CN108020581A - A kind of Space Thermal tube performance testing experimental provision - Google Patents
A kind of Space Thermal tube performance testing experimental provision Download PDFInfo
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- CN108020581A CN108020581A CN201711166964.3A CN201711166964A CN108020581A CN 108020581 A CN108020581 A CN 108020581A CN 201711166964 A CN201711166964 A CN 201711166964A CN 108020581 A CN108020581 A CN 108020581A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N25/00—Investigating or analyzing materials by the use of thermal means
- G01N25/18—Investigating or analyzing materials by the use of thermal means by investigating thermal conductivity
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Abstract
The present invention provides a kind of Space Thermal tube performance testing experimental provision, including isoperibol case system, heat pipe evaporation ends cooling system, adopting heat pipes for heat transfer Performance Test System and acquisition and control system.The various Space-Work environment of heat pipe can be simulated by isoperibol case, heat transfer property that can be in ground simulation heat pipe under the state of weightlessness of space by adopting heat pipes for heat transfer Performance Test System.The present invention solves the heat transfer property test problem that space heat pipe carries out weightless flight on ground, has the advantages that compact-sized, easy to operate.
Description
Technical field
The present invention relates to refrigeration technology field, more particularly to a kind of heat transfer property experimental apparatus for testing of space heat pipe.
Background technology
With the development of space technology, space heat pipe is increasingly used widely.Using space heat pipe, one crucial
Technology is that the heat transfer property test of heat pipe is carried out on ground.Since the gravity in space is almost nil, and there are gravity on ground
In the case of, the result tested using conventional adopting heat pipes for heat transfer experimental apparatus for capability is deposited with the result under real space application environment
In very big difference.Therefore, how contrived experiment device carried out on ground simulation space heat pipe heat transfer become extremely important.
The content of the invention
It is contemplated that overcome drawbacks described above, there is provided a kind of Space Thermal tube performance testing experiment for being capable of space environmental simulation
Device.
The present invention provides a kind of Space Thermal tube performance testing experimental provision, carries out simulation sky on ground for space heat pipe
Between heat transfer property test under below-G conditions, it is characterised in that including：Isoperibol case system, heat pipe evaporation ends cooling system
With adopting heat pipes for heat transfer Performance Test System；
Wherein, above-mentioned isoperibol case system, for simulating environment temperature and pressure of the heat pipe under the conditions of Space-Work；
Above-mentioned heat pipe evaporation ends cooling system, for simulating the temperature and heat of heat pipe evaporation ends；
Above-mentioned adopting heat pipes for heat transfer Performance Test System, the test of heat transfer property is carried out for opposite heat tube.
Further, a kind of Space Thermal tube performance testing experimental provision provided by the invention, also has a structure in which spy
Point：I.e., above-mentioned isoperibol case system includes heat-insulation unit, constant temperature unit one, pressure control unit；
Wherein, above-mentioned constant temperature unit one, for adjusting and controlling the temperature of isoperibol case system；So as to simulate space work
Temperature under the conditions of work.
Above-mentioned pressure control unit, for adjusting and controlling the pressure of isoperibol case system；So as to simulate Space-Work condition
Under environmental pressure；
Above-mentioned heat-insulation unit, for being kept the temperature to isoperibol case.So as to be kept the temperature to current isoperibol
Processing, avoids the loss of temperature, reduces working time and the frequency of constant temperature unit.
