CN108482712A - Multi cabin spacecraft thermal load analysis method - Google Patents
Multi cabin spacecraft thermal load analysis method Download PDFInfo
- Publication number
- CN108482712A CN108482712A CN201810175647.6A CN201810175647A CN108482712A CN 108482712 A CN108482712 A CN 108482712A CN 201810175647 A CN201810175647 A CN 201810175647A CN 108482712 A CN108482712 A CN 108482712A
- Authority
- CN
- China
- Prior art keywords
- heat
- bay section
- cabin
- thermal component
- 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.)
- Granted
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
- B64G1/46—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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
- Environmental & Geological Engineering (AREA)
- Environmental Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The present invention relates to a kind of multi cabin spacecraft thermal load analysis methods, including：(a) Orbital heat flux situation of the analysis multi cabin spacecraft under various operating modes；(b) according to quantity of heat production and uncontrollable heat dissipation capacity inside each bay section in each mode, the controllable heat dissipation amount that each bay section generates under each pattern is counted；(c) it determines each bay section heat-sinking capability, controllable heat dissipation amount described in each bay section is allocated accordingly, each bay section thermal component is designed.The multi cabin spacecraft thermal load analysis method of the present invention, can effectively control the weight of heat management system, evade the risk that radiator freezes failure.
Description
Technical field
The present invention relates to spacecraft overall design technique field more particularly to a kind of multi cabin spacecraft thermal load analysis sides
Method.
Background technology
Using extensive multi cabin, scalability, more aerial missions as development trend, such as external the Peace is empty for space station at present
Between station, international space station be made of multiple bay sections, to complete extravehicular activity, earth observation, the tasks such as microgravity experiment, design
Multiple-working mode.
Space station heat management system is using air in control cabinet and device temperature as task, generally using radiator as heat dissipation
Component.Period, internal heat resource include mainly equipment heat production and energy resource system waste heat Q in orbit for space stations, occupant's metabolic heat production
Qr, external heat source is mainly the Orbital heat flux Q from the sun and the earthw.After space station reaches thermal balance, any of the above energy stream
Enter, including nacelle leaking heat Q equal to exterior space heat exhaust with space stationl, the outside radiations heat energy Q of radiatorf, that is, have as follows
Equilibrium relation：
Qs+Qr+Qw=Qf+Ql
The set of equipment heat production and energy resource system waste heat Qs, occupant's metabolic heat production Qr and Orbital heat flux Qw, characterizes space station
The offline mode of total thermic load and space station is corresponding inside and outside heat management system.Nacelle leaking heat QlWith the big compression ring in space station
The equilibrium temperature of border and structural device is related, and one of main task of space station heat management system is to adapt to different thermic loads, is led to
Overregulate the outside radiations heat energy Q of radiatorf, the equilibrium temperature of atmospheric environment and structural device is controlled within indication range.Cause
This, thermal load analysis is to design the important step of radiator and heat management system.
To adapt to various the case where being likely to occur, when conventional heat pipe manages system design, single bay section endogenous pyrogen and outer is considered
The maximum situation of hot-fluid difference, this method can guarantee that space station heat obtains dissipation, but its drawback is：
1. maximum situation is reflected respectively for endogenous pyrogen and Orbital heat flux, the case where being not necessarily necessary being, therefore press
When this condition is designed, total heat duties increase, and need the outside radiations heat energy Q of radiatorfIncrease.Due to QfAnd radiator surface
The biquadratic and radiator area of temperature are directly proportional, and there are upper limit value, conventional heat pipe reason design methods will make spoke for surface temperature
Emitter area is excessive.For the large-scale multi cabin spacecraft such as space station, weight indicator is to first have to solve the problems, such as, excessive spoke
Emitter area will cause weight exceeded.
