CN113029339B - On-orbit multi-source-tracing spectral radiance calibration method for deep space detection imaging spectrometer - Google Patents
On-orbit multi-source-tracing spectral radiance calibration method for deep space detection imaging spectrometer Download PDFInfo
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Abstract
The invention discloses an on-orbit multi-source-tracing spectral radiation calibration method for a deep space exploration imaging spectrometer, which comprises the following steps: (1) when the surrounding device reaches the distant celestial body track of the surrounding device track, daily calibration is carried out; (2) after the daily calibration data is acquired, calibrating the cold space and the integrating sphere; (3) and (4) deducting dark backgrounds in the calibration radiation data of the sun and the integrating sphere, and respectively calculating spectral radiation calibration coefficients. Calibrating a radiometric calibration coefficient calibrated for the integrating sphere by using the spectral radiometric calibration coefficient calibrated for the day; (4) the surrounding device arrives at the near celestial body orbit and simultaneously acquires imaging spectrum data and dark background data; (5) and converting the imaging spectrum data into radiance by using the obtained on-orbit spectral radiance scaling factor. The method overcomes the deviation of the calibration coefficient caused by the radiation intensity of the integrating sphere, and ensures the real-time performance and the continuity of the on-orbit radiation calibration and the accuracy of data.
Description
Technical Field
The invention relates to the technical field of deep space detection, in particular to an on-orbit multi-source-tracing spectral radiometric calibration method suitable for a deep space detection imaging spectrometer.
Background
The hyperspectral imaging technology is an imaging technology integrating spectra, which can acquire two-dimensional space information of a detected target and also can acquire multi-spectral-band spectral information of the detected target. The imaging spectrum technology has the advantages of strong detection capability, strong identification capability and the like, and is widely applied to the fields of food safety, medical diagnosis, mineral resources, military, national defense and the like, and also widely applied to the field of deep space detection. In recent years, a plurality of surrounds carrying imaging spectrometers are emitted at home and abroad, and the surrounds play an irreplaceable role in detecting compositions of celestial bodies such as moon, asteroid, celestial body star and the like.
Radiometric calibration is a crucial part of the quantification of material composition spectral data, and the quality of radiometric calibration directly affects the quality of material composition spectral information. Radiometric calibration may convert image signal values acquired by an imaging spectrometer into physically meaningful radiance. By inversion of the detected target image signal values, a reflectance spectrum or an emissivity spectrum reflecting the target substance components can be obtained. Through long-term research and practice, a radiometric calibration system mainly based on methods such as laboratory calibration, field calibration, on-orbit calibration, cross calibration and the like is gradually formed in the field of earth observation, and smooth implementation of quantification of imaging spectrum data in the field of earth observation is ensured. The deep space exploration is greatly different from the scene observed to the ground, the deep space exploration is difficult to implement the cross calibration which needs a plurality of loads, and the field calibration which needs the field synchronous measurement can not be implemented. This has resulted in on-orbit calibration being almost the only way for radiometric calibration of deep space probe imaging spectrometers after surround emission. In on-orbit radiometry, the sun is often the standard source for radiometric calibration, and cold space calibration is often the primary means of acquiring background radiation. However, due to the effects of the orbit period of the surround, the imaging angle, the design of the load of the surround, and the like, the imaging spectrometer cannot continuously calibrate the sun. Therefore, the invention provides an on-orbit radiometric calibration method combining calibration of the sun, an integrating sphere and a cold space.
Disclosure of Invention
Aiming at the blank and the defects of the prior art, the invention aims to provide an on-orbit radiation calibration method which has better effect and is suitable for a deep space detection imaging spectrometer.
