CN115547523A - Space reactor double-sided radiation radiator based on high-power loop heat pipe - Google Patents
Space reactor double-sided radiation radiator based on high-power loop heat pipe Download PDFInfo
- Publication number
- CN115547523A CN115547523A CN202211162682.7A CN202211162682A CN115547523A CN 115547523 A CN115547523 A CN 115547523A CN 202211162682 A CN202211162682 A CN 202211162682A CN 115547523 A CN115547523 A CN 115547523A
- Authority
- CN
- China
- Prior art keywords
- radiation
- heat
- space
- double
- heat pipe
- 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.)
- Granted
Links
- 230000005855 radiation Effects 0.000 title claims abstract description 102
- 238000009833 condensation Methods 0.000 claims abstract description 22
- 230000005494 condensation Effects 0.000 claims abstract description 22
- 238000000576 coating method Methods 0.000 claims abstract description 5
- 230000008878 coupling Effects 0.000 claims abstract 2
- 238000010168 coupling process Methods 0.000 claims abstract 2
- 238000005859 coupling reaction Methods 0.000 claims abstract 2
- 230000017525 heat dissipation Effects 0.000 claims description 13
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 239000004519 grease Substances 0.000 claims description 4
- 229920001296 polysiloxane Polymers 0.000 claims description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 3
- 239000000945 filler Substances 0.000 claims description 3
- 239000013585 weight reducing agent Substances 0.000 claims description 3
- 230000003287 optical effect Effects 0.000 claims description 2
- 239000002918 waste heat Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000003973 paint Substances 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 239000010426 asphalt Substances 0.000 description 1
- 239000000084 colloidal system Substances 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G21—NUCLEAR PHYSICS; NUCLEAR ENGINEERING
- G21C—NUCLEAR REACTORS
- G21C15/00—Cooling arrangements within the pressure vessel containing the core; Selection of specific coolants
- G21C15/02—Arrangements or disposition of passages in which heat is transferred to the coolant; Coolant flow control devices
- G21C15/14—Arrangements or disposition of passages in which heat is transferred to the coolant; Coolant flow control devices from headers; from joints in ducts
-
- G—PHYSICS
- G21—NUCLEAR PHYSICS; NUCLEAR ENGINEERING
- G21C—NUCLEAR REACTORS
- G21C15/00—Cooling arrangements within the pressure vessel containing the core; Selection of specific coolants
-
- G—PHYSICS
- G21—NUCLEAR PHYSICS; NUCLEAR ENGINEERING
- G21C—NUCLEAR REACTORS
- G21C15/00—Cooling arrangements within the pressure vessel containing the core; Selection of specific coolants
- G21C15/02—Arrangements or disposition of passages in which heat is transferred to the coolant; Coolant flow control devices
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Plasma & Fusion (AREA)
- General Engineering & Computer Science (AREA)
- High Energy & Nuclear Physics (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
The invention provides a space reactor double-sided radiation radiator based on a high-power loop heat pipe, which comprises radiation plates, a space nuclear reactor, a connecting pipeline, a hinge, a condensation pipeline and a heat conduction base, wherein 12 groups of single 3kW loop heat pipes are used for coupling the radiation plates to meet the 30 kW-level radiation requirement, working media in the condensation pipeline of the loop heat pipe are condensed to release heat to the space in a radiation heat transfer mode, a loop heat pipe evaporator positioned in the space reactor transfers the heat to a condensation section in the radiation plates through the connecting pipeline, the heat is transferred to the radiation plates on two sides through the heat conduction base, and high-emissivity heat control coatings are arranged on the outer sides of the radiation plates.
Description
Technical Field
The invention belongs to the technical field of radiation radiators, and relates to a space reactor double-sided radiation radiator based on a high-power loop heat pipe.
Background
In the space environment, the spacecraft cannot discharge the rest heat to the space by utilizing a heat conduction and convection mode, and radiation heat dissipation is the only heat dissipation way of the spacecraft.
According to different application scenes of the integrated space reactor, the requirements on a waste heat discharge structure are different. For example, in ground applications waste heat can be removed by water cooling or air cooling, while in space vehicle applications heat is removed by radiators with a large radiation area. The space heat discharge system plays an important role in a spacecraft system, and has the function of discharging waste heat generated by a reactor into the universe so as to ensure the normal and safe operation of each instrument and equipment of the spacecraft system. The invention meets the requirement of high-power heat dissipation capacity of the space stack by the double-sided radiation radiator based on the high-power loop heat pipe.
Disclosure of Invention
The invention aims to provide a space reactor double-sided radiation radiator based on a high-power loop heat pipe, so as to solve the problems in the background technology.
The purpose of the invention can be realized by the following technical scheme: a space reactor double-sided radiation radiator based on a high-power loop heat pipe comprises radiation plates, a space nuclear reactor, connecting pipelines, hinges, a condensation pipeline and a heat conduction base, wherein 12 groups of single 3kW loop heat pipes are used for being coupled with the radiation plates to meet the 30 kW-level heat dissipation requirement, working media in the condensation pipelines of the loop heat pipes are condensed to release heat to the space in a radiation heat transfer mode, a loop heat pipe evaporator in the space reactor conveys the heat to a condensation section in the radiation plates through the connecting pipelines, the heat is transferred to the radiation plates on two sides through the heat conduction base, high-emissivity thermal control coatings are arranged on the outer sides of the radiation plates, and the heat is finally released to the space through radiation heat dissipation;
the radiation plate is made of high-heat-conductivity carbon fibers, is positioned on the outer side of the space nuclear reactor, and one end of the radiation plate is fixed by a hinge and can rotate around the end; the outer surface of the radiation plate is adhered with an optical solar reflector.
In the space reactor double-sided radiation radiator based on the high-power loop heat pipe, the contact part of the radiation plate and the heat conduction base is filled with the high-heat-conduction filler to reduce the contact thermal resistance, the outer side of the pipe wall of the condensation pipeline is tightly matched with the inner side of the heat conduction base and filled with the heat conduction silicone grease to reduce the contact thermal resistance, and the heat conduction base is made of aluminum, so that the requirements of good heat conductivity and weight reduction can be met.
In the space reactor double-sided radiation radiator based on the high-power loop heat pipe, in order to achieve the aim of double-sided radiation, the cross section of the heat conduction base is designed into a fin-like structure which is distributed in an up-and-down symmetrical mode, the purpose of closely contacting a condensation pipeline is achieved, meanwhile, the heat conduction base is conveniently contacted with a plane structure of a radiation plate, and the contact area is increased.
In the space reactor double-sided radiation radiator based on the high-power loop heat pipe, in order to avoid mutual radiation heat transfer among all the radiation plates, the upper surface and the lower surface of 12 groups of radiation plates are completely faced to space radiation heat radiation.
In the space reactor double-sided radiation radiator based on the high-power loop heat pipe, in order to meet certain strength, the thickness of the radiation plate is more than 1 mm.
Compared with the prior art, the space reactor double-sided radiation radiator based on the high-power loop heat pipe has the advantages that: the high-power double-sided radiation radiator based on the loop heat pipe can solve the problem of high-power radiation of a space nuclear reactor, provides a good temperature environment for a spacecraft, has the advantages of strong heat transfer capacity, light weight, high reliability and the like, and does not need a pump to convey working media.
Drawings
FIG. 1 is a schematic view of a radiant heat sink system provided by the present invention.
Fig. 2 is a schematic diagram of the internal structure of the radiation plate coupled condenser section provided by the present invention.
FIG. 3 is a schematic diagram of an internal structure of a heat conducting base coupled with a condensing pipe of a condensing section according to the present invention.
In the figure, 1, a radiation plate; 2. a spatial nuclear reactor; 3. connecting a pipeline; 4. a hinge; 5. a condensing line; 6. a thermally conductive base.
Detailed Description
The following are specific embodiments of the present invention and are further described with reference to the drawings, but the present invention is not limited to these embodiments.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the high-power double-sided radiation radiator based on the loop heat pipe mainly comprises a radiation plate, a condensation pipeline, a heat conduction base and a connecting pipeline; the loop heat pipe evaporator positioned in the space reactor star body conveys heat to a condensation section in the radiation plate through a connecting pipeline, the heat is transferred to the radiation plates on two sides through the heat conducting base, the high-emissivity thermal control coating is arranged on the outer side of each radiation plate, and the heat is finally discharged to the space through radiation heat dissipation.
One or more loop heat pipes are arranged, a condensation section of each loop heat pipe is sleeved on the heat conduction base and fixed on the inner surface of the radiation cold plate, and an evaporator and a heat reservoir of each loop heat pipe are fixed on the heat dissipation device.
And a glass secondary surface mirror (OSR) is pasted on the outer surface of the radiation cold plate or KS-ZA white paint is sprayed on the outer surface of the radiation cold plate.
The radiation cold plate is made of heat conduction materials with the heat conduction coefficient of more than 350W/(m.K).
The radiation plate is made of asphalt-based high-thermal-conductivity carbon fibers.
The distance between any two adjacent condensation pipes is 100-200 mm.
The contact surface of the heat conduction base and the radiation plate is coated with heat conduction silver colloid or heat conduction silicone grease.
The loop heat pipe is a cylindrical loop heat pipe.
Furthermore, the working medium of the loop heat pipe is water.
As shown in the attached drawing, the heat released by the condensation of the working medium in the condensation pipeline 5 of the loop heat pipe can be discharged to the space by means of radiation heat transfer. The invention mainly comprises a radiation plate 1, a condensation pipeline 5, a heat conduction base 6 and a connecting pipeline 3; a loop heat pipe evaporator positioned in a space reactor star body 2 conveys heat to a condensation section in a radiation plate 1 through a connecting pipeline 3, the heat is transferred to the radiation plates 1 on two sides through a heat conduction base 6, a high-emissivity thermal control coating is arranged on the outer sides of the radiation plates 1, and the heat is finally discharged to the space through radiation heat dissipation.
The radiation plate is made of high-thermal-conductivity carbon fiber, the thermal conductivity coefficient is larger than 350W/m.K, the density is not larger than 1.9g/cm < 3 >, the radiation plate 1 is positioned on the outer side of the space nuclear reactor star body 2, and one end of the radiation plate is fixed by a hinge 4 and can rotate around the end; and an OSR sheet is stuck on the outer surface of the radiation plate or high-emissivity white paint is sprayed on the outer surface of the radiation plate.
The contact position of the radiation plate 1 and the heat conduction base 6 is filled with high-heat-conduction filler to reduce contact thermal resistance, the outer side of the pipe wall of the condensation pipeline 5 is tightly matched with the inner side of the heat conduction base 6 and is filled with heat-conduction silicone grease to reduce contact thermal resistance, and the heat conduction base 6 is made of aluminum, so that the requirements of good heat conductivity and weight reduction can be met.
In order to realize the aim of double-sided heat dissipation, the cross section of the heat conduction base 6 is designed into a fin-like structure which is distributed in an up-down symmetrical mode, so that the purpose of closely contacting the condensation pipeline 5 is realized, meanwhile, the heat conduction base is conveniently contacted with the plane structure of the radiation plate 1, and the contact area is increased.
In order to satisfy a certain strength, the thickness of the radiation plate 1 is more than 1 mm.
In order to avoid mutual radiation heat transfer among the radiation plates 1, 12 groups of radiation plates 1 are arranged as shown in figure 1, and the upper and lower surfaces of the radiation plates are completely faced to space radiation heat dissipation.
The high-power double-sided radiation radiator based on the loop heat pipe can solve the problem of high-power radiation of a space nuclear reactor, provides a good temperature environment for a spacecraft, has the advantages of strong heat transfer capacity, light weight, high reliability and the like, and does not need a pump to convey working media.
Those not described in detail in this specification are within the skill of the art. The specific embodiments described herein are merely illustrative of the spirit of the invention. Various modifications or additions may be made to the described embodiments, or alternatives may be employed, by those skilled in the art, without departing from the spirit or ambit of the invention as defined in the appended claims.
Claims (5)
1. A space reactor double-sided radiation radiator based on a high-power loop heat pipe is characterized by comprising radiation plates (1), a space nuclear reactor (2), a connecting pipeline (3), a hinge (4), a condensation pipeline (5) and a heat conduction base (6), wherein 12 groups of single 3kW loop heat pipes are used for coupling the radiation plates (1) to meet the 30 kW-level heat dissipation requirement, working media in the condensation pipeline (5) of the loop heat pipes are condensed and discharged to the space in a radiation heat transfer mode, a loop heat pipe evaporator positioned in the space reactor (2) transfers heat to a condensation section in the radiation plates (1) through the connecting pipeline (3), the heat is transferred to the radiation plates (1) on two sides through the heat conduction base (6), a high-emissivity heat control coating is arranged on the outer side of the radiation plates (1), and the heat is finally discharged to the space through radiation heat dissipation;
the radiation plate (1) is made of high-heat-conductivity carbon fibers, the radiation plate (1) is positioned on the outer side of the space nuclear reactor (2), and one end of the radiation plate (1) is fixed by a hinge (4) and can rotate around the end; the outer surface of the radiation plate is adhered with an optical solar reflector.
