CN114030586B - Infrared stealth composite material structure of high-speed aircraft - Google Patents
Infrared stealth composite material structure of high-speed aircraft Download PDFInfo
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- CN114030586B CN114030586B CN202111406178.2A CN202111406178A CN114030586B CN 114030586 B CN114030586 B CN 114030586B CN 202111406178 A CN202111406178 A CN 202111406178A CN 114030586 B CN114030586 B CN 114030586B
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- 239000002131 composite material Substances 0.000 title claims abstract description 26
- 239000011241 protective layer Substances 0.000 claims abstract description 36
- 238000002329 infrared spectrum Methods 0.000 claims abstract description 20
- 239000010408 film Substances 0.000 claims description 75
- 239000010410 layer Substances 0.000 claims description 58
- 239000000463 material Substances 0.000 claims description 26
- 230000003287 optical effect Effects 0.000 claims description 13
- SBIBMFFZSBJNJF-UHFFFAOYSA-N selenium;zinc Chemical compound [Se]=[Zn] SBIBMFFZSBJNJF-UHFFFAOYSA-N 0.000 claims description 6
- 229910016036 BaF 2 Inorganic materials 0.000 claims description 3
- 230000008033 biological extinction Effects 0.000 claims description 3
- 238000001659 ion-beam spectroscopy Methods 0.000 claims description 3
- 238000001755 magnetron sputter deposition Methods 0.000 claims description 3
- 238000002207 thermal evaporation Methods 0.000 claims description 3
- 238000007736 thin film deposition technique Methods 0.000 claims 3
- 230000005855 radiation Effects 0.000 abstract description 18
- 238000002310 reflectometry Methods 0.000 abstract description 9
- 238000001228 spectrum Methods 0.000 abstract description 9
- 230000017525 heat dissipation Effects 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 5
- 238000000926 separation method Methods 0.000 abstract 1
- 238000001514 detection method Methods 0.000 description 9
- 238000000034 method Methods 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- 230000000903 blocking effect Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 239000011248 coating agent Substances 0.000 description 3
- 238000000576 coating method Methods 0.000 description 3
- 238000000151 deposition Methods 0.000 description 3
- 230000008021 deposition Effects 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 230000000670 limiting effect Effects 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000000427 thin-film deposition Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 230000002829 reductive effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010894 electron beam technology Methods 0.000 description 1
- 238000000295 emission spectrum Methods 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 238000003892 spreading Methods 0.000 description 1
- 230000035899 viability Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B5/00—Optical elements other than lenses
- G02B5/20—Filters
- G02B5/26—Reflecting filters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Laminated Bodies (AREA)
- Photometry And Measurement Of Optical Pulse Characteristics (AREA)
Abstract
The application provides a high-speed aircraft infrared stealth composite structure, be equipped with in proper order at the aircraft surface and be used for reflecting infrared spectrum's reflection stratum and be used for protecting the protective layer on reflection stratum, the reflection stratum includes first dielectric film and the second dielectric film that set gradually alternately, the emissivity is less than or equal to 5% in 3 ~ 10 mu m wave band when the protective layer temperature is less than or equal to 500 ℃, the reflection stratum has the effect of separation aircraft surface 3.7 ~ 4.8 mu m and 7.5 ~ 9.7 mu m wave band infrared spectrum outward radiation, and has lower reflectivity in the spectrum of other wave bands, makes it can see through this infrared stealth composite outward transfer heat, satisfies aircraft surface radiation heat dissipation's requirement, the protective layer has lower emissivity in 3 ~ 10 mu m scope when the temperature is less than or equal to 500 ℃, makes it can not outwards radiate a large amount of infrared spectrum after high-speed friction produces high temperature yet.
Description
Technical Field
The invention relates to the technical field of infrared stealth materials, in particular to an infrared stealth composite material structure of a high-speed aircraft.
Background
When the aircraft flies in the atmosphere at the speed of sound velocity which is several times that of the air, a great amount of heat is generated due to the intense friction between the aircraft and the air, so that the surface temperature of the aircraft skin is increased to several hundred ℃ and the aircraft skin has obvious infrared characteristics. Various high-precision infrared alarm and detection systems are rapidly developed at present, so that the sudden prevention and the viability of the high-speed aircraft are seriously threatened. Therefore, infrared stealth performance becomes an extremely important design requirement for high-speed aircraft.
