CN107607230A - A kind of probe and method for measuring hall thruster wall ion hot-fluid - Google Patents
A kind of probe and method for measuring hall thruster wall ion hot-fluid Download PDFInfo
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Abstract
A kind of probe and method for measuring hall thruster wall ion hot-fluid, it is related to a kind of temperature measuring device and method, and to solve the problems, such as that existing measurement hall thruster wall ion deposition power is in technical bottleneck, it includes metallic rod, radiating block and temperature thermometric line；Metallic rod connects radiating block, is also equipped with thermometric boss in metallic rod, thermometric boss connects temperature thermometric line respectively on two surfaces relative with radiating block, and metallic rod, thermometric boss and radiating block are non-magnetic rustproof Steel material.The step of this method is：Step 1: bore mounting hole on hall thruster ceramics wall；Step 2: it is respectively arranged several temperature thermometric lines on two relative faces of thermometric boss and radiating block；Step 3: the metallic rod of cladding heat-insulating material is arranged in mounting hole；Step 4: start hall thruster, probe, which reaches, to be measured the temperature of probe axial direction diverse location after hot stable state and can obtain hot-fluid.The present invention is used for the measurement of hall thruster wall ion deposition hot-fluid.
Description
Technical field
The present invention relates to a kind of temperature measuring device and method, and in particular to a kind of measurement hall thruster wall ion hot-fluid
Probe and method.
Background technology
Hall thruster is a kind of using crossed electric and magnetic field ionization and acceleration working medium, so as to convert electrical energy into the dynamic of kinetic energy
Power apparatus.It has it is simple in construction, than leaping high, efficiency high, long working life, that power density is high, in-orbit active time is long etc. is excellent
Gesture, suitable for the gesture stability of all kinds of spacecrafts, orbital exponent, Orbit Transformation, power compensation, position keep, reposition, from
The tasks such as rail processing, survey of deep space, it is at present in the world using at most most ripe electric thruster.
Compared to chemical propulsion, hall thruster have one it is important the advantages of be efficiency high, at present, hall thruster
Gross efficiency generally 50% or so, but the efficiency of high voltage and small-power hall thruster is generally relatively low, it is therefore desirable to grinds
Study carefully hall thruster internal energy conversion process, establish rational energy loss system, analyze each several part energy loss.It is existing to grind
Study carefully display, the main energy loss in the hall thruster course of work has：Wall heat deposition, anode heat deposition, plume diverging damage
Lose.Therefore, wall heat deposition mechanism is studied, and how to reduce wall heat deposition to turn into an important problem.
In the hall thruster course of work, its wall is exposed in plasma environment, wall heat deposition comes from etc. from
Daughter and the interaction of insulation wall.Research currently for hall thruster wall heat deposition is concentrated mainly on theoretical model
Prediction and numerical value dummy run phase, there are two kinds of different sayings for wall heat deposition mechanism on theory analysis：First, think electronics
Quality be far smaller than mass of ion, ignore electronic deposition power；Second, think that electronics and wall action can produce substantial amounts of two
Secondary electronics, quantitatively it is more than ion with the electronics of wall action, electronic deposition power is more than ion deposition power, therefore is directed to
The research of hall thruster wall heat deposition needs a kind of laboratory facilities to enter electronic deposition power and ion deposition power
Row is distinguished.
Wall electronic deposition power Pe=Ie,in·Te,in-Ie,out·Te,out, wherein, Ie,inFor wall incident electron fluence,
Te,inFor wall incident electron average energy, Ie,outFor wall outgoing electron flux, Te,outFor wall outgoing electron average energy.
Measurement wall electronic deposition power needs average energy to incident electron and outgoing electron and flux to diagnose, at present for
The technology of hall thruster plasma diagnostics mainly has two kinds of spectroscopic diagnostics and probe diagnostics, and either spectroscopic diagnostics is still visited
Pin measurement can not all be made a distinction to the information of incident electron and outgoing electron, therefore wall heat can only be measured by laboratory facilities
Ion deposition power in deposition power.After ion and collision with wall with electronics is compound rebounds out as atom, measurement ion
Deposition power needs to diagnose the information such as the angle of wall ionic flux, ion energy and ion incidence wall, at present
The means of possessed diagnosis ion energy are mainly RPA probes, and RPA probe volumes are bigger, tied by hall thruster
Structure limits, it is impossible to which inside the discharge channel of hall thruster, Langmuir probe small volume can be used in discharge channel
Portion, but can only obtain ionic flux, it is impossible to diagnose ion energy.Therefore, discharge plasma environment and existing diagnosis hand
The shortcomings that section, forms technical bottleneck to direct measurement wall ion deposition power.
