CN113686184B - Spacecraft thermal control single-phase fluid loop device based on shaftless pump - Google Patents
Spacecraft thermal control single-phase fluid loop device based on shaftless pump Download PDFInfo
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- CN113686184B CN113686184B CN202111012667.XA CN202111012667A CN113686184B CN 113686184 B CN113686184 B CN 113686184B CN 202111012667 A CN202111012667 A CN 202111012667A CN 113686184 B CN113686184 B CN 113686184B
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- 239000012530 fluid Substances 0.000 title claims abstract description 55
- 238000013461 design Methods 0.000 claims abstract description 22
- 239000007788 liquid Substances 0.000 claims abstract description 6
- 238000012546 transfer Methods 0.000 abstract description 14
- 238000007789 sealing Methods 0.000 abstract description 5
- 230000010354 integration Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 3
- 230000001276 controlling effect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000003247 decreasing effect 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
- 239000011810 insulating material Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000001105 regulatory effect Effects 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
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
-
- 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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- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
- Environmental & Geological Engineering (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Sustainable Development (AREA)
- Thermal Sciences (AREA)
- Environmental Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a spacecraft thermal control single-phase fluid circuit device based on a shaftless pump, which comprises a liquid storage device, the shaftless pump, a first heat sink, a second heat sink and a fluid pipeline. The invention abandons the traditional driving pump and adopts a shaftless pump which can be used in series in areas to drive working medium to flow. The shaftless pump adopts the integrated design of the pump and the pipeline, and the motor and the pump are integrated, so that the structure is more compact. The invention solves the sealing problem of the pump in the pipeline of the fluid circuit, reduces the on-way resistance of the circuit, and has the characteristics of rapid integration and high adaptability. The method can be applied to heat transfer of the small satellite spacecraft and isothermal design of partial areas of the spacecraft.
Description
Technical Field
The invention relates to the field of fluid loop devices, in particular to a shaftless pump-based spacecraft thermal control single-phase fluid loop device.
Background
Spacecraft are required to have a certain thermal control means facing complex thermal environments, and the thermal control means comprise active thermal control technology and passive thermal control technology. As the complexity of space tasks increases, passive thermal management means, such as loop heat pipes, insulating materials, often fail to meet the requirements for zone isothermicity or more heat transfer. Meanwhile, for some satellite thermal control systems with higher precision requirements, the thermal control system needs to be adjustable for the heat transfer process. Active thermal control techniques are therefore particularly important. In recent years, as an important technical means for active thermal control of a spacecraft, a pump driving fluid loop thermal control technology has been widely applied to various space tasks and scientific experiments by researchers. The heat in the heat radiator is collected and transmitted to the radiator by utilizing the flowing and heat transfer characteristics of working media, so that the thermal management of the spacecraft is realized. However, according to the index requirements of different satellite fluid circuits, corresponding type selection designs need to be carried out on the driving pump and the fluid circuits, so that the research cost and the task complexity are increased. Conventional pump designs also suffer from leakage and increased resistance along the tubing.
Disclosure of Invention
The invention aims to provide a spacecraft thermal control single-phase fluid circuit device based on a shaftless pump, so that the problems in the prior art are solved.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
a spacecraft thermal control single-phase fluid circuit device based on a shaftless pump comprises a liquid reservoir, the shaftless pump, a first heat sink, a second heat sink and a fluid pipeline; the shaftless pump, the first heat sink and the second heat sink are connected into a closed loop through the fluid pipeline, and the connection sequence of the shaftless pump, the first heat sink and the second heat sink is not sequential; the liquid storage device is connected to the fluid pipeline and used for adjusting working media in the closed loop.
Further, the number of shaftless pumps is more than one and is connected in series in the closed loop.
Further, the shaftless pump comprises a first shaftless pump and a second shaftless pump, wherein the first shaftless pump, the first heat sink, the second 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 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 radiating heat transferred by the working medium through radiant heat.
Further, the reservoir is a rubber bag type reservoir.
