CN116750214B - Flexible heat-proof skin for ultra-high temperature environment - Google Patents
Flexible heat-proof skin for ultra-high temperature environment Download PDFInfo
- Publication number
- CN116750214B CN116750214B CN202311041344.2A CN202311041344A CN116750214B CN 116750214 B CN116750214 B CN 116750214B CN 202311041344 A CN202311041344 A CN 202311041344A CN 116750214 B CN116750214 B CN 116750214B
- Authority
- CN
- China
- Prior art keywords
- flexible
- flexible wave
- microporous
- wave
- absorbing rubber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 229920001971 elastomer Polymers 0.000 claims abstract description 48
- 239000004744 fabric Substances 0.000 claims abstract description 40
- 238000001816 cooling Methods 0.000 claims abstract description 14
- 230000000149 penetrating effect Effects 0.000 claims abstract description 4
- 239000007788 liquid Substances 0.000 claims description 13
- 239000002033 PVDF binder Substances 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 229920002981 polyvinylidene fluoride Polymers 0.000 claims description 3
- 239000011148 porous material Substances 0.000 claims description 3
- 239000010453 quartz Substances 0.000 claims description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 3
- 229920002379 silicone rubber Polymers 0.000 claims description 3
- 239000000463 material Substances 0.000 description 4
- 238000002679 ablation Methods 0.000 description 3
- 230000008595 infiltration Effects 0.000 description 3
- 238000001764 infiltration Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000033228 biological regulation Effects 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 239000000110 cooling liquid Substances 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000012466 permeate Substances 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention provides a flexible heat-proof skin for an ultra-high temperature environment, which is characterized by comprising the following components: a flexible wave-transparent fabric, flexible wave-absorbing rubber and a microporous seepage pipeline; the microporous seepage pipeline is embedded between the flexible wave-transmitting fabric and the flexible wave-absorbing rubber, and the lower surface of the flexible wave-transmitting fabric is glued with the upper surface of the flexible wave-absorbing rubber; and the pipe wall of the microporous seepage pipe is provided with holes for conveying and penetrating cooling working medium into the flexible wave-transmitting fabric.
Description
Technical Field
The invention belongs to the field of high-temperature thermal protection design, and particularly relates to a flexible thermal protection skin for an ultra-high temperature environment.
Background
In the process of returning the return type aerospace craft to the earth at high atmospheric speed and maneuver, the surface of the craft is in intense friction with the surrounding atmosphere, and the environmental temperature in a large area is up to more than 4000K. In order to ensure that the outer surface is not severely deformed and internal electronic equipment is not burnt out due to high-temperature ablation, the surface of the return type aerospace craft needs to be coated with a thick and expensive rigid heat-proof and insulating material, and the requirements of the craft on variable-configuration flight are difficult to adapt. Flexible deformation of the heat-resistant structure and regulation of surface infrared target characteristics and radar reflection area (RCS) in a high-temperature environment are worldwide difficult problems.
Disclosure of Invention
The invention aims to provide a flexible heat-proof skin for an ultra-high temperature environment, which solves the problems existing in the prior art.
According to one aspect of the present invention, there is provided a flexible heat-resistant skin for an ultra-high temperature environment, the flexible heat-resistant skin being constituted by: a flexible wave-transparent fabric, flexible wave-absorbing rubber and a microporous seepage pipeline; the microporous seepage pipeline is embedded between the flexible wave-transmitting fabric and the flexible wave-absorbing rubber, and the lower surface of the flexible wave-transmitting fabric is glued with the upper surface of the flexible wave-absorbing rubber; and the pipe wall of the microporous seepage pipe is provided with holes for conveying and penetrating cooling working medium into the flexible wave-transmitting fabric.
Further, a limiting groove is formed in the upper surface of the flexible wave-absorbing rubber, and the microporous seepage pipeline is paved and fixed in the limiting groove.
Further, the microporous seepage pipeline is fixed in the limit groove in a cementing manner.
Further, the limit grooves are arranged in an S-shaped array.
Further, the flexible wave-absorbing rubber is provided with a liquid inlet, and the end head of the microporous seepage pipeline extends out of the liquid inlet.
Further, the ratio of the thickness of the flexible wave-transmitting fabric to the thickness of the flexible wave-absorbing rubber to the height of the microporous seepage pipeline is 1:2:1.
