CN110906770A - Semi-open type high-temperature heat pipe structure - Google Patents
Semi-open type high-temperature heat pipe structure Download PDFInfo
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- CN110906770A CN110906770A CN201911114199.XA CN201911114199A CN110906770A CN 110906770 A CN110906770 A CN 110906770A CN 201911114199 A CN201911114199 A CN 201911114199A CN 110906770 A CN110906770 A CN 110906770A
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- open type
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- 229910052751 metal Inorganic materials 0.000 claims abstract description 32
- 239000002184 metal Substances 0.000 claims abstract description 32
- 238000003860 storage Methods 0.000 claims abstract description 21
- 239000007788 liquid Substances 0.000 claims description 17
- 238000010438 heat treatment Methods 0.000 claims description 15
- 229910052783 alkali metal Inorganic materials 0.000 claims description 11
- 150000001340 alkali metals Chemical class 0.000 claims description 11
- 238000005555 metalworking Methods 0.000 claims description 11
- 230000003014 reinforcing effect Effects 0.000 claims description 10
- 239000010935 stainless steel Substances 0.000 claims description 10
- 229910001220 stainless steel Inorganic materials 0.000 claims description 10
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 7
- 229910052750 molybdenum Inorganic materials 0.000 claims description 7
- 239000011733 molybdenum Substances 0.000 claims description 7
- 229910001257 Nb alloy Inorganic materials 0.000 claims description 5
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 claims description 4
- 229910052744 lithium Inorganic materials 0.000 claims description 4
- DGAQECJNVWCQMB-PUAWFVPOSA-M Ilexoside XXIX Chemical compound C[C@@H]1CC[C@@]2(CC[C@@]3(C(=CC[C@H]4[C@]3(CC[C@@H]5[C@@]4(CC[C@@H](C5(C)C)OS(=O)(=O)[O-])C)C)[C@@H]2[C@]1(C)O)C)C(=O)O[C@H]6[C@@H]([C@H]([C@@H]([C@H](O6)CO)O)O)O.[Na+] DGAQECJNVWCQMB-PUAWFVPOSA-M 0.000 claims description 3
- ZLMJMSJWJFRBEC-UHFFFAOYSA-N Potassium Chemical compound [K] ZLMJMSJWJFRBEC-UHFFFAOYSA-N 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 229910000623 nickel–chromium alloy Inorganic materials 0.000 claims description 3
- 229910052700 potassium Inorganic materials 0.000 claims description 3
- 239000011591 potassium Substances 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 3
- 229910052708 sodium Inorganic materials 0.000 claims description 3
- 239000011734 sodium Substances 0.000 claims description 3
- 229910000679 solder Inorganic materials 0.000 claims description 3
- 238000001816 cooling Methods 0.000 abstract description 9
- 230000017525 heat dissipation Effects 0.000 abstract description 8
- 239000002826 coolant Substances 0.000 abstract description 6
- 238000000034 method Methods 0.000 abstract description 3
- 239000011550 stock solution Substances 0.000 abstract description 3
- 230000008859 change Effects 0.000 abstract description 2
- 230000008569 process Effects 0.000 abstract description 2
- 238000007789 sealing Methods 0.000 abstract description 2
- 238000005728 strengthening Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 11
- 230000007246 mechanism Effects 0.000 description 7
- 238000002679 ablation Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 3
- 238000009826 distribution Methods 0.000 description 2
- 230000002265 prevention Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 238000005219 brazing Methods 0.000 description 1
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000005429 filling process Methods 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 238000001179 sorption measurement Methods 0.000 description 1
- 230000005068 transpiration Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
- F28D15/00—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies
- F28D15/02—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes
- F28D15/04—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes with tubes having a capillary structure
- F28D15/046—Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls ; Heat-exchange apparatus employing intermediate heat-transfer medium or bodies in which the medium condenses and evaporates, e.g. heat pipes with tubes having a capillary structure characterised by the material or the construction of the capillary structure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
Abstract
The invention relates to a semi-open type high-temperature heat pipe structure, which comprises: metal cavity, capillary structure, stock solution structure, filling pipe, blast pipe, temperature control switch and additional strengthening. The heat pipe is in a normal-temperature closed and high-temperature opened state, and the non-ablative heat protection of the structure is realized by utilizing the heat dissipation in the phase change and discharge processes of the working medium in the cavity. The temperature control switch is used for controlling the closing or opening of the exhaust pipe, and the sealing storage of the semi-open type heat pipe at normal temperature and the smooth exhaust at high temperature are ensured. Construct capillary structure and stock solution structure through the wire mesh, realize transporting and the storage of coolant working medium for semi-open high temperature heat pipe both has the heat dissipation ability of active cooling technique, does not need storage tank and supply system again, and the structure is simple more reliable, is applicable to the local thermal protection under the high thermal environment state of reply.