Further, the 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 blades, the rotating component and the second bearing are all positioned inside the pipe body of the fixed pipeline; the magnetic shoe is embedded on the outer side of the rotor, the inner side special bayonet is assembled with the first boss of the rotating part in a matched mode, and the second boss of the rotating part is higher than the inner side 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 radially and relatively; the first bearing and the second bearing are respectively connected with two ends of the rotating part, so that the rotating part can rotate along the axis of the fixed pipeline; the first bearing is in interference fit with the closing end of the fixed pipeline; an annular boss is measured 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, the first bearing and the rotor are limited to move radially, a special bayonet design is arranged on the inner side of the limiting workpiece and is connected with the first boss of the rotating part, the limiting workpiece and the rotating part are prevented from moving relatively, and meanwhile, the radial movement of the rotating part is limited; the second bearing is a stepped shaft and is connected with the second boss of the rotating part and the end cover; the blades are assembled inside the rotating member at a fixed angle and position.
Further, the inside diameter of the tube at the closing end of the fixed tube and the outlet end of the end cap in the shaftless pump is not more than 15mm.
Further, in the shaftless pump, the stator adopts a small brushless motor stator structure, and the external dimension of the stator is not more than 10cm by 10cm.
Further, in the shaftless pump, an annular small groove is formed in the inner side of the end cover, and a sealing ring is placed in the annular small groove.
The beneficial effects of the invention are as follows:
1. the invention can be applied to heat transfer of a small satellite spacecraft and isothermal design of partial areas of the spacecraft;
2. the shaftless pump which can be used in series in the area is adopted to drive the working medium to flow, the shaftless pump adopts the integrated design of the pump and the pipeline, the integrated design of the motor and the pump is more compact in structure, the design volume is further reduced, the risk of leakage of the whole pipeline is further reduced, and the shaftless pump has the characteristics of rapid integration and high adaptability;
3. the shaftless pump solves the vibration problem caused by the traditional pump, the bent pipe design problem and the on-way resistance problem caused by the bent pipe, and improves the adaptability and vibration resistance of the whole device;
4. the flow rate of working medium in the fluid loop can be controlled by controlling the rotation speeds of shaftless pumps at different positions, so that the control of heat transfer is realized. At the same time, the heat transfer capacity of the fluid circuit can be increased or reduced by increasing or reducing the working quantity of the shaftless pump according to different heat transfer.
Drawings
FIG. 1 is a schematic illustration of an exemplary circuit of a shaftless pump-based spacecraft thermal control single-phase fluid circuit apparatus of the present invention;
FIG. 2 is a schematic diagram of the overall structure of a shaftless pump of the spacecraft thermal control single-phase fluid circuit device based on the shaftless pump of the present invention;
FIG. 3 is an axial cross-sectional view of a shaftless pump of the present invention of a spacecraft thermal control single-phase fluid circuit device based on shaftless pumps;
FIG. 4 is a radial schematic of a shaftless pump of the present invention of a spacecraft thermal control single phase fluid circuit device based on shaftless pumps;
FIG. 5 is a schematic illustration of the internal vanes and rotating parts of a shaftless pump of a spacecraft thermal control single phase fluid circuit device based on shaftless pumps of the present invention;
wherein, 1-bolt; 2-stator end caps; 3-a first bearing; 4-limiting the workpiece; 5-rotor; 6-fixing the pipeline; 7-a sealing ring; 8-end caps; 9-leaf blades; 10-rotating a component; 11-a second bearing; 12-stator; 13-a base; 14-rotating member first boss; 15-rotating member second boss; 16-a reservoir; 17-a first shaftless pump; 18-a second shaftless pump; 19-a first heat sink; 20-a second heat sink; 21-fluid line.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the detailed description is presented by way of example only and is not intended to limit the invention.
FIG. 1 illustrates a schematic circuit diagram of an exemplary shaftless pump-based spacecraft thermal control single-phase fluid circuit device of the present invention. The circuit arrangement comprises a reservoir 16, a first shaftless pump 17, a second shaftless pump 18, a first heat sink 19, a second heat sink 20 and a fluid line 21; the first shaftless pump 17, the first heat sink 19, the second shaftless pump 18 and the second heat sink 20 are connected in series in a closed loop through the fluid line 21; the reservoir 16 is connected to the fluid line 21 between the first shaftless pump 17 and the first heat sink 19 for regulating the working medium in the closed loop.
The first shaftless pump 17 and the second shaftless pump 18 drive the working medium to circulate in the fluid pipeline 21, the working medium passes through the first heat sink 19 and takes away the heat absorbed by the first heat sink 19, the working medium continues to flow to the second heat sink 20, and the second heat sink 20 discharges the heat transferred by the working medium through radiation, so as to achieve the purpose of controlling the heat.
