Monochromatic infrared temperature calibration method for space station electrostatic levitation experiment

Abstract

The present application relates to a kind of monochromatic infrared temperature calibration methods for space station electrostatic suspension experiment, existing temperature data are calibrated in combination with characteristic temperature, can obtain corrected monochromatic infrared emissivity and calibrated temperature, solve the monochromatic infrared temperature calibration problem obtained in space station electrostatic suspension containerless experiment.In addition, for the problem that monochromatic infrared emissivity is difficult to quickly and accurately adjust in space station electrostatic suspension containerless experiment, the method proposed in the present application helps to realize the quick calibration of monochromatic infrared emissivity in space station electrostatic suspension containerless experiment, improves the efficiency of space station electrostatic suspension containerless experiment.The present application can quickly determine monochromatic infrared emissivity without the aid of thermocouple, avoids the failure problem of thermocouple in electrostatic field, for quickly and accurately obtaining the temperature variation of space station electrostatic suspension containerless experiment.The present application is suitable for the calibration of monochromatic infrared temperature in high temperature environment, and the calibrated monochromatic infrared temperature is in the small error range of characteristic temperature.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of space station containerless experiment, and relates to a monochromatic infrared temperature calibration method for a space station electrostatic suspension experiment. BACKGROUND

[0002] There are generally two methods for measuring the temperature of a high-temperature object, namely, thermocouple temperature measurement and infrared temperature measurement. The principle of the former is based on the thermoelectric effect, and the change in temperature causes a change in the thermocouple potential. The temperature can be measured according to the change in the potential by determining the corresponding relationship between the potential and the temperature. The principle of the latter is based on Planck's law of radiation. Any object with a temperature greater than absolute zero radiates energy outward. Most of these energies are concentrated in the infrared region, and their radiation characteristics are related to the wavelength and temperature. Accordingly, the temperature of the measured object can be determined. The monochromatic infrared temperature measurement method has a short response time and is sensitive to the composition and surface condition of the measured object. In combination with the dual-color infrared temperature measurement method, the composition change, macroscopic morphological change and phase change of the measured object can be determined.

[0003] High-temperature objects such as alloys usually have high activity. Under conventional casting conditions, the contact between the high-temperature object and the container wall will bring impurities, which will affect the physical and chemical processes such as solidification. The space environment has the characteristics of microgravity, containerless and high vacuum, which provides more convenient conditions for studying the mechanism of deep undercooling and rapid solidification of alloys. In November 2022, with the successful docking of the Mengtian cabin and the Tianhe core cabin, the Chinese space station was completed. Before that, the containerless experiment cabinet in the Tianhe core cabin of the Chinese space station had carried out some electrostatic suspension containerless experiments.

[0004] The space station electrostatic suspension containerless experiment has the following limitations:

[0005] (1) Due to satellite communication and safety considerations, the duration of a single space station electrostatic suspension containerless experiment is only 30-50 minutes (see the space station electrostatic suspension containerless experiment process), which results in the inability to heat the sample multiple times in the same electrostatic suspension containerless experiment. Therefore, the complete heating temperature data measured at multiple monochromatic infrared emissivities cannot be obtained in the same space station electrostatic suspension containerless experiment. Figure 2

[0006] (2) Due to the time-consuming data transmission and processing, the detailed temperature data of the space station electrostatic suspension containerless experiment usually needs to be completely downloaded to the ground server 12 hours after the experiment is completed.

[0007] ​(3)At present, the space station electrostatic suspension containerless experiment can only rely on multiple parameter changes for testing to determine the accurate monochromatic infrared emissivity. If the monochromatic infrared emissivity is changed at intervals of 0.01 in the interval of 0.10-0.40 (the monochromatic infrared emissivity of the alloy is usually in this interval), dozens of changes are needed to obtain a more accurate monochromatic infrared emissivity. However, due to the limitation of the number of 29 samples per box in the space station electrostatic suspension containerless experiment, if the monochromatic infrared temperature is calibrated by relying on this method, a large amount of space station containerless experiment resources will be wasted.

