CN100561392C - A kind of nano-satellite spacing heat sink simulator - Google Patents
A kind of nano-satellite spacing heat sink simulator Download PDFInfo
- Publication number
- CN100561392C CN100561392C CNB2009100767718A CN200910076771A CN100561392C CN 100561392 C CN100561392 C CN 100561392C CN B2009100767718 A CNB2009100767718 A CN B2009100767718A CN 200910076771 A CN200910076771 A CN 200910076771A CN 100561392 C CN100561392 C CN 100561392C
- Authority
- CN
- China
- Prior art keywords
- temperature
- heat
- controller
- satellite
- hot
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention discloses a kind of nano-satellite spacing heat sink simulator, comprise analogue unit, data acquisition unit, controller, power drive unit and communication unit; Described analogue unit comprises thermoelectric module TEC, heat flux sensor, fan, temperature sensor A and temperature sensor B and fin; Feedback heat flow value that controller obtains according to data acquisition unit and given heat flow value generate the control signal of TEC as the input of algorithmic controller, realize of the good tracking of feedback hot-fluid to given hot-fluid, promptly realize the good simulation of heat conduction heat flux to the space radiation hot-fluid, when guaranteeing that hot-fluid is followed the tracks of, the heat that TEC derives is transmitted to fin, require to realize the temperature control of fan according to control to fin, unnecessary heat is loose in air, realized simulation space low temperature and black background environment.The device thermal inertia is little, response speed is fast, volume is little, has realized the desktopization of nano-satellite hot proving installation.
Description
Technical field
The present invention relates to spacecraft environment and control hot technical field of measurement and test, be specifically related to a kind of nano-satellite spacing heat sink simulator, utilize the heat radiation temperature control ability of the active energy transmission capacity of TEC and fan to realize simulation spacecraft radiant heat flux under space vacuum, low temperature and the black background space environment.
Background technology
In order to verify the allomeric function of spacecraft under space environment, guarantee spacecraft at the rail reliability service, must carry out sufficient environmental simulation experiment on ground, the wherein heat test of most importantly under virtual space thermal environment condition, carrying out.
The satellite of receiving is meant the moonlet of weight between 1～10kg, have in light weight, volume is little, design, advantage cheap for manufacturing cost, this moonlet flies in the mode of formation or composition constellation, it is strong to have viability, at numerous areas such as space environment detection, earth observation, communication navigations very application prospects is arranged.Undertaking and keep satellite and the temperature required vital task of satellite borne equipment operate as normal thereof as receiving the heat control system of one of satellite important composition system, thereby nano-satellite hot control system is carried out ground simulation test is essential.
Traditional ground simulation technology is to realize vacuum with a huge vacuum tank and support equipment, the simulation of low temperature and black background, as adopt mechanical pump and diffusion pump to keep the vacuum tightness of vacuum tank, adopt aluminium, copper or stainless cylindrical shell are combined with the cooling duct implementation space low temperature black background simulation of heat eliminating medium (as liquid nitrogen), a whole set of simulator bulky, realize technical sophistication, when experimental verification, the equipment set thermal inertia is big, experimental period is long and expensive high, for the nano-satellite hot test, because the satellite weight of receiving is little, thermal inertia is little, and traditional ground simulation device is difficult to the dynamic property requirement that the satisfied heat of receiving satellite is tested.
Summary of the invention
The present invention has designed this spacing heat sink simulator in order to solve the deficiency of traditional space environment ground simulation device at the nano-satellite hot testing requirement.This spacing heat sink simulator adopts TEC and fan as controlling object, realizes simulating heat loss through radiation rule under vacuum, low temperature and the black background with heat conduction.