Currently, the common infrared stealth methods include two types: firstly, aiming at the heat source in the system, a heat insulation material with low heat conductivity is generally adopted to block heat from diffusing to the surface, so that the surface temperature is reduced to inhibit the infrared radiation of the system, and infrared stealth is realized, but the method cannot solve the problem of system infrared characteristic enhancement caused by surface temperature rise and surface heat radiation enhancement caused by the pneumatic heating process; secondly, aiming at a system with high surface temperature, the method for inhibiting the infrared characteristics of the system comprises the steps of preparing a layer of metal coating or skin with low infrared emissivity and high infrared reflection on the surface of the system, and blocking the infrared emission spectrum of the surface of a high-temperature object from spreading to the outside of the metal coating or skin, wherein the metal coating or skin has high reflection effect on the infrared full spectrum, and the wrapped system cannot transmit heat which is transmitted to the inside under the action of pneumatic heating in a radiation mode, so that the internal heat is rapidly accumulated, the temperature is rapidly increased, and the internal load is damaged.
Disclosure of Invention
In view of the above-mentioned defects or shortcomings in the prior art, the present application aims to provide a high-speed aircraft infrared stealth composite material structure, wherein the infrared stealth composite material has higher reflectivity in the infrared detection wave bands of 3.7-4.8 μm and 7.5-9.7 μm, can block the infrared radiation of the aircraft surface in the two wave bands, realizes the infrared stealth of the aircraft in the wave band, and has lower reflectivity in other infrared wave bands, so that the infrared radiation in other wave bands can transmit heat outwards through the infrared stealth composite material, and the requirements of the radiation and heat dissipation of the aircraft surface are met.
The application provides an infrared stealth composite material structure of a high-speed aircraft, which comprises a reflecting layer and a protective layer, wherein the reflecting layer is used for reflecting infrared spectrums and the protective layer is used for protecting the reflecting layer are sequentially arranged on the outer surface of the aircraft; the reflecting layer comprises a first dielectric film and a second dielectric film which are alternately arranged; the extinction coefficient of the first dielectric film and the second dielectric film in the infrared band range is less than or equal to 1 multiplied by 10 ～3 And the refractive index of the first dielectric film is 1.3-1.9, and the refractive index of the second dielectric film is 2.1-2.7.
Specifically, the sum of the layers of the first dielectric film and the second dielectric film at least comprises 20 layers; the reflection layer is formed by alternately arranging a first dielectric film and a second dielectric film, accurately designing the thickness of each film, enabling the thickness of each film to be different from hundreds of nm to more than 1 mu m, enabling light rays with different wavelengths to have different transmission and reflection modulation effects by the two alternately arranged dielectric films based on a multi-beam interference principle, finally enabling the infrared spectrum of the reflection layer to form high reflection characteristics at 3.7-4.8 mu m and 7.5-9.7 mu m, playing a role of blocking infrared spectrum radiation in wave bands of 3.7-4.8 mu m and 7.5-9.7 mu m on the surface of the aircraft, and controlling infrared radiation of the wave bands in the aircraft; the protective layer has the characteristics of high strength, high temperature resistance and friction resistance, and provides a protective effect for the reflecting layer.
Preferably, the thickness of the first dielectric film is 500-2600 nm. Specifically, the optical thickness of the first dielectric film is calculated according to the following formula:
D m ＝x m L
wherein D is m Represents the optical thickness x of the first dielectric film of the mth layer m The optical thickness coefficient of the first dielectric film of the mth layer is represented, and m is more than or equal to 1 and is an odd number; l represents the 1/4 center wavelength optical thickness of the first dielectric film.
Preferably, the thickness of the second dielectric film is 500-2800 nm. Specifically, the optical thickness of the second dielectric film is calculated according to the following formula:
D n ＝x n H
wherein D is n Indicating the optical thickness x of the second dielectric film of the nth layer n The optical thickness coefficient of the second dielectric film of the nth layer is represented, and n is more than or equal to 2 and is an even number; h represents the optical thickness of the second dielectric film at 1/4 of the center wavelength.
Preferably, the reflective layer includes 12 layers of the first dielectric film and 12 layers of the second dielectric film. Specifically, the reflecting layer includes 12 layers of the first dielectric film and 12 layers of the second dielectric film, and the specific structure and the thickness of each layer are as follows:
x 1 L→x 2 H→x 3 L→x 4 H→x 5 L→x 6 H→x 7 L→x 8 H→x 9 L→x 10 H→x 11 L→x 12 H→x 13 L→x 14 H→x 15 L→x 16 H→x 17 L→x 18 H→x 19 L→x 20 H→x 21 L→x 22 H→x 23 L→x 24 H
wherein x is 1 、x 3 、x 5 、x 7 、x 9 、x 11 、x 13 、x 15 、x 17 、x 19 、x 21 、x 23 Representing an optical thickness coefficient of the first dielectric film of the corresponding layer; x is x 2 、x 4 、x 6 、x 8 、x 10 、x 12 、x 14 、x 16 、x 18 、x 20 、x 22 、x 24 Representing the optical thickness coefficient of the second dielectric film of the corresponding layer.