[0008] The above factors result in the inability to quickly determine the emissivity for measurement by the monochromatic infrared temperature measuring device, thereby resulting in the inability to guide the experimental operation according to the real-time downloaded rough temperature data during the experiment, and greatly reducing the efficiency of the space station electrostatic suspension containerless experiment. In summary, it is necessary to calibrate the monochromatic infrared temperature obtained by the space station electrostatic suspension containerless experiment and quickly predict the monochromatic infrared emissivity.

[0009] Patent No. CN112630261B (hereinafter referred to as "Patent 1") discloses a method for calibrating infrared temperature: a data receiving processing device acquires a temperature signal of a surface of a measured material measured by an infrared thermal imaging device and a temperature signal obtained by a thermocouple measurement, and then obtains the surface emissivity of the sample at different temperatures by calculation, and performs experimental correction. This method can correct the emissivity of the measured object in real time, but this method needs the continuous cooperation of the thermocouple contact temperature measurement and the infrared non-contact temperature measurement device during the temperature measurement to correct the emissivity of the measured object in real time. In the space station electrostatic suspension containerless experiment, the contact type temperature measurement method will destroy the containerless suspension state, and the measured sample is in an electrostatic suspension state, and the existence of the electrostatic field will cause the thermocouple to fail to work, so this method cannot be used to correct the monochromatic infrared emissivity of the space station electrostatic suspension containerless experiment.

[0010] Patent No. CN102620833B (hereinafter referred to as "Patent 2") discloses an infrared temperature measurement method and an infrared temperature measurement system. The method provided by this invention also needs the continuous cooperation of the thermocouple temperature measurement and the infrared temperature measurement, otherwise the temperature error obtained by this method is large, and it is shown in the subsequent report of this invention that the infrared temperature measurement method and the infrared temperature measurement system are not suitable for high temperature measurement. In the space station electrostatic suspension containerless experiment, the electrostatic field will cause the thermocouple to fail, and the highest experimental temperature exceeds 2500K, so this method cannot be used to calibrate the monochromatic infrared temperature of the space station electrostatic suspension experiment. SUMMARY

[0011] TECHNICAL PROBLEM TO BE SOLVED

[0012] In order to avoid the shortcomings of the prior art, the present application provides a monochromatic infrared temperature calibration method for space station electrostatic suspension experiments, which solves the above problems and obtains the temperature change of the space station electrostatic suspension containerless experiment. The method first needs to obtain the sample heating temperature-time curve measured at a predetermined monochromatic infrared emissivity. Then mark the characteristic temperature on the temperature-time curve, according to the principle of equal monochromatic radiation before and after calibration, substitute the predetermined monochromatic infrared emissivity, the characteristic temperature and the phase transition temperature obtained by phase diagram or thermal analysis experiment into the established equation relationship. Solve the corrected monochromatic infrared emissivity. Substitute the corrected monochromatic infrared emissivity back into the equation relationship, and substitute all the obtained temperature data into it one by one, and solve the corresponding calibrated temperature. According to the above steps, the corrected monochromatic infrared emissivity and the calibrated temperature data are obtained.

[0013] Technical scheme

[0014] A monochromatic infrared temperature calibration method for space station electrostatic suspension experiments, characterized by the following steps:

[0015] Step 1, determine the detection wavelength of the monochromatic infrared temperature measuring device:

[0016] Case 1, if the detection wavelength λ of the given monochromatic infrared temperature measuring device is an exact value, then use the value as the value of λ;

[0017] Case 2, if the given monochromatic infrared temperature measuring device λ is a range value, then λ is determined as follows:

[0018]

[0019] Where: λ * is the wavelength value to be solved, λ a , λ b are the lower limit and upper limit of the given wavelength range respectively; T p is the characteristic temperature obtained by phase diagram or thermal analysis experiment, unit: K; A, B are constants; λ * is a constant between λ a and λ b , and λ * is determined as the detection wavelength λ of the monochromatic infrared temperature measuring device, the wavelength unit is m;

