阅读说明：本技术 一种真空红外定标辐射响应一致性方法 (Vacuum infrared calibration radiation response consistency method ) 是由 王阳 钮新华 张锷 陈帅帅 胡秀清 张冬冬 王向华 熊千千 于 2021-08-13 设计创作，主要内容包括：本发明涉及一种真空红外定标辐射响应一致性方法。针对真空红外定标过程中镜片污染及探测头部温度非一致性等,导致红外辐射计各通道定标系数及铂电阻转换系数获取不准确的问题,利用红外定标中获得的面源黑体及星上黑体变温数据,将红外辐射计真空红外定标过程中定标状态的响应度进行辐射一致性处理,以保证空间辐射基准到星上黑体辐射传递过程的辐射准确性。真空红外定标辐射响应一致性方法基于红外辐射计线性响应系统、红外辐射计单一系统状态响应稳定性以及空间辐射基准源辐射稳定性,建立了红外通道辐射定标响应一致性模型,实现对红外辐射计辐射定标数据再处理,有效提高了真空红外辐射定标精度。(The invention relates to a vacuum infrared calibration radiation response consistency method. Aiming at the problem that the calibration coefficients of all channels and the platinum resistance conversion coefficient of the infrared radiometer are not accurately obtained due to lens pollution, non-uniformity of the temperature of a detection head and the like in the vacuum infrared calibration process, the radiation uniformity processing is carried out on the responsivity of the calibration state in the vacuum infrared calibration process of the infrared radiometer by utilizing the variable temperature data of the surface source black body and the satellite black body obtained in the infrared calibration so as to ensure the radiation accuracy in the radiation transfer process from the space radiation reference to the satellite black body. The vacuum infrared calibration radiation response consistency method establishes an infrared channel radiation calibration response consistency model based on an infrared radiometer linear response system, infrared radiometer single system state response stability and space radiation reference source radiation stability, so that the reprocessing of infrared radiometer radiation calibration data is realized, and the vacuum infrared radiation calibration precision is effectively improved.)

1. A vacuum infrared calibration radiation response consistency method is characterized by comprising the following specific steps:

1) in the infrared calibration stage, the decomposition of the infrared radiometer signal response function,

1-1) in the infrared calibration stage, obtaining the system response code value after deducting the cold space signal,

black body on starAcquiring the response code value of the satellite blackbody or surface source blackbody system with the deducted cold and air signals under the temperature changing stage and the surface source blackbody temperature changing calibration stageComprises the following steps:

wherein CS represents the satellite blackbody temperature variation calibration stage or the surface source blackbody temperature variation calibration stage in the infrared calibration, BB represents the satellite blackbody or the surface source blackbody observed by the infrared radiometer, T^mRepresenting the physical temperature, T, of a surface source black body^xIndicating the physical temperature of the star black body and the temperature of the probe head,representing the physical temperature T of the surface source black body and the CS in the infrared calibration stage^mPhysical temperature T of star black body^xAnd detecting the head temperature T^xThe BB black-body code value of (a),representing the physical temperature T of the surface source black body and the CS in the infrared calibration stage^mPhysical temperature T of star black body^xAnd detecting the head temperature T^xA cold air code value of;

1-2) decomposition of the infrared radiometer signal response function at each stage of infrared calibration,

in the infrared calibration, the infrared radiometer detects the temperature change of the head and the star blackbody at the same time, the response code value of the infrared radiometer consists of three parts including a reference working condition code value, an external target source radiation function and a system response consistency function, and according to the step 1-1), the response code value of the infrared radiometer is obtainedThe following response function decomposition is performed:

wherein, the surface source black body temperatureTemperature of black body on satelliteAnd detecting head temperatureAs a reference working condition of infrared calibration of the infrared radiometer,is the value of the system response code, H, under the reference operating condition_{Inner part}(T^m,T^x) Indicating the temperature T of the infrared radiometer at the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xLower system response consistency function, H_{Outer cover}(T^m,T^x) Indicating the temperature T of the external radiation source at the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xA target source radiance function of;

2) in the satellite blackbody temperature changing stage, the radiation response consistency of the infrared radiometer is corrected,

2-1) in the phase of changing temperature of the starry black body, when the temperature of the head is detected, the system response consistency function is obtained,

in the satellite blackbody temperature changing stage, the surface source blackbody is controlled at the temperatureAnd (3) aiming at each detection head temperature point, the infrared radiometer carries out radiation measurement on the surface source black body, and according to the functional relation of the step 1-2), the code value of the surface source black body is decomposed by the following response function:

wherein, the temperature of the surface source black body is calibrated at the black body temperature change calibration stage on the infrared radiometer satelliteUnder the condition of the reaction, the reaction kettle is used for heating,is temperature T of black body on satellite^xAnd head temperature T^xThe face source black body at the time responds to the code value,is temperature of black body on satelliteAnd head temperatureThe face source black body at the time responds to the code value,is temperature T of black body on satellite^xAnd head temperature T^xThe surface source black body radiation function of time,is temperature T of black body on satellite^xAnd head temperature T^xThe system response consistency function of time, the surface source black body is controlled at the temperatureWhen the medicine is taken,based on an infrared radiometer linear response system and a high-precision surface source black body temperature control system, a surface is utilizedTemperature of source black bodyCalculating a system response consistency function when the infrared radiometer detects the head temperature change according to the face source black body response code value:

2-2) in the on-satellite blackbody temperature changing stage, the on-satellite blackbody radiation response consistency of the infrared radiometer is corrected,

in the satellite blackbody temperature changing stage, the infrared radiometer detects that the head and the satellite blackbody are simultaneously changed in temperature, and according to the functional relation of the step 1-2), the code value of the satellite blackbody is decomposed by the following response function:

wherein the variable is the surface blackbody temperature of the infrared radiometer at the on-satellite blackbody temperature variation calibration stageThe variable of the time of day is,is temperature T of black body on satellite^xAnd detecting the head temperature T^xThe bold on the time star responds to the code value,is temperature of black body on satelliteAnd detecting head temperatureTime satellite black body reference working condition codeThe value of the one or more of the one,is temperature T of black body on satellite^xAnd detecting the head temperature T^xThe on-satellite black body radiation function is corrected to obtain the on-satellite black body response code value under the condition of ensuring the consistency of the response state of the head detection system during the process of detecting the head temperature change by the infrared radiometerExpressed as:

system response consistency function using infrared radiometersLinearly correcting the on-satellite blackbody response code value in the on-satellite blackbody temperature-changing calibration stage, and correcting the on-satellite blackbody response code valueThe method comprises the following steps:

3) in the temperature changing stage of the surface source black body, the radiation response consistency of the infrared radiometer is corrected,

3-1) a surface source blackbody temperature changing stage, obtaining a radiation function of a satellite blackbody,

when the detecting head and the star blackbody are controlled at the temperature T^xIn the process of changing the temperature of the surface source black body, the temperature of the satellite black body and the temperature of the detection head fluctuate simultaneously, the system responsivity changes, and according to the functional relation in the step 1-2), the response code value of the satellite black body in the phase of changing the temperature of the surface source black body is decomposed by the following response function:

wherein the variables are variables of the infrared radiometer in the surface source black body temperature variation calibration stage,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xThe value of the black body on the star of the time,is the temperature of a surface source black bodyTemperature of black body on satelliteAnd detecting head temperatureThe value of the reference operating condition of the on-satellite black body,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xThe system response to the consistency function of time,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xCalculating the temperature T of different on-satellite blackbodies according to the infrared channel spectral response function, the energy spectral distribution and the emissivity of the on-satellite blackbody of the infrared radiometer^xCorresponding radiation energy N (T)^x) Measured by deducting the temperature fluctuation of the black bodyThe system response influence is calculated as follows:

in the formula, v_iIs the ith wave number, R (v)_i) Is the relative spectral response of the channel, ε (v)_i) Is the black body emissivity on the star, c1 is 1.1910427 × 10^-5mW/(m²sr¹cm^-4)，c2＝1.4387752cm¹K¹As radiation constant, in the phase of changing temperature of surface source black body, radiation function of star black bodyThe calculation is as follows:

wherein the content of the first and second substances,is temperature of black body on satelliteRadiation energy of time, the emissivity epsilon (v) of the star black body in the above formula_i) Can be ignored;

3-2) in the process of changing the temperature of the surface source black body, obtaining a radiation response consistency function of the infrared radiometer,

according to the on-satellite blackbody response function decomposition formula in the step 3-1) and the on-satellite blackbody radiation functionDeducting the influence of the temperature fluctuation of the satellite blackbody at the surface source blackbody temperature change stage on the response of the satellite blackbody system, and acquiring the radiation response consistency function of the infrared radiometer based on the linear response system of the infrared radiometer

3-3) in the phase of changing the temperature of the surface source black body, the radiation response consistency of the surface source black body of the infrared radiometer is corrected,

according to the functional relation of the step 1-2), in the temperature changing stage of the surface source black body, the surface source black body response code value is decomposed by the following response function:

wherein the variables are variables of the infrared radiometer in the surface source black body temperature variation calibration stage,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xThe value of the face source black body code at the time,is the temperature of a surface source black bodyTemperature of black body on satelliteAnd detecting head temperatureThe value of the normal face source black body reference condition code,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xA time surface source blackbody radiation function, a surface source blackbody code value in the surface source blackbody temperature changing calibration stage, and a system response consistency function of the infrared radiometerLinearly corrected surface source black body code value, corrected surface source black body code value thereofComprises the following steps:

4) in the process of transmitting the radiation of the surface source black body radiation reference to the on-board black body, the radiation response consistency of the calibration state of the infrared radiometer is corrected,

according to the reference working condition code value in the step 2-1) and the step 3-3), the surface source blackbody code value is changed in temperature by the surface source blackbodyFor the reference, the calibration state consistency factor γ in the process of transferring the surface source black body radiation standard to the on-satellite black body is calculated:

utilizing calibration state consistency coefficient upsilon to on-satellite black body temperature change stage on-satellite black body code valueLinear correction is carried out, and the corrected star black body code valueThe method comprises the following steps:

Technical Field

The invention relates to the technical field of vacuum infrared radiation calibration, in particular to a radiation response consistency method for vacuum infrared calibration.

Background

The aerospace infrared remote sensing technology is developing towards high quantification, and particularly, in the fields of numerical weather forecast, climate change, environmental monitoring and the like, higher and higher requirements are put forward on the quantification level of the aerospace infrared remote sensing technology. In order to meet the magnitude traceability requirement of the infrared remote sensing load in the aspect of radiometric calibration, vacuum infrared calibration before emission is one of the most important ways for ensuring the accuracy of the magnitude, so that the establishment of a measurement standard method for tracing to the international unit (SI) is particularly critical for realizing high-precision calibration of the infrared remote sensing load.

At present, the infrared remote sensing load vacuum infrared calibration usually adopts a calibration method of transmitting standard surface source black body radiation to a satellite black body, the calibrated satellite black body and a cold space are used for realizing on-orbit infrared calibration, and a vacuum infrared calibration method of a typical satellite infrared radiometer is provided by a Document [1] (Jack Xiong, MODIS Level 1B Algorithm Theoretical Basis Document, 2013), a Document [2] (Gongyu, a vacuum low background infrared brightness temperature calibration method research, 2017) and a Document [3] (Gulingling, a radiation calibration device and a radiation calibration method before satellite-borne interference infrared hyperspectral detector emission, 2021), wherein the measurement method is mature, but in the vacuum infrared calibration process, the infrared remote sensing load system responsivity is easily influenced by system temperature factors such as head pollution, head temperature change, radiation cold temperature fluctuation and the like, so as to cause the inconsistency of the system responsivity in an infrared radiation calibration chain, the calibration precision of the infrared remote sensing load and the source tracing transfer precision of the on-satellite black body are seriously influenced. Therefore, aiming at infrared remote sensing load and on-satellite blackbody calibration, research on a radiation response consistency method in vacuum infrared calibration is a key for realizing a high-precision satellite-borne calibration system.

Disclosure of Invention

In order to solve the problem of non-uniformity of response of radiation transmission of instruments such as an infrared radiometer in the vacuum infrared calibration process in the prior art, the invention provides a vacuum infrared calibration radiation response uniformity method.

The technical scheme adopted by the invention is as follows:

1. a vacuum infrared calibration radiation response consistency method is characterized by comprising the following specific steps:

1) in the infrared calibration stage, the decomposition of the infrared radiometer signal response function,

1-1) in the infrared calibration stage, obtaining the system response code value after deducting the cold space signal,

acquiring the value of the satellite blackbody or surface source blackbody system response code obtained after deducting the cold and air signals in the satellite blackbody temperature changing stage and the surface source blackbody temperature changing calibration stage

Wherein CS represents the satellite blackbody temperature variation calibration stage or the surface source blackbody temperature variation calibration stage in the infrared calibration, BB represents the satellite blackbody or the surface source blackbody observed by the infrared radiometer, T^mRepresenting the physical temperature, T, of a surface source black body^xIndicating the physical temperature of the star black body and the temperature of the probe head,representing the physical temperature T of the surface source black body and the CS in the infrared calibration stage^mPhysical temperature T of star black body^xAnd detecting the head temperature T^xThe BB black-body code value of (a),representing the physical temperature T of the surface source black body and the CS in the infrared calibration stage^mPhysical temperature T of star black body^xAnd detecting head temperatureDegree T^xA cold air code value of;

1-2) decomposition of the infrared radiometer signal response function at each stage of infrared calibration,

in the infrared calibration, the infrared radiometer detects the temperature change of the head and the star blackbody at the same time, the response code value of the infrared radiometer consists of three parts including a reference working condition code value, an external target source radiation function and a system response consistency function, and according to the step 1-1), the response code value of the infrared radiometer is obtainedThe following response function decomposition is performed:

wherein, the surface source black body temperatureTemperature of black body on satelliteAnd detecting head temperatureAs a reference working condition of infrared calibration of the infrared radiometer,is the value of the system response code, H, under the reference operating condition_{Inner part}(T^m,T^x) Indicating the temperature T of the infrared radiometer at the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xLower system response consistency function, H_{Outer cover}(T^m,T^x) Indicating the temperature T of the external radiation source at the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xA target source radiance function of;

2) in the satellite blackbody temperature changing stage, the radiation response consistency of the infrared radiometer is corrected,

2-1) in the phase of changing temperature of the starry black body, when the temperature of the head is detected, the system response consistency function is obtained,

in the satellite blackbody temperature changing stage, the surface source blackbody is controlled at the temperatureAnd (3) aiming at each detection head temperature point, the infrared radiometer carries out radiation measurement on the surface source black body, and according to the functional relation of the step 1-2), the code value of the surface source black body is decomposed by the following response function:

wherein, the temperature of the surface source black body is calibrated at the black body temperature change calibration stage on the infrared radiometer satelliteUnder the condition of the reaction, the reaction kettle is used for heating,is temperature T of black body on satellite^xAnd head temperature T^xThe face source black body at the time responds to the code value,is temperature of black body on satelliteAnd head temperatureThe face source black body at the time responds to the code value,is temperature T of black body on satellite^xAnd head temperature T^xThe surface source black body radiation function of time,is temperature T of black body on satellite^xAnd head temperature T^xThe system response consistency function of time, the surface source black body is controlled at the temperatureWhen the medicine is taken,based on an infrared radiometer linear response system and a high-precision surface source black body temperature control system, the temperature of the surface source black body is utilizedCalculating a system response consistency function when the infrared radiometer detects the head temperature change according to the face source black body response code value:

2-2) in the on-satellite blackbody temperature changing stage, the on-satellite blackbody radiation response consistency of the infrared radiometer is corrected,

in the satellite blackbody temperature changing stage, the infrared radiometer detects that the head and the satellite blackbody are simultaneously changed in temperature, and according to the functional relation of the step 1-2), the code value of the satellite blackbody is decomposed by the following response function:

wherein the variable is the surface blackbody temperature of the infrared radiometer at the on-satellite blackbody temperature variation calibration stageThe variable of the time of day is,is temperature T of black body on satellite^xAnd detecting the head temperature T^xThe bold on the time star responds to the code value,is temperature of black body on satelliteAnd detecting head temperatureThe value of the reference operating condition of the on-satellite black body,is temperature T of black body on satellite^xAnd detecting the head temperature T^xThe on-satellite black body radiation function is corrected to obtain the on-satellite black body response code value under the condition of ensuring the consistency of the response state of the head detection system during the process of detecting the head temperature change by the infrared radiometerExpressed as:

system response consistency function using infrared radiometersLinearly correcting the on-satellite blackbody response code value in the on-satellite blackbody temperature-changing calibration stage, and correcting the on-satellite blackbody response code valueThe method comprises the following steps:

3) in the temperature changing stage of the surface source black body, the radiation response consistency of the infrared radiometer is corrected,

3-1) a surface source blackbody temperature changing stage, obtaining a radiation function of a satellite blackbody,

when the detecting head and the star blackbody are controlled at the temperature T^xHour, face is blackThe temperature of the star blackbody and the temperature of the detection head fluctuate simultaneously in the body temperature changing process, the system responsivity changes, and according to the functional relation in the step 1-2), the star blackbody response code value in the surface source blackbody temperature changing stage is decomposed by the following response functions:

wherein the variables are variables of the infrared radiometer in the surface source black body temperature variation calibration stage,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xThe value of the black body on the star of the time,is the temperature of a surface source black bodyTemperature of black body on satelliteAnd detecting head temperatureThe value of the reference operating condition of the on-satellite black body,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xThe system response to the consistency function of time,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xThe radiation function of the satellite black body is determined according to the infrared channel spectral response function of the infrared radiometer and the energy spectral distribution of the black bodyAnd the emissivity of the on-satellite blackbody, and calculating the temperature T of different on-satellite blackbodies^xCorresponding radiation energy N (T)^x) And deducting the influence of the temperature fluctuation of the satellite blackbody on the system response of the satellite blackbody measurement, wherein the specific calculation process is as follows:

in the formula, v_iIs the ith wave number, R (v)_i) Is the relative spectral response of the channel, ε (v)_i) Is the black body emissivity on the star, c1 is 1.1910427 × 10^-5mW/(m²sr¹cm^-4)，c2＝1.4387752cm¹K¹As radiation constant, in the phase of changing temperature of surface source black body, radiation function of star black bodyThe calculation is as follows:

wherein the content of the first and second substances,is temperature of black body on satelliteRadiation energy of time, the emissivity epsilon (v) of the star black body in the above formula_i) Can be ignored;

3-2) in the process of changing the temperature of the surface source black body, obtaining a radiation response consistency function of the infrared radiometer,

according to the on-satellite blackbody response function decomposition formula in the step 3-1) and the on-satellite blackbody radiation functionThe influence of the temperature fluctuation of the satellite blackbody at the phase of deducting the surface source blackbody temperature change on the response of the satellite blackbody system is based on the linearity of the infrared radiometerResponse system for obtaining radiation response consistency function of infrared radiometer

3-3) in the phase of changing the temperature of the surface source black body, the radiation response consistency of the surface source black body of the infrared radiometer is corrected,

according to the functional relation of the step 1-2), in the temperature changing stage of the surface source black body, the surface source black body response code value is decomposed by the following response function:

wherein the variables are variables of the infrared radiometer in the surface source black body temperature variation calibration stage,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xThe value of the face source black body code at the time,is the temperature of a surface source black bodyTemperature of black body on satelliteAnd detecting head temperatureThe value of the normal face source black body reference condition code,is the temperature T of the surface source black body^mBlack body on starTemperature T^xAnd detecting the head temperature T^xA time surface source blackbody radiation function, a surface source blackbody code value in the surface source blackbody temperature changing calibration stage, and a system response consistency function of the infrared radiometerLinearly corrected surface source black body code value, corrected surface source black body code value thereofComprises the following steps:

4) in the process of transmitting the radiation of the surface source black body radiation reference to the on-board black body, the radiation response consistency of the calibration state of the infrared radiometer is corrected,

according to the reference working condition code value in the step 2-1) and the step 3-3), the surface source blackbody code value is changed in temperature by the surface source blackbodyFor the reference, the calibration state consistency factor γ in the process of transferring the surface source black body radiation standard to the on-satellite black body is calculated:

utilizing calibration state consistency coefficient upsilon to on-satellite black body temperature change stage on-satellite black body code valueLinear correction is carried out, and the corrected star black body code valueThe method comprises the following steps:

by the infrared calibration data processing method, the consistency of the system responsivity of the infrared radiometer at the satellite blackbody temperature changing stage and the surface source blackbody temperature changing stage is ensured, so that the corrected surface source blackbody code value is obtainedAnd values of starboard black body

Compared with the prior art, the invention has the beneficial effects that: the vacuum infrared calibration radiation response consistency method provided by the invention is based on the state response stability of an infrared radiometer linear response system, an infrared radiometer single system and the radiation stability of a space radiation reference source, establishes a radiation response consistency model in the infrared remote sensing load vacuum infrared calibration radiation transfer process, and ensures the radiation response consistency and accuracy of data of each stage of infrared calibration. Aiming at the calibration of the infrared remote sensing load and the on-satellite black body thereof, the vacuum infrared calibration radiation response consistency method effectively improves the on-orbit infrared radiation calibration precision of the infrared remote sensing load.

Drawings

The invention is further described below in conjunction with the appended drawings and the detailed description.

FIG. 1 is a schematic view of the scanning sequence and position of an infrared radiometer according to the present invention;

FIG. 2 is a schematic diagram of a vacuum infrared calibration method for an infrared radiometer according to the present invention;

FIG. 3 is a schematic diagram of the vacuum infrared calibration radiation response consistency method in the invention.

Detailed Description

In order to make the technical means, the creation features, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below with reference to the attached drawings and the embodiments.

As shown in fig. 1, during vacuum infrared calibration, the infrared radiometer sequentially receives radiation of a cold space, a surface source black body and an on-satellite black body through a scanning mirror, an optical receiving aperture is aligned with the surface source black body, a detection head is subjected to thermostatic control, a deep cooling black body is used as a space zero radiation reference, and a standard surface source black body is used as a target.

As shown in fig. 2, the calibration coefficient of the probing head is obtained by changing the temperature (radiation amount) of the surface source black body to obtain the corresponding system output signal code value, and the conversion coefficient between the satellite black body temperature measurement platinum code value and the equivalent black body temperature is obtained by obtaining the calibration coefficient of the system, the satellite black body signal code value and the satellite black body temperature measurement platinum code value, so that the radiation standard of the surface source black body is introduced to the satellite black body through the probing head.

In the infrared calibration test process, the temperature of the detection head of the infrared radiometer and the star blackbody is changed at the same time and has the same temperature. The acquired test data comprise temperature data and signal data, the temperature data comprise surface source black body temperature, radiation cooling temperature, satellite black body temperature measurement platinum resistance code value and head temperature, and the signal data comprise a surface source black body, a satellite black body and a deep cooling space.

As shown in fig. 3, the method includes,

1) in the infrared calibration stage, the decomposition of the infrared radiometer signal response function,

1-1) in the infrared calibration stage, obtaining the system response code value after deducting the cold space signal,

acquiring the value of the satellite blackbody or surface source blackbody system response code obtained after deducting the cold and air signals in the satellite blackbody temperature changing stage and the surface source blackbody temperature changing calibration stage

Wherein CS represents the satellite blackbody temperature variation calibration stage or the surface source blackbody temperature variation calibration stage in the infrared calibration, BB represents the satellite blackbody or the surface source blackbody observed by the infrared radiometer, T^mWhich represents the physical temperature of the planar source black body,T^xindicating the physical temperature of the star black body and the temperature of the probe head,representing the physical temperature T of the surface source black body and the CS in the infrared calibration stage^mPhysical temperature T of star black body^xAnd detecting the head temperature T^xThe BB black-body code value of (a),representing the physical temperature T of the surface source black body and the CS in the infrared calibration stage^mPhysical temperature T of star black body^xAnd detecting the head temperature T^xThe cold air code value of.