2. The space reactor double-sided radiation radiator based on the high-power loop heat pipe as claimed in claim 1, wherein the contact position of the radiation plate (1) and the heat conduction base (6) is filled with high heat conduction filler to reduce contact thermal resistance, the outer side of the pipe wall of the condensation pipeline (5) is tightly matched with the inner side of the heat conduction base (6) and filled with heat conduction silicone grease to reduce contact thermal resistance, and the heat conduction base (6) is made of aluminum, so that the requirements of good heat conductivity and weight reduction can be met.
3. The double-sided radiation radiator of the space reactor based on the high-power loop heat pipe as claimed in claim 1, wherein, in order to achieve the double-sided radiation, the cross section of the heat conducting base (6) is designed into a fin-like structure which is distributed symmetrically up and down, so as to achieve the purpose of closely contacting the condensing pipeline (5), facilitate the contact with the plane structure of the radiation plate (1), and increase the contact area.
4. The double-sided radiation radiator of the space reactor based on the high-power loop heat pipe as claimed in claim 1, in order to avoid mutual radiation heat transfer among all the radiation plates (1), the upper surface and the lower surface of 12 groups of radiation plates (1) are completely faced to the space for radiation heat dissipation.
5. The space reactor double-sided radiation radiator based on the high-power loop heat pipe as claimed in claim 1, characterized in that, in order to satisfy a certain strength, the thickness of the radiation plate (1) is more than 1 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211162682.7A CN115547523B (en) | 2022-09-23 | 2022-09-23 | Space reactor double-sided radiation radiator based on high-power loop heat pipe |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211162682.7A CN115547523B (en) | 2022-09-23 | 2022-09-23 | Space reactor double-sided radiation radiator based on high-power loop heat pipe |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115547523A true CN115547523A (en) | 2022-12-30 |
| CN115547523B CN115547523B (en) | 2024-02-13 |
Family
ID=84729101
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211162682.7A Active CN115547523B (en) | 2022-09-23 | 2022-09-23 | Space reactor double-sided radiation radiator based on high-power loop heat pipe |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115547523B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3709781A (en) * | 1968-05-24 | 1973-01-09 | Euratom | Space nuclear plant |
| CN103258576B (en) * | 2012-02-17 | 2015-12-16 | 中国原子能科学研究院 | Nuclear reactor for moon surface |
| US10276271B2 (en) * | 2013-04-25 | 2019-04-30 | Triad National Security, LLC. | Electric fission reactor for space applications |
| CN110085330A (en) * | 2019-04-10 | 2019-08-02 | 西安交通大学 | A kind of crash sub-critical spaces nuclear reactor power supply |
| CN109631634B (en) * | 2019-01-17 | 2020-03-31 | 西安交通大学 | Rotary expansion type variable power space radiation radiator |
| CN112284172A (en) * | 2020-10-29 | 2021-01-29 | 上海卫星装备研究所 | Space radiation radiator |
-
2022
- 2022-09-23 CN CN202211162682.7A patent/CN115547523B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3709781A (en) * | 1968-05-24 | 1973-01-09 | Euratom | Space nuclear plant |
| CN103258576B (en) * | 2012-02-17 | 2015-12-16 | 中国原子能科学研究院 | Nuclear reactor for moon surface |
| US10276271B2 (en) * | 2013-04-25 | 2019-04-30 | Triad National Security, LLC. | Electric fission reactor for space applications |