[0020] Step 2: correct the monochromatic infrared emissivity at the characteristic temperature to obtain the corrected monochromatic emissivity:

[0021]

[0022] Where: ε λ ′ is the corrected monochromatic emissivity, ε λ is the original monochromatic emissivity, T mT is the characteristic temperature of the original temperature curve, T p T is the characteristic temperature of the original temperature curve, T m T is the characteristic temperature of the original temperature curve, T

[0023] Step 3, all temperatures are calibrated according to the corrected monochromatic infrared emissivity:

[0024] Step 3.1: Substitute the corrected monochromatic infrared emissivity of step 2 into the following formula:

[0025]

[0026] The calibrated temperature is obtained:

[0027]

[0028] Where T1 is the emissivity ε λ The original temperature data obtained, unit: K; T2 is the calibrated temperature corresponding to T1 under the emissivity ε λ ′, unit: K;

[0029] Step 3.2: Substitute the temperature data obtained under the emissivity ε λ ′ into the T2 formula of step 3.1 one by one to solve, and obtain all the calibrated temperature data.

[0030] The constant A = 2πhc 2 , where π is the circular constant, h is the Planck constant, c is the speed of light, and k is the Boltzmann constant.

[0031] The constant A = 2πhc , where h is the Planck constant, c is the speed of light, and k is the Boltzmann constant.

[0032] The corrected monochromatic emissivity ε λ ′ is obtained according to the monochromatic radiance equation relationship:

[0033] Step 2.1: The relationship between monochromatic radiance and detection wavelength and temperature is:

[0034]

[0035] Where M(T) is the monochromatic radiance, unit: W·m -2 ; T is the temperature, unit: K; λ is the measurement wavelength of the monochromatic infrared temperature measurement equipment, unit: m; ε λ is the monochromatic emissivity corresponding to the corresponding wavelength, which is a dimensionless quantity between 0 and 1; δλ is the actual detection wavelength interval of λ, unit: m;

[0036] Step 2.2: According to the actual situation Simplify the relationship of step 2.1 as follows:

[0037]

[0038] Step 2.3: According to the principle that the monochromatic radiant intensity before and after calibration is equal, the following relationship is obtained:

[0039]

[0040] Where, λ is the detection wavelength of the monochromatic infrared temperature measuring device, unit is m; T m is the characteristic temperature of the original temperature curve, T p is the characteristic temperature corresponding to T m obtained from the phase diagram or thermal analysis experiment, and the units are all K; ε λ is the original monochromatic emissivity, ε λ ' is the corrected monochromatic emissivity;

[0041] Step 2.4: The corrected monochromatic infrared emissivity is obtained as follows:

[0042]

[0043] The selection principle of the characteristic temperature is: (1) If there are multiple phase changes in the research temperature range of the object being studied, then select one of the phase change temperatures as the characteristic temperature; (2) If there is no phase change in the research temperature range of the object being studied, then select the phase change temperature closest to the midpoint of the research temperature range as the characteristic temperature.

[0044] Beneficial effects

[0045] The monochromatic infrared temperature calibration method for space station electrostatic suspension experiment provided by the application uses Planck's law of radiation, and combines the characteristic temperature to correct the temperature measured by the monochromatic infrared emissivity ε λ . The method includes the following processes: (1) marking the characteristic temperature T λ on the temperature curve obtained by the emissivity ε m , i.e. a certain phase change temperature; (2) determining the characteristic temperature T m corresponding to T p given by thermal analysis experiment or phase diagram; (3) obtaining the mathematical relationship containing ε λ , T m , T p and the corrected monochromatic infrared emissivity ε λ ', and solving ε λ ' determined by the characteristic temperature T p ; (4) obtaining the mathematical relationship containing ε λ , ε λThe mathematical relationship between the original temperature T1 and the calibrated temperature T2 is used to solve the calibrated temperature T2. For the space station electrostatic suspension containerless experiment of the Nb-Si eutectic alloy and the Zr-V eutectic alloy, the monochromatic infrared emissivity is respectively corrected and the original temperature is calibrated by using the calibration method of the application.