1-2) decomposition of the infrared radiometer signal response function at each stage of infrared calibration,

in infrared calibration, the IR radiometer response code value consists of three parts, including a reference condition code value, an external target source radiometric function, and a system response coherency function, according to step 1-1), the IR radiometer response code valueThe following response function decomposition is performed:

wherein, the temperature of the surface source black body is 300K, the temperature of the star black body is 10 ℃, and the temperature of the detection head is 10 ℃ as the reference working condition of the infrared calibration of the infrared radiometer,is the value of the system response code, H, under the reference operating condition_{Inner part}(T^m,T^x) Indicating the temperature T of the infrared radiometer at the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xThe lower system response consistency function, the influence of factors such as system head pollution, head temperature change, radiation cooling temperature fluctuation and the like can cause the change of the system responsiveness H_{Outer cover}(T^m,T^x) Indicating the temperature T of the external radiation source at the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xAnd the lower target source radiation function is related to the temperature change of the surface source black body and the satellite black body in the infrared calibration test.

2) In the satellite blackbody temperature changing stage, the radiation response consistency of the infrared radiometer is corrected,

2-1) in the phase of changing temperature of the starry black body, when the temperature of the head is detected, the system response consistency function is obtained,

in the satellite blackbody temperature changing stage, the surface source blackbody is controlled at the temperature of 300K, the infrared radiometer carries out radiation measurement on the surface source blackbody aiming at each detection head temperature point, and according to the functional relation in the step 1-2), the code value of the surface source blackbody is decomposed by the following response function:

wherein, under the condition that the temperature of a surface source blackbody is 300K at the blackbody temperature varying calibration stage on an infrared radiometer satellite,is temperature T of black body on satellite^xAnd head temperature T^xThe face source black body at the time responds to the code value,is the response code value of the surface source black body when the temperature of the star black body is 10 ℃ and the temperature of the head is 10 ℃,is temperature T of black body on satellite^xAnd head temperature T^xThe surface source black body radiation function of time,is temperature T of black body on satellite^xAnd head temperature T^xThe system response consistency function of time, when the plane source blackbody is controlled at the temperature of 300K,based on an infrared radiometer linear response system and a high-precision surface source black body temperature control system, a system response consistency function when the infrared radiometer detects head temperature variation is calculated by utilizing the surface source black body response code value at the surface source black body temperature of 300K:

2-2) in the on-satellite blackbody temperature changing stage, the on-satellite blackbody radiation response consistency of the infrared radiometer is corrected,

in the satellite blackbody temperature changing stage, the infrared radiometer detects that the head and the satellite blackbody are simultaneously changed in temperature, and according to the functional relation of the step 1-2), the code value of the satellite blackbody is decomposed by the following response function:

wherein the variable is the variable of the infrared radiometer at the surface source blackbody temperature of 300K at the on-satellite blackbody temperature variation calibration stage,is temperature T of black body on satellite^xAnd detecting the head temperature T^xThe bold on the time star responds to the code value,is the standard working condition code value of the black body on the satellite when the temperature of the black body on the satellite is 10 ℃ and the temperature of the detection head is 10 ℃,is temperature T of black body on satellite^xAnd detecting the head temperature T^xThe on-satellite black body radiation function is corrected to obtain the on-satellite black body response code value under the condition of ensuring the consistency of the response state of the head detection system during the process of detecting the head temperature change by the infrared radiometerExpressed as:

system response consistency function using infrared radiometersLinearly correcting the on-satellite blackbody response code value in the on-satellite blackbody temperature-changing calibration stage, and correcting the on-satellite blackbody response code valueThe method comprises the following steps:

3) in the temperature changing stage of the surface source black body, the radiation response consistency of the infrared radiometer is corrected,

3-1) a surface source blackbody temperature changing stage, obtaining a radiation function of a satellite blackbody,

when the detecting head and the star blackbody are controlled at the temperature T^xIn the process of changing the temperature of the surface source black body, the temperature of the satellite black body and the temperature of the detection head fluctuate simultaneously, the system responsivity changes, and according to the functional relation in the step 1-2), the response code value of the satellite black body in the phase of changing the temperature of the surface source black body is decomposed by the following response function:

wherein the variables are variables of the infrared radiometer in the surface source black body temperature variation calibration stage,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xOf the hourThe values of the black body on the star,is a reference working condition code value of the black body on the satellite when the temperature of the surface source black body is 300K, the temperature of the black body on the satellite is 10 ℃ and the temperature of the detection head is 10 ℃,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xThe system response to the consistency function of time,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xCalculating the temperature T of different on-satellite blackbodies according to the infrared channel spectral response function, the energy spectral distribution and the emissivity of the on-satellite blackbody of the infrared radiometer^xCorresponding radiation energy N (T)^x) And deducting the influence of the temperature fluctuation of the satellite blackbody on the system response of the satellite blackbody measurement, wherein the specific calculation process is as follows:

in the formula, v_iIs the ith wave number, R (v)_i) Is the relative spectral response of the channel, ε (v)_i) Is the black body emissivity on the star, c1 is 1.1910427 × 10^-5mW/(m²sr¹cm^-4)，c2＝1.4387752cm¹K¹As radiation constant, in the phase of changing temperature of surface source black body, radiation function of star black bodyThe calculation is as follows:

wherein N (10 ℃) is the radiation energy of the satellite blackbody at the temperature of 10 ℃, and the emissivity epsilon (v) of the satellite blackbody in the formula_i) Can be ignored.

3-2) in the process of changing the temperature of the surface source black body, obtaining a radiation response consistency function of the infrared radiometer,

according to the on-satellite blackbody response function decomposition formula in the step 3-1) and the on-satellite blackbody radiation functionDeducting the influence of the temperature fluctuation of the satellite blackbody at the surface source blackbody temperature change stage on the response of the satellite blackbody system, and acquiring the radiation response consistency function of the infrared radiometer based on the linear response system of the infrared radiometer

3-3) in the phase of changing the temperature of the surface source black body, the radiation response consistency of the surface source black body of the infrared radiometer is corrected,

according to the functional relation of the step 1-2), in the temperature changing stage of the surface source black body, the surface source black body response code value is decomposed by the following response function:

wherein the variables are variables of the infrared radiometer in the surface source black body temperature variation calibration stage,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xThe value of the face source black body code at the time,the temperature of the surface source black body is 300K,The temperature of the star blackbody is 10 ℃, and the reference working condition code value of the surface source blackbody is detected when the temperature of the head is 10 ℃,is the temperature T of the surface source black body^mTemperature T of black body on satellite^xAnd detecting the head temperature T^xA time surface source blackbody radiation function, a surface source blackbody code value in the surface source blackbody temperature changing calibration stage, and a system response consistency function of the infrared radiometerLinearly corrected surface source black body code value, corrected surface source black body code value thereofComprises the following steps:

4) in the process of transmitting the radiation of the surface source black body radiation reference to the on-board black body, the radiation response consistency of the calibration state of the infrared radiometer is corrected,

based on the radiation responsivity invariance of the infrared radiometer under the fixed working condition, the responsivity of the infrared radiometer in the radiation transfer process is subjected to consistency correction by utilizing radiation measurement data at the 300K temperature of the surface source black body in the surface source black body temperature change stage and the satellite black body temperature change stage. According to the reference working condition code value in the step 2-1) and the step 3-3), the surface source blackbody code value is changed in temperature by the surface source blackbodyFor the reference, the calibration state consistency factor γ in the process of transferring the surface source black body radiation standard to the on-satellite black body is calculated:

gamma versus upper-star black by calibration state consistency factorVolume temperature change stage on-satellite black body code valueLinear correction is carried out, and the corrected star black body code valueThe method comprises the following steps:

by the infrared calibration data processing method, as shown in fig. 3, the consistency of the system responsivity of the infrared radiometer at the phase of changing the temperature of the black body on the satellite and the temperature of the surface source black body is ensured, so that the corrected code value of the surface source black body is obtainedAnd values of starboard black bodyAnd accurately calculating the radiometric calibration coefficient required by the on-track calibration of the infrared radiometer.

It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.