Further, the thickness of the flexible wave-transmitting fabric is 2mm, the thickness of the flexible wave-absorbing rubber is 4mm, and the height of the micro-pore seepage pipeline embedded in the flexible wave-absorbing rubber is 2mm.
Further, the flexible wave-transmitting fabric is made of quartz fiber fabric, the flexible wave-absorbing rubber is made of silicon rubber, and the microporous seepage pipeline is a polyvinylidene fluoride hollow pipeline with a microporous structure on the surface of the pipeline wall.
According to another aspect of the invention, an aircraft is provided, the aircraft exterior surface Meng Fushang being the flexible heat shield skin.
The beneficial effects of the invention are as follows:
the invention breaks through the active regulation and control technology of the infrared target characteristic and the RCS characteristic of the flexible heat-proof skin in the high-temperature flow of the surface of the return type aerospace vehicle for the first time, realizes the long-time (more than 1000 s) non-ablation and fracture extensibility of the flexible skin structure, ensures that the infrared radiation brightness of short waves (2.7-2.95 mu m) is less than 3W/Sr. square meters, reduces the RCS of the surface by 5-10dB compared with a metal material, and provides a key technical support for improving the capability of the return type aerospace vehicle for returning to the earth atmosphere.
The invention adopts a composite structure mainly comprising the flexible wave-transmitting fabric, the micropore seepage pipeline and the flexible wave-absorbing rubber for the first time, thereby ensuring the full infiltration of the cooling working medium of the outer surface of the flexible skin in a high-temperature environment and ensuring the extensibility and wave-absorbing property of the skin structure.
According to the invention, the micropore seepage pipeline is adopted for conveying the cooling working medium in the heat-proof skin of the return type aerospace craft for the first time, so that the problem of stable conveying of the liquid working medium under the condition of large overload flight (the acceleration is more than 6 g) is solved, and the stable and uniform supply of the cooling working medium on the surface of the flat-meter-level large-size heat-proof skin is realized.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiments of the invention and together with the description serve to explain the invention, without limitation to the invention, the accompanying drawings, in which:
FIG. 1 is a structural exploded view of a flexible heat shield skin for an ultra-high temperature environment according to an embodiment of the present invention;
FIG. 2 is a front view of a flexible wave absorbing rubber according to an embodiment of the present invention;
FIG. 3 is a reverse side view of a flexible wave absorbing rubber according to an embodiment of the present invention;
fig. 4 is a side view of a flexible wave absorbing rubber according to an embodiment of the present invention.
Wherein: 1-flexible wave-transparent fabric 2-microporous seepage pipeline 3-flexible wave-absorbing rubber 4-limit groove 5-liquid inlet
Detailed Description
In order that those skilled in the art will better understand the present invention, a technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in which it is apparent that the described embodiments are only some embodiments of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present invention without making any inventive effort, shall fall within the scope of the present invention.
Example 1
The present embodiment provides a flexible heat-proof skin for an ultra-high temperature environment, the structure of which is shown in fig. 1 to 4, the flexible heat-proof skin is formed, comprising: the flexible wave-transmitting fabric 1, the microporous seepage pipeline 2 and the flexible wave-absorbing rubber 3; the microporous seepage pipeline 2 is embedded between the flexible wave-transmitting fabric 1 and the flexible wave-absorbing rubber 3; the lower surface of the flexible wave-transmitting fabric 1 is glued with the upper surface of the flexible wave-absorbing rubber 3; and the pipe wall of the microporous seepage pipe 2 is provided with holes for conveying and penetrating cooling working medium into the flexible wave-transmitting fabric 1.
When the aircraft is in a high-temperature environment, a cooling medium is flushed into the microporous seepage pipeline 2, the cooling medium is conveyed along the microporous seepage pipeline 2, and permeates the flexible wave-transmitting fabric 1 through micropores, so that the whole infiltration of the flexible wave-transmitting fabric 1 is realized, and the cooling liquid evaporates and takes away heat when the outer surface of the flexible heat-proof skin contacts with the external high-temperature environment, so that the temperature of the outer surface of the flexible heat-proof skin is ensured not to rise. When electromagnetic waves are injected from the outside, the flexible wave-transmitting fabric 1 can be penetrated and absorbed by the flexible wave-absorbing rubber 3, so that the RCS of the flexible heat-proof skin structure is reduced.