[0046] The application calibrates the existing temperature data in combination with the characteristic temperature, and the corrected monochromatic infrared emissivity and the calibrated temperature are obtained, thereby solving the calibration problem of the monochromatic infrared temperature obtained by the space station electrostatic suspension containerless experiment. In addition, the method provided by the application is helpful to realize the rapid calibration of the monochromatic infrared emissivity of the space station electrostatic suspension containerless experiment and improve the efficiency of the space station electrostatic suspension containerless experiment. Compared with the method disclosed in the patent 1, the method provided by the application can quickly determine the monochromatic infrared emissivity without the help of a thermocouple, thereby avoiding the failure problem of the thermocouple in the electrostatic field and providing guidance for quickly and accurately obtaining the temperature change of the space station electrostatic suspension containerless experiment. Compared with the method disclosed in the patent 2, the method provided by the application can be applied to the calibration of the monochromatic infrared temperature in a high-temperature environment, and the calibrated monochromatic infrared temperature by the method provided by the application can be controlled within a small error range near the characteristic temperature. BRIEF DESCRIPTION OF DRAWINGS

[0047] Figure 1 Fig. 1 is a flowchart of the monochromatic infrared temperature calibration method for the space station electrostatic suspension containerless experiment.

[0048] Figure 2 Fig. 2 is a flowchart of the space station electrostatic suspension containerless experiment.

[0049] Figure 3 Fig. 3 is a temperature-time curve of the Nb-Si eutectic alloy in the heating process when the monochromatic infrared emissivity is 0.26: (a) before calibration, the characteristic temperature is 2159K; (b) after calibration, the characteristic temperature is 2189K.

[0050] Figure 4 Fig. 4 is a temperature-time curve of the Zr-V eutectic alloy in the heating process when the monochromatic infrared emissivity is 0.20: (a) before calibration, the characteristic temperature is 1560K; (b) after calibration, the characteristic temperature is 1538K. DETAILED DESCRIPTION

[0051] The application will be further described in combination with the embodiments and the drawings:

[0052] The technical solution for solving the technical problem of the application is: a monochromatic infrared temperature calibration method for a space station electrostatic suspension containerless experiment, which comprises the following steps:

[0053] Step one, determine the detection wavelength of monochromatic infrared temperature measuring equipment:

[0054] 1. If the detection wavelength λ of the given monochromatic infrared temperature measuring equipment is an exact value, use the value as the value of λ.

[0055] 2. If the given λ is a range value, in order to ensure the accuracy of the characteristic temperature after the emissivity is corrected, the corresponding λ is selected by the following way:

[0056]

[0057] Wherein, λ * is the wavelength value to be solved, the unit is m; λ a , λ b are the lower limit and upper limit of the given wavelength range, respectively, the unit is m; T p is the characteristic temperature obtained from the phase diagram or thermal analysis experiment, the unit is K; A, B are constants, which are given by formula (2), formula (3). According to the mean value theorem, λ * must be a constant between λ a and λ b , so the detection wavelength λ of the monochromatic infrared temperature measuring equipment can be determined.

[0058] A= 2πhc 2 (2)

[0059]

[0060] Wherein, π is the circular ratio, h is the Planck constant, c is the light speed, and k is the Boltzmann constant.

[0061] Step two, correct the monochromatic infrared emissivity at the characteristic temperature according to the monochromatic radiance equation relationship:

[0062] 1. The relationship between monochromatic radiance and detection wavelength and temperature:

[0063]

[0064] Wherein, M(T) is the monochromatic radiance, the unit is W·m -2 ; T is the temperature, the unit is K; λ is the measurement wavelength of monochromatic infrared temperature measuring equipment, the unit is m; ε λ is the corresponding monochromatic emissivity at the corresponding wavelength, which is a dimensionless quantity between 0 and 1; δλ is the actual detection wavelength interval of λ, the unit is m.