2. heat management system adjusts the outside radiations heat energy Q of radiatorfWhen, the work of radiator is generally entered by valve regulated
Mass flow amount, to control the temperature of radiator surface.When thermic load is reduced, the working medium flow into radiator is reduced.By biography
System method design when, since artificial increases maximum heating load, cause into radiator maximum stream flow and normal work and
Flow difference when thermic load is relatively low is larger.When designing valve, to meet maximum stream flow requirement, normal work and thermic load are relatively low
When valve aperture it is smaller, the valve working region poor in performance is unfavorable for controlling.
3. since radiator area is fixed, radiator surface temperature design is upper limit value, thermic load drop when maximum heating load
Radiator surface temperature will be reduced by biquadratic rule when low.When traditionally designing, since artificial increases maximum heat
Load, radiator surface running temperature is too low when causing thermic load relatively low.Meanwhile radiator internal working medium running temperature is too low,
Working medium viscosity is caused to increase, running resistance increases, and the power consumption of circulating pump improves, or even will produce working medium and freeze, radiator failure
Risk.
Invention content
It is an object of the invention to solve above-mentioned technical problem, a kind of multi cabin spacecraft thermal load analysis method is provided,
Effectively control heat management system weight evades the risk that radiator freezes failure.
For achieving the above object, the present invention provides a kind of multi cabin spacecraft thermal load analysis method, including：
(a) Orbital heat flux situation of the analysis multi cabin spacecraft under various operating modes；
(b) according to quantity of heat production and uncontrollable heat dissipation capacity inside each bay section in each mode, each bay section production under each pattern is counted
Raw controllable heat dissipation amount；
(c) it determines each bay section heat-sinking capability, controllable heat dissipation amount described in each bay section is allocated accordingly, radiate to each bay section
Component is designed.
According to an aspect of the present invention, in step (a), too according to thermal component threedimensional model, thermal component surface
Positive absorptivity, thermal component surface infrared emittance, establish thermal component Orbital heat flux analysis model；
Each operating mode lower railway parameter of the multi cabin spacecraft and flight attitude are set；
Calculate each cabin thermal component surface average absorption Orbital heat flux surface density.
According to an aspect of the present invention, quantity of heat production includes below deck equipment heat production and energy resource system waste heat inside the bay section
With occupant's metabolic heat production, the uncontrollable heat dissipation capacity is nacelle leaking heat.
According to an aspect of the present invention, the controllable heat dissipation amount be the below deck equipment heat production and energy resource system waste heat,
The difference of the sum of described occupant's metabolic heat production and the nacelle leaking heat.
According to an aspect of the present invention, in step c,
According to Orbital heat flux situation of the spacecraft obtained in step a under various operating modes, each bay section radiating part is determined
The heat-sinking capability of part；
The controllable heat dissipation amount is allocated between each bay section；
According to the heat-sinking capability of the controllable heat dissipation amount and each bay section thermal component of the distribution of each bay section, each Working mould is determined
The area of thermal component needed for each bay section under formula；
Choose heat dissipation of the maximum value of each bay section thermal component area under different working modes as each bay section actual disposition
The area of component.
According to an aspect of the present invention, the heat-sinking capability of the thermal component is the outside spoke of thermal component on unit area
Penetrate the difference of heat and Orbital heat flux.
According to an aspect of the present invention, the thermal component is radiator.
The multi cabin spacecraft thermal load analysis method of the present invention, design method compared with the prior art, due to analysis
When be all made of actual thermic load situation, will not due to artificial origin increase need the outside radiations heat energy Q of radiatorf, therefore
The problem of artificially increasing radiator area would not occur, can significantly save material, and can effectively control thermistor(-ter)
The weight of reason system.On the other hand, due to according to each cabin radiator heat-sinking capability to controllable heat dissipation amount QkIt is allocated, it can be to each
The radiator area of cabin configuration optimizes, and also can effectively mitigate the weight of thermal control management system.
The multi cabin spacecraft thermal load analysis method of the present invention, design method compared with the prior art, due to each cabin
Maximum heating load be not increased, into radiator maximum stream flow and relatively low thermic load when the difference of flow be in normal model
It encloses, valve occurs the case where being unfavorable for control when thermic load will not be caused relatively low.
