral irradiance of solar radiation under AM 1.5 standard conditions; I BB (λ, T abs ) is the Planckian blackbody distribution; α obj ( λ ) is the spectral absorptivity; ε obj ( λ ) is the spectral emissivity, which is related to the spectral absorptivity by Kirchhoff's law ε obj ( λ ) = α obj ( λ ). 6.The micro air vehicle skin according to claim 5, characterized in that: The change pattern of photoelectric conversion efficiency (PCE) is similar to the spectral absorption, and the value thereof increases first and then decreases with the increase of h 0; even if there is manufacturing deviation in the top oxide film h 0, the photoelectric conversion efficiency (PCE) remains stable. 7.The micro air vehicle skin according to claim 6, characterized in that: The multilayer structure meets the following wide-angle stability conditions in the range of 0°-60° incident angle: The visible light band reflectivity deviation rate is low, the CIE 1931 chromaticity coordinate offset is small, and the wide-angle color camouflage is stable. 8.The micro air vehicle skin according to claim 7, characterized in that: The micro air vehicle skin has a small target and background radiation temperature difference in a wide temperature range, and a low signal attenuation rate in the mid-infrared and long-wave infrared bands, which meets the infrared camouflage conditions. 9.The micro air vehicle skin according to claim 8, characterized in that: The wide temperature range includes a working temperature of 100-500℃ and an environmental temperature of -20-20℃.

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