[0065] 2. According to the principle that the monochromatic radiance before and after calibration is equal, the preset monochromatic infrared emissivity is corrected:

[0066] Because of the actual situation:

[0067]

[0068] Therefore, formula (4) can be simplified as:

[0069]

[0070] According to the principle that the monochromatic radiant intensity before and after calibration is equal, the following relationship is obtained:

[0071]

[0072] Wherein, λ is the detection wavelength of the monochromatic infrared temperature measuring device, and the unit is m; T m is the characteristic temperature of the original temperature curve, T p is the characteristic temperature corresponding to T m obtained from the phase diagram or thermal analysis experiment, and the units are K; ε λ is the original monochromatic emissivity, ε λ ' is the corrected monochromatic emissivity.

[0073] The corrected monochromatic emissivity is obtained from formula (7):

[0074]

[0075] Step three, calibrate all temperatures according to the corrected monochromatic infrared emissivity:

[0076] 1, the corrected monochromatic infrared emissivity obtained from formula (8) is substituted into the following formula:

[0077]

[0078] Wherein, T1 is the original temperature data obtained under the emissivity ε λ , and the unit is K; T2 is the calibrated temperature corresponding to T1 under the emissivity ε λ ', and the unit is K. The calibrated temperature T2 is obtained from formula (9):

[0079]

[0080] 2, the temperature data obtained under the emissivity ε λ is substituted into formula (10) one by one to obtain all the calibrated temperature data.

[0081] Specific embodiments: Taking the space station electrostatic suspension containerless experiment of Nb-Si eutectic alloy in the Nb-rich region and Zr-V eutectic alloy as examples, the present application is described in detail in combination with the drawings:

[0082] Example 1, space station electrostatic suspension containerless experiment of Nb-Si eutectic alloy in the Nb-rich region:

[0083] Step one, determine the characteristic temperature:

[0084] The selection of characteristic temperature is related to the research object and research content. The selection principle is: (1) if there are multiple phase transitions in the research temperature range of the research object, one of the phase transition temperatures is selected as the characteristic temperature; (2) if there is no phase transition in the research temperature range of the research object, the phase transition temperature closest to the midpoint of the research temperature range is selected as the characteristic temperature. In this embodiment, the eutectic platform temperature of Nb-Si eutectic alloy is selected as its characteristic temperature, which is determined by the binary Nb-Si alloy phase diagram. The characteristic temperature T p1 of Nb-Si eutectic alloy is 2189K.

[0085] Step two, determine the detection wavelength of monochromatic infrared temperature measurement equipment:

[0086] 1. The monochromatic infrared temperature measurement instrument used in the Chinese space station is a temperature measurement instrument produced by LumaSense Techbologies Company, and its model is IGA5-TV. According to the data provided in its instruction manual, the value range of λ is 1.45μm~1.80μm.

[0087] 2. According to formula (1), formula (2) and formula (3), the measurement wavelength λ1of the Nb-Si eutectic alloy is obtained:

[0088]

[0089] Wherein, the values of each parameter in formula (2) and formula (3) are: h=6.62607015×10 -34 J·s, c=2.99792458×10 8 m·s -1 , k=1.380649×10 -23 J·K -1 , the above data is from the data published by the International Scientific Association Scientific and Technical Data Committee (CODATA) in 2019. The values of the parameters in formula (11) are: T p1 =2189K, λ a =1.45μm, λ b =1.80μm. Using Steffensen iteration method, λ1=1.633μm can be obtained.

