CN115547523B - 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
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- CN115547523B CN115547523B CN202211162682.7A CN202211162682A CN115547523B CN 115547523 B CN115547523 B CN 115547523B CN 202211162682 A CN202211162682 A CN 202211162682A CN 115547523 B CN115547523 B CN 115547523B
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- 230000005855 radiation Effects 0.000 title claims abstract description 81
- 230000017525 heat dissipation Effects 0.000 claims abstract description 18
- 238000009833 condensation Methods 0.000 claims abstract description 14
- 230000005494 condensation Effects 0.000 claims abstract description 14
- 239000011248 coating agent Substances 0.000 claims abstract description 5
- 238000000576 coating method Methods 0.000 claims abstract description 5
- 230000008878 coupling Effects 0.000 claims abstract description 4
- 238000010168 coupling process Methods 0.000 claims abstract description 4
- 238000005859 coupling reaction Methods 0.000 claims abstract description 4
- 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
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 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
- 239000000945 filler Substances 0.000 claims description 3
- 230000003287 optical effect Effects 0.000 claims description 2
- 239000013585 weight reducing agent Substances 0.000 claims 1
- 230000008901 benefit Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000000843 powder Substances 0.000 description 3
- 239000002918 waste heat Substances 0.000 description 3
- 238000001816 cooling Methods 0.000 description 2
- 238000007599 discharging 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
- 101100110009 Caenorhabditis elegans asd-2 gene Proteins 0.000 description 1
- 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
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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 high-power loop heat pipes, which comprises a radiation plate, a space nuclear reactor, a connecting pipeline, a hinge, a condensing pipeline and a heat conduction base, wherein 12 groups of single 3kW loop heat pipes are used for coupling the radiation plate to meet the heat dissipation requirement of 30kW level, the heat released by condensation of working media in the condensing pipeline of the loop heat pipes is discharged to space in a radiation heat transfer mode, the loop heat pipe evaporator in the space reactor transmits the heat to the condensing section in the radiation plate through the connecting pipeline, the heat is transmitted to the radiation plates on two sides through the heat conduction base, and a high-emissivity heat control coating is arranged on the outer side of the radiation plate.
Description
Technical Field
The invention belongs to the technical field of radiation radiators, and relates to a high-power loop based
A space reactor double-sided radiation radiator of a heat pipe.
Background
In a space environment, a spacecraft cannot conduct the rest of the heat in a heat conduction and convection manner
Discharged to space, and radiation heat dissipation is the only heat dissipation way of the spacecraft.
According to different application scenes of the integrated space reactor, the waste heat discharging structure
The requirements are also different. For example, waste heat can be discharged by water cooling and air cooling in ground application
Application in spacecraft requires dissipation by radiators with large radiating areas
And (5) heat. Space heat exhaust system plays an important role in the system of spacecraft and its function
Waste heat generated by the reactor is discharged into the universe, so that each spacecraft system is ensured
The instrument and equipment normally and safely run. The invention uses double heat pipes based on high-power loop
The surface radiation radiator meets the requirement of high-power heat dissipation capacity of the space pile.
Disclosure of Invention
The invention aims to provide a space reaction based on a high-power loop heat pipe
The double sided radiant heat sink is stacked to solve the problems set forth in the background art described above.
The aim of the invention can be achieved by the following technical scheme: based on high-power
Space reactor double-sided radiant radiator of loop heat pipe, said radiant radiator comprising a spoke
Jet plate, space nuclear reactor, connecting pipeline, hinge, condensing pipeline and heat conducting base group
In the process, 12 groups of single 3kW loop heat pipe coupling radiation plates are used to meet 30kW level
Heat dissipation requirement, working medium in a condensation pipeline of the loop heat pipe is subjected to radiation heat transfer mode
The heat released by condensation is discharged to space, and loop heat pipes positioned in the space reactor are steamed
The generator transmits heat to the condensing section inside the radiation plate through the connecting pipeline, and the heat passes through
The heat conducting base is transferred to the radiation plates at the two sides, the outer side of the radiation plate is provided with a high emissivity heat control coating,
the heat is finally discharged to space through radiation and heat dissipation;
the radiation plate is made of high heat conduction carbon fiber and is positioned outside the space nuclear reactor
One end of the radiating plate is fixed by a hinge and can rotate around the end; radiant panel appearance
The surface is stuck with an optical solar reflector.
The contact part of the radiation plate and the heat conduction base is filled with high heat conduction filler for reducing the contact
Thermal contact 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 heat conduction is filled in the condensation pipeline
The silicone grease reduces contact thermal resistance, and the heat conduction base is made of aluminum, so that the heat conduction base can meet the requirements of good heat conduction and reduction
Low weight requirements.
Space reactor double-sided radiation powder based on high-power loop heat pipe
In the heater, in order to achieve the aim of double-sided heat dissipation, the cross section shape of the heat conduction base is designed
The fin-like structure is distributed up and down symmetrically, and the purpose of closely contacting with the condensing pipeline is achieved
Meanwhile, the contact with the plane structure of the radiation plate is convenient, and the contact area is increased.
Space reactor double-sided radiation powder based on high-power loop heat pipe
In the heater, 12 groups of radiating plates are arranged up and down to avoid mutual radiation heat transfer between the radiating plates
The two sides face to the space radiation heat dissipation completely.
Space reactor double-sided radiation powder based on high-power loop heat pipe
In the heater, the thickness of the radiation plate is more than 1mm to meet certain strength.
Compared with the prior art, the invention relates to a space inversion based on a high-power loop heat pipe
The advantage of the double-sided radiation radiator of the reactor is: the invention relates to a high-power heat pipe based on a loop
The double-sided radiation radiator can solve the problem of high-power heat radiation of the space nuclear reactor, and is suitable for spaceflight
The device provides good temperature environment, has strong heat transfer capability, light weight, high reliability and the like
The advantage, and need not the pump to carry working medium.
Drawings
Fig. 1 is a schematic diagram of a radiant heat radiator system provided by the present invention.
Fig. 2 is a schematic diagram of the internal structure of the coupling condensing section of the radiation plate provided by the invention.
FIG. 3 shows the interior of the heat-conducting base-coupled condensing duct of the condensing section according to the present invention
A schematic structural diagram.
In the figure, 1, a radiation plate; 2. a spatial nuclear reactor; 3. a connecting pipeline; 4. closing device
A page; 5. a condensing pipeline; 6. and a heat conducting base.
Description of the embodiments
The following is a specific embodiment of the invention and is combined with the accompanying drawings
The present invention is further described by way of examples, but the invention is not limited to these examples.
The technical scheme adopted for solving the technical problems is as follows:
the high-power double-sided radiation radiator based on loop heat pipe mainly comprises a radiation plate and a cold
The device comprises a condensation pipeline, a heat conduction base and a connecting pipeline; loop inside space reactor star
The heat pipe evaporator transmits heat to the condensing section inside the radiation plate through the connecting pipeline, and the heat pipe evaporator heats
The quantity is transferred to the radiation plates at two sides through the heat conducting base, and the outer sides of the radiation plates are provided with high emissivity heat
And controlling the coating, and finally discharging heat to the space through radiation and heat dissipation.
The external surface of the radiation cold plate is stuck with a glass secondary surface mirror (OSR) or sprayed with KS-ZA
White paint.
The radiation cold plate is made of a heat conduction material with a heat conduction coefficient of more than 350W/(m.K).
The radiation plate is made of asphalt-based high-heat-conductivity carbon fiber.
The distance between any two adjacent condensing pipes is 100-200 mm.
The contact surface of the heat conduction base and the radiation plate is coated with heat conduction silver glue or heat conduction silicone grease.
The loop heat pipe is a cylindrical loop heat pipe.
Further, the working medium of the loop heat pipe is water.
As shown in the drawing, the condensing tube of the loop heat pipe can be connected with the condensing tube by radiation heat transfer
The heat released by the condensation of the working medium in the road 5 is discharged to the space. The invention mainly comprises radiation
The heat-conducting plate comprises a plate 1, a condensation pipeline 5, a heat-conducting base 6 and a connecting pipeline 3; star in space reactor
The loop heat pipe evaporator in the body transmits heat to the radiation plate through the connecting pipeline 3
1. An internal condensing section, heat is transferred to the radiation plates 1 at two sides through the heat conducting base 6, and radiation
The outer side of the jet plate 1 is provided with a high emissivity thermal control coating, and heat is finally discharged to the outside through radiation heat dissipation
Space is provided.
The radiation plate is made of high heat conduction carbon fiber, and the heat conduction coefficient is more than 350W/m.K, and the density is high
The degree is not more than 1.9g/cm3, the radiation plate 1 is positioned outside the star 2 of the space nuclear reactor,
one end of the hinge is fixed by a hinge 4 and can rotate around the end; OSR is pasted to radiant panel surface
A sheet or a high emissivity white paint.
The contact part of the radiation plate 1 and the heat conduction base 6 is filled with a high heat conduction filler for lowering
The outer side of the pipe wall of the condensation pipe 5 is tightly matched with the inner side of the heat conduction base 6 and has low contact thermal resistance
The heat conduction silicone grease is filled to reduce contact thermal resistance, and the heat conduction base 6 is made of aluminum, so that the heat conduction can be satisfied
Good heat and reduced weight.
For the purpose of double-sided heat dissipation, the cross-sectional shape of the heat conducting base 6 is designed to be
The fin-like structure which is distributed vertically symmetrically realizes the purpose of closely contacting the condensation pipeline 5
At the same time, it is convenient to contact with the planar structure of the radiation plate 1 and increase the contact area.
The thickness of the radiation plate 1 is 1mm or more in order to satisfy a certain strength.
To avoid mutual radiation heat transfer between the radiation plates 1, 12 groups of radiation plates 1 are shown in FIG. 1
The two surfaces are placed in a way that the upper and lower surfaces of the two surfaces are completely faced to space radiation for heat dissipation.
The high-power double-sided radiation radiator based on the loop heat pipe can solve the problem of empty space
The high-power heat dissipation problem of the nuclear reactor provides good temperature environment for the spacecraft, and has
The device has the advantages of strong heat transfer capability, light weight, high reliability and the like, and does not need a pump to convey working media.
What is not described in detail in this specification is well within the skill of those in the art
Known in the art. The specific embodiments described herein are merely illustrative of the invention
As exemplified. Those skilled in the art to which the invention pertains will appreciate that the described embodiments
Various modifications or additions or substitutions are made to the embodiments in a similar manner, but
Without departing from the spirit of the invention or exceeding the scope of the invention as defined by the appended claims.
Claims (4)
1. A space reactor double-sided radiation radiator based on a high-power loop heat pipe,
the radiator is characterized by comprising a radiation plate (1), a space nuclear reactor (2),
A connecting pipeline (3), a hinge (4), a condensing pipeline (5) and a heat conducting base (6),
12 groups of single 3kW loop heat pipe coupling radiation plates (1) are used to meet 30kW level
Heat dissipation requirement, condensing pipeline (5) of loop heat pipe by radiation heat transfer
The heat released by the condensation of the working medium is discharged to the space, and the ring is positioned in the space nuclear reactor (2)
The heat pipe evaporator transmits heat to the inside of the radiation plate (1) through the connecting pipeline (3)
Heat is transferred to the radiation plates (1) at the two sides through the heat conducting base (6), and the radiation plates are connected with the heat conducting base
The outer side of the jet plate (1) is provided with a high emissivity thermal control coating, and heat is finally discharged through radiation and heat dissipation
To space;
the radiation plate (1) is made of high heat conduction carbon fiber, and the radiation plate (1) is positioned in a space core
One end of the radiation plate (1) is fixed by a hinge (4) at the outer side of the reactor (2) and can wind around
The end rotates; an optical solar reflector is stuck on the outer surface of the radiation plate;
the contact part of the radiation plate (1) and the heat conduction base (6) is filled with a high heat conduction filler
For reducing contact thermal resistance;
one or more loop heat pipes are arranged, and the condensation section of the loop heat pipe is sleeved on the heat conduction base
The evaporator and the heat reservoir of the loop heat pipe are fixed on the inner surface of the radiation cold plate and are fixed on the heat dissipation
On the device; the outer side of the pipe wall of the condensation pipe (5) is tightly matched with the inner side of the heat conduction base (6)
And filling heat-conducting silicone grease to reduce contact thermal resistance;
to achieve the aim of double-sided heat dissipation, the cross section shape of the heat conduction base (6) is designed
The structure of the quasi-fin is symmetrically distributed up and down, and the purpose of closely contacting with a condensation pipeline (5) is realized
Is convenient to contact with the plane structure of the radiation plate (1) and increases the contact area.
2. The space reversal based on high-power loop heat pipe as claimed in claim 1
The double-sided radiation radiator of the reactor is characterized in that the heat conducting base (6) is made of aluminum
To meet the requirements of good thermal conductivity and weight reduction.
3. The space reversal based on high-power loop heat pipe as claimed in claim 1
A double-sided radiant radiator for a reactor is characterized in that, in order to avoid mutual radiation between the radiation plates (1)
The radiation heat transfer, the upper and lower surfaces of the 12 groups of radiation plates (1) are completely faced to the space radiation heat dissipation.
4. The space reversal based on high-power loop heat pipe as claimed in claim 1
A dual-sided radiant radiator of the reactor, characterized in that, to satisfy a certain intensity, the radiation
The thickness of the 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 CN115547523A (en) | 2022-12-30 |
| CN115547523B true CN115547523B (en) | 2024-02-13 |
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| 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)
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| 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 |
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| US10276271B2 (en) * | 2013-04-25 | 2019-04-30 | Triad National Security, LLC. | Electric fission reactor for space applications |
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2022
- 2022-09-23 CN CN202211162682.7A patent/CN115547523B/en active Active
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|---|---|---|---|---|
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| US10276271B2 (en) * | 2013-04-25 | 2019-04-30 | Triad National Security, LLC. | Electric fission reactor for space applications |
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| CN115547523A (en) | 2022-12-30 |
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