CN113686184A - Spacecraft thermal control single-phase fluid loop device based on novel shaftless pump - Google Patents
Spacecraft thermal control single-phase fluid loop device based on novel shaftless pump Download PDFInfo
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- CN113686184A CN113686184A CN202111012667.XA CN202111012667A CN113686184A CN 113686184 A CN113686184 A CN 113686184A CN 202111012667 A CN202111012667 A CN 202111012667A CN 113686184 A CN113686184 A CN 113686184A
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- 239000012530 fluid Substances 0.000 title claims abstract description 56
- 238000013461 design Methods 0.000 claims abstract description 22
- 239000007788 liquid Substances 0.000 claims abstract description 11
- 238000007789 sealing Methods 0.000 claims abstract description 6
- 238000012546 transfer Methods 0.000 abstract description 14
- 230000010354 integration Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 3
- 230000003247 decreasing effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000005855 radiation Effects 0.000 description 2
- 230000003750 conditioning effect Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 229910000856 hastalloy Inorganic materials 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000012774 insulation material Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 238000004804 winding Methods 0.000 description 1
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- 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
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- 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
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/503—Radiator panels
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- Biodiversity & Conservation Biology (AREA)
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a spacecraft thermal control single-phase fluid loop device based on a novel shaftless pump, which comprises a liquid reservoir, the novel shaftless pump, a first heat sink, a second heat sink and a fluid pipeline. The invention abandons the traditional driving pump and adopts a novel shaftless pump which can be used in series in a region to drive the working medium to flow. The novel shaftless pump adopts the integrated design of a pump and a pipeline, and the structure is more compact due to the integrated design of a motor and the pump. The invention solves the sealing problem of the pump in the fluid loop pipeline, reduces the on-way resistance of the loop, and has the characteristics of quick integration and high adaptability. The method can be applied to heat transfer of a small satellite spacecraft and isothermal design of a partial region of the spacecraft.
Description
Technical Field
The invention relates to the field of fluid circuit devices, in particular to a spacecraft thermal control single-phase fluid circuit device based on a novel shaftless pump.
Background
The spacecraft is required to have certain thermal control means in the face of complex thermal environment, and the thermal control means comprises active thermal control technology and passive thermal control technology. With the complexity of space tasks increasing, passive thermal control means, such as loop heat pipes, thermal insulation materials, often cannot meet the requirements of isothermal or more heat transfer in the area. Meanwhile, for some satellite thermal control systems with higher precision requirements, the adjustment of the thermal control systems needs to be performed according to the heat transfer process. Active thermal control techniques are therefore of particular importance. In recent years, as an important technical means for active thermal control of a spacecraft, a pump drive fluid loop thermal control technology has been widely applied to various space tasks and scientific experiments by researchers. The heat control management system utilizes the flowing and heat transfer characteristics of working media to collect and transmit the internal heat to the radiator, thereby realizing the heat control management of the spacecraft. However, for the index requirements of different satellite fluid circuits, the driving pump and the fluid circuit need to be correspondingly selected, which increases the research cost and the task complexity. Conventional pump designs also suffer from leakage and increased on-way resistance of the tubing.
Disclosure of Invention
The invention aims to provide a spacecraft thermal control single-phase fluid loop device based on a novel shaftless pump, so as to solve the problems in the prior art.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a spacecraft thermal control single-phase fluid loop device based on a novel shaftless pump comprises a liquid reservoir, the novel shaftless pump, a first heat sink, a second heat sink and a fluid pipeline; the novel shaftless pump, the first heat sink and the second heat sink are connected into a closed loop through the fluid pipeline, and the novel shaftless pump, the first heat sink and the second heat sink are not connected in sequence; the liquid storage device is connected to the fluid pipeline and used for adjusting the working medium in the closed loop.
Further, the number of the novel shaftless pumps is more than one, and the novel shaftless pumps are connected in series in the closed loop.
Further, the novel shaftless pump comprises a first novel shaftless pump and a second novel shaftless pump, and the first novel shaftless pump, the first heat sink, the second novel shaftless pump and the second heat sink are sequentially connected into a closed loop through the fluid pipeline; the reservoir is connected to the fluid line between the first new shaftless pump and the first heat sink.