Description
Technical Field
The invention particularly relates to a semi-open type high-temperature heat pipe structure, and belongs to the field of thermal protection of hypersonic aircrafts.
Background
With the progress of the hypersonic aircraft, the performance requirement of the hypersonic aircraft is higher and higher, the thermal environment of the hypersonic aircraft is also severer, and the thermal protection technology of the key part of the hypersonic aircraft is a key bottleneck technology which restricts the development of the hypersonic aircraft.
The hypersonic aircraft has the requirement of shape preservation, the aircraft is required to adopt non-micro ablation thermal protection, and the traditional ablation thermal protection technology is difficult to meet the requirement. The passive thermal protection technology mainly based on composite materials such as C/C, C/SiC and the like is applied more at present, but the passive thermal protection technology has the problems of oxidation and high-temperature ablation, and has larger heat protection pressure in an extremely high heat flow state. The sparse conduction type thermal protection technology using the closed high-temperature heat pipe as the core is lack of a heat dissipation mechanism, is only suitable for thermal protection under the condition of heat centralized distribution such as a front edge structure and the like, and has limited heat prevention effect on the condition of controlling large-area areas such as a rudder surface and the like to be heated. Active cooling technologies such as regenerative cooling and transpiration cooling have extremely high cooling efficiency, but require a coolant supply system and a tank, and have high demands for energy and space, complicated systems, and low technical maturity.
Therefore, it is necessary to develop a new thermal protection technology, which can deal with higher thermal environment conditions and has a simple and reliable system, so as to provide a new solution for thermal protection of an aircraft in an extremely high condition.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the idea of active cooling is fused with the dredging type heat protection technology, and a semi-open type high-temperature heat pipe structure, in particular to a semi-open type high-temperature heat pipe heat-proof structure with a heat dissipation mechanism is provided.
The technical scheme adopted by the invention is as follows:
a semi-open high temperature heat pipe structure comprising: the device comprises a metal cavity, a capillary structure, a liquid storage structure, a filling pipe, an exhaust pipe, a temperature control switch and n reinforcing structures;
the metal cavity is a closed cavity structure, an alkali metal working medium is filled in the metal cavity, the capillary structure is tightly attached to the inner wall surface of the cavity, the liquid storage structure is placed on the non-heating wall surface in the cavity, the filling pipe and the exhaust pipe are provided with holes on the non-heating wall surface, the temperature control switch is arranged in the exhaust pipe, and the n reinforcing structures are arranged in the cavity.
The metal cavity is made of any one of stainless steel, nickel-chromium alloy or niobium alloy, and the range of the wall thickness of the metal cavity is 1-3 mm.
The capillary structure is composed of 3 layers of capillary silk screens and is used for providing capillary force for working medium backflow, the capillary silk screens are made of stainless steel or molybdenum, the 3 layers of capillary silk screens are arranged in a thick-thin-thick mode, the mesh number of the screen meshes of the capillary silk screen positioned in the middle layer is 300 meshes, and the mesh number of the screen meshes of the capillary silk screens positioned in the two layers of the outer layer is 100 meshes.
The liquid storage structure is formed by pressing 10-20 layers of capillary silk screens, and the total thickness of the liquid storage structure is less than half of the thickness of the metal cavity; the capillary screen of the liquid storage structure is made of stainless steel or molybdenum, and the mesh number of the screen is 100 meshes.
The filling pipe adopts a metal straight circular pipe, the value range of the diameter of the filling pipe is 4-10 mm, and the wall thickness of the filling pipe is 1 mm.