| CN109631634B (en) * | 2019-01-17 | 2020-03-31 | 西安交通大学 | Rotary expansion type variable power space radiation radiator |
| CN110085330A (en) * | 2019-04-10 | 2019-08-02 | 西安交通大学 | A kind of crash sub-critical spaces nuclear reactor power supply |
| CN112284172A (en) * | 2020-10-29 | 2021-01-29 | 上海卫星装备研究所 | Space radiation radiator |
Non-Patent Citations (13)
| Title |
|---|
| GENGLEI XIA: "study on flow and heat transfer performance of space reactor radiator water heat pipe", INTERNATIONAL CONFERENCE ON NUCLEAR ENGINEERING, vol. 4, 12 August 2022 (2022-08-12) * |
| 丰茂龙;范含林;黄家荣;陈江平;: "国外新型热管式空间辐射器研究进展", 航天器工程, no. 06, 15 November 2011 (2011-11-15) * |
| 余小章: "热管辐射器热分析", 南京航空航天大学学报, no. 02, 30 April 1995 (1995-04-30) * |
| 刘欣;梁新刚;: "太空辐射器传热优化设计及分析", 宇航学报, vol. 37, no. 05, 30 May 2016 (2016-05-30), pages 607 * |
| 刘欣等: "太空辐射器传热优化设计及分析" * |
| 刘逍;张文文;王成龙;张大林;田文喜;秋穗正;苏光辉;: "空间堆辐射散热器设计分析" * |
| 刘逍;张文文;王成龙;张大林;田文喜;秋穗正;苏光辉;: "空间堆辐射散热器设计分析", 原子能科学技术, no. 005, 31 December 2018 (2018-12-31) * |
| 卢佳鑫;孙贺涛;栾秀春;周成;王戈: "空间大功率热排放***设计", 空间电子技术, no. 002, 31 December 2021 (2021-12-31) * |
| 张文文;刘逍;田文喜;秋穗正;苏光辉;: "兆瓦级空间热管反应堆动力***概念设计", 原子能科学技术, no. 12, 20 December 2017 (2017-12-20) * |
| 张昊春: "MW级空间核反应堆***热管式辐射散热器分析及优化", vol. 54, no. 7 * |
| 张秀;张昊春;刘秀婷;尹德状;: "空间核电源热管式辐射散热器热分析与参数优化", no. 04 * |
| 石佳子: "空间大功率热排放***的设计与优化", 硕士论文工程科技II辑, vol. 2020, 15 December 2020 (2020-12-15) * |
| 胡古等: "空间核反应堆电源技术概览", vol. 4, no. 5 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115547523B (en) | 2024-02-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6542951B2 (en) | High efficiency heat dissipation device and cogeneration system for photovoltaic panels | |
| CN101510533B (en) | Novel microelectronic device radiator | |
| CN207099513U (en) | A kind of good degree of protection of heat sinking function is up to 65 grades and the electric cabinet of the above | |
| CN109219319B (en) | Isothermal integrated heat dissipation device suitable for micro-nano satellite | |
| CN109612315A (en) | Phase-change heat radiating device | |
| CN110190356A (en) | A kind of new-energy automobile power battery pallet with heat-pipe radiating apparatus | |
| CN103591824A (en) | Heat collecting storer | |
| CN115547523A (en) | Space reactor double-sided radiation radiator based on high-power loop heat pipe | |
| CN201106736Y (en) | Heat-insulating layer capable of shielding radiating heat and convection heat | |
| CN111902019B (en) | Thermal control device of satellite-borne phased array radar | |
| WO2022027751A1 (en) | Big-data server case | |
| CN208156595U (en) | A kind of radiator | |
| CN201837956U (en) | External radiator of notebook computer and portable small heat emitting machine | |
| WO2014157761A1 (en) | Vacuum solar heat collection panel and solar heat collection module using same | |
| CN211666127U (en) | Wall heating plate | |
| CN213593836U (en) | Thermal insulation board with good thermal insulation | |
| CN210432265U (en) | Heat radiation structure of high-heating graphene | |
| CN209845609U (en) | Radiation heat transfer and dissipation device | |
| CN110863626A (en) | Wall heating plate | |
| CN201050897Y (en) | Solar heat-collecting tube | |
| RU2797894C1 (en) | Radiant hybrid structure panel | |
| CN204943932U (en) | Near space solar heat-storing device | |
| CN215984137U (en) | Radiator using spring heat pipe | |
| CN220417451U (en) | Gravity heat pipe radiator | |
| CN115493432A (en) | Low-temperature heat pipe and low-temperature heat control device |
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 |