Further, the first heat sink is a cold plate, and the cold plate is used for absorbing heat of the heating workpiece and transmitting the heat to the working medium.
Further, the second heat sink is a radiator, and the radiator is used for dissipating heat transferred by the working medium through radiant heat.
Further, the liquid storage device is a rubber bag type liquid storage device.
Furthermore, the novel shaftless pump adopts an integral sleeve type design and comprises a stator end cover, a first bearing, a limiting workpiece, a rotor, a fixed pipeline, an end cover, blades, a rotating part, a second bearing and a stator; the two ends of the stator are bolted with the stator end covers, the fixed pipeline penetrates through the stator end covers and the stator, and the end covers are connected with the fixed pipeline through flanges; the first bearing, the limiting workpiece, the rotor, the blade, the rotating part and the second bearing are all positioned inside the pipe body of the fixed pipeline; the outer side of the rotor is embedded with a magnetic shoe, an inner special bayonet is matched and assembled with the first boss of the rotating part, and the second boss of the rotating part is higher than the inner special bayonet of the rotor and the first boss of the rotating part, so that the rotor and the rotating part are prevented from moving relatively in the radial direction; the first bearing and the second bearing are respectively connected with two ends of the rotating component, so that the rotating component can rotate along the axis of the fixed pipeline; the first bearing is in interference fit with the closed end of the fixed pipeline; an annular boss is arranged in the end cover, and the second bearing is in interference fit with the annular boss of the end cover; the limiting workpiece is arranged between the first bearing and the rotor and limits the first bearing and the rotor to move radially, and the inner side of the limiting workpiece is provided with a special bayonet design and is connected with the first boss of the rotating component, so that the limiting workpiece and the rotating component are prevented from relative rotation movement, and the radial movement of the rotating component is limited; the second bearing is a stepped shaft and is connected with the second boss of the rotating component and the end cover; the vanes are assembled inside the rotating member at a fixed angle and position.
Furthermore, the pipe inner diameter of the closed end of the fixed pipeline and the outlet end of the end cover in the novel shaftless pump is not more than 15mm in size.
Furthermore, the stator in the novel shaftless pump adopts a small brushless motor stator structure, and the external dimension of the stator does not exceed 10cm by 10 cm.
Furthermore, in the novel shaftless pump, the inner side of the cover end is provided with a small annular groove in which a sealing ring is placed.
The invention has the beneficial effects that:
1. the invention can be applied to the heat transfer of the small satellite spacecraft and the isothermal design of the spacecraft partial area;
2. the novel shaftless pump which can be used in series in an area mode is adopted to drive working media to flow, the novel shaftless pump adopts an integrated design of a pump and a pipeline, and the integrated design of a motor and the pump is adopted, so that the structure is more compact, the design volume is further reduced, the risk of leakage of the whole pipeline is further reduced, and the novel shaftless pump has the characteristics of quick integration and high adaptability;
3. the novel shaftless pump solves the problems of vibration, bent pipe design and on-way resistance caused by bent pipes in the conventional pump, and improves the adaptability and vibration resistance of the whole device;
4. the flow rate of the working medium in the fluid loop can be controlled by controlling the rotating speed of the novel shaftless pump at different positions, so that the control of heat transfer is realized. Meanwhile, the heat transfer capacity of the fluid circuit can be increased or decreased by increasing or decreasing the working number of the shaftless pumps aiming at the transfer of different heat.