A kind of nano-satellite spacing heat sink simulator comprises analogue unit, data acquisition unit, controller, power drive unit and communication unit;
Described analogue unit comprises thermoelectric module TEC, heat flux sensor, fan, temperature sensor A and temperature sensor B and fin;
Heat flux sensor is used for detecting the TEC heat conduction heat flux, for TEC control provides feedback signal, makes the control of simulator heat flux simulation form closed loop;
The fin heat that conduction is come as heat sink reception TEC, and by fan heat is dispersed in the middle of the air;
Temperature sensor A and temperature sensor B are separately positioned on and receive satellite surface and fin surface, obtain to receive the accurate numerical value of satellite surface and fin temperature;
Under the control of controller, heat flow signal and temperature signal that data acquisition unit is gathered analogue unit are transferred to controller, and controller is given power drive unit with the control signal that the heat flow signal that receives and temperature signal generate TEC and fan respectively;
Power drive unit receives controller control signal, and it is amplified rear drive TEC and fan work;
Communication unit is the passage that host computer and controller carry out exchanges data, receives the information of host computer, and the data that controller is handled are sent to host computer simultaneously, are the data analysis service.
Described controller is made of temperature controller and hot-fluid controller, and temperature controller wherein is with generating fan control signal, and the hot-fluid controller is with generating the TEC control signal.
The fixed temperature of giving of described temperature controller is set by communication unit by host computer according to job requirement, and feedback temperature is calculated through temperature transition by the fin temperature signal numerical value that data acquisition unit obtains; Give the input as temperature controller of fixed temperature and feedback temperature, generate fan control signal through computing, this temperature controller is closed-loop control, realizes during stable state that feedback temperature is to giving the tracking of fixed temperature.
The feedback hot-fluid is that the heat flux sensor signal numerical value that obtains of data acquisition unit obtains through the hot-fluid numerical evaluation in the described hot-fluid controller, and given hot-fluid then is that the computing by following step obtains:
A, the satellite surface temperature signal of receiving that obtains according to data acquisition unit calculate Temperature numerical through temperature transition,
B, according to formula T
f=t+273.15 realizes the conversion of Celsius temperature to thermodynamic temperature, obtains thermodynamic temperature numerical value, wherein T
fBe thermodynamic temperature, t is a Celsius temperature;
C, according to thermodynamic temperature numerical value, calculate the hot-fluid set-point, computation process is as follows:
Do not having under the outer hot-fluid situation, the thermal balance equation of satellite in the space of receiving is:
Wherein Q receives satellite to the net radiation heat dissipation capacity in space, Q
pFor receiving the heat power consumption of satellite, A
1For receiving the heat loss through radiation area of satellite, ε
1For receiving the radiance of satellite table flooring, σ is the Stefan-Boltzmann constant, is about 5.67 * 10
-8W/ (m
2K
4), T
fFor receiving satellite surface mechanics temperature;
Get by equation (1) version:
Q receives satellite to the net radiation hot-fluid in space, the same equation of other parameter (1);
Given hot-fluid and feedback hot-fluid generate the TEC control signal as the input of hot-fluid controller through the computing of superheat flow controller;
Described heat flow signal is to record by being installed in the heat flux sensor of receiving between satellite and the TEC; Described temperature signal one tunnel is for receiving the satellite surface temperature signal, and A records by temperature sensor; Another road is the fin temperature signal, is recorded by the temperature sensor B that is installed on the fin.
Under the control action of controller, data acquisition unit with the heat flow signal that records, receive satellite surface temperature signal, fin temperature signal and feed back to controller, the given signal that controller sends by communication unit according to these feedback signals and host computer generates TEC control signal and fan control signal; TEC passage in the TEC control signal power input driver element generates power drive signal out1+ and out1-, and out1+ and out1-are as driving TEC work; Fan passage in the fan control signal power input driver element generates power drive signal out2+ and out2-, and out2+ and out2-are as drive fan work.
