CN106516171B - A kind of fluid loop system suitable for multi cabin spacecraft - Google Patents
A kind of fluid loop system suitable for multi cabin spacecraft Download PDFInfo
- Publication number
- CN106516171B CN106516171B CN201610875343.1A CN201610875343A CN106516171B CN 106516171 B CN106516171 B CN 106516171B CN 201610875343 A CN201610875343 A CN 201610875343A CN 106516171 B CN106516171 B CN 106516171B
- Authority
- CN
- China
- Prior art keywords
- disconnection device
- fluid path
- path disconnection
- fluid
- radiator
- 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.)
- Active
Links
Classifications
-
- 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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Quick-Acting Or Multi-Walled Pipe Joints (AREA)
Abstract
The invention discloses a kind of fluid loop systems suitable for multi cabin spacecraft, belong to multi cabin spacecraft technology field, including：Cold plate, fluid circuit, radiator, four fluid path disconnection device and separator；Two cold plates are separately mounted between below deck equipment and fascia panel the upper surface and the lower surface, and the looping pit of two cold plates passes through pipeline connection；Radiator is fixed on the outer surface of sealed compartment；Fluid path disconnection device I and fluid path disconnection device II are mounted at retro module and service module docking by separator；Fluid path disconnection device III and fluid path disconnection device IV are mounted at recovery capsule and retro module docking；One end of two-way fluid circuit is connect with the looping pit of cold plate respectively, after other end sequence passes through fluid path disconnection device III or fluid path disconnection device IV, fluid path disconnection device I or fluid path disconnection device II, is connect across the shell of service module, and with the tubular structure of radiator；The present invention, which can be laid out between cabin by fluid pipe road, connects design, the posture without influencing return capsule.
Description
Technical field
The invention belongs to multi cabin spacecraft technology fields, and in particular to a kind of fluid suitable for multi cabin spacecraft time
Road system.
Background technique
Retrievable satellite has become defending dedicated for the research of " Microgravity Science and space life science " Space Experiments
Star platform.With the increase of space science experiment demand, the quantity of the experiment loading device in retrievable satellite recovery capsule is also
More and more, average power consumption is also bigger than in the past, the living body class scientific experiment project especially carried out now, to the temperature of recovery capsule
It is required that also more stringent.Traditional recovery capsule heat dissipation has been unable to meet the demand of load.
For the demand for adapting to the big power consumption of recovery capsule load, applicating fluid circuit Active thermal control technology, i.e., inside recovery capsule
Heat consumption in cold plate collecting chamber is installed, by will be hot through recovery capsule, retro module, service module and the pump of sealed compartment, valve, pipe-line system
Amount is transmitted on the radiator on the outside of sealed compartment, and last radiator is gone out heat dissipation out of my cabin by radiation.Due to returning
Satellite needs to carry out before returning to separate between cabin twice, then the fluid loop system through four bay sections is needed to have the disconnecting of adaptation
Ability is to meet the requirement that bay section separates.
Fluid circuit pipeline is typically employed in single cabin structure at present, is seldom used in the case where connecting across bay section, even
You use, and also for the connection without in-orbit separation requirement between bay section, the connection between bay section is without considering in-orbit Dynamic Separation
State.And to realize the multi cabin connection of fluid circuit while need in-orbit separation, then it has the following problems：
1, fluid circuit pipeline will across bay section connection, then its piping connection, which has to have, to assemble or separate with bay section
The problems such as adaptable disconnection device, therefore the installation of disconnection device is considered when bay section is docked and is separated, connection, separation, from knot
Corresponding installation interface and operation port must be provided on structure, increase the responsible property of structure design；
2, when the separation of in-orbit bay section must be taken into consideration, how disconnection device realizes separation between pipeline cabin, and can not make after separating
Working medium in pipeline is leaked on space and other cabins, this just proposes higher requirement to the classification of disconnection device, traditional
Band separate mode cannot achieve；
3, disconnection device then has to extraneous needed for considering disconnection device itself separation make according to passive separate mode between cabin
Firmly, that is, the separating force for acting on disconnection device should be greater than the contact engaging and separating force of disconnection device itself, this just proposes bay section separation higher
Requirement, it is necessary to active force when increasing bay section separation drives disconnection device to separate with this, and the active force is larger, generally require
It pays biggish cost or faces technical problem.