In addition, the upper surface of the flexible wave-absorbing rubber 3 is provided with a limit groove 4, and the microporous seepage pipeline 2 is paved and fixed in the limit groove 4; the microporous seepage pipeline 2 adopts an S-shaped array arrangement mode, so that the cooling working medium conveying capacity of the microporous seepage pipeline 2 is not affected when the flexible skin is deformed.
In order to conveniently realize the input of cooling working medium from the inside of the aircraft, the flexible wave-absorbing rubber 3 is provided with a liquid inlet 5, and the end head of the micropore seepage pipeline extends out of the liquid inlet 5.
Finally, in the embodiment, the ratio of the thickness of the flexible wave-transparent fabric 1, the thickness of the flexible wave-absorbing rubber 3 and the height of the microporous seepage pipeline 2 is 1:2:1 in terms of specific parameters and material selection. The thickness of the flexible wave-transmitting fabric 1 is 2mm, the thickness of the flexible wave-absorbing rubber 3 is 4mm, and the height of the micro-pore seepage pipeline 2 embedded in the flexible wave-absorbing rubber 3 is 2mm. The flexible wave-transmitting fabric 1 is made of quartz fiber fabric, the flexible wave-absorbing rubber 3 is made of silicon rubber, and the microporous seepage pipeline 2 is a polyvinylidene fluoride hollow pipeline with a microporous structure on the surface of the pipeline wall.
The thickness of the flexible wave-transmitting fabric with the thickness of 2mm can achieve good working medium infiltration characteristics under the condition of realizing flexible deformation; the flexible wave-absorbing rubber has two functions, namely, the upper layer of the flexible wave-absorbing rubber has a 2mm area and provides position limitation for the embedded microporous seepage pipeline, so that the embedded microporous seepage pipeline and the flexible wave-absorbing rubber are in the same deformation state under the action of external force; and secondly, the lower layer of the heat-resistant rubber material is provided with a 2mm area for sealing the cooling working medium, and the thickness of 2mm is used for ensuring that the rubber material bears flexible deformation load and the sealing function of the working medium, and meanwhile, the heat-resistant rubber material has the heat-resistant skin and the maximum weight-reducing benefit.
Example 2
The embodiment provides an aircraft, wherein the outer surface Meng Fushang of the aircraft is a flexible heat-proof skin, and the structural composition and the function of the flexible heat-proof skin are the same as those of embodiment 1, and are not described herein again.
Example 3
1) As shown in fig. 1, the technology for regulating and controlling the target characteristics of the flexible heat-resistant skin for the ultra-high temperature environment mainly comprises a flexible wave-transparent fabric 1, a microporous seepage pipeline 2 and flexible wave-absorbing rubber 3.
2) As shown in the flexible heat-proof skin structure in fig. 1, in the invention, the microporous seepage pipeline 2 is preset in the limiting grooves 4 arranged in an S-shaped array on the surface of the flexible wave-absorbing rubber 3 in a cementing manner, and then the lower surface of the flexible wave-transmitting fabric 1 is fixedly glued on the upper surface of the flexible wave-absorbing rubber 3 (taking the edge of the reserved limiting groove 4 as a limit), so that the flexible heat-proof skin structure is ensured to have integral coordinated deformation capability. After the bonding is finished, the upper surface of the flexible skin product is covered by a flexible wave-transmitting fabric 1, and the back surface of the flexible skin is provided with a flexible wave-absorbing rubber 3.
3) As shown in the front, back and side surfaces of the flexible wave-absorbing rubber 3 in fig. 2-4, a cooling working medium liquid inlet 5 is reserved in the center of the wave-absorbing rubber. In the use process, the liquid cooling working medium enters the microporous seepage pipeline 2 through the liquid inlet 5, and is dispersed and conveyed to the back surface of the flexible wave-transmitting fabric 1 through the microporous seepage pipeline 2, so that the flexible wave-transmitting fabric 1 can be fully infiltrated by the liquid cooling working medium all the time under the action of high-temperature airflow.