Preferably, the first heat sink 19 is a cold plate, and the cold plate absorbs heat of the 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 radiant heat.
Preferably, the reservoir 16 is a rubber bag type reservoir, 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 circuit generally adopts a mode of arranging one-way valves on two pipelines respectively to parallel two or more pumps so that the two or more pumps are mutually backed up, and the cost of the pipelines and the space occupation are increased. The shaftless pump used in the invention comprises the first shaftless pump 17 and the second shaftless pump 18, and the shaftless pump has the design characteristics of integrating an axial flow passage, a pump and a pipeline, can be used in series in a fluid circuit, does not influence on-way resistance, and can also increase the hydraulic performance. In addition, when shaftless pumps are used in series, as in fig. 1, the first shaftless pump 17 and the second shaftless pump 18 are connected in series and are back-up to each other, and even if one of them is problematic, normal circulation of working fluid can be ensured, and reliability of the overall fluid circuit device is increased.
Whereby the shaftless pump can be flexibly connected in series in a fluid circuit, with no specific tandem relationship with the connection of a heat absorbing component, such as the first heat sink 19, and a heat dissipating component, such as the second heat sink 20; the number of the shaftless pumps can be increased or decreased according to actual needs, so that the heat transfer capacity of the fluid circuit is enhanced or reduced.
The shaftless pump comprises the first shaftless pump 17 and the second shaftless pump 18, adopts an integral sleeve type design, and mainly 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 outer dimension is no more than 10cm by 10cm. The two ends of the stator 12 are bolted with the stator end cover 2, the fixed pipeline 6 passes through the stator end cover 2 and the stator 12, the end cover 8 is in flange connection with the fixed pipeline 6, and an annular small 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 closing end, and the other end is closed through the end cover 8, so that a workpiece is conveniently installed from one side.
For convenience of connection with selected pipelines of the fluid circuit of the spacecraft, the inner diameter of the fixed pipeline 6 and the outlet end of the end cover 8 is 15mm.
Further, a base 13 is fixed on the outer side of the stator 12, and is used for fixing the pump body in the 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 pipe body of the fixed pipe 6, and the working medium flows through the inside of the pipe body of the fixed pipe 6, so that heat can be effectively taken away, and simultaneously, the first bearing 3 and the second rotating shaft 11 are lubricated.
Because the selected working medium of the spacecraft thermal control fluid circuit is complex in type, the required material needs to 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 current effect generated by the fixed pipeline can be reduced to the greatest extent.
As shown in fig. 4 and 5, the magnetic shoe is embedded on the outer side of the rotor 5, the inner side special bayonet is assembled in cooperation with the first boss 14 of the rotating component 10, and the second boss 15 of the rotating component 10 is higher than the inner side special bayonet of the rotor 5 and the first boss 14 of the rotating component 10, so as to prevent the rotor 5 and the rotating component 10 from moving radially relative to each other.
As shown in fig. 3, the first bearing 3 and the second bearing 11 are respectively connected with two ends of the rotating component 10, so that the rotating component 10 can rotate along the axis of the fixed pipeline 6; the first bearing 3 is in interference fit with the closing end of the fixed pipeline 6; an annular boss is measured 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, so that the radial movement of the first bearing 3 and the rotor 5 is limited, a special bayonet design is arranged on the inner side of the limiting workpiece 4 and is connected with the first boss 14 of the rotating component 10, the limiting workpiece 4 and the rotating component 10 are prevented from relatively rotating, 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 rotary 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, without a central shaft connection, assembled inside the rotary member 10 at a fixed angle and position. The design dimensions of the blade 9 are in the millimeter range. The internal winding of the stator 12 generates a rotating magnetic field after being electrified, so as to drive the rotor 5 to rotate along the axis of the fixed pipeline 6, and simultaneously drive the rotating component 10 and the blades 9 to rotate, thereby driving the working medium to flow along the fixed pipeline 6. The rotational magnetic field intensity of the stator 12 is controlled by the adjusting controller, so that the rotational speeds of the rotor 5, the rotating member 10 and the blades 9 are controlled, and 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 heat transfer of a small satellite spacecraft and isothermal design of partial areas of the spacecraft;
2. the shaftless pump which can be used in series in the area is adopted to drive the working medium to flow, the shaftless pump adopts the integrated design of the pump and the pipeline, the integrated design of the motor and the pump is more compact in structure, the design volume is further reduced, the risk of leakage of the whole pipeline is further reduced, and the shaftless pump has the characteristics of rapid integration and high adaptability;
3. the shaftless pump solves the vibration problem caused by the traditional pump, the bent pipe design problem and the on-way resistance problem caused by the bent pipe, and improves the adaptability and vibration resistance of the whole device;
4. the flow rate of working medium in the fluid loop can be controlled by controlling the rotation speeds of shaftless pumps at different positions, so that the control of heat transfer is realized. At the same time, the heat transfer capacity of the fluid circuit can be increased or reduced by increasing or reducing the working quantity of the shaftless pump according to different heat transfer.
The foregoing is merely a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention, which is also intended to be covered by the present invention.
Claims (9)
1. The spacecraft thermal control single-phase fluid circuit device based on the shaftless pump is characterized by comprising a liquid reservoir, the shaftless pump, a first heat sink, a second heat sink and a fluid pipeline; the shaftless pump, the first heat sink and the second heat sink are connected into a closed loop through the fluid pipeline, and the connection sequence of the shaftless pump, the first heat sink and the second heat sink is not sequential; the liquid storage device is connected to the fluid pipeline and is used for adjusting working media in the closed loop;
the 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 blades, the rotating component and the second bearing are all positioned inside the pipe body of the fixed pipeline; the magnetic shoe is embedded on the outer side of the rotor, the inner side special bayonet is assembled with the first boss of the rotating part in a matched mode, and the second boss of the rotating part is higher than the inner side 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 radially and relatively; the first bearing and the second bearing are respectively connected with two ends of the rotating part, so that the rotating part can rotate along the axis of the fixed pipeline; the first bearing is in interference fit with the closing end of the fixed pipeline; an annular boss is arranged on the inner side of 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, the first bearing and the rotor are limited to move radially, a special bayonet design is arranged on the inner side of the limiting workpiece and is connected with the first boss of the rotating part, the limiting workpiece and the rotating part are prevented from moving relatively, and meanwhile, the radial movement of the rotating part is limited; the second bearing is a stepped shaft and is connected with the second boss of the rotating part and the end cover; the blades are assembled inside the rotating member at a fixed angle and position.
2. The shaftless pump-based spacecraft thermal control single phase fluid circuit device of claim 1, wherein said shaftless pumps are more than one in number and are connected in series in said closed loop.
3. The shaftless pump-based spacecraft thermal control single-phase fluid circuit device of claim 2, wherein said shaftless pump comprises a first shaftless pump and a second shaftless pump, said first heat sink, said second shaftless pump, and said second heat sink being sequentially connected in a closed loop through said fluid conduit; the reservoir is connected to the fluid line between the first shaftless pump and the first heat sink.
4. The shaftless pump-based spacecraft thermal control single-phase fluid circuit device of claim 1, wherein said first heat sink is a cold plate for absorbing heat from a heat generating workpiece and transferring the heat to said working medium.
5. The shaftless pump-based spacecraft thermal control single-phase fluid circuit device of claim 1, wherein the second heat sink is a radiator for dissipating heat transferred by the working medium through radiant heat.
6. The shaftless pump-based spacecraft thermal control single-phase fluid circuit device of claim 1, wherein said reservoir is a rubber bladder reservoir.
7. The shaftless pump-based spacecraft thermal control single phase fluid circuit device of claim 1, wherein the tube inside diameter dimension of the closed end of the fixed tube and the outlet end of the end cap in the shaftless pump is no more than 15mm.
8. The shaftless pump-based spacecraft thermal control single-phase fluid circuit device of claim 1, wherein said stator in said shaftless pump is a small brushless motor stator structure having an outer dimension of no more than 10cm x 10cm.
9. The shaftless pump-based spacecraft thermal control single-phase fluid circuit device of claim 1, wherein said shaftless pump has an annular small groove inside said end cap in which a seal 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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113686184A CN113686184A (en) | 2021-11-23 |
| CN113686184B true CN113686184B (en) | 2023-11-24 |
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| CN202111012667.XA Active 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 | 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 |
| 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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| CN113686184A (en) | 2021-11-23 |
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