The exhaust pipe is a metal straight circular pipe, the diameter range of the exhaust pipe is 4-20 mm, the wall thickness range of the exhaust pipe is 1-3 mm, and the pipe opening of the exhaust pipe is arranged at the center of the metal cavity.
The temperature control switch is made of Ag5 brazing filler metal.
And 3 layers of capillary silk screens are laid on the surfaces of the n reinforcing structures and are communicated with the capillary silk screens on the inner wall surface of the metal cavity.
The alkali metal working medium in the cavity of the metal cavity is any one of potassium, sodium or lithium, the purity of the alkali metal working medium is not lower than 95%, and the total amount of the working medium accounts for 30-50% of the volume in the cavity.
The invention has the advantages and positive effects that:
1) the invention uses the thought of actively cooling the consumed working medium mass to realize heat dissipation, and can effectively solve the problem of heat protection in an extremely high heat flow state.
2) The invention realizes the storage and transportation of the working medium by utilizing the capillary structure, does not need an additional coolant supply system and an additional storage tank, has small requirements on energy and space, and has simpler and more reliable heat-proof structure.
3) The invention relates to a semi-open type high-temperature heat pipe, which belongs to the non-ablative heat protection technology, adopts metal materials and can be used for the heat prevention/bearing integrated function.
Drawings
FIG. 1 is a schematic view of a semi-open type high temperature heat pipe according to the present invention;
FIG. 2 is a thermal environment condition graph;
fig. 3 is a schematic diagram showing comparison of calculation results of a passive heat protection scheme and a semi-open heat pipe scheme.
Detailed Description
Aiming at the local thermal protection requirement of the future hypersonic aircraft, the invention provides a semi-open type high-temperature heat pipe structure with a heat dissipation mechanism.
The invention discloses a semi-open type high-temperature heat pipe structure, as shown in figure 1, comprising: metal cavity 1, capillary structure 2, stock solution structure 3, blast pipe 4, blast pipe 5, temperature control switch 6 and additional strengthening 7. Wherein, metal cavity 1 is closed cavity structure at normal atmospheric temperature, places high-purity alkali metal working medium in the cavity, reaches the design temperature value under the high temperature after, becomes the open mode by blast pipe 5 department. The metal used for the metal cavity 1 is stainless steel, nickel-chromium alloy or niobium alloy, and the wall thickness is 1-3 mm. The alkali metal working medium is used as a coolant, potassium, sodium or lithium is adopted, the purity is not lower than 95%, and the total amount of the working medium accounts for 30-50% of the volume in the cavity. The capillary structure 2 is tightly attached to the inner wall surface of the cavity and consists of 3 layers of capillary silk screens and is used for providing capillary force for the backflow of the working medium and ensuring that the liquid-state coolant working medium exists at the heating surface all the time. The capillary screen is made of stainless steel or molybdenum and is arranged in a coarse-fine-coarse mode, and the specification is 100-. The liquid storage structure 3 is placed on a non-heating surface in the cavity and is formed by pressing 10-20 layers of capillary silk screens, and the total thickness of the liquid storage structure is smaller than half of the thickness of the cavity. The capillary screen is made of stainless steel or molybdenum and has the specification of 100 meshes. The alkali metal working medium is uniformly distributed in the capillary structure 2 and the liquid storage structure 3. The filling pipe 4 and the exhaust pipe 5 are opened on the non-heating surface. The filling pipe 4 is used for filling the alkali metal working medium into the cavity in a vacuum environment, sealing treatment is carried out after the filling process, and a metal straight circular pipe is adopted, wherein the pipe diameter is 4-10 mm, and the pipe wall thickness is 1 mm. The exhaust pipe 5 is used for connecting the inside and the outside of a hot pipe cavity, the discharge process of the working medium is controlled through the internal and external pressure difference, a metal straight circular pipe is adopted, the pipe diameter is 4-20 mm, the pipe wall thickness is 1-3 mm, and the pipe opening is arranged at the center of the metal cavity. The pipe diameter should be designed and optimized according to the requirement of working medium discharge amount to ensure that the discharged working medium amount is enough. The temperature control switch 6 is arranged in the exhaust pipe 5 and is realized by Ag5 solder, and the melting point of the solder can be changed by adjusting the material proportion, so that the switch is melted at a designed temperature point, and the adjustable temperature range of the switch is 600-800 ℃. The n reinforcing structures 7 are arranged inside the cavity and used for ensuring the structural strength, and the number and the distribution of the reinforcing structures are determined according to the strength checking result. 3 layers of capillary screens are laid on the surface of the reinforcing structure 7, and the capillary screens are communicated with the capillary screens on the inner wall surface of the metal cavity 1, so that the liquid alkali metal working medium can be circulated to the heating surface in a shorter path. The capillary screen is made of stainless steel or molybdenum and is arranged in a coarse-fine-coarse mode, and the specification is 100-.