Drawings
FIG. 1 is a schematic diagram of a typical circuit of a novel shaftless pump-based spacecraft thermal control single-phase fluid circuit device of the present invention;
FIG. 2 is a schematic diagram of the overall structure of the novel shaftless pump of the spacecraft thermal control single-phase fluid circuit device based on the novel shaftless pump according to the invention;
FIG. 3 is an axial cross-sectional view of the novel shaftless pump of the present invention based on the novel shaftless pump spacecraft thermally controlled single-phase fluid circuit apparatus;
FIG. 4 is a radial schematic view of the novel shaftless pump of the present invention based on the novel shaftless pump spacecraft thermally controlled single-phase fluid circuit arrangement;
FIG. 5 is a schematic structural view of the internal vanes and rotating parts of the novel shaftless pump of the spacecraft thermal control single-phase fluid circuit device based on the novel shaftless pump according to the present invention;
wherein, 1-bolt; 2-stator end cover; 3-a first bearing; 4-limiting the workpiece; 5-a rotor; 6-fixing a pipeline; 7-sealing ring; 8-end cap; 9-blades; 10-a rotating member; 11-a second bearing; 12-a stator; 13-a base; 14-rotating member first boss; 15-rotating member second boss; 16-a reservoir; 17-a first novel shaftless pump; 18-a second novel shaftless pump; 19-a first heat sink; 20-a second heat sink; 21-fluid line.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the invention, are intended for purposes of illustration only and are not intended to limit the scope of the invention.
Fig. 1 shows a typical circuit diagram of a spacecraft thermal control single-phase fluid circuit device based on a novel shaftless pump. The loop device comprises a liquid storage tank 16, a first novel shaftless pump 17, a second novel shaftless pump 18, a first heat sink 19, a second heat sink 20 and a fluid pipeline 21; the first novel shaftless pump 17, the first heat sink 19, the second novel shaftless pump 18 and the second heat sink 20 are sequentially connected into a closed loop through the fluid pipeline 21; the reservoir 16 is connected to the fluid line 21 between the first novel shaftless pump 17 and the first heat sink 19 for conditioning the working fluid in the closed loop.
The first novel shaftless pump 17 and the second novel shaftless pump 18 drive working media to circularly flow in the fluid pipeline 21, the working media continuously flow to the second heat sink 20 through the first heat sink 19 and take away heat absorbed by the first heat sink 19, and the second heat sink 20 discharges the heat transferred by the working media through radiation, so that the purpose of controlling the heat is achieved.
Preferably, the first heat sink 19 is a cold plate, and the cold plate absorbs heat of a heat-generating workpiece and transfers the heat to the second heat sink 20 along with the liquid working medium in the fluid pipeline 21.
Preferably, the second heat sink 20 is a radiator, and dissipates heat transferred by the working medium through radiation heat.
Preferably, the liquid accumulator 16 is a rubber bag type liquid accumulator, and compensates or inhibits the working medium according to the pressure condition of the pipeline, so as to ensure the normal operation of the closed loop.
The existing fluid loop generally adopts a mode of respectively arranging one-way valves on two pipelines to enable two or more pumps to be parallel and to be mutually backed up, so that the cost of the pipeline is increased and the space is occupied. The novel shaftless pump used in the invention comprises the first novel shaftless pump 17 and the second novel shaftless pump 18, and the novel shaftless pump has the design characteristic of integrating an axial flow channel, a pump and a pipeline, can be used in series in a fluid loop, does not influence on-way resistance, and can also increase the hydraulic performance. In addition, when the novel shaftless pumps are used in series, as shown in fig. 1, the first novel shaftless pump 17 and the second novel shaftless pump 18 are connected in series and are backup to each other, so that even if one of the pumps goes wrong, the normal circulation of the working medium can be ensured, and the reliability of the whole fluid loop device is improved.
Thus, the novel shaftless pump can be flexibly connected in series in a fluid circuit, and the connection between the heat absorbing component, such as the first heat sink 19, and the heat radiating component, such as the second heat sink 20, has no specific front-back sequence relation; the number of the novel shaftless pumps can be increased or reduced according to actual needs, so that the heat transfer capacity of the fluid circuit can be increased or reduced.
The novel shaftless pump comprises a first novel shaftless pump 17 and a second novel shaftless pump 18, and adopts an integral sleeve type design, and the main structure comprises a stator end cover 2, a first bearing 3, a limiting workpiece 4, a rotor 5, a fixed pipeline 6, a sealing ring 7, an end cover 8, a blade 9, a rotating part 10, a second bearing 11 and a stator 12.
As shown in fig. 2, the stator 12 is a small brushless motor stator structure, and its external dimension is not more than 10cm by 10 cm. The stator end cover 2 is bolted at two ends of the stator 12, the fixed pipeline 6 penetrates through the stator end cover 2 and the stator 12, the end cover 8 is in flange connection with the fixed pipeline 6, and a small annular groove for placing the sealing ring 7 is formed in the inner side of the end cover 8, so that working medium leakage at the flange connection position is prevented. One end of the fixed pipeline 6 is a closed end, and the other end of the fixed pipeline is closed through the end cover 8, so that the workpiece can be conveniently installed from one side.
In order to facilitate connection with a pipeline selected by a spacecraft fluid loop, the pipe inner diameter of the closed end of the fixed pipeline 6 and the pipe inner diameter of the outlet end of the end cover 8 are within 15 mm.
Further, a base 13 is fixed on the outer side of the stator 12 and used for fixing the pump body in a spacecraft structure.
As shown in fig. 3, the first bearing 3, the limiting workpiece 4, the rotor 5, the vane 9, the rotating component 10, and the second bearing 11 are all located inside the tube body of the fixed pipe 6, and working medium flows through the inside of the tube body of the fixed pipe 6, so that heat can be effectively taken away, and the first bearing 3 and the second rotating shaft 11 are lubricated.
Because the types of the working media selected by the thermal control fluid loop of the spacecraft are complex, the required materials have the characteristics of high strength and corrosion resistance. Therefore, the fixed pipeline 6 is made of stainless steel or Hastelloy, the thickness of the pipe wall is not more than 1mm, and the eddy effect generated by the fixed pipeline can be reduced to the greatest extent.
As shown in fig. 4 and 5, the rotor 5 is embedded with magnetic shoes on the outer side, the inner special bayonet is assembled with the first boss 14 of the rotating member 10 in a matching manner, and the second boss 15 of the rotating member 10 is higher than the inner special bayonet of the rotor 5 and the first boss 14 of the rotating member 10, so that the rotor 5 and the rotating member 10 are prevented from moving relative to each other in the radial direction.
As shown in fig. 3, the first bearing 3 and the second bearing 11 are respectively in contact with both ends of the rotary member 10, so that the rotary member 10 can rotate along the axis of the fixed pipe 6; the first bearing 3 is in interference fit with the closed end of the fixed pipeline 6; an annular boss is arranged in the end cover 8, and the second bearing 11 is in interference fit with the annular boss of the end cover 8; the limiting workpiece 4 is arranged between the first bearing 3 and the rotor 5, and limits the radial movement of the first bearing 3 and the rotor 5, and the inner side of the limiting workpiece 4 is provided with a special bayonet design and is connected with the first boss 14 of the rotating component 10, so that the relative rotation movement of the limiting workpiece 4 and the rotating component 10 is prevented, and the radial movement of the rotating component 10 is limited; the second bearing 11 is a stepped shaft, and is connected to the second boss 15 of the rotating member 10 and the end cap 8.
As shown in fig. 4 and 5, the blade 9 is composed of a plurality of individual blades, connected without a central shaft, assembled at a fixed angle and position inside the rotating part 10. The design dimensions of the blades 9 are in the millimeter range. After the internal winding of the stator 12 is electrified, a rotating magnetic field is generated to drive the rotor 5 to rotate along the axis of the fixed pipeline 6, and meanwhile, the rotating part 10 and the blades 9 are driven to rotate, so that the working medium is driven to flow along the fixed pipeline 6. The rotational magnetic field strength of the stator 12 is controlled by an adjustment controller, and the rotational speed of the rotor 5, the rotating member 10, and the blades 9 is controlled, whereby the flow rate of the working medium can be controlled.
By adopting the technical scheme disclosed by the invention, the following beneficial effects are obtained:
1. the invention can be applied to the heat transfer of the small satellite spacecraft and the isothermal design of the spacecraft partial area;
2. the novel shaftless pump which can be used in series in an area mode is adopted to drive working media to flow, the novel shaftless pump adopts an integrated design of a pump and a pipeline, and the integrated design of a motor and the pump is adopted, so that the structure is more compact, the design volume is further reduced, the risk of leakage of the whole pipeline is further reduced, and the novel shaftless pump has the characteristics of quick integration and high adaptability;
3. the novel shaftless pump solves the problems of vibration, bent pipe design and on-way resistance caused by bent pipes in the conventional pump, and improves the adaptability and vibration resistance of the whole device;
4. the flow rate of the working medium in the fluid loop can be controlled by controlling the rotating speed of the novel shaftless pump at different positions, so that the control of heat transfer is realized. Meanwhile, the heat transfer capacity of the fluid circuit can be increased or decreased by increasing or decreasing the working number of the shaftless pumps aiming at the transfer of different heat.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements should also be considered within the scope of the present invention.
Claims (10)
1. A spacecraft thermal control single-phase fluid loop device based on a novel shaftless pump is characterized by comprising a liquid storage device, the novel shaftless pump, a first heat sink, a second heat sink and a fluid pipeline; the novel shaftless pump, the first heat sink and the second heat sink are connected into a closed loop through the fluid pipeline, and the novel shaftless pump, the first heat sink and the second heat sink are not connected in sequence; the liquid storage device is connected to the fluid pipeline and used for adjusting the working medium in the closed loop.
2. The new shaftless pump-based spacecraft thermal control single-phase fluid circuit apparatus of claim 1, wherein the number of the new shaftless pumps is more than one and is connected in series in the closed loop.
3. The new shaftless pump-based spacecraft thermal control single-phase fluid circuit apparatus of claim 2, wherein the new shaftless pump comprises a first new shaftless pump and a second new shaftless pump, and the first new shaftless pump, the first heat sink, the second new shaftless pump and the second heat sink are sequentially connected into a closed loop through the fluid pipeline; the reservoir is connected to the fluid line between the first new shaftless pump and the first heat sink.
4. The novel shaftless pump-based spacecraft thermal control single-phase fluid loop device as claimed in claim 1, wherein said first heat sink is a cold plate for absorbing heat of a heat generating workpiece and transferring the heat to said working medium.
5. The novel shaftless pump-based spacecraft thermal control single-phase fluid loop apparatus of claim 1, wherein the second heat sink is a radiator for dissipating heat transferred by the working medium through radiant heat.
6. The new shaftless pump-based spacecraft thermal control single-phase fluid circuit apparatus of claim 1, wherein the reservoir is a rubber bladder reservoir.
7. The new shaftless pump-based spacecraft thermal control single-phase fluid circuit device according to claim 1, wherein the new shaftless pump is of an integral sleeve type design and comprises a stator end cover, a first bearing, a limiting workpiece, a rotor, a fixed pipeline, an end cover, a blade, a rotating component, a second bearing and a stator; the two ends of the stator are bolted with the stator end covers, the fixed pipeline penetrates through the stator end covers and the stator, and the end covers are connected with the fixed pipeline through flanges; the first bearing, the limiting workpiece, the rotor, the blade, the rotating part and the second bearing are all positioned inside the pipe body of the fixed pipeline; the outer side of the rotor is embedded with a magnetic shoe, an inner special bayonet is matched and assembled with the first boss of the rotating part, and the second boss of the rotating part is higher than the inner special bayonet of the rotor and the first boss of the rotating part, so that the rotor and the rotating part are prevented from moving relatively in the radial direction; the first bearing and the second bearing are respectively connected with two ends of the rotating component, so that the rotating component can rotate along the axis of the fixed pipeline; the first bearing is in interference fit with the closed end of the fixed pipeline; an annular boss is arranged in the end cover, and the second bearing is in interference fit with the annular boss of the end cover; the limiting workpiece is arranged between the first bearing and the rotor and limits the first bearing and the rotor to move radially, and the inner side of the limiting workpiece is provided with a special bayonet design and is connected with the first boss of the rotating component, so that the limiting workpiece and the rotating component are prevented from relative rotation movement, and the radial movement of the rotating component is limited; the second bearing is a stepped shaft and is connected with the second boss of the rotating component and the end cover; the vanes are assembled inside the rotating member at a fixed angle and position.
8. A novel shaftless pump-based spacecraft thermal control single-phase fluid circuit apparatus according to claim 7, wherein the pipe inner diameter dimension of the terminating end of said fixed pipe and the outlet end of said end cap in said novel shaftless pump is not more than 15 mm.
9. The new shaftless pump-based spacecraft thermal control single-phase fluid circuit device according to claim 7, wherein the stator in the new shaftless pump is of a small brushless motor stator structure, and the external dimension of the stator does not exceed 10cm by 10 cm.
10. The new shaftless pump-based spacecraft thermal control single-phase fluid circuit apparatus of claim 7, wherein the new shaftless pump has a small annular groove inside the cap end, in which a sealing ring is placed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111012667.XA CN113686184B (en) | 2021-08-31 | 2021-08-31 | Spacecraft thermal control single-phase fluid loop device based on shaftless pump |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111012667.XA CN113686184B (en) | 2021-08-31 | 2021-08-31 | Spacecraft thermal control single-phase fluid loop device based on shaftless pump |
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| Publication Number | Publication Date |
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| CN113686184A true CN113686184A (en) | 2021-11-23 |
| CN113686184B CN113686184B (en) | 2023-11-24 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN1489020A (en) * | 2002-10-10 | 2004-04-14 | 中国科学院理化技术研究所 | Radiating device of chip radiation using low-melting-point metal or its alloy as flow working medium |
| CN101004175A (en) * | 2007-01-19 | 2007-07-25 | 清华大学 | Double suction microminiature type vane pump with no spindle drive |
| CN101581307A (en) * | 2009-05-20 | 2009-11-18 | 清华大学 | Hydrodynamic float vane type microminiature pump |
| CN106542124A (en) * | 2016-11-23 | 2017-03-29 | 上海宇航系统工程研究所 | A kind of spacecraft Fluid for Single-phase Fluid Loop System heat transfer unit (HTU) driven based on axial-flow pump |
| CN110500287A (en) * | 2019-07-12 | 2019-11-26 | 西安交通大学 | A kind of shaftless pump based on brushless motor |
| CN111918535A (en) * | 2020-08-17 | 2020-11-10 | 中国科学院微小卫星创新研究院 | Spaceborne and ground single-phase fluid loop heat dissipation system |
| CN112855561A (en) * | 2019-11-27 | 2021-05-28 | 北汽福田汽车股份有限公司 | Through-flow pump, vehicle thermal management system and vehicle |
-
2021
- 2021-08-31 CN CN202111012667.XA patent/CN113686184B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1489020A (en) * | 2002-10-10 | 2004-04-14 | 中国科学院理化技术研究所 | Radiating device of chip radiation using low-melting-point metal or its alloy as flow working medium |
| CN101004175A (en) * | 2007-01-19 | 2007-07-25 | 清华大学 | Double suction microminiature type vane pump with no spindle drive |
| CN101581307A (en) * | 2009-05-20 | 2009-11-18 | 清华大学 | Hydrodynamic float vane type microminiature pump |
| CN106542124A (en) * | 2016-11-23 | 2017-03-29 | 上海宇航系统工程研究所 | A kind of spacecraft Fluid for Single-phase Fluid Loop System heat transfer unit (HTU) driven based on axial-flow pump |
| CN110500287A (en) * | 2019-07-12 | 2019-11-26 | 西安交通大学 | A kind of shaftless pump based on brushless motor |
| CN112855561A (en) * | 2019-11-27 | 2021-05-28 | 北汽福田汽车股份有限公司 | Through-flow pump, vehicle thermal management system and vehicle |
| CN111918535A (en) * | 2020-08-17 | 2020-11-10 | 中国科学院微小卫星创新研究院 | Spaceborne and ground single-phase fluid loop heat dissipation system |
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| CN113686184B (en) | 2023-11-24 |
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