In satellite high-speed cruising, when bay section separation force is larger, then the posture of satellite may be made to generate variation, solved
Method be that disconnection device separating force is made to can act on centroid of satellite, often relatively difficult to achieve from layout, conventional method is symmetrical
Distribution is disconnected,；Device is connect, contact engaging and separating force is variant when due to disconnection device separation, separates asynchronous etc. influence, leads to this method simultaneously
The influence to the attitude of satellite cannot be eliminated, can only be reduced as far as possible, restores the posture of variation using other means, when leading to design
Need to increase analysis and other safeguard means.In addition the installation when disconnection device on star cannot achieve when being arranged symmetrically, then to appearance
State influences more serious.
4, the gesture stability adjustment equipment of retrievable satellite is arranged in the instrument room of service module and sealed compartment composition, is defended
For star bay section after first separation, the return capsule that can not be formed to recovery capsule and retro module carries out pose adjustment, therefore how to reduce
Disconnection device separation influences the posture after cabin separation particularly important.
Summary of the invention
In view of this, being returned the object of the present invention is to provide a kind of fluid loop system suitable for multi cabin spacecraft
The formula of returning needs to carry out using release screw bolt to be laid out by fluid pipe road and cabin on the spacecraft of bay section separation twice
Between connect design, without influence return capsule posture.
The present invention is achieved through the following technical solutions：
A kind of fluid loop system suitable for multi cabin spacecraft, including：Cold plate, fluid circuit, radiator, four liquid
Road disconnection device and separator；
Its peripheral equipment is：The spacecraft shape knot formed is sequentially docked by recovery capsule, retro module, service module and sealed compartment
Structure and the fascia panel being mounted in recovery capsule；The upper and lower surface of fascia panel is mounted below deck equipment；
The coaxial looping pit of two circles or more is machined in the cold plate, and looping pits more than two circles communicates with each other；
The fluid path disconnection device has self-sealing function, and fluid path disconnection device both ends are respectively fixing end and separating end；Four
Fluid path disconnection device is respectively fluid path disconnection device I, fluid path disconnection device II, fluid path disconnection device III and fluid path disconnection device IV；
The radiator is equipped with the tubular structure of S-shaped distribution；
The separator is used to separate the fixing end and separating end of fluid path disconnection device；
Integrated connection relationship is as follows：Two cold plates be separately mounted to below deck equipment and fascia panel the upper surface and the lower surface it
Between, and the looping pit of two cold plates passes through pipeline connection；Radiator is fixed on the outer surface of sealed compartment；
Fluid path disconnection device I and fluid path disconnection device II are mounted at retro module and service module docking by separator；Its
In, separator is fixed on service module by separator mounting bracket, the fixation of fluid path disconnection device I and fluid path disconnection device II
End be fixedly connected respectively with the fixation bracket of separator, the separating end of fluid path disconnection device I and fluid path disconnection device II respectively with point
Separating support from device is fixedly connected；
Fluid path disconnection device III and fluid path disconnection device IV are mounted at recovery capsule and retro module docking, and III He of fluid path disconnection device
Fluid path disconnection device IV is located at the two sides of recovery capsule, and along the distribution substantially symmetrical about its central axis of recovery capsule；Wherein, fluid path disconnection device III and liquid
The fixing end of road disconnection device IV passes through fixing end mounting bracket respectively and is fixedly connected with recovery capsule, and fluid path disconnection device III and fluid path are disconnected
The separating end for connecing device IV passes through separating end mounting bracket respectively and is fixedly connected with retro module；
One end of two-way fluid circuit is connect with the looping pit of cold plate respectively, wherein the other end sequence of fluid circuit all the way
After fluid path disconnection device III, fluid path disconnection device I, across the shell of service module, and pass through the pipe of removable tap and radiator
The arrival end of shape structure connects；After the other end sequence of another way fluid circuit passes through fluid path disconnection device IV, fluid path disconnection device II,
It is connect across the shell of service module, and with the outlet end of the tubular structure of radiator；The looping pit of cold plate, two-way fluid circuit and
The tubular structure of radiator forms a closed fluid loop, is full of coolant liquid in fluid loop.