The working principle is as follows: the semi-open type high-temperature heat pipe is pneumatically heated by the outside, and the working medium in the heating side cavity absorbs heat and changes phase and is gasified. Under the action of pressure difference, the gaseous working medium carries heat to the unheated surface, releases the heat and condenses into liquid. Under the action of capillary force, the liquid working medium flows back to the heating surface from the liquid storage structure along the wall surface of the cavity and the capillary silk screen on the surface of the reinforcing structure, and circulation is completed. After the heat pipe cavity reaches a saturated state, the structure temperature can continuously rise under the action of pneumatic heating until the temperature reaches the temperature set by the temperature control switch. The welding material melts in the switch, and the switch is opened, and gaseous working medium carries the heat and is spouted out the hot tube cavity body by the blast pipe, realizes thermal dissipation. When the pneumatic heating quantity is the same as the heat carried by the ejected working medium, the structure reaches a thermal equilibrium state, and the temperature does not rise any more. Through reasonable design blast pipe size, steerable working medium discharge amount to control structure temperature is in reasonable scope.
The semi-open type high-temperature heat pipe structure draws the thought of an active cooling technology for reference, and realizes heat dissipation by depending on the mass of consumed working media. However, the semi-open type high-temperature heat pipe does not need a coolant supply system and a storage tank, the working medium is stored in the heat pipe, and the working medium is continuously transported to a heating surface by the adsorption force of the capillary structure, so that the whole structure is cooled. The semi-open type high-temperature heat pipe is provided with a heat dissipation mechanism, a supply system and a storage tank are not needed, the system structure is greatly simplified, the requirements of a cooling system on energy and space are reduced, and a new solution is provided for aircraft heat protection in an extremely high state.
Examples
In order to further explain the effectiveness of the semi-open type high-temperature heat pipe structure in thermal protection, numerical calculation is carried out on the lithium working medium/niobium alloy semi-open type heat pipe. The heating conditions are shown in FIG. 2, and the temperature calculation results are shown in FIG. 3. From the results of FIG. 3, it can be seen that without the semi-open heat pipe mechanism, the side wall temperature heated by the heat pipe will reach TinThe niobium alloy heat pipe would thermally break at 2350 c as shown. If a semi-open type heat pipe mechanism is considered, the temperature of the heating side wall surface of the heat pipe can be reduced to T by means of the consumed heat of the phase change ejection of the working mediumin_LiShown at 1000 c to ensure safety against heat. The calculation result shows the effectiveness of the semi-open type heat pipe mechanism provided by the invention.
Those skilled in the art will appreciate that the details of the invention not described in detail in the specification are within the skill of those skilled in the art.
Claims (9)
1. A semi-open type high-temperature heat pipe structure is characterized by comprising: the device comprises a metal cavity (1), a capillary structure (2), a liquid storage structure (3), a filling pipe (4), an exhaust pipe (5), a temperature control switch (6) and n reinforcing structures (7);
the metal cavity (1) is a closed cavity structure, an alkali metal working medium is filled inside the metal cavity, the inner wall surface of the cavity is tightly attached to the capillary structure (2), the liquid storage structure (3) is placed on the non-heating wall surface inside the cavity, the filling pipe (4) and the exhaust pipe (5) are opened on the non-heating wall surface, the temperature control switch (6) is placed in the exhaust pipe (5), and the n reinforcing structures (7) are arranged inside the cavity.
2. The semi-open type high-temperature heat pipe structure according to claim 1, wherein the metal cavity (1) is made of any one of stainless steel, nickel-chromium alloy or niobium alloy, and the wall thickness of the metal cavity (1) ranges from 1mm to 3 mm.