In order to solve the technical problems, the in-orbit radiation calibration method suitable for the deep space exploration imaging spectrometer provided by the invention is based on a sun-facing orientation mode 101, a sun-facing adjustment process 102, a sun-facing calibration process 103, a cold space adjustment process 104, a cold space and integrating sphere calibration process 105, a circulator 106, an optical fiber 108, an imaging spectrometer 107, a solar calibration probe 109 and an integrating sphere 110, and is characterized by comprising the following steps:
(1) when the surround 106 reaches the distant celestial track of the surround track, when the surround 106 is close to the sun 112, in the opposite-day orientation mode 101;
(2) when the circulator 106 is in the sun-facing adjustment process 102, the temperature is adjusted to the working temperature by the refrigerator, and the circulator 106 enables the sun calibration probe 109 to face the sun 112 through posture adjustment;
(3) after the posture of the surround 106 is stabilized, the solar calibration process 103 is performed, and the imaging spectrometer 107 collects solar spectrum radiation data for the solar calibration. The calibration pixel responds to the solar signal, and the imaging pixel is a dark background;
(4) after the solar calibration data is acquired, the cold space calibration process 104 is carried out, the surrounding device 106 carries out posture adjustment again to enable the imaging spectrometer 107 to face away from the sun 112, after the posture is stabilized, the cold space and integrating sphere calibration process 105 is carried out, the imaging spectrometer 107 acquires dark background data and spectral radiation data of the integrating sphere 110 arranged in the spectrometer, and the cold space and the integrating sphere are calibrated. When the cold space is imaged, the imaging pixel and the calibration pixel are both dark backgrounds; when the integrating sphere is calibrated, the calibration pixel responds to a signal of the integrating sphere, and the imaged pixel is a dark level;
(5) and (4) subtracting dark background signals in the daily calibration spectral radiation data and the integrating sphere calibration spectral radiation data, and calculating a spectral radiation calibration coefficient for calibrating the integrating sphere and a spectral radiation calibration coefficient for calibrating the day. Calibrating a radiometric calibration coefficient for calibrating the integrating sphere by the radiometric calibration coefficient for daily calibration;
(6) when the surrounding device (106) arrives at the celestial body approaching orbit, the imaging spectrum data of the target area is collected. Converting the original imaging spectrum into radiance data according to the dark background of each frame of imaging data and a calibrated integrating sphere scaling coefficient;
(7) converting the imaging spectrum data of the target area at the corresponding moment into radiance according to the obtained on-orbit spectral radiance scaling factor;
the calibration frequency of the calibration is less than 2 times/month;
the imaging spectrometer 107 in the above method is connected with the sun calibration probe 109 and the integrating sphere 110 through the optical fiber 108, respectively, and is mounted on the circulator 106, the observation main optical axis direction 111 of the imaging spectrometer 107 is parallel to the circulator + Z direction, and the included angle between the observation direction Nc of the sun calibration probe and the observation main optical axis direction 111 of the imaging spectrometer 107 is x;
the detector in the imaging spectrometer (107) in the method is divided into an imaging area and a calibration area, and the pixels for calibration and the pixels for detection imaging are pixels in different columns in the same area array detector;
the surround 106 in the above method is first in the sun-facing orientation mode 101 (-Z-direction sun-facing), which uses the maneuvering capability of the platform to perform y-angle attitude adjustment around the + X-axis, so that the sun-targeting probe direction Nc is rotated to the sun irradiation direction 113, where X + y is 180 °. After the acquisition is finished, returning to a solar orientation mode 101 of the surround device;