Further, the tubular structure of the connection of the looping pit of the fluid circuit and cold plate and fluid circuit and radiator
Connection pass through removable tap and be detachably connected to.
Further, separation of the separation of the fluid path disconnection device I and fluid path disconnection device II prior to retro module and service module.
Further, the fluid path disconnection device III and fluid path disconnection device IV carry out passive with the separation of recovery capsule and retro module
Separation.
Beneficial effect：(1) for the present invention by the method in first separation using actively separation, i.e. fluid path disconnection device separation is logical
Separator control is crossed, is separated prior to bay section；Secondary separation passes through the symmetrical cloth of fluid path disconnection device using the method passively separated
It sets, and is separated simultaneously with cabin；The layout of separate mode and entire pipeline can satisfy making for fluid circuit between used cabin
With requiring, separating between the cabin of fluid circuit not influences bay section separation, and on the celestial body posture after separation without influence.
(2) design structure that the present invention carries out separator in first separation meets stiffness and strength requirement, Dynamic Separation
When, active force can satisfy the maximum separation power of fluid path disconnection device；Disturbance in secondary separation to the max-Q reentered, most
Big overload and voyage influence to can be ignored less than 0.4%.
(3) arrangement that fluid path disconnection device of the invention carries out first separation is not necessarily to consider AXIALLY SYMMETRIC PROBLEMS, and can be arranged in needs
Any position wanted, and cloth is postponed and is separated prior to bay section, will not generate interference to the attitude of satellite；And two fluid path disconnection device installations
On same fixation (or separation) bracket of separator, it is convenient for the design of fixed (or separation) bracket, to guarantee fluid path
Size index request after disconnection device installation.
(4) separator of the present invention can effectively solve the problem that the excessive problem of fluid path disconnection device contact engaging and separating force, pass through separator
The active force of generation separates disconnection device.
(5) the fluid path disconnection device in present invention progress secondary separation and fluid circuit, can using the form being arranged symmetrically
Reduce to the influence after separation to return capsule posture；
(6) fluid path disconnection device of the invention selects the disconnection device of self-sealing, can guarantee in fluid circuit after isolation
Coolant liquid is not revealed, and celestial body will not be polluted.
(7) it the cold plate connection on fluid circuit and fascia panel of the invention and is all made of with the tubular structure of radiator removable
The type of attachment unloaded, to facilitate the operation of satellite assembly process.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention.
Fig. 2 is the scheme of installation of the fluid path disconnection device of first separation.
Fig. 3 is the scheme of installation of the fluid path disconnection device of secondary separation.
Fig. 4 is the connection schematic diagram of fluid circuit and cold plate.
Wherein, 1- recovery capsule, 2- retro module, 3- service module, 4- sealed compartment, 5- fascia panel, 6- cold plate, 7- fluid circuit,
8- radiator, the fixation bracket of 9- separator, the separating support of 10- separator, 11- separator, 12- separator peace
Fill bracket, 14- fixing end mounting bracket, 15- separating end mounting bracket, removable tap 16.
Specific embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
The present invention provides a kind of fluid loop systems suitable for multi cabin spacecraft, referring to attached drawing 1-4, including：It is cold
Plate 6, fluid circuit 7,8, four fluid path disconnection device of radiator, separator 11 and removable tap 16；
Its peripheral equipment is：Recovery capsule 1, retro module 2, service module 3, sealed compartment 4 and fascia panel 5；The recovery capsule 1, system
Dynamic cabin 2, service module 3 and sealed compartment 4 sequentially dock the contour structures for forming spacecraft；Fascia panel 5 is mounted in recovery capsule 1,
Upper and lower surface is mounted below deck equipment；
The coaxial looping pit of two circles or more is machined in the cold plate 6, and looping pits more than two circles communicates with each other；
The fluid path disconnection device selects the disconnection device with self-sealing function, to meet after bay section separates in fluid circuit 7
Coolant liquid do not reveal, while fluid path disconnection device can be docked and be separated with cabin；Fluid path disconnection device both ends are respectively solid
Fixed end and separating end；Four fluid path disconnection device are respectively fluid path disconnection device I, fluid path disconnection device II, fluid path disconnection device III and fluid path