Preferably, the emissivity is less than or equal to 5% when the temperature of the protective layer is less than or equal to 500 ℃. Specifically, the thickness of the protective layer is more than or equal to 1mm, and the protective layer can keep extremely low infrared emissivity in a band range of 3-10 mu m at high temperature, so that the infrared spectrum can not be radiated to the outside basically after high-speed pneumatic heating is carried out, and the probability of detection by an infrared detector is reduced.
Preferably, the first dielectric film material is YF 3 、YbF 3 、BaF 2 、Y 2 O 3 Any one of the following.
Preferably, the second dielectric film material is any one of ZnS and ZnSe.
Preferably, the protective layer material is any one of ZnS and ZnSe.
Preferably, the material of the first dielectric film and the material of the second dielectric film are sequentially and alternately deposited on the inner surface of the protection layer by adopting a thermal evaporation thin film deposition technology, a magnetron sputtering thin film deposition technology or an ion beam sputtering thin film deposition technology.
In summary, the application discloses an infrared stealth composite material structure of a high-speed aircraft, which has the beneficial effects that the outer surface of the aircraft is sequentially provided with a reflecting layer for reflecting an infrared spectrum and a protecting layer for protecting the reflecting layer; the reflecting layer comprises a first dielectric film and a second dielectric film which are alternately arranged; the extinction coefficient of the first dielectric film and the second dielectric film in the infrared band range is less than or equal to 1 multiplied by 10 ～3 The refractive index of the first dielectric film is 1.3-1.9, and the refractive index of the first dielectric film is 1.3-1.9The refractive index of the second dielectric film is 2.1-2.7; when the temperature of the protective layer is less than or equal to 500 ℃, the emissivity is less than or equal to 5 percent, and a plurality of layers of first dielectric films and a plurality of layers of second dielectric films are sequentially and alternately arranged on the inner surface of the reflecting layer, so that the reflecting layer has the effect of blocking infrared spectrums in wave bands of 3.7-4.8 mu m and 7.5-9.7 mu m of the surface of the aircraft from being transmitted outwards, infrared radiation of the wave bands is controlled in the aircraft, and spectrums in other wave bands have lower reflectivity, so that the infrared stealth composite material can transmit heat outwards, and the radiation and heat dissipation requirements of the surface of the aircraft are met. In the flying process, heat generated by the pneumatic action protective layer is transmitted inwards to the surface of the aircraft, so that the surface of the aircraft becomes a radiation source, the reflection layer modulates infrared spectrums radiated by the surface of the aircraft, so that spectrums of two infrared detection wave bands of 3.7-4.8 mu m and 7.5-9.7 mu m cannot be transmitted outwards, infrared spectrums of the aircraft in the wave bands of 3.7-4.8 mu m and 7.5-9.7 mu m cannot be detected by the infrared detection equipment, spectrums of other wave bands can be transmitted outwards, the infrared detection wave band stealth of the aircraft is realized, certain radiation heat dissipation capacity is maintained, the stability of the temperature of the aircraft is maintained, the protective layer has the characteristics of high strength, high temperature resistance and friction resistance, the protective layer is provided with a lower emissivity, and the infrared spectrums of the protective layer cannot radiate outwards basically even after the infrared spectrums are rubbed at a high speed within the range of 3-10 mu m at the temperature of less than or equal to 500 ℃.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments made with reference to the following drawings.
Fig. 1 is a schematic view of an infrared stealth composite structure of a high-speed aircraft according to the present application.
FIG. 2 is a graph of emissivity at high temperature and temperature for a protective layer in accordance with an embodiment of the present application.
FIG. 3 is a reflectance curve of an infrared stealth composite of an aircraft according to an embodiment of the present application.
In the figure, 1, the outer surface of an aircraft; 2. a reflective layer; 3. and (3) a protective layer.
Detailed Description
The present application is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be noted that, for convenience of description, only the portions related to the invention are shown in the drawings. The present application will be described in detail with reference to the accompanying drawings in conjunction with embodiments.