Further, a kind of Space Thermal tube performance testing experimental provision provided by the invention, also has a structure in which spy
Point：I.e., above-mentioned heat-insulation unit includes ecto-entad, successively the insulation tank shell of packaging type setting layer by layer, incubator heat insulation layer, guarantor
Incubator body refrigerating oxidant layer and thermal-insulating body liner；
The insulation tank shell can be that the various materials such as metal, nonmetallic are fabricated；
The incubator heat insulation layer can by the heat-insulating materials such as rubber, cotton, vacuum layer, doubling plate or structure manufacture and
Into；
The thermal-insulating body refrigerating oxidant layer is generally the pipeline around whole system, the circulation for refrigerating medium；
Above-mentioned constant temperature unit one includes thermostat, which can be that thermostat etc. is capable of providing constant temperature refrigerating medium
Equipment, above-mentioned thermostat connects with thermal-insulating body refrigerating oxidant layer, forms circulation loop, is conveyed to thermal-insulating body refrigerating oxidant layer
It is recycled mobile refrigerating medium one；I.e., can be penetrated through by two between thermostat and thermal-insulating body refrigerating oxidant layer whole
Insulation tank shell, incubator heat insulation layer, the inlet pipe of thermal-insulating body refrigerating oxidant layer are connected with outlet pipe, and thermostat carries out refrigerating medium
After temperature control, the refrigerating medium (or other liquid) of certain temperature is passed through in thermal-insulating body refrigerating oxidant layer by inlet pipe, in refrigerating medium
Laminar flow after a week, is returned in thermostat by outlet pipe, under which continues after re-starting heating or refrigeration processing
One circulation.
Above-mentioned pressure control unit includes pressure control component, and above-mentioned pressure control component is connected with the inside of environmental cabinet, in environmental cabinet
Space carry out pressure controlling.The pressure control component, which generally comprises one, has vaccum-pumping equipment and a pressure control mechanism (pressure valve
Or pressure control mouth), which vacuumizes the space in environmental cabinet, the suction/true by the pressure control mechanism
Empty rate is regulated and controled by the pressure control mechanism, and in general, which generally extends through whole insulation tank shell, incubator
Heat insulation layer, thermal-insulating body refrigerating oxidant layer and liner.
Further, a kind of Space Thermal tube performance testing experimental provision provided by the invention, also has a structure in which spy
Point：I.e., above-mentioned heat pipe evaporation ends cooling system includes constant temperature unit two；
Above-mentioned adopting heat pipes for heat transfer Performance Test System, is arranged at the inside of isoperibol case system, including evaporation ends cooler
Structure and condensation end thermal insulation mechanism；
Above-mentioned constant temperature unit two is connected with evaporation ends cooling body, forms circulation loop, defeated into evaporation ends cooling body
Send recyclable mobile refrigerating medium two (or other can temperature control working media).
Above-mentioned condensation end thermal insulation mechanism is adjustable structure for the air blanketing spacing between condensation end of heat pipe.In reality
During testing, the interlayer spacing, generally according to parameters such as heat pipe diameter, length, heat outputs, to the length of condensation end thermal insulation mechanism
Wide high size is adjusted, so as to there was only the condensation end heat transfer situation of heat conduction during zero-gravity simulation without free convection.
Further, a kind of Space Thermal tube performance testing experimental provision provided by the invention, also has a structure in which spy
Point：I.e., the constant temperature unit two includes refrigerating medium outlet 1 and refrigerating medium import 1；
The evaporation ends cooling body includes refrigerating medium import 2 and refrigerating medium outlet 2；
Wherein, the refrigerating medium outlet 1 of the constant temperature unit two is connected with the refrigerating medium import 2 of evaporation ends cooling body；
The refrigerating medium outlet 2 of the evaporation ends cooling body is connected with the refrigerating medium import 1 of the constant temperature unit two, is formed
Refrigerating medium loop；
The refrigerating medium loop is equipped with liquid transporting body；
The refrigerating medium loop is equipped with flow metering devices.
During performance test, pass through the refrigerating medium temperature difference and flow techniques meter imported and exported to evaporation ends cooling body
Calculate the heat transfer property of heat pipe.
Further, a kind of Space Thermal tube performance testing experimental provision provided by the invention, also has a structure in which spy
Point：I.e., above-mentioned adopting heat pipes for heat transfer Performance Test System further includes angle adjusting mechanism；
Installation that above-mentioned angle adjusting mechanism interfixes with evaporation ends cooling body or dismountable, for by calorimetric
The adjusting of tube angulation.The scope of the adjusting can realize the universal adjustment on space angle.When heat pipe to be measured is fixed on angle tune
After saving in mechanism, by adjusting angle adjusting mechanism, change the angle of heat pipe to be measured and surface water horizontal line, angle can be in 360 ° of models
Interior arbitrarily change is enclosed, in any angle such as horizontal, vertical, inversion, inclination.Heat pipe can so be simulated under differing tilt angles
Heat transfer property.On this basis, the adopting heat pipes for heat transfer performance to be measured under the state of weightlessness of space is drawn.