Disconnection device IV；
The radiator 8 is equipped with the tubular structure of S-shaped distribution；
The separator 11 is used to separate the fixing end and separating end of fluid path disconnection device；
The removable tap 16 is bolt or buckle；
Integrated connection relationship is as follows：Two cold plates 6 be separately mounted to below deck equipment and 5 the upper surface and the lower surface of fascia panel it
Between, for collecting the heat of below deck equipment generation, and the looping pit of two cold plates 6 passes through pipeline connection；Radiator 8 is fixed on close
The outer surface of batten down 4；
Fluid path disconnection device I and fluid path disconnection device II are mounted on retro module 2 and service module 3 by the same separator 11
At docking；Wherein, separator 11 is fixed on service module 3 by separator mounting bracket 12, fluid path disconnection device I and fluid path
The fixing end of disconnection device II is fixedly connected with the fixation bracket 9 of separator respectively, fluid path disconnection device I and fluid path disconnection device II
Separating end is fixedly connected with the separating support of separator 10 respectively；
Fluid path disconnection device III and fluid path disconnection device IV are mounted at 2 docking of recovery capsule 1 and retro module, and fluid path disconnection device III
It is located at the two sides of recovery capsule 1 with fluid path disconnection device IV, and along the distribution substantially symmetrical about its central axis of recovery capsule 1；Wherein, fluid path disconnection device III
Pass through fixing end mounting bracket 14 respectively with the fixing end of fluid path disconnection device IV to be fixedly connected with recovery capsule 1, fluid path disconnection device III
Pass through separating end mounting bracket 15 respectively with the separating end of fluid path disconnection device IV to be fixedly connected with retro module 2；
One end of two-way fluid circuit 7 passes through removable tap 16 respectively and connect with the looping pit of cold plate 6, wherein flowing all the way
After the other end sequence of body pipeline 7 passes through fluid path disconnection device III, fluid path disconnection device I, across the shell of service module 3, and passing through can
Connector 16 is split to connect with the arrival end of the tubular structure of radiator 8；The other end sequence of another way fluid circuit 7 passes through fluid path
After disconnection device IV, fluid path disconnection device II, across the shell of service module 3, and pass through the tubulose knot of removable tap 16 and radiator 8
The outlet end of structure connects；The tubular structure of the looping pit of cold plate 6, two-way fluid circuit 7 and radiator 8 forms a closed liquid
Body circuit is full of coolant liquid in fluid loop, for by heat collection and transmitting；
When work, the cold plate 6 inside recovery capsule 1 collects the heat that below deck equipment generates, and by through recovery capsule 1, system
Dynamic cabin 2, service module 3 fluid circuit 7 in coolant liquid by heat transmission to the radiator 8 being located at outside sealed compartment 3, last spoke
Emitter 8 radiates heat dissipation out of my cabin by space；
When spacecraft carries out cabin separation：Firstly, the fixing end and separating end of fluid path disconnection device I and fluid path disconnection device II
It is separated by the active force that separator 11 generates, and is carried out after fluid path disconnection device I and the separation of fluid path disconnection device II
Self-sealing prevents the coolant liquid in fluid circuit 7 from flowing out；Therefore, fluid path disconnection device I and fluid path disconnection device II are actively to separate,
The separation of fluid path disconnection device I and fluid path disconnection device II can guarantee fluid path disconnection device I prior to the separation of retro module 2 and service module 3
Separation with fluid path disconnection device II, which will not separate bay section, to be had an impact；Then, in fluid path disconnection device I and fluid path disconnection device II
After separation, retro module 2 and service module 3 carry out first separation；Finally, recovery capsule 1 and retro module 2 carry out secondary separation, by returning
The fixing end and separating end that active force when receiving cabin 1 and the separation of retro module 2 makes fluid path disconnection device III and fluid path disconnection device IV are simultaneously
It separates, and carries out self-sealing after fluid path disconnection device III and the separation of fluid path disconnection device IV, prevent the cooling liquid stream in fluid circuit 7
Out；Therefore, fluid path disconnection device III and fluid path disconnection device IV are passive separation.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in of the invention
Within protection scope.
Claims (4)
1. a kind of fluid loop system suitable for multi cabin spacecraft, which is characterized in that including：Cold plate (6), fluid circuit
(7), radiator (8), four fluid path disconnection device and separator (11)；
Peripheral equipment is：The spacecraft formed is sequentially docked by recovery capsule (1), retro module (2), service module (3) and sealed compartment (4)
Contour structures and the fascia panel (5) being mounted in recovery capsule (1)；The upper and lower surface of fascia panel (5) is mounted below deck equipment；
The coaxial looping pit of two circles or more is machined in the cold plate (6), and looping pits more than two circles communicates with each other；
The fluid path disconnection device has self-sealing function, and fluid path disconnection device both ends are respectively fixing end and separating end；Four fluid path
Disconnection device is respectively fluid path disconnection device I, fluid path disconnection device II, fluid path disconnection device III and fluid path disconnection device IV；
The radiator (8) is equipped with the tubular structure of S-shaped distribution；
The separator (11) is used to separate the fixing end and separating end of fluid path disconnection device；
Integrated connection relationship is as follows：Two cold plates (6) be separately mounted to below deck equipment and fascia panel (5) the upper surface and the lower surface it
Between, and the looping pit of two cold plates (6) passes through pipeline connection；Radiator (8) is fixed on the outer surface of sealed compartment (4)；
Fluid path disconnection device I and fluid path disconnection device II are mounted on retro module (2) and service module (3) docking by separator (11)
Place；Wherein, separator (11) is fixed on service module (3) by separator mounting bracket (12), fluid path disconnection device I and liquid
The fixing end of road disconnection device II is fixedly connected with the fixation bracket (9) of separator respectively, fluid path disconnection device I and fluid path disconnection device
II separating end is fixedly connected with the separating support of separator (10) respectively；
Fluid path disconnection device III and fluid path disconnection device IV are mounted at recovery capsule (1) and retro module (2) docking, and fluid path disconnection device III
It is located at the two sides of recovery capsule (1) with fluid path disconnection device IV, and along the distribution substantially symmetrical about its central axis of recovery capsule (1)；Wherein, fluid path disconnecting
The fixing end of device III and fluid path disconnection device IV passes through fixing end mounting bracket (14) respectively and is fixedly connected with recovery capsule (1), fluid path
The separating end of disconnection device III and fluid path disconnection device IV passes through separating end mounting bracket (15) respectively and is fixedly connected with retro module (2)；
One end of two-way fluid circuit (7) is connect with the looping pit of cold plate (6) respectively, wherein fluid circuit (7) all the way is another
After end sequence passes through fluid path disconnection device III, fluid path disconnection device I, the shell of service module (3) is passed through, and pass through removable tap (16)
It is connect with the arrival end of the tubular structure of radiator (8)；The other end sequence of another way fluid circuit (7) passes through fluid path disconnection device
IV, after fluid path disconnection device II, the shell of service module (3) is passed through, and is connect with the outlet end of the tubular structure of radiator (8)；It is cold
The tubular structure of the looping pit of plate (6), two-way fluid circuit (7) and radiator (8) forms a closed fluid loop, liquid
Coolant liquid is full of in circuit.
2. a kind of fluid loop system suitable for multi cabin spacecraft as described in claim 1, which is characterized in that the stream
The connection of the connection of body pipeline (7) and the looping pit of cold plate (6) and fluid circuit (7) and the tubular structure of radiator (8) is logical
Removable tap (16) is crossed to be detachably connected to.
3. a kind of fluid loop system suitable for multi cabin spacecraft as described in claim 1, which is characterized in that the liquid
Separation of the separation of road disconnection device I and fluid path disconnection device II prior to retro module (2) and service module (3).