[0090] Step three, select the preset monochromatic infrared emissivity (usually select the empirical value, for example, the value near 0.20 is usually selected for the alloy), and then obtain the temperature-time curve of the sample under this emissivity:

[0091] When the emissivity is 0.26, the characteristic temperature of the Nb-Si eutectic alloy in the heating process is 2159K, as shown in Figure 3(a) shown. This characteristic temperature differs from the characteristic temperature 2189 K of the eutectic Nb-Si alloy given in the phase diagram by more than 1%, so the temperature obtained at this emissivity needs to be calibrated.

[0092] Step four, correction of monochromatic infrared emissivity:

[0093] 1. First, the monochromatic infrared emissivity is corrected according to formula (3), formula (8). The values of various parameters in formula (8) are: ε λ = 0.26, T m = 2159 K, T p = 2189 K, λ = 1.633 μm.

[0094] 2. The corrected monochromatic emissivity of the Nb-Si eutectic alloy is: ε1' = 0.246.

[0095] Step five, calibration of the original temperature:

[0096] According to formula (10), all the temperature data are calibrated. Figure 3 (b) gives the temperature-time calibration curve corresponding to Figure 3 (a).

[0097] Example 2, space station static electrostatic suspension containerless experiment of Zr-V eutectic alloy:

[0098] Step one, determine the characteristic temperature:

[0099] The selection of the characteristic temperature is related to the research object and the research content, and the selection principle is: (1) if there are multiple phase transitions in the research temperature range of the research object, then one of the phase transition temperatures is selected as the characteristic temperature; (2) if there is no phase transition in the research temperature range of the research object, then the phase transition temperature closest to the midpoint of the research temperature range is selected as the characteristic temperature. In this embodiment, the eutectic platform temperature of the Zr-V eutectic alloy is selected as its characteristic temperature, and the characteristic temperature T p2 of the binary Zr-V alloy phase diagram is 1538 K.

[0100] Step two, determine the detection wavelength of the monochromatic infrared temperature measurement equipment:

[0101] 1. The monochromatic infrared temperature measurement instrument used in the Chinese space station is a temperature measurement equipment produced by LumaSense Techbologies Company, and its model is IGA5-TV. According to the data provided in its instruction manual, the value range of λ is 1.45 μm-1.80 μm.

[0102] 2. According to formula (1), formula (2), formula (3), the measurement wavelength λ2 of the Zr-V eutectic alloy is obtained:

[0103]

[0104] wherein the values of the parameters in equation (2), equation (3) are: h = 6.62607015 x 10 -34 J s, c = 2.99792458 x 10 8 m s -1 , k = 1.380649 x 10 -23 J K -1 , the above data are from the 2019 CODATA published data. The values of the parameters in equation (12) are: T p2 = 1538 K, l a = 1.45 pm, l b = 1.80 pm. Using Steffensen iteration method, we can get: l2= 1.603 pm.

[0105] Step three, select a pre-set monochromatic infrared emissivity (usually select an empirical value, for example, the alloy usually selects a value near 0.20), then obtain the temperature-time curve of the sample at this emissivity:

[0106] When the emissivity is 0.20, the characteristic temperature of the Zr-V eutectic alloy in the heating process is 1560 K, as shown in Figure 4 (a). The characteristic temperature is more than 1% different from the characteristic temperature of the Zr-V eutectic alloy given by the phase diagram, which is 1538 K, so the temperature obtained at this emissivity needs to be calibrated.

[0107] Step four, correct the monochromatic infrared emissivity:

[0108] 1. According to equation (3), equation (8), first correct the monochromatic infrared emissivity. The values of the parameters in equation (8) are: e λ = 0.20, T m = 1560 K, T p = 1538 K, l = 1.603 pm.

[0109] 2. The corrected monochromatic emissivity of the Zr-V eutectic alloy is: e2' = 0.217.

[0110] Step five, calibrate the original temperature:

[0111] According to equation (10), calibrate all the temperature data. Figure 4 (b) gives the temperature-time calibration curve corresponding to Figure 4 (a).

Claims

1. A monochromatic infrared temperature calibration method for electrostatic levitation experiments on space stations, characterized in that... The steps are as follows: Step 1: Determine the detection wavelength of the monochromatic infrared thermometer: Case 1: If the detection wavelength λ of the given monochromatic infrared temperature measuring device is an exact value, then use that value as the value of λ. Case 2: If the given λ value for a monochromatic infrared thermometer is a range value, then λ is determined by the following formula: Where: λ * Let λ be the wavelength value to be determined. a , λ b These represent the lower and upper limits of a given wavelength range, respectively; T p Characteristic temperatures obtained from phase diagrams or thermal analysis experiments, in Kelvin; A and B are constants; λ * For those between λ a With λ b The constants between them determine λ * λ is the detection wavelength of the monochromatic infrared thermometer, with the unit of wavelength being meters (m). Step 2: Correct the monochromatic infrared emissivity at the characteristic temperature to obtain the corrected monochromatic emissivity: Where: ε λ ' is the corrected monochromatic emissivity, ε λ For the original monochromatic emissivity, T m T represents the characteristic temperature of the original temperature curve. p The corresponding T obtained from phase diagrams or thermal analysis experiments m The characteristic temperatures are all in Kelvin (K). Step 3: Calibrate all temperatures based on the corrected monochromatic infrared emissivity: Step 3.1: Substitute the corrected monochromatic infrared emissivity from Step 2 into the following formula: The calibrated temperature was obtained: Where T1 is the emissivity ε λ The raw temperature data obtained below is in K; T2 is the emissivity ε. λ The temperature below corresponds to the calibrated temperature of T1, in K. Step 3.2: The part to be calibrated at emissivity ε λ Substitute the obtained temperature data one by one into the T2 formula in step 3.1 to solve for all the calibrated temperature data.

2. The monochromatic infrared temperature calibration method for electrostatic levitation experiments on space stations according to claim 1, characterized in that: The constant A = 2πhc 2 Where π is the mathematical constant of a circle, h is Planck's constant, c is the speed of light, and k is Boltzmann's constant.

3. The monochromatic infrared temperature calibration method for electrostatic levitation experiments on space stations according to claim 1, characterized in that: The constant Where h is Planck's constant, c is the speed of light, and k is Boltzmann's constant.

4. The monochromatic infrared temperature calibration method for electrostatic levitation experiments on space stations according to claim 1, characterized in that: The corrected monochromatic emissivity ε λ Based on the monochromatic radiance equation, we obtain: Step 2.1: The relationship between monochromatic radiance and detection wavelength and temperature is as follows: Where M(T) is the monochromatic radiance, with units of W·m -2 T represents temperature in Kelvin (K); λ represents the measurement wavelength of the monochromatic infrared thermometer in meters (m); ε λ λ is the monochromatic emissivity corresponding to the wavelength, which is a dimensionless quantity between 0 and 1; δλ is the actual detection wavelength range of λ, in meters. Step 2.2: Based on the actual situation The relationship in step 2.1 can be simplified to: Step 2.3: Based on the principle that the monochromatic radiance is equal before and after calibration, the following relationship is obtained: Where λ is the detection wavelength of the monochromatic infrared thermometer, in meters (m); T m T represents the characteristic temperature of the original temperature curve. p The corresponding T obtained from phase diagrams or thermal analysis experiments m Characteristic temperatures, all in K; ε λ ε is the original monochromatic emissivity. λ ′ represents the corrected monochromatic emissivity; Step 2.4: Obtain the corrected monochromatic infrared emissivity:

5. The monochromatic infrared temperature calibration method for electrostatic levitation experiments on space stations according to claim 1, characterized in that: The selection principle of the characteristic temperature is: (1) If there are multiple phase transitions within the study temperature range of the object under study, then one of the phase transition temperatures shall be selected as the characteristic temperature; (2) If there are no phase transitions within the study temperature range of the object under study, then the phase transition temperature closest to the midpoint of the study temperature range shall be selected as the characteristic temperature.

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