Described analogue unit comprises fan, fin, TEC and heat flux sensor and temperature sensor A and temperature sensor B;
Heat flux sensor and TEC, and all closely be connected by heat-conducting silicone grease between TEC and the fin guarantee to receive reliably the shedding of satellite surface amount; During use temperature sensor A and temperature sensor B are pasted on tested receiving on satellite surface and the fin respectively with heat conductive silica gel; Described fan is threaded with fin.Control TEC electric current realizes that its heat flow value is recorded by the heat flux sensor of being close to the TEC huyashi-chuuka (cold chinese-style noodles) to the control of TEC huyashi-chuuka (cold chinese-style noodles) to the hot side conductive heat flow; The heat transferred of TEC hot side arrives fin, and by fan control, the fin temperature is controlled at set-point; In order to make fan form closed loop, temperature sensor B has been installed on fin to the temperature control of fin; For computer memory radiomimesis hot-fluid, temperature sensor A is pasted on heat conductive silica gel receives the satellite surface.
The invention has the advantages that:
(1) the present invention adopts TEC and fan as controlled device, and whole simulator thermal inertia is little, response speed is fast, and inferior simulation body is long-pending little, has realized the desktopization of nano-satellite hot proving installation;
(2) adopted the hot-fluid controller to realize the tracking Control of TEC heat conduction heat flux, reduced the complexity of vacuum simulation, controlled accurately and be easy to and realize space radiation simulation hot-fluid;
(3) adopt temperature controller to realize the control of fin temperature, the heat that the simulation radiation law is shed is fully arranged diffusing, has realized the simulation to space low temperature and black background environment, has greatly reduced the volume of low temperature and black background analogue means;
Description of drawings
Fig. 1 is a simulator structured flowchart of the present invention;
Fig. 2 is a controller architecture block diagram of the present invention;
Fig. 3 is an analogue unit instantiation structural drawing of the present invention;
Fig. 4 is a TEC hot-fluid aircraft pursuit course of the present invention;
Fig. 5 is a fan temperature aircraft pursuit course of the present invention.
Embodiment
The present invention is described in further detail below in conjunction with drawings and Examples.
As shown in Figure 1, a kind of nano-satellite spacing heat sink simulator 1 of the present invention comprises analogue unit 101, data acquisition unit 103, controller 102, power drive unit 104 and communication unit 105.
Described analogue unit 101 comprises thermoelectric module TEC101-1, heat flux sensor 101-2, fan 101-3, film platinum resistor temperature sensor A101-4, B101-5 and fin 101-6.
TEC101-1 is the core of analogue unit 101 structures, utilizes the Peltier effect to realize the Current Control heat transferred, and it is controlled to transmit heat controllable that is hot-fluid, transmits hot-fluid control by TEC101-1 and realizes heat conduction virtual space heat loss through radiation.
Heat flux sensor 101-2 is used for detecting the TEC101-1 heat conduction heat flux, for TEC101-1 provides feedback signal, thereby makes the control of simulator 1 heat flux simulation form closed loop.
The fin 101-6 heat that conduction is come as heat sink reception TEC 101-1, and by fan 101-3 heat is dispersed in the middle of the air.
Film platinum resistor temperature sensor A101-4 and temperature sensor B101-5 are separately positioned on and receive on satellite surface and the fin 101-6, become the film shape design, be easy to install, and highly sensitive, cooperate the high-acruracy survey circuit to obtain to receive the accurate numerical value of satellite surface and fin 101-6 temperature.
As shown in Figure 2, controller 102 comprises two algorithmic controllers, and one is with the temperature controller 102-1 that generates fan control signal, and another is the hot-fluid controller 102-2 that generates the TEC control signal.
The fixed temperature of giving of temperature controller 102-1 is set by communication unit 105 by host computer according to job requirement, feedback temperature is calculated through temperature transition by the fin temperature signal that data acquisition unit 103 obtains, give the input of fixed temperature and feedback temperature two-way Temperature numerical as temperature controller 102-1, generate fan control signal through computing, this temperature controller 102-1 is closed-loop control, can realize during stable state that feedback temperature is to giving the tracking of fixed temperature.