The utility model provides a high-speed aircraft infrared stealth combined material structure, for aircraft surface 1, infrared stealth combined material from inside to outside includes reflector layer 2 and protective layer 3, and as shown in the schematic diagram that this application aircraft infrared stealth combined material structure is shown in fig. 1, for the internal surface of protective layer 3 sets gradually 12 layers of first dielectric film and 12 layers of second dielectric film from inside to outside in proper order, first dielectric film is YF 3 The refractive index of the material is about 1.4, the second dielectric film and the protective layer 3 are both ZnS materials, and the refractive index is about 2.2.
The structural composition of the reflective layer 2 and the thickness of each layer are as follows,
x 1 L→x 2 H→x 3 L→x 4 H→x 5 L→x 6 H→x 7 L→x 8 H→x 9 L→x 10 H→x 11 L→x 12 H→x 13 L→x 14 H→x 15 L→x 16 H→x 17 L→x 18 H→x 19 L→x 20 H→x 21 L→x 22 H→x 23 L→x 24 H
wherein x is 1 ＝0.891、x 2 ＝0.970、x 3 ＝1.071、x 4 ＝1.007、x 5 ＝0.948、x 6 ＝1.007、x 7 ＝1.099、x 8 ＝0.876、x 9 ＝0.988、x 10 ＝1.184、x 11 ＝0.734、x 12 ＝1.162、x 13 ＝1.068、x 14 ＝0.644、x 15 ＝0.416、x 16 ＝0.478、x 17 ＝0.493、x 18 ＝0.496、x 19 ＝0.422、x 20 ＝0.559、x 21 ＝0.498、x 22 ＝0.411、x 23 ＝0.440、x 24 ＝0.619，
The center wavelength was designed to be 8500nm, so that 1/4 of the center wavelength optical thickness of L and H was 2125nm.
The thickness of the protective layer 3 is 3mm, and as shown in fig. 2, the emissivity curve of the protective layer 3 from normal temperature to high temperature shows that the ZnS material has lower emissivity in the range of 25-500 ℃ and 3-10 mu m, and the infrared spectrum radiated outwards after high temperature is generated by high-speed friction in the flying process is less.
The first dielectric film YF is formed according to the calculated thickness of each layer of the reflecting layer 2 by adopting an electron beam thermal evaporation film deposition technology 3 And the material and the ZnS material of the second dielectric film are sequentially and alternately deposited on the inner surface of the protective layer 3 to obtain the infrared stealth composite material. As shown in fig. 3, the reflectivity curve of the infrared stealth composite material of the aircraft of the embodiment can be seen to have very high reflectivity in the wavelength ranges of 3.7-4.8 μm and 7.5-9.7 μm, and the reflectivity reaches more than 90%, while the other wavelength ranges have lower reflectivity, which indicates that the spectrum of the wavelength of the other infrared wavelength ranges can penetrate through the infrared stealth composite material and radiate outwards.
Furthermore, the first dielectric film YF may be formed by magnetron sputtering film deposition or ion beam sputtering film deposition according to the design structure of the reflective layer 2 and the thickness of each layer 3 And the material and the ZnS material of the second dielectric film are sequentially and alternately deposited on the inner surface of the protective layer 3 to obtain the infrared stealth composite material.
Further, the first dielectric film may be YbF 3 、BaF 2 、Y 2 O 3 Any one of the materials.
Further, the second dielectric film can be made of ZnSe material.
Further, the protective layer 3 may be made of ZnSe material.
Combining the above embodimentsIt can be seen that the application provides an infrared stealth composite material structure of a high-speed aircraft, wherein a reflecting layer 2 for reflecting infrared spectrum and a protecting layer 3 for protecting the reflecting layer 2 are sequentially arranged on the outer surface 1 of the aircraft; the reflecting layer 2 comprises 12 layers of first dielectric films and 12 layers of second dielectric films which are alternately arranged in sequence; the first dielectric film is YF 3 The material, the second dielectric film and the protective layer are ZnS materials, the refractive index of the first dielectric film is about 1.4, and the refractive index of the second dielectric film is about 2.2; the protective layer 3 has the emissivity less than or equal to 5 percent at the temperature less than or equal to 500 ℃, so that the reflecting layer 2 has the function of blocking infrared spectrums in wave bands of 3.7-4.8 mu m and 7.5-9.7 mu m on the surface of the aircraft from being transmitted outwards, infrared radiation in the wave band is controlled in the aircraft, and spectrums in other wave bands have lower reflectivity, so that the infrared stealth composite material can be transmitted outwards, and the radiation and heat dissipation requirements on the surface of the aircraft are met. In the flying process, heat generated by aerodynamic action on the protective layer 3 is transferred to the surface of the aircraft, so that the surface of the aircraft becomes a radiation source, the reflection layer 2 modulates infrared spectrums radiated by the surface of the aircraft, so that spectrums of two infrared detection wave bands of 3.7-4.8 mu m and 7.5-9.7 mu m cannot be transferred to the outside, infrared detection equipment cannot detect infrared spectrums of the aircraft in the wave bands of 3.7-4.8 mu m and 7.5-9.7 mu m, spectrums of other wave bands can be transferred to the outside, the effect that the aircraft is hidden in the infrared detection wave bands is achieved, certain radiation heat dissipation capacity is maintained, the stability of the temperature of the aircraft is maintained, the protective layer 3 has the characteristics of high strength, high temperature resistance and friction resistance, the protective layer 2 is provided with a protective effect, and the protective layer 3 has lower emissivity in the range of 3-10 mu m, so that the infrared spectrums cannot radiate outwards basically even after the high-speed friction generates high temperature.