the integrating sphere 110 is composed of a calibration lamp 201 and a baffle 202, the calibration lamp 201 is fixed on two holes of the integrating sphere 110, the two calibration lamps 201 are positioned on the same straight line, the baffle 202 is fixed between an integrating sphere outlet of the optical fiber 108 and the calibration lamp 201, and when the integrating sphere is calibrated, the optical fiber 108 guides uniform radiation in the integrating sphere 110 into the imaging spectrometer 107 through the optical fiber 108;
the calibration of the cold space in the step (4) requires that celestial bodies do not enter the field of view of the imaging spectrometer 107;
the method for calculating the calibration coefficient of the spectral radiance of the sun and the integrating sphere in the step (5) is as follows
Calculating the radiation brightness of the imaging spectrometer at the entrance pupil by the following method
Wherein, L (k) is a wave band k, and the radiation brightness at the entrance pupil of the imaging spectrometer corresponding to the time t; e (lambda) is the standard calibration source radiation brightness corresponding to the wave band lambda, and tau (lambda) is the transmission efficiency; srf (k, λ) is the imaging spectrumSpectral response function of k-band of the instrument; lambda 1 And λ 2 Respectively the starting wavelength and the cut-off wavelength of the imaging spectrometer; if the standard calibration source is the sun, E (lambda) is the corresponding radiation brightness of the sunlight at the wave band lambda on the calibration probe; if the standard calibration source is an integrating sphere, E (lambda) is the radiance of the integrating sphere corresponding to the waveband lambda, and the standard calibration source is generally obtained by calibration before emission;
and calculating the spectral radiance scaling factor. Calculating spectral radiance scaling factor according to the calibration source radiance signal value and the entrance pupil sphere calibration source radiance recorded by the imaging spectrometer
C (k, t) is a wave band k, and the spectral radiance scaling coefficient of the imaging spectrometer corresponding to the moment t is obtained; s (k, t) is a signal value for subtracting a dark background;
and (5) the daily spectral radiance scaling factor is used for correcting the spectral radiance scaling factor. After obtaining the spectral radiance scaling factor of the integrating sphere, the solar radiance data is inverted by the following formula. The spectral radiance calibration coefficient of the imaging spectrometer is adjusted through the radiation brightness contrast with the theoretical sun, and the corrected spectral radiance calibration coefficient is the final on-orbit spectral radiance calibration coefficient
Wherein the content of the first and second substances,
the solar radiation brightness inverted by an integrating sphere spectral radiance scaling factor corresponding to the wave band k and the time t, c clb (k, t) is the corresponding integrating sphere spectral radiance scaling factor, S solar (k, t) are the corresponding solar radiation signal values with dark background subtracted;
the method for calculating the imaging radiation brightness of the target area in the step (7) comprises
L img (i,t,k)＝c(k,t)×S img (i,t,k)
Wherein L is img (i, t, k) is a wave band k, and at the moment t, the radiation brightness of the imaging data corresponding to the detection unit i is detected;
S img (i, t, k) subtracting the dark background and the non-uniformity corrected imaging data signal values; and c (k, t) is the spectral radiance scaling coefficient of the imaging spectrometer after correction.
The beneficial effects of the invention are as follows: the sun calibration, the cold space calibration and the integrating sphere calibration are realized through the attitude adjustment of the surrounding device. The multi-source tracing calibration mode has simple system composition, and improves the efficiency of on-orbit calibration while ensuring the calibration precision.
Drawings
Fig. 1 is a schematic diagram of a remote celestial body orbit multi-tracing spectral radiometric calibration acquisition process and a surrounding device posture adjustment.
FIG. 2 is a schematic diagram of an in-orbit spectral radiance scaling system of a deep space exploration imaging spectrometer.
FIG. 3 shows a flow of an on-track multi-trace spectral radiometric calibration method.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are provided by way of example only for purposes of explanation of the invention, and are not intended to be limiting, and all similar and analogous methods and variations using the invention are intended to be within the scope of the invention.
As shown in the flow chart of fig. 3, after the surround that is installed in the rail radiometric calibration system and performs ground calibration is launched to the mars, the detection or calibration mode can be selected to implement on-rail radiometric calibration data acquisition and data processing at different environments and different surround poses. The method comprises the following steps:
(1) when the surround is in the sun-facing orientation mode 101, the sun calibration probe 109 observes the optical axis direction Nc back-sun, and the surround 106 is in the sun-facing orientation mode; in the adjustment process 102, the temperature is adjusted to the working temperature by the refrigerator, and the circulator 106 performs 135-degree posture adjustment around the + X axis to enable the sun calibration probe 109 to be aligned with the sun 112; after the attitude is stabilized, the surround 106 enters the calibration process 103, and at this time, the imaging spectrometer 107 is turned on and the calibration radiation signal value is obtained. The calibration pixel responds to the solar signal, and the imaging pixel is a dark background. (2) After the acquisition of the data of the sun is completed, the surround 106 performs 135-degree attitude adjustment as shown in the adjustment process 104 of the cold space around the + X axis, and returns to the surround sun-facing orientation mode (-Z-direction sun-facing), as shown in the calibration process 105 of the cold space and the integrating sphere in fig. 1, at this time, the integrating sphere and the cold space can be calibrated. When the Mars is outside the field of view of the imaging spectrometer 107, the detection optical axis (+ Z) is aligned to the cold space, the cold space can be calibrated, the imaging spectrometer 107 is started, and a cold space radiation signal value is obtained; starting the imaging spectrometer 107, allowing uniform integrating sphere radiation in the integrating sphere 110 to enter the imaging spectrometer 107 through the optical fiber 108, and obtaining an integrating sphere radiation signal value; when the cold space is imaged, the imaging pixel and the calibration pixel are both dark backgrounds; and when the integrating sphere is calibrated, the calibration pixel responds to a signal of the integrating sphere, and the imaged pixel is a dark level. After a cold space radiation signal value is obtained, subtracting a daily calibration radiometric calibration signal value from a dark background of an integrating sphere radiometric calibration signal value;
(3) the calculation of the calibration coefficient of the spectral radiance of the sun and the integrating sphere is carried out by the following method
(3-1) calculating the radiance of the entrance pupil of the imaging spectrometer by the following method
Wherein, L (k) is a wave band k, and the radiation brightness at the entrance pupil of the imaging spectrometer corresponding to the time t; e (lambda) is the radiation brightness of a standard calibration source corresponding to the wave band lambda, and tau (lambda) is the transmission efficiency; srf (k, λ) is the spectral response function of the k-band of the imaging spectrometer; lambda [ alpha ] 1 And λ 2 Respectively the starting wavelength and the cut-off wavelength of the imaging spectrometer; if the standard calibration source is the sun, E (lambda) is the corresponding radiation brightness of the sunlight at the wave band lambda on the calibration probe; if the standard calibration source is an integrating sphere, E (lambda) is a wave band lambdaThe radiance of the corresponding integrating sphere is typically scaled before emission.
And (3-2) calculating a spectral radiance scaling coefficient. Calculating spectral radiance scaling factor according to the calibration source radiance signal value and the entrance pupil sphere calibration source radiance recorded by the imaging spectrometer
C (k, t) is a wave band k, and the spectral radiance scaling coefficient of the imaging spectrometer corresponding to the moment t is obtained; s (k, t) is a signal value for subtracting a dark background;
(4) after obtaining the spectral radiance scaling factor of the integrating sphere, the solar spectral radiance data is inverted through the following formula. The spectral radiance calibration coefficient of the imaging spectrometer is adjusted through the comparison with the spectral radiance brightness of the theoretical sun, and the corrected spectral radiance calibration coefficient is the final on-orbit spectral radiance calibration coefficient
Wherein the content of the first and second substances,
the solar radiation brightness inverted by an integrating sphere spectral radiance scaling factor corresponding to the wave band k and the time t, c clb (k, t) is the corresponding integrating sphere spectral radiance scaling factor, S solar (k, t) are the corresponding solar radiation signal values with dark background subtracted;
(5) when the surround enters the near-fire track, modulating the refrigerator to the working temperature, and acquiring imaging spectrum data of a target area to obtain an imaging spectrum signal value of the target area;
(6) converting the acquired target area imaging spectrum signal value into radiance according to the acquired and corrected on-orbit spectral radiance scaling factor
L img (i,t,k)＝c(k,t)×S img (i,t,k)
Wherein L is img (i, t, k) is a wave band k, and at the moment t, the radiation brightness of the imaging data corresponding to the detection unit i is detected; s img (i, t, k) subtracting the dark background and the non-uniformity corrected imaging data signal values; and c (k, t) is an imaging spectrometer spectral radiance scaling factor obtained according to sunlight or integrating sphere light.