The feedback hot-fluid is that the heat flux sensor 101-2 signal numerical value that obtains of data acquisition unit 103 obtains through the hot-fluid numerical evaluation among the hot-fluid controller 102-2, and given hot-fluid then is that the computing by following step obtains:
A, the satellite surface temperature signal of receiving that obtains according to data acquisition unit 103 calculate Temperature numerical through temperature transition
B, according to formula T
f=T+273.15 (T wherein
fBe thermodynamic temperature, T is a Celsius temperature) realize the conversion of Celsius temperature to thermodynamic temperature, obtain thermodynamic temperature numerical value;
C, according to Temperature numerical, calculate by given hot-fluid, obtain given heat flow value, computation process is as follows:
Do not having under the outer hot-fluid situation, the thermal balance equation of satellite in the space of receiving is:
Wherein Q receives satellite to the net radiation heat in space, Q
pFor receiving the heat power consumption of satellite, A
1For receiving the heat loss through radiation area of satellite, ε
1For receiving the radiance of satellite table flooring, σ is the Stefan-Boltzmann constant, is about 5.67 * 10
-8W/ (m
2K
4), T
fFor receiving satellite surface mechanics temperature.
Can get by equation (1) version:
Q receives satellite to the net radiation hot-fluid in space, the same equation of other parameter (1).
Given hot-fluid and feedback hot-fluid generate the TEC control signal as the input of hot-fluid controller 102-2 through superheat flow controller 102-2 computing, and this hot-fluid controller 102-2 also for closed-loop control, can realize feeding back the tracking of hot-fluid to given hot-fluid.
Under the control action of controller 102, data acquisition unit 103 with the heat flow signal that records, receive satellite surface temperature signal, fin temperature signal and feed back to controller 102, controller 102 by the given signal that communication unit 105 sends, carries out algorithm process according to these feedback signals and host computer.Some useful data information via communication units 105 that generate in processing procedure are sent to host computer, use in order to data analysis, controller 102 final TEC control signal and the fan control signals of generating, TEC passage in the TEC control signal power input driver element 104 generates power drive signal out1+ and out1-, and out1+ and out1-are as driving TEC101-1 work; Fan passage in the fan control signal power input driver element 104 generates power drive signal out2+ and out2-, out2+ and out2-be as drive fan 101-3 work, the collaborative heat flux simulation work that realizes receiving the satellite spatial simulator of TEC101-1 and fan 101-3 under the control action of controller 102.
Described analogue unit is specifically as follows following structure.
As shown in Figure 3, the analogue unit structure is made up of fan 101-3, fin 101-6, TEC101-1 and heat flux sensor 101-2 and film platinum resistor temperature sensor A101-4 and temperature sensor B 101-5;
Heat flux sensor 101-2 and TEC101-1, and all closely be connected by heat-conducting silicone grease between TEC101-1 and the fin 101-6 guarantee to receive reliably the shedding of satellite surface amount.During use film platinum resistor temperature sensor A101-4 and resistance temperature sensor B101-5 being pasted on tested receiving respectively with heat conductive silica gel gets final product on satellite surface and the fin 101-6.Described fan 101-3 is threaded with fin 101-6.
TEC101-1 and fan 101-3 are execution unit, can realize the huyashi-chuuka (cold chinese-style noodles) that makes TEC101-1 is conducted to hot side the control of heat by the change of control TEC101-1 electric current, just heat conduction heat flux is controlled, and its numerical value can be recorded by the heat flux sensor 101-2 that is close to the TEC huyashi-chuuka (cold chinese-style noodles).TEC101-1 must be conducted heat and in time shed for guaranteeing the hot-fluid continuous controllable, TEC101-1 is close to fin 101-6 just can arrive the good fin 101-6 of heat conductivility with the heat transferred of TEC101-1 hot side, by control, the TEC101-1 hot-face temperature can be controlled at the setting level to fan 101-3.In order to make fin 101-6 temperature be controlled at set-point, film platinum resistor sensors A 103 has been installed on fin 101-6, make fan 101-3 form closed loop to the temperature control of fin 101-6, realization is to the simulation of space environment low temperature and black background, for computer memory radiomimesis hot-fluid, need to measure the spacecraft surface temperature, during use film platinum resistor temperature lower sensor 101-5 is pasted on heat conductive silica gel and receives the satellite surface and get final product.