Further, a kind of Space Thermal tube performance testing experimental provision provided by the invention, also has a structure in which spy
Point：I.e., above-mentioned adopting heat pipes for heat transfer Performance Test System further includes condensation end thermal insulation mechanism mounting bracket；
Installation that above-mentioned condensation end thermal insulation mechanism mounting bracket interfixes with condensation end thermal insulation mechanism or dismountable, is used
In fixation and/or the adjusting of fixed angle that equipment is carried out to condensation end thermal insulation mechanism.During experiment, with treating calorimetric
The difference of pipe placed angle, the angle for adjusting and fixing the condensation end thermal insulation mechanism is identical with the angle of heat pipe to be measured, treats this
The condensation end of calorimetric pipe can keep coaxial effect with condensation end thermal insulation mechanism.
Further, a kind of Space Thermal tube performance testing experimental provision provided by the invention, also has a structure in which spy
Point：I.e., above-mentioned condensation end thermal insulation mechanism is formed by least one layer of coaxial thermal insulation/insulating layer intussusception installation；
When above-mentioned thermal insulation/insulating layer is more than one layer, each thermal insulation/insulating layer is dismountable installation.
Further, a kind of Space Thermal tube performance testing experimental provision provided by the invention, also has a structure in which spy
Point：I.e., acquisition and control system is further included, for the environment or equipment in experimental provision, carrying out data acquisition and control
System.
So as to realize the properties of hot pipe test under the conditions of different spaces, such as：Test under different temperatures or pressure environment
Heat-transfer capability, and the heat-transfer capability etc. under test different angle and reduced gravity situations.
Further, a kind of Space Thermal tube performance testing experimental provision provided by the invention, also has a structure in which spy
Point：I.e., above-mentioned acquisition and control system include data acquisition and control device, at least one temperature monitoring/sensor and
At least one pressure monitoring/sensor；
Wherein, above-mentioned temperature monitoring/sensor, and pressure monitoring/sensor are respectively arranged in following location extremely
At few one：Keep the temperature tank shell, incubator heat insulation layer, thermal-insulating body refrigerating oxidant layer, thermal-insulating body liner, refrigerating medium two and enter evaporation
Hold in the entrance and/or exit, heat pipe to be measured of cooling body, in condensation end thermal insulation mechanism；
Above-mentioned data acquisition and control device and temperature monitoring/sensor, pressure monitoring/sensor, and isoperibol
All or part of equipment electrical connection in case system, heat pipe evaporation ends cooling system and adopting heat pipes for heat transfer Performance Test System.
The function and effect of the present invention
The present invention provides a kind of Space Thermal tube performance testing experimental provision, including isoperibol case system, heat pipe to evaporate
Hold cooling system, adopting heat pipes for heat transfer Performance Test System and acquisition and control system.Heat pipe can be simulated by isoperibol case
Various Space-Work environment, biography that can be in ground simulation heat pipe under the state of weightlessness of space by adopting heat pipes for heat transfer Performance Test System
Hot property.The present invention solve space heat pipe ground carry out weightless flight heat transfer property test problem, have it is compact-sized,
The advantages of easy to operate.
In the present invention, refrigerating medium one is adjusted into the temperature of thermal-insulating body refrigerating oxidant layer by constant temperature unit one, to insulation
The temperature inside the box is controlled to simulate space temperature.The pressure such as the outer end opening of pressure control mouth and vacuum pump is adjusted in incubator
Equipment is connected, and pressure in incubator is controlled, and simulates the different pressures environment in space.
In the present invention, temperature of the adjusting refrigerating medium two of constant temperature unit two into evaporation ends cooling body, conveying mechanism are passed through
The flow of refrigerating medium two is adjusted, evaporation ends heat output is controlled.Refrigerating medium two is imported and exported according to evaporation ends cooling body
The temperature difference, flow calculate in real time the heat output of heat pipe.
In the present invention, the air blanketing spacing between the size of condensation end thermal insulation mechanism and heat pipe is adjustable, analogue zero weight
There was only the condensation end heat transfer situation of heat conduction during power without free convection.Interlayer spacing is adjusted according to heat pipe diameter, length, heat output
Section.
In the present invention, tested heat pipe is fixed on angular adjustment frame, by adjusting angle adjusting bracket, change tested heat pipe with
The angle of surface water horizontal line, angle can change in the range of 360 °, in the unspecified angle such as horizontal, vertical, inversion, inclination.So
Heat transfer property of the heat pipe under differing tilt angles can be simulated.On this basis, draw under the state of weightlessness of space by calorimetric
Pipe heat transfer property.
In addition, the performance test of ground heat pipe can also be applied to by the method for the present invention.
Brief description of the drawings
The structure diagram for the Space Thermal tube performance testing experimental provision that attached drawing 1, the present embodiment are related to；
Wherein, 1- thermal-insulating bodies shell；2- thermal-insulating body heat insulation layers；3- thermal-insulating body refrigerating oxidant layer；4- thermal-insulating bodies
Liner；5- thermostats 1；6- refrigerating mediums one；7- thermostats 2；8- refrigerating mediums two；9- flowmeters；10- water pumps；11- evaporation ends
Coolant jacket；12- is tested heat pipe；13- condensation end jackets；14- angular adjustment framves；16- evaporation ends coolant jacket import refrigeratings
Agent temperature point；16- evaporation ends coolant jacket exports refrigerant temperature measuring point；17- is tested the temperature of heat pipe and condensation end jacket
Spend pressure series measuring point；18- data acquisitions and control device；19- pipelines and line channel；Pressure controls in 20- incubators
Mouthful；21- vacuum pumps；22- condensation end jacket fixing brackets；Temperature and pressure series measuring point in 23- thermal-insulating bodies.
The structure diagram for the condensation end jacket that attached drawing 2, the present embodiment are related to.
Specific embodiment
As shown in Figure 1, present embodiments provide a kind of Space Thermal tube performance testing experimental provision, for heat pipe ground into
Heat transfer property test under row simulation space below-G conditions, including：Isoperibol case system, heat pipe evaporation ends cooling system, heat
Pipe heat transfer property tests system and acquisition and control system composition；
Wherein, the isoperibol case system, for simulating environment temperature and pressure of the heat pipe under the conditions of Space-Work, bag
Contain：Incubator, thermostat 1 (5), refrigerating medium one (6), pressure control mouth (20) in vacuum pump (21) and incubator.
The incubator is by thermal-insulating body shell (1), thermal-insulating body heat insulation layer (2), thermal-insulating body refrigerating oxidant layer (3) and insulation
Box liner (4), the setting of above layers from outside to inside.
The refrigerating medium 1 (6) is arranged in thermostat 1 (5), and the thermostat 1 (5) is by pipeline and thermal-insulating body refrigerating oxidant layer
(3) communicate, which is provided with refrigerating medium export and import, the refrigerating medium one (6) in its groove body flows into thermal-insulating body refrigerating from outlet
In oxidant layer (3), then by import inflow groove body, the circulation of a liquid phase being formed, so as to fulfill to thermal-insulating body liner (4)
Temperature adjustment.
Pressure control mouth (20) is arranged on the babinet of incubator in the incubator, penetrates through whole babinet, vacuum pump (21)
Incubator liner is vacuumized by pressure control mouth (20) in the incubator, during vacuumizing, passes through insulation
In case pressure control mouth (20) come control inside vacuum, pressure is reached the scope of setting.
The heat pipe evaporation ends cooling system, for simulating the temperature and heat of heat pipe evaporation ends, comprising：Thermostat 2 (7),
Refrigerating medium two (8), flowmeter (9) and water pump (10)；
The adopting heat pipes for heat transfer Performance Test System, for the test of space heat pipe heat transfer property, is arranged at thermal-insulating body liner
(4) in, comprising：Evaporation ends coolant jacket (11), is tested heat pipe (12), condensation end jacket (13), angular adjustment frame (14) and cold
Solidifying end jacket fixing bracket (22)；
The refrigerating medium two (8) is arranged in thermostat 2 (7), thermostat 2 (7) be equipped with refrigerating medium outlet and refrigerating medium into
Mouthful, evaporation ends coolant jacket (11) is equipped with the outlet of evaporation ends refrigerating medium and evaporation ends refrigerating medium import, and refrigerating medium outlet passes through pipe
Road 1 and evaporation ends refrigerating medium inlet communication, evaporation ends outlet are passed through by pipeline 2 and refrigerating medium inlet communication, refrigerating medium two (8)
The pipeline 1 enters in evaporation ends coolant jacket (11), after flowing through whole evaporation ends coolant jacket (11), by pipeline 2 by refrigerating medium into
Mouth is returned in thermostat 2 (7), and water pump (10) is equipped with pipeline 1, for refrigerating medium two (8) to be sent into evaporation ends coolant jacket
(11) in, flowmeter (9) is equipped with pipeline 2, for monitoring the flow of refrigerating medium two in real time.
The evaporation ends coolant jacket (11) can also be replaced to simulate heat output with electrical heating etc..
As shown in Fig. 2, the condensation end jacket (13) is formed by the coaxial heat-insulating material intussusception of multilayer, by since internal layer
Each layer can be extracted out, so as to adjust the air blanketing spacing between the condensation end jacket and the tested heat pipe.The condensation
Hold jacket (11) identical with tested heat pipe (12) shape, can be cylinder, square column type etc..The condensation end jacket (11)
Heat-insulating material can be any type thermal insulation material and structure.
In addition, the size of the condensation end jacket (13) can also be come according to the length of different heat pipes, width and radial width
It is adjusted.
The angular adjustment frame (14) is arranged at the lower section of evaporation ends coolant jacket (11), is used to support tested heat pipe and heat pipe and steams
Originator coolant jacket (11), the angular adjustment frame (14) are equipped with everything rotation axis, can be to being tested heat pipe by the rotation to the axis
The angle of placement carries out the adjusting of 360 ° of any angle scopes.
The condensation end jacket fixing bracket (22) is arranged at the lower section of condensation end jacket (13), is used to support by calorimetric
Pipe and condensation end of heat pipe jacket (13), and the controllable support condensation end jacket of the condensation end jacket fixing bracket (22)
(13) angle, during experiment, with the difference of tested heat pipe placed angle, adjusts and fixes the condensation end jacket
(13) angle is identical with the angle of tested heat pipe, tested condensation end of heat pipe (11) is kept same with condensation end jacket (13)
Axis.
The acquisition and control system, data acquisition and equipment control for experimental provision, comprising：Evaporation ends cool down
Import refrigerant temperature measuring point (15) is covered, evaporation ends coolant jacket outlet refrigerant temperature measuring point (16), is tested heat pipe and condensation end
The temperature, pressure series measuring point (17) of jacket, the temperature and pressure series measuring point (23) in liner, data acquisition are filled with control
Put (18).
The data acquisition is electrically connected with control device (18) and the sensor of each temperature or pressure-measuring-point, so as to real-time
Gather the temperature and pressure parameter of each measuring point.
Meanwhile the data acquisition and control device (18) also with thermostat 1 (5), thermostat 2 (7), flowmeter (9), water pump
(10), vacuum pump (21), condensation end jacket (13), angular adjustment frame (14) and condensation end jacket fixing bracket (22) are electric
Connection, can be controlled each equipment according to the requirement of test, so as to pass through adjusting ambient temperature, pressure, the temperature of evaporation ends
The angle of degree and tested heat pipe obtains the adopting heat pipes for heat transfer results of property under different condition.
The specifically used method of the present embodiment experimental provision：
Refrigerating medium one is adjusted into the temperature of thermal-insulating body refrigerating oxidant layer by thermostat 1, insulation the temperature inside the box is controlled
Make to simulate space temperature.
The outer end opening of pressure control mouth is connected with pressure adjustment devices such as vacuum pumps in incubator, by incubator
Pressure is controlled, and simulates the different pressures environment in space.
Refrigerating medium two is adjusted into the temperature of evaporation ends coolant jacket, the flow of testing pump refrigerating medium by thermostat 2, to steaming
Originator heat is controlled.The temperature difference of refrigerating medium two is imported and exported according to evaporation ends coolant jacket, flow carries out calculating heat pipe in real time
Heat output.
By the adjusting of the air blanketing spacing between the size to condensation end jacket and heat pipe, during zero-gravity simulation
No free convection only has the condensation end heat transfer situation of heat conduction.Interlayer spacing is adjusted according to heat pipe diameter, length, heat output.
After tested heat pipe is fixed on angular adjustment frame, by adjusting angle adjusting bracket, change tested heat pipe and the surface water
The angle of horizontal line, angle can change in the range of 360 degree, in the unspecified angle such as horizontal, vertical, inversion, inclination.So can be with mould
Intend heat transfer property of the heat pipe under differing tilt angles.On this basis, the tested adopting heat pipes for heat transfer under the state of weightlessness of space is drawn
Performance.
Claims (10)
1. a kind of Space Thermal tube performance testing experimental provision, carries out under simulation space below-G conditions for space heat pipe on ground
Heat transfer property is tested, it is characterised in that including：Isoperibol case system, heat pipe evaporation ends cooling system and adopting heat pipes for heat transfer performance
Test system；
Wherein, the isoperibol case system, for simulating environment temperature and pressure of the heat pipe under the conditions of Space-Work；
The heat pipe evaporation ends cooling system, for simulating the temperature and heat of heat pipe evaporation ends；
The adopting heat pipes for heat transfer Performance Test System, the test of heat transfer property is carried out for opposite heat tube.
A kind of 2. Space Thermal tube performance testing experimental provision as claimed in claim 1, it is characterised in that：
The isoperibol case system includes heat-insulation unit, constant temperature unit one, pressure control unit；
Wherein, the constant temperature unit one, for adjusting and controlling the temperature of isoperibol case system；
The pressure control unit, for adjusting and controlling the pressure of isoperibol case system；
The heat-insulation unit, for being kept the temperature to isoperibol case.
A kind of 3. Space Thermal tube performance testing experimental provision as claimed in claim 2, it is characterised in that：
The heat-insulation unit includes ecto-entad, successively the insulation tank shell of packaging type setting layer by layer, incubator heat insulation layer, insulation
Babinet refrigerating oxidant layer and thermal-insulating body liner；
The constant temperature unit one includes thermostat, and the thermostat is connected with thermal-insulating body refrigerating oxidant layer, and formation is recycled back to
Road, the refrigerating medium one of recyclable flowing is conveyed to thermal-insulating body refrigerating oxidant layer；
The pressure control unit includes pressure control component, and the pressure control component is connected with the inner space of the heat-insulation unit, to institute
State the regulation and control that the space inside heat-insulation unit carries out pressure.
A kind of 4. Space Thermal tube performance testing experimental provision as claimed in claim 1, it is characterised in that：The heat pipe evaporation ends
Cooling system includes constant temperature unit two；
The adopting heat pipes for heat transfer Performance Test System, is arranged at the inside of isoperibol case system, including evaporation ends cooling body and
Condensation end thermal insulation mechanism；
The constant temperature unit two is connected with evaporation ends cooling body, forms liquid circulation loop, defeated into evaporation ends cooling body
Send the refrigerating medium two of recyclable flowing.
The condensation end thermal insulation mechanism is adjustable structure for the air blanketing spacing between condensation end of heat pipe.
A kind of 5. Space Thermal tube performance testing experimental provision as claimed in claim 4, it is characterised in that：
The constant temperature unit two includes refrigerating medium outlet 1 and refrigerating medium import 1；
The evaporation ends cooling body includes refrigerating medium import 2 and refrigerating medium outlet 2；
Wherein, the refrigerating medium outlet 1 of the constant temperature unit two is connected with the refrigerating medium import 2 of evaporation ends cooling body；The steaming
The refrigerating medium outlet 2 of originator cooling body is connected with the refrigerating medium import 1 of the constant temperature unit two, forms refrigerating medium loop；
The refrigerating medium loop is equipped with liquid transporting body；
The refrigerating medium loop is equipped with flow metering devices.