3. The semi-open type high-temperature heat pipe structure according to claim 1, wherein the capillary structure (2) is composed of 3 layers of capillary screens, and is used for providing capillary force for working medium backflow, the material of the capillary screens is stainless steel or molybdenum, the 3 layers of capillary screens are arranged in a thick-thin-thick mode, the mesh number of the capillary screens positioned in the middle layer is 300 meshes, and the mesh number of the capillary screens positioned in the outer two layers is 100 meshes.
4. A semi-open type high-temperature heat pipe structure according to claim 1, wherein the liquid storage structure (3) is formed by pressing 10-20 layers of capillary wire mesh, and the total thickness of the liquid storage structure (3) is less than half of the thickness of the metal cavity (1); the capillary screen of the liquid storage structure (3) is made of stainless steel or molybdenum, and the mesh number of the screen is 100 meshes.
5. The semi-open type high-temperature heat pipe structure according to claim 1, wherein the filling pipe (4) is a straight circular metal pipe, the diameter of the filling pipe (4) ranges from 4 mm to 10mm, and the wall thickness of the filling pipe (4) is 1 mm.
6. The semi-open type high-temperature heat pipe structure according to claim 1, wherein the exhaust pipe (5) is a straight metal circular pipe, the diameter of the exhaust pipe (5) ranges from 4 mm to 20mm, the thickness of the pipe wall of the exhaust pipe (5) ranges from 1mm to 3mm, and the pipe orifice of the exhaust pipe (5) is arranged at the center of the metal cavity (1).
7. A semi-open type high-temperature heat pipe structure according to claim 1, wherein the temperature control switch (6) is made of Ag5 solder.
8. A semi-open type high temperature heat pipe structure according to claim 1, wherein 3 layers of capillary screens are laid on the surfaces of the n reinforcing structures (7) to maintain connectivity with the capillary screens on the inner wall surface of the metal cavity (1).
9. The structure of any one of claims 1 to 8, wherein the alkali metal working medium in the cavity of the metal cavity (1) is any one of potassium, sodium or lithium, the purity of the alkali metal working medium is not less than 95%, and the total amount of the working medium accounts for 30 to 50% of the volume in the cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911114199.XA CN110906770A (en) | 2019-11-14 | 2019-11-14 | Semi-open type high-temperature heat pipe structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911114199.XA CN110906770A (en) | 2019-11-14 | 2019-11-14 | Semi-open type high-temperature heat pipe structure |
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| CN110906770A true CN110906770A (en) | 2020-03-24 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111660062A (en) * | 2020-05-06 | 2020-09-15 | 中国航天空气动力技术研究院 | High-temperature heat pipe based on 3D printing and forming method thereof |
| CN112357054A (en) * | 2020-11-19 | 2021-02-12 | 中国航天空气动力技术研究院 | Self-starting type heat-proof structure and high-speed aircraft |
| CN114313213A (en) * | 2022-01-05 | 2022-04-12 | 南京航空航天大学 | Novel aircraft wing section high temperature heat transfer system |
| CN115123586A (en) * | 2022-05-20 | 2022-09-30 | 东南大学 | Self-opening dissipation cooling device and thermal protection method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111660062A (en) * | 2020-05-06 | 2020-09-15 | 中国航天空气动力技术研究院 | High-temperature heat pipe based on 3D printing and forming method thereof |
| CN112357054A (en) * | 2020-11-19 | 2021-02-12 | 中国航天空气动力技术研究院 | Self-starting type heat-proof structure and high-speed aircraft |
| CN112357054B (en) * | 2020-11-19 | 2022-06-24 | 中国航天空气动力技术研究院 | Self-starting type heat-proof structure and high-speed aircraft |
| CN114313213A (en) * | 2022-01-05 | 2022-04-12 | 南京航空航天大学 | Novel aircraft wing section high temperature heat transfer system |
| CN115123586A (en) * | 2022-05-20 | 2022-09-30 | 东南大学 | Self-opening dissipation cooling device and thermal protection method |
| CN115123586B (en) * | 2022-05-20 | 2023-12-08 | 东南大学 | Self-opening dissipation cooling device and heat protection method |
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