As shown in Figure 4, be the hot-fluid aircraft pursuit course under the TEC101-1 control, given hot-fluid is the heat flow value that calculates according to radiation law among the figure, the feedback hot-fluid is the feedback heat flow value that heat flux sensor 101-2 detects in real time under TEC101-1 control, because given heat flow value is according to receiving the numerical value that the satellite table surface temperature calculates in real time, be constantly to change, thereby the feedback hot-fluid has some deviations in tracing process on phase place, experimental data shows that with heat conduction simulation heat loss through radiation rule be feasible.
As shown in Figure 5, temperature aircraft pursuit course for fan 101-3, wherein set by host computer to fixed temperature, feedback temperature is to record by the temperature sensor B101-5 that is installed on the fin 101-6, because fan 101 heat radiations are by fan 101 convection heat transfer in air, thereby the host computer design temperature must be greater than environment temperature, this test is to record when environment temperature is 23 ℃, experimental data shows that fan 101 and fin 101-6 are the TEC101-1 heat radiation, and the simulation of implementation space low temperature and black background environment is feasible.
Claims (8)
1, a kind of nano-satellite spacing heat sink simulator is characterized in that: comprise analogue unit, data acquisition unit, controller, power drive unit and communication unit;
Described analogue unit comprises thermoelectric module TEC, heat flux sensor, fan, temperature sensor A and temperature sensor B and fin;
Heat flux sensor is used for detecting the TEC heat conduction heat flux, for TEC control provides feedback signal, makes the control of simulator heat flux simulation form closed loop;
The fin heat that conduction is come as heat sink reception TEC, and by fan with heat dissipation in air;
Temperature sensor A and temperature sensor B are separately positioned on and receive satellite surface and fin surface, obtain to receive the numerical value of satellite surface and fin temperature;
Under the control of controller, heat flow signal and temperature signal that data acquisition unit is gathered analogue unit are transferred to controller, and controller is given power drive unit with the control signal that the heat flow signal that receives and temperature signal generate TEC and fan respectively;
Power drive unit receives controller control signal, and it is amplified rear drive TEC and fan work;
Communication unit is the passage that host computer and controller carry out exchanges data, receives the information of host computer, and the data that controller is handled are sent to host computer simultaneously, are the data analysis service.
2, a kind of according to claim 1 nano-satellite spacing heat sink simulator, it is characterized in that: described controller is made of temperature controller and hot-fluid controller, temperature controller wherein is with generating fan control signal, and the hot-fluid controller is with generating the TEC control signal.
3, as a kind of nano-satellite spacing heat sink simulator as described in the claim 2, it is characterized in that: the fixed temperature of giving of described temperature controller is set by communication unit by host computer according to job requirement, and feedback temperature is calculated through temperature transition by the fin temperature signal numerical value that data acquisition unit obtains; Give the input as temperature controller of fixed temperature and feedback temperature, generate fan control signal through computing, this temperature controller is closed-loop control, realizes during stable state that feedback temperature is to giving the tracking of fixed temperature.
4, as a kind of nano-satellite spacing heat sink simulator as described in the claim 2, it is characterized in that: the feedback hot-fluid is that the heat flux sensor signal numerical value that obtains of data acquisition unit obtains through the hot-fluid numerical evaluation in the described hot-fluid controller, and given hot-fluid then is that the computing by following step obtains:
A, the satellite surface temperature signal of receiving that obtains according to data acquisition unit calculate Temperature numerical through temperature transition,
B, according to formula T
f=t+273.15 realizes the conversion of Celsius temperature to thermodynamic temperature, obtains thermodynamic temperature numerical value, wherein T
fBe thermodynamic temperature, t is a Celsius temperature;
C, according to thermodynamic temperature numerical value, calculate the hot-fluid set-point, computation process is as follows:
Do not having under the outer hot-fluid situation, the thermal balance equation of satellite in the space of receiving is:
Wherein Q receives satellite to the net radiation heat dissipation capacity in space, Q
pFor receiving the heat power consumption of satellite, A
1For receiving the heat loss through radiation area of satellite, ε
1For receiving the radiance of satellite table flooring, σ is the Stefan-Boltzmann constant, is about 5.67 * 10
-8W/ (m
2K
4), T
fFor receiving satellite surface mechanics temperature;
Get by equation (1) version:
Q receives satellite to the net radiation hot-fluid in space, the same equation of other parameter (1);
Given hot-fluid and feedback hot-fluid generate the TEC control signal as the input of hot-fluid controller through the computing of superheat flow controller.
5, a kind of according to claim 1 nano-satellite spacing heat sink simulator is characterized in that: described heat flow signal is to record by being installed in the heat flux sensor of receiving between satellite and the TEC; Described temperature signal one tunnel is for receiving the satellite surface temperature signal, and A records by temperature sensor; Another road is the fin temperature signal, is recorded by the temperature sensor B that is installed on the fin.
6, the heavy simulator of a kind of according to claim 1 nano-satellite hot, it is characterized in that: under the control action of controller, data acquisition unit with the heat flow signal that records, receive satellite surface temperature signal, fin temperature signal and feed back to controller, the given signal that controller sends by communication unit according to these feedback signals and host computer generates TEC control signal and fan control signal; TEC passage in the TEC control signal power input driver element generates power drive signal out1+ and out1-, and out1+ and out1-are as driving TEC work; Fan passage in the fan control signal power input driver element generates power drive signal out2+ and out2-, and out2+ and out2-are as drive fan work.
7, a kind of according to claim 1 nano-satellite spacing heat sink simulator, it is characterized in that: described analogue unit, heat flux sensor wherein and TEC, and all closely be connected by heat-conducting silicone grease between TEC and the fin guarantee to receive reliably the shedding of satellite surface amount; During use temperature sensor A and temperature sensor B are pasted on tested receiving on satellite surface and the fin respectively with heat conductive silica gel; Described fan is threaded with fin.
8, as a kind of nano-satellite spacing heat sink simulator as described in the claim 7, it is characterized in that: control TEC electric current realizes that its heat flow value is recorded by the heat flux sensor of being close to the TEC huyashi-chuuka (cold chinese-style noodles) to the control of TEC huyashi-chuuka (cold chinese-style noodles) to the hot side conductive heat flow; The heat transferred of TEC hot side arrives fin, and by fan control, the fin temperature is controlled at set-point; In order to make fan form closed loop, temperature sensor B has been installed on fin to the temperature control of fin; For computer memory radiomimesis hot-fluid, temperature sensor A is pasted on heat conductive silica gel receives the satellite surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2009100767718A CN100561392C (en) | 2009-01-21 | 2009-01-21 | A kind of nano-satellite spacing heat sink simulator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2009100767718A CN100561392C (en) | 2009-01-21 | 2009-01-21 | A kind of nano-satellite spacing heat sink simulator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101477382A CN101477382A (en) | 2009-07-08 |
| CN100561392C true CN100561392C (en) | 2009-11-18 |
Family
ID=40838109
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2009100767718A Expired - Fee Related CN100561392C (en) | 2009-01-21 | 2009-01-21 | A kind of nano-satellite spacing heat sink simulator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100561392C (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101819445B (en) * | 2010-02-05 | 2012-05-16 | 北京航空航天大学 | Embedded satellite-borne fault-tolerant temperature control system and verification method thereof |
| CN102768548B (en) * | 2012-07-25 | 2014-09-03 | 北京卫星环境工程研究所 | Heat sink temperature control system and method for thermal vacuum test |
| CN105407684B (en) * | 2014-07-16 | 2018-07-06 | 中车大连电力牵引研发中心有限公司 | Locomotive electric cad system cabinet cooling device and locomotive electric cad system cabinet |
| CN104483993B (en) * | 2014-11-07 | 2016-09-14 | 北京卫星环境工程研究所 | The automatic temperature control system of alternation thermic load test specimen and control method under spatial environments |
| CN106516180B (en) * | 2015-09-10 | 2018-09-14 | 北京卫星环境工程研究所 | The operating mechanism that liquid nitrogen refrigerating under vacuum low-temperature environment is heat sink |
| CN106371483B (en) * | 2016-11-03 | 2018-05-08 | 浙江大学 | A kind of method of space simulator heat sink temperature autonomous control |
| CN110018679B (en) * | 2019-04-11 | 2020-07-14 | 上海卫星工程研究所 | Closed-loop test system and test method for spacecraft autonomous temperature control system |
| CN111077855B (en) * | 2019-11-26 | 2023-07-28 | 上海空间电源研究所 | Single-machine heat balance control system applied to spacecraft |
-
2009
- 2009-01-21 CN CNB2009100767718A patent/CN100561392C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN101477382A (en) | 2009-07-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100561392C (en) | A kind of nano-satellite spacing heat sink simulator | |
| Rezvanpour et al. | Using CaCl2· 6H2O as a phase change material for thermo-regulation and enhancing photovoltaic panels’ conversion efficiency: Experimental study and TRNSYS validation | |
| Rejeb et al. | Numerical and model validation of uncovered nanofluid sheet and tube type photovoltaic thermal solar system | |
| Jang et al. | Optimization of thermoelectric generator module spacing and spreader thickness used in a waste heat recovery system | |
| CN101393148B (en) | Test device for coating heat dispersion and test method thereof | |
| CN104071360B (en) | A kind of transitional heat balance test method based on radiation Coupled Heat Transfer equivalent simulation and system | |
| CN102141422B (en) | Flow-temperature integrated measurement device for moonlet single-phase fluid thermal control loop | |
| CN102768548B (en) | Heat sink temperature control system and method for thermal vacuum test | |
| Namvar et al. | Transient heat and moisture transfer characteristics of a liquid-to-air membrane energy exchanger (LAMEE) model verification and extrapolation | |
| CN105867170A (en) | Space optical remote sensor temperature control circuit simulation system and simulation testing method | |
| Paradis et al. | A 2-D transient numerical heat transfer model of the solar absorber plate to improve PV/T solar collector systems | |
| Bambrook et al. | A solvable thermal circuit for modelling PVT air collectors | |
| Wang et al. | Experimental study and multi-objective optimisation of a novel integral thermoelectric wall | |
| Buzás et al. | Modelling and simulation aspects of a solar hot water system | |
| Tiddens et al. | Air return ratio measurements at the solar tower Jülich using a tracer gas method | |
| CN103983365A (en) | Multi-measuring-head transient radiation heat flow meter and measuring method for thermal radiation heat flow density | |
| CN107421980A (en) | Heating impedance compensation type thermo-resistance measurement method | |
| Xing et al. | A thermal balance method for measuring thermal conductivity by compensation of electric cooling or heating based on thermoelectric modules | |
| CN106053527A (en) | Method for testing anisotropic heat diffusion coefficient of power battery at same time | |
| Redpath et al. | Experimental investigation of natural convection heat exchange within a physical model of the manifold chamber of a thermosyphon heat-pipe evacuated tube solar water heater | |
| CN109269682A (en) | A kind of caliberating device and scaling method of heat flow transducer | |
| CN103365319A (en) | Cluster system of heating dummy model | |
| Puluckul et al. | Harvesting Energy from Soil-Air Temperature Differences for Batteryless IoT Devices: A Case Study | |
| CN115452883A (en) | Universal characterization method for radiation refrigeration material | |
| Siltala et al. | Physical and data-driven models for edge data center cooling system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20091118 Termination date: 20110121 |