The multi cabin spacecraft thermal load analysis method of the present invention, design method compared with the prior art, due to control
And radiator area is optimized, radiator surface running temperature increases compared with traditional design method when thermic load is relatively low, no
The power consumption that will appear circulating pump improves the risk of even radiator failure.
Description of the drawings
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the present invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached drawings.
Fig. 1 is the flow chart for schematically showing multi cabin spacecraft thermal load analysis method according to the present invention；
Fig. 2 is the four cabin space station models schematically shown according to one embodiment of the present invention.
Specific implementation mode
The description of this specification embodiment should be combined with corresponding attached drawing, and attached drawing should be used as the one of complete specification
Part.In the accompanying drawings, the shape of embodiment or thickness can expand, and to simplify or facilitate mark.Furthermore it is respectively tied in attached drawing
The part of structure will be to describe to illustrate respectively, it is notable that the member for being not shown in figure or not illustrated by word
Part is the form known to a person of ordinary skill in the art in technical field.
The description of embodiments herein, any reference in relation to direction and orientation are merely for convenience of describing, and cannot manage
Solution is any restrictions to the scope of the present invention.It can be related to the combination of feature below for the explanation of preferred embodiment,
These features may be individually present or combine presence, and the present invention is not defined in preferred embodiment particularly.The present invention
Range be defined by the claims.
Fig. 1 is the flow chart for schematically showing multi cabin spacecraft thermal load analysis method according to the present invention.Such as Fig. 1 institutes
Show, multi cabin spacecraft thermal load analysis method according to the present invention includes the following steps：A. analysis multi cabin spacecraft is each
Orbital heat flux situation under kind operating mode；B. according to quantity of heat production and uncontrollable heat dissipation capacity inside each bay section in each mode, statistics
The controllable heat dissipation amount that each bay section generates under each pattern；C. each bay section heat-sinking capability is determined, accordingly to controllable heat dissipation described in each bay section
Amount is allocated, and is designed to each bay section thermal component.
The Orbital heat flux of the multi cabin spacecraft of the present invention is the Orbital heat flux Q from the sun and the earthw, bay section inside quantity of heat production
Including below deck equipment heat production and energy resource system waste heat QsWith occupant's metabolic heat production Qr, uncontrollable heat dissipation capacity is nacelle leaking heat Ql。
The multi cabin spacecraft thermal load analysis method of the present invention analyzes the large-scale multi cabin under different working modes first
The Orbital heat flux Q of spacecraftw, the specific method is as follows：According to thermal component threedimensional model, thermal component surface solar absorptance, dissipate
Thermal part surface infrared emittance establishes thermal component Orbital heat flux analysis model；Then each work of multi cabin spacecraft is set
Operation mode lower railway parameter and flight attitude；Finally calculate each cabin thermal component surface average absorption Orbital heat flux surface density.
Later by equipment heat production under different working modes and energy resource system waste heat Qs, occupant's metabolic heat production QrStatistics
And nacelle leaking heat QlStatistics, determine the controllable heat dissipation amount Q needed under large size multi cabin spacecraft different working modesk.It needs
The controllable heat dissipation amount Q wantedkFor below deck equipment heat production and energy resource system waste heat Qs, occupant's metabolic heat production QrThe sum of, with nacelle leaking heat
QlDifference.
Then according to Orbital heat flux Q under different working modeswAnalysis result determine each bay section thermal component of spacecraft dissipate
Thermal energy power, the present invention in thermal component be radiator, i.e., according to Orbital heat flux Q under different working modeswAnalysis result determine
The heat-sinking capability of each bay section radiator of spacecraft.The heat-sinking capability of each bay section radiator be on unit area radiator to external radiation
Heat QfWith Orbital heat flux QwDifference.