5) In the high-temperature flow, a large amount of heat is taken away mainly through the evaporation and heat dissipation of the liquid cooling working medium on the upper surface of the flexible wave-transmitting fabric 1, so that the high-temperature flow (the total temperature is more than 4000K) of the flexible skin structure is realized, the non-ablation and fracture extensibility is more than 40% for a long time (more than 1000 s), the short wave (2.7-2.95 mu m) infrared radiation brightness is less than 3W/Sr. square meters, and the surface RCS is reduced by 5-10dB compared with a metal material.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (5)
1. A flexible heat-resistant skin for an ultra-high temperature environment, comprising: a flexible wave-transparent fabric, flexible wave-absorbing rubber and a microporous seepage pipeline; the microporous seepage pipeline is embedded between the flexible wave-transmitting fabric and the flexible wave-absorbing rubber, and the lower surface of the flexible wave-transmitting fabric is glued with the upper surface of the flexible wave-absorbing rubber; the pipe wall of the microporous seepage pipe is provided with holes for conveying and penetrating cooling working media into the flexible wave-transparent fabric; the upper surface of the flexible wave-absorbing rubber is provided with a limit groove, and the microporous seepage pipeline is paved and fixed in the limit groove; the micropore seepage pipeline is fixed in the limit groove in a cementing manner; the limit grooves are arranged in an S-shaped array; the flexible wave-absorbing rubber is provided with a liquid inlet, and the end head of the microporous seepage pipeline extends out of the liquid inlet.
2. The flexible heat-resistant skin for an ultra-high temperature environment according to claim 1, wherein the ratio of the thickness of the flexible wave-transparent fabric, the thickness of the flexible wave-absorbing rubber and the height of the microporous seepage pipeline is 1:2:1.
3. The flexible heat-proof skin for the ultra-high temperature environment according to claim 2, wherein the thickness of the flexible wave-transparent fabric is 2mm, the thickness of the flexible wave-absorbing rubber is 4mm, and the height of the micro-pore seepage pipeline embedded in the flexible wave-absorbing rubber is 2mm.
4. The flexible heat-resistant skin for the ultra-high temperature environment according to claim 1, wherein the flexible wave-transmitting fabric is quartz fiber fabric, the flexible wave-absorbing rubber is silicon rubber, and the microporous seepage pipeline is a polyvinylidene fluoride hollow pipeline with a microporous structure on the surface of the pipeline wall.
5. An aircraft, characterized in that the aircraft outer surface is covered with a flexible heat-resistant skin for ultra-high temperature environments according to any one of claims 1 to 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311041344.2A CN116750214B (en) | 2023-08-18 | 2023-08-18 | Flexible heat-proof skin for ultra-high temperature environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311041344.2A CN116750214B (en) | 2023-08-18 | 2023-08-18 | Flexible heat-proof skin for ultra-high temperature environment |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116750214A CN116750214A (en) | 2023-09-15 |
| CN116750214B true CN116750214B (en) | 2024-04-16 |
Family
ID=87948284
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311041344.2A Active CN116750214B (en) | 2023-08-18 | 2023-08-18 | Flexible heat-proof skin for ultra-high temperature environment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116750214B (en) |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1832883A (en) * | 2003-06-05 | 2006-09-13 | 波音公司 | Surface temperature control system |
| CN108153997A (en) * | 2018-01-23 | 2018-06-12 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of flexible covering of deformable Bump air intake ducts embeds matrix parameter and determines method |
| CN109264030A (en) * | 2018-09-29 | 2019-01-25 | 北京机械设备研究所 | A kind of cooling active thermal protection structure of convection current |
| CN109823508A (en) * | 2019-02-22 | 2019-05-31 | 西安电子科技大学 | The high-speed aircraft flexible covering that thermal protection of transfiniting is perceived with survival condition |
| CN110696440A (en) * | 2019-10-08 | 2020-01-17 | 西安电子科技大学 | High-speed aircraft over-limit thermal protection flexible skin based on porous foam and method thereof |
| CN211352977U (en) * | 2020-01-10 | 2020-08-25 | 深圳市正昊精密科技有限公司 | Wave absorbing plate for shielding electromagnetic interference |
| CN111674541A (en) * | 2020-05-25 | 2020-09-18 | 哈尔滨工业大学 | Flexible composite skin, manufacturing method thereof and tool structure |
| CN113844636A (en) * | 2021-10-19 | 2021-12-28 | 大连理工大学 | Omega-shaped flexible skin honeycomb structure |