A kind of 6. Space Thermal tube performance testing experimental provision as claimed in claim 4, it is characterised in that：
The adopting heat pipes for heat transfer Performance Test System further includes angle adjusting mechanism；
Installation that the angle adjusting mechanism interfixes with evaporation ends cooling body or dismountable, for being tested heat pipe
Angle of inclination carries out the adjusting of 360 degree of scopes.
A kind of 7. Space Thermal tube performance testing experimental provision as claimed in claim 4, it is characterised in that：
The adopting heat pipes for heat transfer Performance Test System further includes condensation end thermal insulation mechanism mounting bracket；The condensation end thermal insulation mechanism consolidates
Installation that fixed rack interfixes with condensation end thermal insulation mechanism or dismountable, for carrying out equipment to condensation end thermal insulation mechanism
Fixed and/or fixed angle adjusting.
A kind of 8. Space Thermal tube performance testing experimental provision as claimed in claim 4, it is characterised in that：
The condensation end thermal insulation mechanism is formed by least one layer of coaxial thermal insulation/insulating layer intussusception installation；
When the thermal insulation/insulating layer is more than one layer, each thermal insulation/insulating layer is dismountable installation.
A kind of 9. Space Thermal tube performance testing experimental provision as described in claim 1-8 is any, it is characterised in that：Further include number
According to collection and control system, for the environment or equipment in experimental provision, carrying out data acquisition and control.
A kind of 10. Space Thermal tube performance testing experimental provision as claimed in claim 9, it is characterised in that：
The acquisition and control system includes data acquisition and control device, at least one temperature monitoring/sensor and extremely
A few pressure monitoring/sensor；
Wherein, the temperature monitoring/sensor, and pressure monitoring/sensor be respectively arranged in following location at least one
Place：It is cold into evaporation ends to keep the temperature tank shell, incubator heat insulation layer, thermal-insulating body refrigerating oxidant layer, thermal-insulating body liner, refrigerating medium two
But the entrance of mechanism and/or exit, on tested heat pipe, in condensation end thermal insulation mechanism；
The data acquisition and control device and temperature monitoring/sensor, pressure monitoring/sensor, and isoperibol case system
All or part of equipment electrical connection in system, heat pipe evaporation ends cooling system and adopting heat pipes for heat transfer Performance Test System.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201711166964.3A CN108020581A (en) | 2017-11-21 | 2017-11-21 | A kind of Space Thermal tube performance testing experimental provision |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711166964.3A CN108020581A (en) | 2017-11-21 | 2017-11-21 | A kind of Space Thermal tube performance testing experimental provision |
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| CN108020581A true CN108020581A (en) | 2018-05-11 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110174432A (en) * | 2019-06-26 | 2019-08-27 | 重庆理工大学 | The thermophoresis experimental provision of Electronic Packaging microbonding point |
| CN110261433A (en) * | 2019-07-05 | 2019-09-20 | 西安交通大学 | A kind of removal model experimental device of aviation gas turbine movable vane internal heat transfer |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105259208A (en) * | 2015-11-23 | 2016-01-20 | 上海卫星装备研究所 | Heat performance test device and method for heat pipe under vacuum |
| CN206505336U (en) * | 2017-02-28 | 2017-09-19 | 海口未来技术研究院 | High/low temperature hypobaric experiment bin |
-
2017
- 2017-11-21 CN CN201711166964.3A patent/CN108020581A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105259208A (en) * | 2015-11-23 | 2016-01-20 | 上海卫星装备研究所 | Heat performance test device and method for heat pipe under vacuum |
| CN206505336U (en) * | 2017-02-28 | 2017-09-19 | 海口未来技术研究院 | High/low temperature hypobaric experiment bin |
Non-Patent Citations (1)
| Title |
|---|
| 刘业凤 等: ""一种新型低温热管传热性能的试验研究"", 《流体机械》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110174432A (en) * | 2019-06-26 | 2019-08-27 | 重庆理工大学 | The thermophoresis experimental provision of Electronic Packaging microbonding point |
| CN110261433A (en) * | 2019-07-05 | 2019-09-20 | 西安交通大学 | A kind of removal model experimental device of aviation gas turbine movable vane internal heat transfer |
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Application publication date: 20180511 |