Later according to each bay section radiator heat-sinking capability under different working modes, it would be desirable to controllable heat dissipation amount QkIn each cabin
Pro rate as desired between section, and according to the controllable heat dissipation amount of each bay section distribution and each radiator heat-sinking capability, determine not
With the area for the radiator that each cabin needs under operating mode, the area of the radiator in each bay section is required controllable heat dissipation in bay section
The ratio of amount and heat loss through radiation ability.Due under different working modes, the controllable heat dissipation amount of each bay section proportional assignment
Difference, and the heat-sinking capability of radiator would also vary under different working modes, so in different operating modes
Under, the size of required radiator will be different, final to select in order to meet the heat dissipation requirement under all working pattern
Select the area of the maximum value of each bay section radiator area under different working modes as the radiator of corresponding bay section actual disposition.
The method of the present invention is described in detail by taking certain four cabin space station as an example below.
Fig. 2 is the four cabin space station models schematically shown according to one embodiment of the present invention.With reference to shown in Fig. 2,
In present embodiment, there are two types of operating modes, including normal mode of operation and earth observation operating mode for four cabin space stations tool.It is first
The Orbital heat flux situation of radiator surface average absorption under two kinds of operating modes is first determined by the way of Orbital heat flux analysis modeling, is had
Steps are as follows for body:
When analyzing the Orbital heat flux situation of multi cabin spacecraft, inhaled according to radiator threedimensional model, the radiator surface sun
Yield, radiator surface infrared emittance establish radiator Orbital heat flux analysis model；
Then orbit parameter and flight attitude under each operating mode of multi cabin spacecraft are set；
Finally each cabin radiator surface is calculated according to the parameter under the Orbital heat flux analysis model and each pattern of foundation averagely to inhale
Receive Orbital heat flux surface density.
The results are shown in Table 1:
Table 1 shows each cabin radiator surface average absorption Orbital heat flux surface density (unit：W/m2)：
| Cabin 1 | Cabin 2 | Cabin 3 | Cabin 4 | |
| Normal flight | 152.2 | 71.6 | 152.1 | 82.9 |
| Earth observation | 153.1 | 87.0 | 153.2 | 109.7 |
Table 1
Then step b is carried out, according to quantity of heat production and uncontrollable heat dissipation capacity inside each bay section in each mode, counts each pattern
Under the controllable heat dissipation amount that generates of each bay section.In the present embodiment, by analysis, each bay section leaking heat under specified temperature control index
QlIt is 1000W.Through statistics, internal quantity of heat production is as shown in table 2 under two kinds of operating modes, controllable heat dissipation amount under two kinds of operating modes
QkAs shown in table 3：
Endogenous pyrogen statistical form (unit in each cabin sealed compartment：W)
| Cabin 1 | Cabin 2 | Cabin 3 | Cabin 4 | |
| Normal flight | 11000 | 9000 | 11000 | 9000 |
| Earth observation | 9000 | 7000 | 9000 | 7000 |
Table 2
Each cabin generates controllable heat dissipation amount and amounts to controllable heat dissipation amount statistical form (unit：W)
| Cabin 1 | Cabin 2 | Cabin 3 | Cabin 4 | It amounts to | |
| Normal flight | 10000 | 8000 | 10000 | 8000 | 36000 |
| Earth observation | 8000 | 6000 | 8000 | 6000 | 28000 |
Table 3
Later in step c, according to each bay section Orbital heat flux Q under each patternwSituation analyzes each bay section heat-sinking capability, right accordingly
Each bay section controllable heat dissipation amount QkIt is allocated, each bay section thermal component is designed.Each cabin radiator heat-sinking capability is unit
The outside radiations heat energy Q of radiator on areafWith Orbital heat flux QwDifference design each cabin radiator to external empty in the present embodiment
Between unit area radiations heat energy maximum be no more than 300W/m2, each cabin radiator heat radiation energy under four two kinds of cabin space station operating modes
Power setting is as shown in table 4：
Each cabin radiator heat-sinking capability (unit：W/m2)
| Cabin 1 | Cabin 2 | Cabin 3 | Cabin 4 | |
| Normal flight | 147.8 | 228.4 | 147.9 | 217.1 |
| Earth observation | 146.9 | 213 | 146.8 | 190.3 |
Table 4
After the heat-sinking capability for setting each bay section radiator, finally it needs to be determined that the area of radiator needed for each bay section.