Claims (7)
1. An on-orbit multi-tracing spectral radiance scaling method for a deep space exploration imaging spectrometer is based on a sun-oriented mode (101), a sun-adjusting process (102), a sun-scaling process (103), a cold space adjusting process (104) and a cold space and integrating sphere scaling process (105), and is realized by using a surrounding device (106), an optical fiber (108), an imaging spectrometer (107), a sun scaling probe (109), an integrating sphere (110) and the sun (112), and the scaling method comprises the following steps:
(1) when the surround (106) reaches the distant celestial body orbit of the surround orbit, the surround (106) is close to the sun (112) and in the opposite-sun orientation mode (101);
(2) when the circulator (106) is in the sun adjustment process (102), the temperature of the refrigerating machine is adjusted to the working temperature, and the circulator (106) enables the sun calibration probe (109) to be aligned to the sun (112) through posture adjustment;
(3) after the posture of the surrounding device (106) is stable, entering a counterglow calibration process (103), collecting spectral radiation data of the sun (112) by an imaging spectrometer (107), performing counterglow calibration, responding to a sun signal by a calibration pixel, and taking an imaging pixel as a dark background;
(4) after the day calibration data is collected, the cold space calibration process (104) is carried out, the posture of the surrounding device (106) is adjusted again, the imaging spectrometer (107) faces back to the sun (112), after the posture is stabilized, the cold space and integrating sphere calibration process (105) is carried out, the imaging spectrometer (107) collects dark background data and spectral radiation data of an integrating sphere (110) arranged in the spectrometer, and the cold space and the integrating sphere are calibrated respectively; when the cold space is imaged, the imaging pixel and the calibration pixel are both dark backgrounds; when the integrating sphere is calibrated, the calibration pixel responds to a signal of the integrating sphere, and the imaged pixel is a dark level;
(5) deducting dark background signals in the calibration spectral radiation data for the day and the calibration spectral radiation data for the integrating sphere, and respectively calculating a spectral radiation calibration coefficient for calibrating the integrating sphere and a spectral radiation calibration coefficient for calibrating the day; calibrating a radiometric calibration coefficient for calibrating the integrating sphere by the radiometric calibration coefficient for daily calibration;
(6) when a surrounding device (106) arrives at a celestial body orbit, acquiring imaging spectrum data of a target area, and converting an original imaging spectrum into radiance data according to a dark background of each frame of imaging data and a calibrated integrating sphere scaling coefficient;
(7) and converting the imaging spectrum data of the target area at the corresponding moment into the radiance according to the on-orbit spectral radiance scaling coefficient.
2. The on-orbit multi-tracing spectral radiance scaling method for deep space exploration imaging spectrometer as claimed in claim 1, characterized in that the imaging spectrometer (107) in the method is connected with the sun scaling probe (109) and the integrating sphere (110) through the optical fiber (108) respectively, and is carried on the surround (106).
3. An in-orbit multi-tracing spectral radiance scaling method for deep space exploration imaging spectrometer as claimed in claim 1 characterized in that the detector in the imaging spectrometer (107) is divided into imaging area and scaling area and the pixels for scaling and the pixels for exploration imaging are different columns of pixels in the same area array detector.
4. An in-orbit multi-tracing spectral radiance scaling method for deep space exploration imaging spectrometer according to claim 1, characterized in that the imaging spectrometer (107) in the method observes the direction of the main optical axis (111) parallel to the surround device + Z direction, and the sun calibration probe observation direction, Nc direction, is included with the direction of the main optical axis (111) observed by the imaging spectrometer (107) by x.
5. An in-orbit multi-tracing spectral radiance scaling method for deep space exploration imaging spectrometers, according to claim 4, characterized in that the surround (106) is first in a sun-oriented mode (101), -Z-direction sun-pair, which uses the platform's mobility to perform y-angle attitude adjustment around the + X-axis, turning the sun-scaling probe (109) direction Nc to the sun illumination direction (113), where y + X is 180 °.
6. The on-orbit multi-tracing spectral radiance scaling method for deep space exploration imaging spectrometer of claim 1, characterized in that the scaling frequency is less than 2 times/month.
7. An in-orbit multi-traceable spectral radiometric calibration method for a deep space exploration imaging spectrometer, according to claim 1, wherein the calibration of cold space in step (4) requires celestial bodies not to enter the field of view of the imaging spectrometer (107).
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