4. a kind of fluid loop system suitable for multi cabin spacecraft as described in claim 1, which is characterized in that the liquid
Road disconnection device III and fluid path disconnection device IV are passively separated with the separation of recovery capsule (1) and retro module (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610875343.1A CN106516171B (en) | 2016-09-30 | 2016-09-30 | A kind of fluid loop system suitable for multi cabin spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610875343.1A CN106516171B (en) | 2016-09-30 | 2016-09-30 | A kind of fluid loop system suitable for multi cabin spacecraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106516171A CN106516171A (en) | 2017-03-22 |
| CN106516171B true CN106516171B (en) | 2018-11-20 |
Family
ID=58333037
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610875343.1A Active CN106516171B (en) | 2016-09-30 | 2016-09-30 | A kind of fluid loop system suitable for multi cabin spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106516171B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639388A (en) * | 2018-03-28 | 2018-10-12 | 北京空间技术研制试验中心 | System for Manned Spacecraft Cabin environmental control system |
| CN110426252B (en) * | 2019-07-05 | 2021-09-24 | 北京空间飞行器总体设计部 | Visual microgravity gas trapping test device |
| CN111532457B (en) * | 2020-04-28 | 2021-08-17 | 中国科学院空间应用工程与技术中心 | Load adapter with liquid cooling runner |
| CN113091490A (en) * | 2021-02-26 | 2021-07-09 | 北京空间飞行器总体设计部 | Combined heat sink-based moon sampling return detector autonomous thermal management system |
| CN115352657B (en) * | 2022-08-08 | 2024-02-06 | 中国科学院空间应用工程与技术中心 | Multifunctional flow distribution device based on space load thermal control requirement |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2157391A4 (en) * | 2007-06-15 | 2011-07-27 | Asahi Kasei Fibers Corp | Loop heat pipe type heat transfer device |
| FR2942774B1 (en) * | 2009-03-06 | 2011-05-06 | Thales Sa | THERMAL CONTROL DEVICE FOR A SPACE ENGINE |
| CN106134371B (en) * | 2010-08-20 | 2014-08-06 | 上海空间推进研究所 | Realize the bi-directional locking arrangement of the floating member that two aircraft gas-liquids add in space |
| CN106134370B (en) * | 2010-08-20 | 2014-02-12 | 上海空间推进研究所 | Realize the floating installation of the unsteady disconnecting device that two aircraft gas-liquids add in space |
| CN105883011B (en) * | 2015-01-23 | 2018-06-12 | 北京空间飞行器总体设计部 | A kind of platform interface system of parallel operation Double tabletop spacecraft |
| CN205345361U (en) * | 2015-12-16 | 2016-06-29 | 北京空间技术研制试验中心 | It disconnects six split type supports to regulation of ware installation accuracy realization to make space float |
-
2016
- 2016-09-30 CN CN201610875343.1A patent/CN106516171B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106516171A (en) | 2017-03-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106516171B (en) | A kind of fluid loop system suitable for multi cabin spacecraft | |
| US10011362B2 (en) | Aircraft outer skin heat exchanger, aircraft cooling system and method for operating an aircraft outer skin heat exchanger | |
| CN101270930B (en) | Thermal control device on board a spacecraft | |
| US7272006B2 (en) | IC coolant microchannel assembly with integrated attachment hardware | |
| EP2400828B1 (en) | Multiple liquid loop cooling for electronics | |
| CA2782850C (en) | Aircraft supplemental liquid cooler and method | |
| CN101715656B (en) | Cooling system and method of use | |
| CN101027530A (en) | Liquid cooling system for multi-processor | |
| US20160198591A1 (en) | Passive aircraft cooling systems and methods | |
| CN115352657A (en) | Multifunctional flow distribution device based on space load thermal control demand | |
| CN102695404B (en) | Liquid cooling system and equipment cabinet of electronic equipment | |
| US9939203B2 (en) | Variable heat rejection using heat pipe heat exchanger | |
| CN106043709B (en) | A kind of multichannel liquid-cooling system temperature control equipment | |
| CN103373469B (en) | Method and the aircraft of aircraft thermal control system, operation thermal control system | |
| CN117341995B (en) | Spacecraft high-integration single-phase fluid loop driving device and thermal control driving device | |
| JP2001102835A (en) | Liquid cooling cooler | |
| WO2023142314A1 (en) | Distributed pumped two-phase cooling system for aircraft | |
| CN113091490A (en) | Combined heat sink-based moon sampling return detector autonomous thermal management system | |
| CN212566452U (en) | Impact-proof cascade cooling system of high-temperature fuel test bed | |
| CN205113728U (en) | For military use mechanical polycell liquid cooling heat abstractor | |
| CN113271747B (en) | Liquid cooling system of data center and data center | |
| WO2021129857A1 (en) | Cooling assembly, and charging and swapping station and energy storage station comprising same | |
| CN115384815A (en) | Coupling structure between fluid loop cabins of spacecraft | |
| CN114455106A (en) | Thermal control structure and satellite comprising same | |
| CN202863755U (en) | Fluid loop thermal control system based on stratospheric airship |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | 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 |