The content of the invention
The present invention is to solve the problems, such as that existing measurement hall thruster wall ion deposition power is in technical bottleneck, carrying
A kind of probe and method for measuring hall thruster wall ion hot-fluid is supplied.
The present invention adopts the technical scheme that to solve the above problems：
A kind of probe for measuring hall thruster wall ion hot-fluid includes metallic rod, radiating block and temperature thermometric line；Gold
Belong to bar connection radiating block, thermometric boss is also equipped with metallic rod, is distinguished on thermometric boss two surfaces relative with radiating block
Temperature thermometric line is connected, metallic rod, thermometric boss and radiating block are non-magnetic rustproof Steel material.
Further, metallic rod, thermometric boss and radiating block are same by being made into integration without magnetic 1Cr18Ni9Ti stainless steels
Heart cylinder.
Further, temperature thermometric line is electric thermo-couple temperature thermometric line.
Further, heat-insulating material is adiabatic coating.
Originally return and a kind of method for measuring hall thruster wall ion hot-fluid is provided, be the step of this method：
Step 1: bore mounting hole on hall thruster ceramics wall；
Step 2: it is respectively arranged several temperature thermometric lines, temperature on two relative faces of thermometric boss and radiating block
The end of probe of thermometric line is connected on thermometric boss and radiating block, and the output end of temperature thermometric line leads to acquisition system；
Step 3: the end of metallic rod to the metallic rod between thermometric boss and thermometric boss is coated with heat-insulating material,
The metallic rod for coating heat-insulating material is arranged in mounting hole, metallic rod front end and heat-insulating material is flushed with ceramic wall face bottom；
Step 4: starting hall thruster, after hall thruster wall surface temperature reaches stable, provided necessarily to probe
Negative potential, electronics is masked completely, while the ion that probe receives reaches saturation；
Probe, which reaches, to be measured the temperature of probe axial direction diverse location after hot stable state and can obtain hot-fluid, is expressed as：
Q-probe measurement hot-fluid, unit：Watt；
The thermal conductivity factor of λ-probe；Probe material 1Cr18Ni9Ti thermal conductivity factor is 21W/ (mK)；
The temperature of T-probe, unit：K；
A-probe front face area, unit：m2；A=π D2/4；D is metal shank diameter, unit：m；
Z-probe axial distance, unit：m；
Wherein, axial displacement of the temperature thermometric line end of probe apart from radiating block bottom surface is z in thermometric boss surface1, measurement
Temperature averages are T1；
Temperature thermometric line end of probe distance probes radiating block at the end of the axial displacement on heat dissipation block surface is z2, measurement temperature
Average value is T2。
Present invention beneficial effect compared with prior art is：The probe of the present invention can be used for macroscopical heat-flow measurement, can will suddenly
That thruster course of work plasma and the complicated microphysics process of wall action are showed by macroscopical hot-fluid, and
And available for the ion deposition heat-flow measurement in wall heat deposition, so as to which electronic deposition, ion deposition in wall heat deposition be entered
Row is distinguished, and a kind of laboratory facilities are provided to research hall thruster internal plasma and the mechanism of wall action.
Brief description of the drawings
Fig. 1 is the probe structure schematic diagram of the present invention；
Fig. 2 is probe temperature measurement location schematic diagram of the present invention；
Fig. 3 is probe and hall thruster assembling schematic diagram；
Fig. 4 is thermal probe biasing circuit figure；
Fig. 5 is emulation detection schematic diagram in the embodiment of the present invention.
Embodiment
Technical solution of the present invention is further described with reference to the accompanying drawings and examples.
As shown in figure 1, a kind of probe for measuring hall thruster wall ion hot-fluid includes metallic rod 1, radiating block 3 and temperature
Spend thermometric line 6；Metallic rod 1 connects radiating block 3, and thermometric boss 2, thermometric boss 2 and the phase of radiating block 3 are also equipped with metallic rod 1
To two surfaces on connect temperature thermometric line 6 respectively, metallic rod 1, thermometric boss 2 and radiating block 3 are non-magnetic rustproof steel
Material.
Present embodiment totally calculates the technological means of hot-fluid using metal electrode shielding electronics, thermocouple temperature measurement, realizes
Hall thruster wall heat deposition intermediate ion deposition power and the purpose of electronic deposition power are distinguished, probe structure is completed and sets
Meter, the thermal probe of installation instead of the sub-fraction of original ceramic wall, plasma and probe in the thruster course of work
Front end face directly acts on generation heat deposition, and the hot-fluid of deposition can be conducted to other structures, by being connect in probe and thruster
Tactile surface spraying heat-insulating material cut-off heat conduction, the hot-fluid that probe receives can only axially conduct along probe, and probe reaches
After hot stable state, internal thermal process is regarded as one-dimensional stable heat transfer, and the hot-fluid that probe front face receives is equal to metallic rod rear portion
Divide conduction hot-fluid, therefore measure the temperature of probe rear end axially distinct position (outside thruster), utilize Fourier Heat Conduction law
It can obtain plasma-deposited hot-fluid.
Illustrate referring to Fig. 1, for the ease of processing probe, and reduce thermal loss, improve the precision of measurement, the spy of design
Metallic rod 1, thermometric boss 2 and radiating block 3 are the concentric cylinder by being made into integration without magnetic 1Cr18Ni9Ti stainless steels in pin.Survey
Warm boss 2 along metallic rod 1 circumferentially.So ensure the temperature stabilization that the temperature thermometric line 6 arranged on thermometric boss 2 is surveyed
Reliably.
The size of probe is mainly determined by the physical dimension and power grade of hall thruster, first can be divided using ANSYS heat
Analyse module and calculate temperature, the temperature of 1 front end face of metallic rod 4 is worked with hall thruster to wall surface temperature during hot stable state and be close to
Preferably.Present embodiment is for HEP100HV hall thrusters (outlet outer ceramic wall thickness 9mm, discharge power 3000w), as one
Individual embodiment, metallic rod 1, thermometric boss 2 and radiating block 3 are concentric cylinder, 1 a diameter of 1mm of metallic rod, and overall length is
40mm, thermometric boss 2 a diameter of 5mm, axial length 1mm, the front end face 5 of thermometric boss 2 and the distance of front end face 4 of metallic rod 1
10mm, ensure that thermometric boss 2 can be placed on outside hall thruster ceramics wall or magnetic cup, on metallic rod front end face 4 to metallic rod 2
1mm is apart from all side sprayed thermal insulants, in order to reduce cost, convenient work, it is preferable that the adiabatic paint of spraying, radiating block 3 it is straight
Footpath is 12mm, axial length 10mm.Influence to reduce the heat radiation on each surface, be processed by shot blasting surface during processing,
Reduce radiant emissivity.
The present embodiment middle probe is mainly used in the measurement of HEP100HV hall thrusters wall heat flux, due to hall thruster table
Face size is smaller, is easily installed, and temperature thermometric line 6 uses thermocouple temperature measurement line.In thermometric boss 2 and the phase of radiating block 3 during measurement
To two surfaces on thermocouple temperature measurement line is installed respectively, such as the 7-1 of surface one in Fig. 1 and the 7-2 positions of surface two.Thermocouple temperature measurement
Line is arranged as shown in Fig. 2 to avoid uncertainty present in thermocouple individual error and experiment, it is preferable that convex in thermometric
Two thermocouple temperature measurement lines are installed, the surface of radiating block 3 is larger, installs four thermocouple temperature measurement lines on platform 2.The principle of measurement is
Based on Fourier Heat Conduction law, when probe does not have outside heat transfer, the thermal process in metallic rod 1 can be approximately that one-dimensional stable is led
Thermal process, probe, which reaches, to be measured the temperature of probe axial direction diverse location after hot stable state and can obtain hot-fluid, and its heat conduction heat flux can table
It is shown as：
Q-probe heat conduction heat flux；
The thermal conductivity factor of λ-probe；Probe material 1Cr18Ni9Ti thermal conductivity factor is 21W/ (mK)；
The temperature of T-probe；
A-probe receiving area；
Z-probe axial distance.
With reference to Fig. 1-Fig. 3 illustrate, using probe measurement hall thruster wall ion hot-fluid method the step of be：
Step 1: bore mounting hole on 8 ceramic wall of hall thruster；
Step 2: several temperature thermometric lines are respectively arranged on two relative faces of thermometric boss 2 and radiating block 3, temperature
The end of probe of degree thermometric line is connected on thermometric boss 2 and radiating block 3, and the output end of temperature thermometric line leads to acquisition system；
Step 3: by the end of metallic rod 1 to the metallic rod 1 between thermometric boss 2 and the heat-insulating material bag of thermometric boss 2
Cover, the metallic rod 1 for coating heat-insulating material is arranged in mounting hole, makes the front end of metallic rod 1 and heat-insulating material and ceramic wall face bottom
Flush；
Step 4: starting hall thruster 8, after the wall surface temperature of hall thruster 8 reaches stable, provided to probe certain
Negative potential, electronics is masked completely, at the same probe receive ion reach saturation；
Probe, which reaches, to be measured the temperature of probe axial direction diverse location after hot stable state and can obtain hot-fluid, is expressed as：
Q-probe measurement hot-fluid, unit：Watt；
The thermal conductivity factor of λ-probe；Probe material 1Cr18Ni9Ti thermal conductivity factor is 21W/ (mK)；
The temperature of T-probe, unit：K；
A-probe front face area, unit：m2；A=π D2/4；D is metal shank diameter, unit：m；
Z-probe axial distance, unit：m；
Wherein, axial displacement of the end of probe of temperature thermometric line 6 apart from the bottom surface of radiating block 3 is z on the surface of thermometric boss 21, survey
Amount temperature average value is T1；
The at the end of the axial displacement of 6 end of probe distance probes radiating block of temperature thermometric line 3 on the surface of radiating block 3 is z2, measurement
Temperature averages are T2。
Simply illustrate the principle of probe measurement hot-fluid herein and the Method And Principle of hot-fluid is obtained by temperature.
Punched during use on thruster ceramics wall (magnetic cup), by the side surface of metallic rod 1 of probe (position 9 in such as Fig. 3
The shown adiabatic paint (thermal conductivity factor is less than 0.2W/ (mK)) of spraying is installed afterwards, as shown in figure 3, making the front end of metallic rod 1 of probe
Face, adiabatic lacquer coat are concordant with the inside of ceramic wall 8.
The energy obtained in the electric field directly and wall action, is converted into wall by thruster course of work plasma
Heat energy, this part energy, which, is converted into the kinetic energy of propulsion, but transfers heat to shell etc. by heat transfer and tie
Structure, and then be dissipated in the form of heat radiation in environment.The thermal probe of installation instead of original pottery in the thruster course of work
The sub-fraction of porcelain wall, plasma directly act on generation heat deposition with probe front face, and the hot-fluid of deposition can be tied to other
Structure is conducted, and separating heat by the surface spraying heat-insulating material contacted in probe with thruster conducts, the heat that probe receives
Stream can only axially conduct along probe, and after probe reaches hot stable state, internal thermal process is regarded as one-dimensional stable heat transfer, probe
The hot-fluid that front end face receives is equal to partial conductance hot-fluid after metallic rod, therefore it is axially distinct (outside thruster) to measure probe rear end
The temperature of position, plasma-deposited hot-fluid is can obtain using Fourier Heat Conduction law, plasma-deposited hot-fluid can represent
For：
qplasma- plasma-deposited hot-fluid, unit：Watt；
qconduct- probe axially conducts hot-fluid, unit：Watt；
The thermal conductivity factor of λ-probe；Probe material 1Cr18Ni9Ti thermal conductivity factor is 21W/ (mK)；
The temperature of T-probe, unit：K；
A-probe front face area, unit：m2；A=π D2/4；D is metal shank diameter, unit：m；
Z-probe axial distance, unit：m.
Thruster course of work middle probe receives the hot-fluid of electronics, ion deposition simultaneously, if probe is connected to such as Fig. 4 institutes
In the external circuitses shown, certain negative potential is provided to probe, electronics is masked completely, while the ion that probe receives reaches
Saturation, the hot-fluid that now probe receives is exactly ion deposition hot-fluid.Because the negative bias potential added by probe can change probe
The local ion velocity of reception, therefore the hot-fluid measured is more than wall ion deposition hot-fluid in the thruster course of work, therefore first
Using thermal probe as Langmuir Single probe, C-V characteristic is measured, obtains the scope of ion saturation region bias potential, within this range
Select several bias potential U1、U2、U3、U4, measure ion hot-fluid respectively under different bias potentials, obtain the potential of thermal probe-
Heatflow characteristics relation.
The ion hot-fluid of deposited probes is represented by：
qion=qi·ΔUi·Ii (3)
qion- ion deposition hot-fluid, unit：Watt；
qiElectrically charged, the unit of-ion：Storehouse；
ΔUi- ion is poor when earth potential and probe potential, unit：Volt；
IiThe ionic flux of-sensing wall.
The energy that electric charge obtains in the electric field is multiplied by electrical potential difference equal to the quantity of electric charge, and ion is got on wall and just transmits energy
Wall has been given, has formed the hot-fluid of wall, but the position that probe is installed in thruster course of normal operation is ceramic wall, is not have
There is applying electrical potential, the effect of probe applying electrical potential is that electron repelling is walked, and the additional effect brought is exactly to change ion
Speed, thus measure in the case of probe applying electrical potential the hot-fluid come and the hot-fluid that actual ions deposit be it is unequal, because
This is needed to measure hot-fluid under different bias potentials, and actual ion deposition is obtained by potential-heatflow characteristics relation of thermal probe
Hot-fluid.
As shown in formula (3), the hot-fluid of ion deposition and ion are linear when earth potential and probe potential difference, by heat
The potential of probe-heatflow characteristics relation (straight line seeks slope), counter can push away ion hot-fluid when bias potential is zero, i.e. thruster
Ion truly deposits to the hot-fluid of wall formation during normal work.
Thermal probe be typically mounted at hall thruster channel outlet nearby wall, thruster work when thermal probe exposed to etc.
In gas ions environment, can plasma electric discharge produce slight interference, therefore the size of metal electrode is small, with reduce equity from
The interference of daughter electric discharge, probe adds negative bias potentials when measuring ion hot-fluid, therefore thermal probe is carried out in installation process with pushing away
Insulating, be adiabatic between power device structure.
The present embodiment by taking the physical dimension of high voltage hall thruster as an example, introduce apply for a patent probe structure design,
Heat probe measurement principle, data processing method, Fig. 1 give probe Each part schematic diagram, and Fig. 2 is thermal probe temperature measurement location
Schematic diagram, Fig. 3 are thermal probe and hall thruster assembling schematic diagram, and Fig. 4 is thermal probe biasing circuit figure.The design of probe needs root
Factually the thruster structural member size used in test amount and power grade determine, the design of radiating block can be first with ANSYS heat point
Analyse module and calculate probe temperature distribution, adjustment size makes probe tip temperature be approached with temperature in use environment, reduces spy with this
Heat radiation of the needle tip into environment on caused by measurement accuracy influence, while it is noted that probe use material temperature limiting,
Adjusting probe size according to result of calculation makes probe face temperature less than the fusing point of material.
Thermal probe Proof-Of Principle process of the present invention：Model is established, is calculated using the temperature of ANSYS thermal analysis modules calculating
Probe measures hot-fluid.Thermal probe material uses 1Cr18Ni9Ti, and thermal conductivity factor is 21W/ (mK), and the thermal conductivity factor of thermal insulation paint is set
0.1W/ (mK) is set to, applies 0.1w thermal forces in probe front face, and considers the environment spoke in probe front face in a model
Penetrate, result of calculation is as shown in Figure 5.Two temperature measuring point temperature computation results during thermal probe use be respectively 259.26 DEG C and
It is 115.42 DEG C, as follows to calculate hot-fluid by the use of this temperature as probe measurement temperature：
The hot-fluid that is calculated and the hot-fluid error that truly inputs are 1.1%, and therefore, this detecting probe method is reliable.Formula (4)
This is exactly the calculating temperature obtained with formula (2) and emulation.
Consider that factor, measurement result and the actual hot-fluids such as thermocouple measurement error have deviation in actual measurement, it is therefore desirable to
Experimental result is verified, in ANSYS thermal analysis modules, the heat flow value for testing measurement set as primary condition, meter
Probe each several part Temperature Distribution is calculated, takes the temperature computation result of experiment middle probe temperature measuring point, then carry out with the temperature of experiment measurement
Contrast, if deviation, within 10%, measurement result is reliable.
The present invention is disclosed as above with preferable case study on implementation, but is not limited to the present invention, any to be familiar with this specialty
Technical staff, without departing from the scope of the present invention, according to the present invention technical spirit to above case study on implementation institute
Any simple modification, equivalent change and modification done, still belongs to technical solution of the present invention scope.
Claims (8)
- A kind of 1. probe for measuring hall thruster wall ion hot-fluid, it is characterised in that：It includes metallic rod (1), radiating block And temperature thermometric line (6) (3)；Metallic rod (1) connects radiating block (3), and thermometric boss (2), thermometric are also equipped with metallic rod (1) Temperature thermometric line (6), metallic rod (1), thermometric boss (2) are connected on boss (2) two surfaces relative with radiating block (3) respectively It is non-magnetic rustproof Steel material with radiating block (3).
- A kind of 2. probe for measuring hall thruster wall ion hot-fluid according to claim 1, it is characterised in that：Thermometric is convex Platform (2) along metallic rod (1) circumferentially.
- A kind of 3. probe for measuring hall thruster wall ion hot-fluid according to claim 1 or claim 2, it is characterised in that：Gold Category bar (1), thermometric boss (2) and radiating block (3) are the concentric cylinder by being made into integration without magnetic 1Cr18Ni9Ti stainless steels.
- A kind of 4. probe for measuring hall thruster wall ion hot-fluid according to claim 3, it is characterised in that：Temperature is surveyed Warm line (6) is electric thermo-couple temperature thermometric line.
- 5. according to a kind of probe for measuring hall thruster wall ion hot-fluid of claim 1,2 or 4, it is characterised in that： All sides of metallic rod (1) scribble heat-insulating material.
- A kind of 6. probe for measuring hall thruster wall ion hot-fluid according to claim 5, it is characterised in that：Heat insulating material Expect for adiabatic coating.
- 7. according to a kind of probe for measuring hall thruster wall ion hot-fluid of claim 1,2,4 or 6, its feature exists In：The distance of the front end face (5) of thermometric boss (2) and the front end face (4) of metallic rod (1) is 10mm.
- A kind of 8. method for measuring hall thruster wall ion hot-fluid, it is characterised in that：The step of this method is：Step 1: bore mounting hole on hall thruster ceramics wall；Step 2: several temperature thermometric lines (6) are respectively arranged on two relative faces of thermometric boss (2) and radiating block (3), The end of probe of temperature thermometric line (6) is connected on thermometric boss (2) and radiating block (3), and the output end of temperature thermometric line (6) is drawn To acquisition system；Step 3: heat insulating material is used into the end of metallic rod (1) to the metallic rod (1) between thermometric boss (2) and thermometric boss (2) Material cladding, the metallic rod (1) for coating heat-insulating material are arranged in mounting hole, make metallic rod (1) front end and heat-insulating material and ceramics Wall bottom hole flushes；Step 4: starting hall thruster, after hall thruster wall surface temperature reaches stable, certain negative electricity is provided to probe Position, electronics is masked completely, while the ion that probe receives reaches saturation；Probe, which reaches, to be measured the temperature of probe axial direction diverse location after hot stable state and can obtain hot-fluid, is expressed as：<mrow> <mi>q</mi> <mo>=</mo> <mi>&lambda;</mi> <mi>A</mi> <mfrac> <mrow> <mi>d</mi> <mi>T</mi> </mrow> <mrow> <mi>d</mi> <mi>z</mi> </mrow> </mfrac> <mo>=</mo> <mi>&lambda;</mi> <mi>A</mi> <mfrac> <mrow> <msub> <mi>T</mi> <mn>1</mn> </msub> <mo>-</mo> <msub> <mi>T</mi> <mn>2</mn> </msub> </mrow> <mrow> <msub> <mi>z</mi> <mn>1</mn> </msub> <mo>-</mo> <msub> <mi>z</mi> <mn>2</mn> </msub> </mrow> </mfrac> </mrow>Q-probe measurement hot-fluid, unit：Watt；The thermal conductivity factor of λ-probe；Probe material 1Cr18Ni9Ti thermal conductivity factor is 21W/ (mK)；The temperature of T-probe, unit：K；A-probe front face area, unit：m2；A=π D2/4；D is metal shank diameter, unit：m；Z-probe axial distance, unit：m；Wherein, axial displacement of temperature thermometric line (6) end of probe apart from radiating block (3) bottom surface is z on thermometric boss (2) surface1, Measurement temperature average value is T1；Temperature thermometric line (6) end of probe distance probes radiating block (3) at the end of the axial displacement on radiating block (3) surface is z2, measurement Temperature averages are T2。
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