| CN114828570A (en) * | 2022-04-22 | 2022-07-29 | 中国电子科技集团公司第二十九研究所 | Small-size covering heat exchanger and heat exchange system |
| CN218337024U (en) * | 2022-08-30 | 2023-01-17 | 苏州微邦材料科技有限公司 | Can realize inhaling anti-interference shielding film of ripples |
| CN116002041A (en) * | 2023-01-16 | 2023-04-25 | 浙大城市学院 | Bearing and sweating integrated skin structure for additive manufacturing |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9003657B2 (en) * | 2012-12-18 | 2015-04-14 | General Electric Company | Components with porous metal cooling and methods of manufacture |
-
2023
- 2023-08-18 CN CN202311041344.2A patent/CN116750214B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1832883A (en) * | 2003-06-05 | 2006-09-13 | 波音公司 | Surface temperature control system |
| CN108153997A (en) * | 2018-01-23 | 2018-06-12 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of flexible covering of deformable Bump air intake ducts embeds matrix parameter and determines method |
| CN109264030A (en) * | 2018-09-29 | 2019-01-25 | 北京机械设备研究所 | A kind of cooling active thermal protection structure of convection current |
| CN109823508A (en) * | 2019-02-22 | 2019-05-31 | 西安电子科技大学 | The high-speed aircraft flexible covering that thermal protection of transfiniting is perceived with survival condition |
| CN110696440A (en) * | 2019-10-08 | 2020-01-17 | 西安电子科技大学 | High-speed aircraft over-limit thermal protection flexible skin based on porous foam and method thereof |
| CN211352977U (en) * | 2020-01-10 | 2020-08-25 | 深圳市正昊精密科技有限公司 | Wave absorbing plate for shielding electromagnetic interference |
| CN111674541A (en) * | 2020-05-25 | 2020-09-18 | 哈尔滨工业大学 | Flexible composite skin, manufacturing method thereof and tool structure |
| CN113844636A (en) * | 2021-10-19 | 2021-12-28 | 大连理工大学 | Omega-shaped flexible skin honeycomb structure |
| CN114828570A (en) * | 2022-04-22 | 2022-07-29 | 中国电子科技集团公司第二十九研究所 | Small-size covering heat exchanger and heat exchange system |
| CN218337024U (en) * | 2022-08-30 | 2023-01-17 | 苏州微邦材料科技有限公司 | Can realize inhaling anti-interference shielding film of ripples |
| CN116002041A (en) * | 2023-01-16 | 2023-04-25 | 浙大城市学院 | Bearing and sweating integrated skin structure for additive manufacturing |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116750214A (en) | 2023-09-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102868021B (en) | A kind of High-performance frequency selection radar cover | |
| CN107834152B (en) | Conformal bearing antenna for realizing array surface heat dissipation by using FSS and miniature heat pipe | |
| CN105799260A (en) | Wave absorbing material for radar camouflage and preparation method thereof | |
| EP2938172B1 (en) | Heat control device for power equipment | |
| CN109664574A (en) | Passive type radiation-cooled structure and cooling means based on composite material | |
| CN102931483A (en) | High-temperature broadband symmetrical gradient multihole silicon nitride antenna housing structure | |
| CN116750214B (en) | Flexible heat-proof skin for ultra-high temperature environment | |
| CN102916251A (en) | High-temperature broadband gradient porous silicon nitride radome structure | |
| CN107444293B (en) | Functional heat insulation plate for automobile | |
| CN103471634B (en) | A kind of space optical remote sensor heat abstractor | |
| CN108562110A (en) | A kind of space radiation cold plate | |
| CN114705082A (en) | 3D aerogel-based phase-change composite material with infrared stealth and visible light double-camouflage functions and preparation method thereof | |
| CN109126643A (en) | One kind is from transparent composite aerogel of Light modulating type and preparation method thereof | |
| CN210072530U (en) | One-way heat-conducting plate of graphite alkene | |
| CN204329612U (en) | A kind of Combined thermal insulative panel for the preparation of stove housing | |
| CN208832834U (en) | A kind of space radiation cold plate | |
| CN108795142A (en) | The waterproof putty powder and its preparation process that low temperature environment uses | |
| CN205171713U (en) | Effectual phase change energy storage board keeps warm | |
| CN211346470U (en) | Temperature-adjusting energy storage device based on radiation cooling | |
| CN211345922U (en) | Winter and summer temperature adjusting device based on radiation cooling and solar energy utilization | |
| CN210917790U (en) | Passive form house high performance energy-conserving nature thermal insulation wall | |
| CN207700409U (en) | A kind of environment-friendly exterior wall thermal insulation board | |
| CN200989008Y (en) | Exposed wall external thermal insulation system with far infrared coating | |
| CN103292114A (en) | Spaceflight thermal protection material | |
| CN207646934U (en) | Ultralight steel insulated wall |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |