CN113945278A - Space optical remote sensing instrument reflection wave band on-orbit full dynamic range radiometric calibration method - Google Patents
Space optical remote sensing instrument reflection wave band on-orbit full dynamic range radiometric calibration method Download PDFInfo
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Abstract
The invention discloses an on-orbit full dynamic range radiometric calibration method for reflection wave bands of a space optical remote sensing instrument, which comprises the following steps of: (1) establishing a variable radiance scaling equation before emission; (2) establishing a variable integral time scaling equation before transmission; (3) establishing a function mapping relation between two calibration equations before transmission; (4) calculating the weighted average spectral radiance L of the diffuse reflection plate after track entering in the wave band0(ii) a (5) Establishing a variable integral time scaling equation after on-track attenuation; (6) and updating the variable radiance scaling equation after the on-track attenuation. The method of the invention does not need to add an additional calibration device on the basis of the traditional solar diffuse reflection plate, thereby ensuring the reliability of the on-orbit operation of the instrument; the flow is simple, and the universality is strong; the multi-point calibration data is obtained by setting the multi-gear integration time to cover the whole dynamic range of the instrument, and the on-orbit updating of the nonlinear calibration parameters can be realized, which is an advantage that the traditional two-point on-orbit calibration method does not have.
Description
Technical Field
The invention belongs to the technical field of radiometric calibration of optical remote sensing instruments, and particularly relates to an on-orbit full-dynamic-range radiometric calibration method for reflection bands of a space optical remote sensing instrument.
Background
Before emission, a spatial optical remote sensing instrument usually adopts a standard light source of an integrating sphere in a laboratory to finish a radiation calibration test of a reflection waveband, and obtains a radiation response model and calibration parameters of the instrument in the whole dynamic range. The remote sensing instrument is influenced by vibration in the transmitting process, severely changed temperature, irradiation, pollution, attenuation of components and the like in the on-orbit running period, and the calibration parameters and the like of the remote sensing instrument can generate sudden change or gradual change. Therefore, in order to improve the application level of high-precision quantification of remote sensing data, the on-orbit radiometric calibration of the instrument is required periodically.
At present, the international mainstream typical space optical remote sensing instrument basically adopts the technical scheme of on-orbit radiometric calibration of 'sun + diffuse reflection plate' or 'sun + attenuation screen + diffuse reflection plate', and uniform and highly stable solar radiation is introduced as a standard source for on-orbit radiometric calibration of reflection wave band. However, the traditional technical scheme of "sun + diffuse reflection plate" or "sun + attenuation screen + diffuse reflection plate" is usually based on two-point (diffuse reflection plate, cold space) calibration, and when the radiation response model of the remote sensing instrument has obvious nonlinear or nonlinear term on-orbit change, the two-point calibration cannot solve the calibration parameters of the nonlinear calibration equation. Therefore, an effective on-track full dynamic range radiometric calibration method needs to be researched, and a calibration equation is obtained in a multi-point calibration mode in the whole dynamic range.
Disclosure of Invention
The invention aims to solve the technical problems that full-dynamic-range radiometric calibration cannot be realized and instrument nonlinear calibration parameters cannot be obtained in the conventional on-orbit radiometric calibration method, and provides an on-orbit full-dynamic-range radiometric calibration method without adding an additional calibration device on the basis of a traditional solar diffuse reflection plate.
In order to solve the problems, the on-orbit full dynamic range radiometric calibration method provided by the invention comprises the following specific steps:
(1) before the space optical remote sensing instrument transmits, under the condition of keeping the integration time of the instrument unchanged, a radiance scaling equation L (f) (DN) of a reflection waveband is obtained by changing the radiance level of a ground scaling light source, wherein L is the radiance received by the instrument, DN is a response signal of the instrument, and f is a function expression of the radiance varying scaling equation;
(2) before the space optical remote sensing instrument emits, under the condition of keeping the radiance level of the ground calibration light source unchanged, the radiometric calibration equation L of the reflection wave band is obtained by changing the integral time gear of the instrumentint＝fint(DN)，LintIs the equivalent radiance of the instrument in variable integration time, DN is the response signal of the instrument, fintIs a function expression of a variable integral time scaling equation;
(3) establishing a variable radiance scaling equation f and a variable integral time scaling equation fintThe functional mapping relation between the two is L ═ F (L)int) L is the radiance received by the instrument, LintThe equivalent radiance of the variable integration time received by the instrument, wherein F is an expression of a function mapping relation;
(4) after the space optical remote sensing instrument is launched and put into orbit, calculating the spectral radiance L generated by the atmospheric upper-bound solar illumination diffuse reflection plate in the instrument observation directionSD(λ); calculating a weighted average spectral radiance L within a band in combination with a pre-emission laboratory measured instrument spectral response function R (λ)0；
(5) After the spatial optical remote sensing instrument is launched and put into orbit, observing the diffuse reflection plate in a multi-gear integration time mode and collecting calibration data; when the integration time is TintThe equivalent radiance of the variable integration time received by the instrument is Lint＝Tint·L0When the corresponding instrument response signal is DNint(ii) a By setting the multi-step integration time, multiple calibration data points (DN) can be obtained over the entire dynamic rangeint，Lint) Obtaining the variable integral time scaling equation after the on-orbit attenuation by adopting a method of regression analysis of a plurality of groups of data points
Is the variable integration time equivalent radiance received by the instrument after the track, DN is the instrument's response signal,
is a function expression of the on-orbit variable integration time scaling equation;
(6) utilizing the function mapping relation F of the two scaling equations obtained in the step (3) and the variable integration time scaling equation after the on-track attenuation obtained in the step (5)
The scaling equation of the variable radiance of the instrument after on-track attenuation can be obtained
LorbitIs the intensity of the radiation received by the instrument after the track,
is the equivalent radiance of the variable integration time received by the instrument after the track.
Preferably, the spectral radiance of step (4)
Wherein λ is a wavelength; thetai，
Respectively as the incident zenith angle and azimuth angle of the sun at the calibration time; thetav，
Respectively the observation zenith angle and azimuth angle of the instrument；E0(λ) is solar spectral irradiance of the upper atmospheric boundary; d is a day-ground distance factor of the calibration time; f. ofrIs the bi-directional reflectivity distribution function of the diffuse reflection plate at the calibration moment.
Preferably, the weighted average spectral radiance within the wavelength band of step (4)
Wherein λ is the wavelength, λ1、λ2Lower and upper wavelength limits, respectively; l isSD(lambda) is the spectral radiance produced by the atmospheric upper sun illumination diffuse reflection plate in the instrument observation direction; r (λ) is the instrument spectral response function measured in the laboratory prior to transmission.
Preferably, the integration time T in step (5)intTo normalize the integration time, the dimension is 1, defined as
In the formula, tintIs the physical integration time of the remote sensing instrument,
and (3) calibrating the physical integration time of the remote sensing instrument for earth observation and variable radiance.
Compared with the prior art, the method has the following advantages:
the invention does not need to add an additional calibration device on the basis of the traditional solar diffuse reflection plate, thereby ensuring the reliability of the on-orbit operation of the instrument; the method has good universality and simple flow and is easy to implement on track.
The invention obtains the multi-point calibration data by setting the multi-gear integration time to cover the whole dynamic range of the instrument, can realize the on-orbit updating of the nonlinear calibration parameters, and has the advantages that the traditional two-point on-orbit calibration method does not have.
Drawings
Fig. 1 is a schematic flow chart of an implementation of an embodiment of the present invention.
Fig. 2 is an example of a variable radiance scaling equation in an embodiment of the present invention.
FIG. 3 is an example of a variable integration time scaling equation in an embodiment of the present invention.
Fig. 4 is an example of a functional mapping relationship between the variable radiance and the variable integral time scaling equation in an embodiment of the present invention.
Detailed Description
The following detailed description of embodiments of the present invention will be made with reference to the accompanying drawings and examples.
The implementation of the space optical remote sensing instrument reflection band on-orbit full dynamic range radiometric calibration method needs 6 steps as shown in figure 1.
(1) And establishing a variable radiance scaling equation before emission.
In a laboratory darkroom, the physical integration time of the instrument selects a gear commonly used for earth observation
And keeping the parameter unchanged, and adjusting the radiance level of the integrating sphere calibration light source to enable the light intensity to cover the whole dynamic range of the instrument. Under each radiance level, collecting the response signal DN of the instrument to the observation of the integrating spherei。
Under each radiance level, after the data acquisition of the remote sensing instrument is finished, the integrating sphere is synchronously calibrated by using a high-precision standard transmission spectrum radiometer to obtain spectrum radiance
Calculating a weighted average spectral radiance L within a band in combination with a pre-emission laboratory measured instrument spectral response function R (λ)i。
Multiple sets of data points (DN) are used throughout the dynamic range of the instrumenti，Li) The regression analysis method obtains a variable radiance scaling equation L (f) (DN) before emission, wherein L is the radiance received by the instrument, DN is a response signal of the instrument, and f is a function expression of the variable radiance scaling equation. FIG. 2 is one embodiment of this equation.
(2) And establishing a variable integration time scaling equation before transmission.
In a laboratory darkroom, selecting a proper integrating sphere spectral radiance level
Keeping the radiance level unchanged, changing the integral time gear of the remote sensing instrument to make the signal cover the whole dynamic range of the instrument, and collecting the response signal DN of the observation integrating sphere under each gear of integral timeint。
From the instrument spectral response function R (lambda) and integrating sphere spectral radiance measured in the pre-launch laboratory
Calculating a weighted average spectral radiance L within a bandIS(ii) a The brightness of the radiation received by the instrument is L under each gear of integration timeint＝Tint·LIS，TintTo normalize the integration time.
Multiple sets of data points (DN) are used throughout the dynamic range of the instrumentint，Lint) Obtaining variable integral time scaling equation L before emission by regression analysis methodint＝fint(DN)，LintIs the equivalent radiance of the instrument in variable integration time, DN is the response signal of the instrument, fintIs a functional expression of a variable integration time scaling equation. FIG. 3 is one embodiment of this equation.
(3) And establishing a function mapping relation between two calibration equations before transmission.
In the dynamic range of the whole instrument, a response signal sequence is generated and is respectively substituted into two calibration equations to obtain two radiance sequences L and LintSimilarly, the function mapping relation L ═ F (L) between the two calibration equations before transmission can be obtained by using the regression analysis methodint) L is the radiance received by the instrument, LintThe equivalent radiance of the variable integration time received by the instrument, and F is an expression of a function mapping relation. FIG. 4 is one embodiment of the mapping relationship.
(4) Calculating the post-orbit diffuse reflection plateWeighted average spectral radiance L within a band0。
Calculating the spectral radiance L generated by the atmospheric upper-bound sun illumination diffuse reflection plate in the observation direction of the instrument according to the orbit and attitude parameters of the space platform, the installation matrix parameters of the diffuse reflection plate, the instrument and the platform, the characterization parameters of the optical characteristics of the diffuse reflection plate, the position of the sun, the spectral irradiance parameters and the likeSD(λ); calculating the weighted average spectral radiance L in the corresponding band in combination with the instrument spectral response function R (lambda) measured in the laboratory before emission0。
(5) And establishing a variable integral time scaling equation after on-track attenuation.
After the space optical remote sensing instrument is launched into orbit, the instrument observes the diffuse reflection plate by multiple grades of different integration time and collects calibration data. When the integration time is TintThe equivalent radiance of the variable integration time received by the instrument is Lint＝Tint·L0When the corresponding instrument response signal is DNint。
By setting multiple different integration times, multiple calibration data points (DN) can be obtained over the entire dynamic rangeint，Lint) Obtaining the variable integral time scaling equation after the on-orbit attenuation by adopting a method of regression analysis of a plurality of groups of data points
Is the variable integration time equivalent radiance received by the instrument after the track, DN is the instrument's response signal,
is a functional expression of the on-track variable integration time scaling equation.
(6) And updating the variable radiance scaling equation after the on-track attenuation.
Utilizing the function mapping relation F of the two scaling equations obtained in the step (3) and the variable integration time scaling equation after the on-track attenuation obtained in the step (5)
The scaling equation of the variable radiance of the instrument after on-track attenuation can be obtained
LorbitIs the intensity of the radiation received by the instrument after the track,
The above description is only an example of the present invention, and is not intended to limit the embodiments, and all embodiments are not necessarily exhaustive. It will be understood by those skilled in the art that any modification, equivalent substitution, or obvious change or modification derived therefrom, which fall within the spirit and principle of the present invention, should be included in the scope of the present invention.
Claims (4)
1. A space optical remote sensing instrument reflection wave band on-orbit full dynamic range radiometric calibration method is characterized by comprising the following steps:
(1) before the space optical remote sensing instrument transmits, under the condition of keeping the integration time of the instrument unchanged, a radiance scaling equation L (f) (DN) of a reflection waveband is obtained by changing the radiance level of a ground scaling light source, wherein L is the radiance received by the instrument, DN is a response signal of the instrument, and f is a function expression of the radiance varying scaling equation;
(2) before the space optical remote sensing instrument emits, under the condition that the radiance level of a ground calibration light source is kept unchanged, a radiometric calibration equation of a reflection waveband is obtained by changing an integral time gear of the instrument:
Lint＝fint(DN)，
in the formula LintIs the equivalent radiance of the instrument in variable integration time, DN is the response signal of the instrument, fintIs a function of a variable integral time scaling equationA numerical expression;
(3) establishing a variable radiance scaling equation expression f and a variable integral time scaling equation expression fintThe functional mapping relation between the two is L ═ F (L)int) L is the radiance received by the instrument, LintThe equivalent radiance of the variable integration time received by the instrument, wherein F is an expression of a function mapping relation;
(4) after the space optical remote sensing instrument is launched and put into orbit, calculating the spectral radiance L generated by the atmospheric upper-bound solar illumination diffuse reflection plate in the instrument observation directionSD(λ) calculating a weighted average spectral radiance L in the band in combination with a pre-emission laboratory measured instrument spectral response function R (λ)0λ is the wavelength;
(5) after the spatial optical remote sensing instrument is launched and put into orbit, observing the diffuse reflection plate in a multi-gear integration time mode and collecting calibration data; when the integration time is TintThe equivalent radiance of the variable integration time received by the instrument is Lint＝Tint·L0When the corresponding instrument response signal is DNint(ii) a By setting the multi-step integration time, multiple calibration data points (DN) can be obtained over the entire dynamic rangeint，Lint) Obtaining the variable integral time scaling equation after the on-orbit attenuation by adopting a method of regression analysis of a plurality of groups of data points
Is the variable integration time equivalent radiance received by the instrument after the track, DN is the instrument's response signal,
is a function expression of the on-orbit variable integration time scaling equation;
(6) using the function mapping relation expression F of the two scaling equations obtained in the step (3) and the variable integration time scaling equation expression after the on-track attenuation obtained in the step (5)
The scaling equation of the variable radiance of the instrument after on-track attenuation can be obtained
LorbitIs the intensity of the radiation received by the instrument after the track,
is the equivalent radiance of the variable integration time received by the instrument after the track.
2. The method for radiometric calibration of the full dynamic range of the spatial remote sensing instrument in-orbit at the reflection band of claim 1, wherein the spectral radiance in step (4)
Wherein λ is a wavelength; thetai，
Respectively as the incident zenith angle and azimuth angle of the sun at the calibration time; thetav，
Respectively an observation zenith angle and an azimuth angle of the instrument; e0(λ) is solar spectral irradiance of the upper atmospheric boundary; d is a day-ground distance factor of the calibration time; f. ofrIs the bi-directional reflectivity distribution function of the diffuse reflection plate at the calibration moment.
3. The method for radiometric calibration of the full dynamic range of the reflection band of space optical remote sensing instrument according to claim 1, wherein the weighted average spectral radiance in said band in step (4)
Wherein λ is the wavelength, λ1、λ2Lower and upper wavelength limits, respectively; l isSD(lambda) is the spectral radiance produced by the atmospheric upper sun illumination diffuse reflection plate in the instrument observation direction; r (λ) is the instrument spectral response function measured in the laboratory prior to transmission.
4. The method for radiometric calibration of the on-orbit full dynamic range of the reflection band of the space optical remote sensing instrument according to claim 1, wherein the integration time T in step (5)intTo normalize the integration time, the dimension is 1, defined as
In the formula, tintIs the physical integration time of the remote sensing instrument,
and (3) calibrating the physical integration time of the remote sensing instrument for earth observation and variable radiance.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116625647A (en) * | 2023-07-20 | 2023-08-22 | 中国科学院合肥物质科学研究院 | Method, device, apparatus and storage medium for determining responsivity coefficient of optical remote sensor |
| CN116625647B (en) * | 2023-07-20 | 2023-10-27 | 中国科学院合肥物质科学研究院 | Method, device, apparatus and storage medium for determining responsivity coefficient of optical remote sensor |
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