In the prior art, when heat management system radiator conceptual design, to adapt to all the case where being likely to occur, by heat production inside bay section
Maximum functional pattern and Orbital heat flux most adverse circumstances are measured as input condition, and such case is practical is not in.For this
Four cabin space stations described in embodiment, the design condition of the prior art are as shown in table 5：
| Project | Cabin 1 | Cabin 2 | Cabin 3 | Cabin 4 |
| Cabin endogenous pyrogen (the normal flight of consideration；W) | 11000 | 9000 | 11000 | 9000 |
| Orbital heat flux environment (the earth observation of consideration；W/m2) | 153.1 | 87.0 | 153.2 | 109.7 |
Table 5
The design method of the prior art considers the heat generated in each cabin dissipation self seal cabin, each cabin radiation designed
Device area and total radiator area are as shown in table 6：
| Cabin 1 | Cabin 2 | Cabin 3 | Cabin 4 | It amounts to | |
| Radiator area | 68.1 | 37.6 | 68.1 | 42.0 | 215.8 |
Table 6
And the thermal load analysis method of the present invention, energy is freely transmitted between cabin according to fluid circuit, to different operating mould
The radiator area that each bay section needs under formula is allocated according to self-radiating ability, in the present embodiment, two kinds of Working moulds
The radiator area that each cabin needs under formula is as shown in table 7, table 8：
Radiator area needed for normal flight designs：
| Project | Cabin 1 | Cabin 2 | Cabin 3 | Cabin 4 | It amounts to |
| The controllable heat dissipation amount (W) of generation | 10000 | 8000 | 10000 | 8000 | 36000 |
| Radiator heat-sinking capability (W/m2) | 147.8 | 228.4 | 147.9 | 217.1 | -- |
| The controllable heat dissipation amount (W) of distribution | 7178.6 | 11093.4 | 7183.5 | 10544.5 | 36000.0 |
| Radiator area (the m of configuration2) | 48.6 | 48.6 | 48.6 | 48.6 | 194.4 |
Table 7
Radiator area needed for earth observation designs：
| Project | Cabin 1 | Cabin 2 | Cabin 3 | Cabin 4 | It amounts to |
| The controllable heat dissipation amount (W) of generation | 8000 | 6000 | 8000 | 6000 | 28000 |
| Radiator heat-sinking capability (W/m2) | 146.9 | 213 | 146.8 | 190.3 | -- |
| The controllable heat dissipation amount (W) of distribution | 5901.3 | 8556.7 | 5897.3 | 7644.8 | 28000 |
| Radiator area (the m of configuration2) | 40.2 | 40.2 | 40.2 | 40.2 | 160.8 |
Table 8
To meet worse operating mode, the heat dissipation need under normal mode of operation and earth observation pattern can be met
It asks, needs to select the larger value of radiator area needed for radiating under two kinds of operating modes as the radiator of actual disposition in cabin
Area.In the present embodiment, for four cabin space stations, with reference to table 7 and table 8, each cabin radiator area should be selected as 48.6m2。
It is compared with existing design method, the area of radiator reduces 21.4m2.Consider the weight of radiator itself, internal working medium
Weight and the increase that pump weight is brought due to increasing pipeline, and be about 8kg per the radiator equivalent weight of square meter area, then exist
In present embodiment, method using the present invention can make thermistor(-ter) reason system total weight mitigate about 171.2kg.
It can be seen from the above, the multi cabin spacecraft thermal load analysis method of the present invention, design side compared with the prior art
Method will not need the outside radiant heat of radiator due to being all made of actual thermic load situation when analysis since artificial origin increases
Measure Qf, therefore the problem of artificially increasing radiator area would not also occur, material can be significantly saved, and can be effective
Control the weight of thermal control management system.On the other hand, due to according to each cabin radiator heat-sinking capability to controllable heat dissipation amount QkIt carries out
Distribution, the radiator area that can be configured to each cabin optimize, and also can effectively mitigate the weight of thermal control management system.
The multi cabin spacecraft thermal load analysis method of the present invention, design method compared with the prior art, due to each cabin
Maximum heating load be not increased, into radiator maximum stream flow and relatively low thermic load when the difference of flow be in normal model
In enclosing, valve occurs the case where being unfavorable for control when thermic load will not be caused relatively low.
The multi cabin spacecraft thermal load analysis method of the present invention, design method compared with the prior art, due to control
And radiator area is optimized, radiator surface running temperature increases compared with traditional design method when thermic load is relatively low, no
The power consumption that will appear circulating pump improves the risk of even radiator failure.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all essences in the present invention
With within principle, any modification, equivalent replacement, improvement and so on should all be included in the protection scope of the present invention god.
Claims (7)
1. multi cabin spacecraft thermal load analysis method, including：
(a) Orbital heat flux situation of the analysis multi cabin spacecraft under various operating modes；
(b) according to quantity of heat production and uncontrollable heat dissipation capacity inside each bay section in each mode, count what each bay section under each pattern generated
Controllable heat dissipation amount；
(c) it determines each bay section heat-sinking capability, controllable heat dissipation amount described in each bay section is allocated accordingly, to each bay section thermal component
It is designed.
2. multistage spacecraft thermal load analysis method according to claim 1, which is characterized in that in step (a),
According to thermal component threedimensional model, thermal component surface solar absorptance, thermal component surface infrared emittance, establishes and dissipate
Thermal part Orbital heat flux analysis model；
Each operating mode lower railway parameter of the multi cabin spacecraft and flight attitude are set；
Calculate each cabin thermal component surface average absorption Orbital heat flux surface density.
3. according to the method described in claim 1, it is characterized in that, the bay section inside quantity of heat production include below deck equipment heat production and
Energy resource system waste heat and occupant's metabolic heat production, the uncontrollable heat dissipation capacity are nacelle leaking heat.
4. according to the method described in claim 1, it is characterized in that, the controllable heat dissipation amount is the below deck equipment heat production and energy
The difference of the sum of source system waste heat, described occupant's metabolic heat production and the nacelle leaking heat.
5. according to the method described in claim 1, it is characterized in that, in step c,
According to Orbital heat flux situation of the spacecraft obtained in step a under various operating modes, each bay section thermal component is determined
Heat-sinking capability；
The controllable heat dissipation amount is allocated between each bay section；
According to the heat-sinking capability of the controllable heat dissipation amount and each bay section thermal component of the distribution of each bay section, determine under each operating mode
The area of thermal component needed for each bay section；
Choose thermal component of the maximum value of each bay section thermal component area under different working modes as each bay section actual disposition
Area.
6. according to the method described in claim 5, it is characterized in that, the heat-sinking capability of the thermal component is to be dissipated on unit area
The difference of thermal part outside radiations heat energy and Orbital heat flux.