It should be understood that the foregoing examples of the present invention are merely illustrative of the present invention and not limiting of the embodiments of the present invention, and that various other changes and modifications can be made by those skilled in the art based on the above description, and it is not intended to be exhaustive of all of the embodiments, and all obvious changes and modifications that come within the scope of the invention are defined by the following claims.
The foregoing description is only of the preferred embodiments of the present application and is presented as a description of the principles of the technology being utilized. It will be appreciated by persons skilled in the art that the scope of the invention referred to in this application is not limited to the specific combinations of features described above, but it is intended to cover other embodiments in which any combination of features described above or equivalents thereof is possible without departing from the spirit of the invention. Such as the above-described features and technical features having similar functions (but not limited to) disclosed in the present application are replaced with each other.
Claims (7)
1. The infrared stealth composite material structure of the high-speed aircraft is characterized by comprising a reflecting layer and a protective layer, wherein the reflecting layer is used for reflecting infrared spectrum and the protective layer is used for protecting the reflecting layer are sequentially arranged on the outer surface of the aircraft; the reflecting layer comprises a first dielectric film and a second dielectric film which are alternately arranged; the extinction coefficient of the first dielectric film and the second dielectric film in the infrared band range is less than or equal to 1 multiplied by 10 -3 The refractive index of the first dielectric film is 1.3-1.9, and the refractive index of the second dielectric film is 2.1-2.7; the first dielectric film material is YF 3 、YbF 3 、BaF 2 、Y 2 O 3 Any one of them; the second dielectric film material is any one of ZnS and ZnSe.
2. The infrared stealth composite structure of claim 1, wherein the first dielectric film has an optical thickness ranging from 500nm to 2600nm.
3. The infrared stealth composite structure of claim 2, wherein the second dielectric film has an optical thickness of 500-2800 nm.
4. A high speed aircraft infrared stealth composite structure according to claim 3, wherein the reflective layer comprises 12 layers of the first dielectric film and 12 layers of the second dielectric film.
5. The infrared stealth composite structure of claim 1, wherein the protective layer has an emissivity of 5% or less at a temperature of 500 ℃.
6. The infrared stealth composite structure of claim 5, wherein the protective layer material is any one of ZnS and ZnSe.
7. The infrared stealth composite structure of claim 6, wherein the material of the first dielectric film and the material of the second dielectric film are sequentially deposited on the inner surface of the protective layer alternately by using a thermal evaporation thin film deposition technique, a magnetron sputtering thin film deposition technique or an ion beam sputtering thin film deposition technique.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108828695A (en) * | 2018-06-25 | 2018-11-16 | 中国人民解放军国防科技大学 | Spectrum selective emission material for infrared stealth and preparation method thereof |
| CN112346160A (en) * | 2020-10-20 | 2021-02-09 | 中国人民解放军国防科技大学 | Nonmetal visible light laser infrared multiband compatible stealth film and preparation method thereof |
| CN113031313A (en) * | 2021-03-19 | 2021-06-25 | 浙江大学 | Adjustable infrared camouflage and stealth film based on phase-change material |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108828695A (en) * | 2018-06-25 | 2018-11-16 | 中国人民解放军国防科技大学 | Spectrum selective emission material for infrared stealth and preparation method thereof |
| CN112346160A (en) * | 2020-10-20 | 2021-02-09 | 中国人民解放军国防科技大学 | Nonmetal visible light laser infrared multiband compatible stealth film and preparation method thereof |
| CN113031313A (en) * | 2021-03-19 | 2021-06-25 | 浙江大学 | Adjustable infrared camouflage and stealth film based on phase-change material |
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