7. according to the method described in claim 1, it is characterized in that, the thermal component is radiator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810175647.6A CN108482712B (en) | 2018-03-02 | 2018-03-02 | Multi cabin spacecraft thermal load analysis method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810175647.6A CN108482712B (en) | 2018-03-02 | 2018-03-02 | Multi cabin spacecraft thermal load analysis method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108482712A true CN108482712A (en) | 2018-09-04 |
| CN108482712B CN108482712B (en) | 2019-02-26 |
Family
ID=63341251
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810175647.6A Active CN108482712B (en) | 2018-03-02 | 2018-03-02 | Multi cabin spacecraft thermal load analysis method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108482712B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109324648A (en) * | 2018-12-07 | 2019-02-12 | 银河航天(北京)通信技术有限公司 | A kind of method of temperature control system, spacecraft and spacecraft temperature control |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101270930A (en) * | 2007-02-26 | 2008-09-24 | 泰勒斯公司 | Thermal control device on board a spacecraft |
| CN103407582A (en) * | 2013-08-08 | 2013-11-27 | 北京空间机电研究所 | Heat management system for spatial large-sized loads |
| CN104217057A (en) * | 2013-05-31 | 2014-12-17 | 北京空间技术研制试验中心 | Three-dimensional collaborative design method for spacecraft final assembly and thermal design |
-
2018
- 2018-03-02 CN CN201810175647.6A patent/CN108482712B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101270930A (en) * | 2007-02-26 | 2008-09-24 | 泰勒斯公司 | Thermal control device on board a spacecraft |
| CN104217057A (en) * | 2013-05-31 | 2014-12-17 | 北京空间技术研制试验中心 | Three-dimensional collaborative design method for spacecraft final assembly and thermal design |
| CN103407582A (en) * | 2013-08-08 | 2013-11-27 | 北京空间机电研究所 | Heat management system for spatial large-sized loads |
Non-Patent Citations (2)
| Title |
|---|
| 付仕明: "空间站热分析综述", 《航天器环境工程》 * |
| 谢敏: "国际空间站站载设备的热环境分析", 《哈尔滨工业大学学报》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109324648A (en) * | 2018-12-07 | 2019-02-12 | 银河航天(北京)通信技术有限公司 | A kind of method of temperature control system, spacecraft and spacecraft temperature control |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108482712B (en) | 2019-02-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20150068703A1 (en) | Thermal management system and method of assembling the same | |
| US9923252B2 (en) | Battery pack with variable-conductance heat pipe (VCHP) cooling | |
| CN104820748B (en) | A kind of carrier rocket endoatmosphere inflight phase bay section thermo parameters method determines method | |
| US9540111B2 (en) | Individual temperature-control of aircraft cabin regions by heating and evaporative cooling | |
| US10611496B2 (en) | Power allocation systems for aircraft | |
| CN107135629A (en) | Heat management system for the structure assembly of the Aero-Space vehicles | |
| CN101590913A (en) | Adopt the anti-icing and deicing method for civil aircraft of loop circuit heat pipe | |
| Zeidler et al. | Greenhouse module for space system: a lunar greenhouse design | |
| EP2573389B1 (en) | Cooling and climate control system and method for a wind turbine | |
| CN113978046B (en) | Thermal protection structure and preparation method thereof | |
| CN108482712B (en) | Multi cabin spacecraft thermal load analysis method | |
| CN201854544U (en) | Condensing radiation heat dissipation plate | |
| CN105843996A (en) | Optimization method of heat-proof structure | |
| CN105674390A (en) | Dynamic hydraulic balance adjusting method for centralized heating system | |
| CN103434659A (en) | High-temperature-uniformity heat radiator for navigation satellite | |
| US20200239152A1 (en) | Thermal management system | |
| CN107738755B (en) | It is a kind of adapt to the world it is round-trip efficiently lead passive heat management system and its design method | |
| CN106081121B (en) | A kind of cabin temperature adaptive control system | |
| CN101730437A (en) | Radiation cooling system for temperature control of electronic equipment close to space vehicle | |
| CN102056468B (en) | Condensing and radiating heating panel | |
| CN105427902A (en) | Direct evaporative passive self-cooling flow guide plate | |
| CN111572821A (en) | Thermal protection wall plate, plate-shaped thermal protection system and annular thermal protection system | |
| CN209337010U (en) | A kind of radiator structure of the dynamic unmanned plane of oil | |
| CN113091490A (en) | Combined heat sink-based moon sampling return detector autonomous thermal management system | |
| Bue et al. | Multifunctional Space Evaporator-Absorber-Radiator (SEAR) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |