CN105352609B - A kind of Optical remote satellite absolute radiation calibration method based on space lambert's sphere - Google Patents
A kind of Optical remote satellite absolute radiation calibration method based on space lambert's sphere Download PDFInfo
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- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
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Abstract
The solar radiation for decaying to OK range by space for its deployment lambert sphere in space, is introduced directly into satellite remote sensor by a kind of Optical remote satellite absolute radiation calibration method based on space lambert's sphere.Background signal is determined by motor-driven be imaged to deep space background of the attitude of satellite；Meet the period of calibration condition using Satellite Tool Kit calculating, and it is selected to as moment point, space lambert's sphere reflected signal is determined to space lambert's spheroid imaging by the way that the attitude of satellite is motor-driven, thus it is calculated as the irradiation level at moment point remote sensor entrance pupil, and passes through and obtain the Absolute Radiometric Calibration Coefficients that multi-group data determines single-point.Inventive process avoids the influences of atmospheric conditions and ground target characteristic, establish unified space optics radiation benchmark, meet full light path, full aperture, are distributed matched radiation calibration requirement with solar spectrum, can realize the normalization monitoring of satellite remote sensor.
Description
Technical field
The invention belongs to remote sensing satellite radiation calibration fields, are related to a kind of in-orbit radiativity to space optical remote satellite
The method that can carry out normalization absolute calibration.
Background technology
With going deep into for remote sensing application, quantitative remote sensing has become the emphasis of remote sensing application, and the basis of quantitative remote sensing is with before
Carry be remote sensor radiation calibration.After the radiation calibration of Space Remote Sensors can be divided into the Laboratory Calibration before transmitting and transmitting
In-flight calibration.After satellite launch, with the influence of the various factors such as working environment and long-term work state, may all it make
Calibration coefficient transmitting before transmitting changes, therefore the In-flight calibration after transmitting is to ensure that the pass of remotely-sensed data reliability and accuracy
Key.
In-flight calibration method after transmitting mainly has the methods of radiometric calibration site, onboard process.Radiometric calibration site is to rely on the earth
Large area uniform and stable atural object in surface realizes the radiation calibration of satellite in orbit as reference source, such method is subject to atural object mesh
Marking characteristic and atmospheric condition influences, and calibration precision is relatively low and cost is higher.Onboard process is realized by onboard process device
Calibration according to the difference of scaling light source used, mainly there is the modes such as Built-in light, the moon, fixed star, sun calibration.Built-in light is early
Common a kind of mode in the calibration scheme of phase, but Built-in light is a kind of artificial light source being added in light path, there are non-complete
The defects of light path and solar spectrum distributional difference are big.The moon by shining by the sun, spectral characteristic and solar spectrum with
And the moon absorption in itself, reflection characteristic are related, due to not yet obtaining accurate moon spatial distribution at present, irradiation model is still
The not up to precision of practical application, therefore can't be directly used in by way of moon calibration in absolute calibration, it may only use
In relative detector calibration.Fixed star is as a kind of Celestial Objects, it may have certain brightness, but the perseverance in addition to the sun in research at present
Star brightness is unable to reach requirement, is not used to spaceborne radiant calibration.A currently used scaling light source is the sun, it is one
Solar energy is decayed to suitable scope by a uniform and highly stable Lambertian source by way of reflecting or transmiting
Afterwards, it can be provided for Space Remote Sensors and stablize and accurately calibrate approach.By spaceborne sun diffusing panel, covered with diffuse material
Sun diffusing reflection plate be respectively provided with good uniformity and Lambertian characteristics, sun diffusing panel can be realized after opening to remote sensor
The sun is calibrated, and this method generally has many advantages, such as that unified, full light path, Spectral matching are good, is the master of current onboard process
Want one of means.But limited be subject to technical conditions, this mode needs to install individual sun diffusing reflection plate in itself in satellite,
Its complex structural designs is easily polluted be subject to satellite effluent, and adds the operation burden of whole star system, this in addition
The failure of parts will bring tremendous influence to subsequent calibration work in mode.
The content of the invention
Present invention solves the technical problem that it is：It has overcome the deficiencies of the prior art and provide a kind of based on space lambert's sphere
Optical remote satellite absolute radiation calibration method, ground can be broken away from the basis of additional Image processing equipment is not increased
The influence of target property and the influence of atmospheric conditions, using the sun as reference source realize full light path, full aperture, Spectral matching it is high-precision
Spend absolute radiometric calibration.
The present invention technical solution be：A kind of Optical remote satellite absolute radiometric calibration based on space lambert's sphere
Method includes the following steps：
(1) radiation pattern is discharged by carrier rocket radiation pattern or satellite and emits artificial lambert's ball into space
Body, diameter and the orbital position of sphere meet requirement of the satellite calibration to signal energy；Artificial lambert's sphere is surface
With the uniform spherome close to Lambertian characteristics；
(2) parameter of satellite remote sensor to be calibrated is set, the time of integration, gain and series is made to be protected in entire calibration process
It holds constant；
(3) attitude maneuver is carried out to satellite, satellite remote sensor to be calibrated is made to be directed toward deep space background, it is distant to obtain satellite to be calibrated
Sensor is imaged the gray value of pixel, carries out n times measurement, the gray value DN of the pixel k measured every time altogetherk0i, wherein n >=1, k
For the position of remote sensor pixel, the value range of k is the sum from 1 to remote sensor pixel, and i is the number of measurement, i=1,2,
3......,n；After n times are measured, the background signal average value DN of satellite remote sensor pixel k to be calibrated is calculatedk0,
(4) scene for including satellite, artificial lambert's sphere and the sun is established, the transmission of solar radiation energy is emulated, obtains
Position relationship between satellite, artificial lambert's sphere and sun three meets the period of calibration condition；The calibration condition
Including the visible condition of geometry and the visible condition of sensor, the visible condition of geometry is satellite and the company of artificial lambert's sphere therebetween
Line blocks from the earth, and the visible condition behaviour of sensor is made lambert's sphere and is in outside ground shadow, and artificial lambert's sphere can reflect
Solar radiant energy is imaged so as to fulfill observation；
(5) a certain imaging moment point is chosen from the period for meeting calibration condition, attitude maneuver is carried out to satellite, makes to treat
The entrance pupil normal for demarcating satellite remote sensor is directed toward lambert's sphere, and the azimuth that remote sensor is observed to artificial lambert's sphere is denoted as φ,
Obtain the relative distance L of artificial lambert's sphere and the sun1(j), artificial lambert's sphere and the phase at satellite remote sensor entrance pupil to be calibrated
Adjust the distance L2(j), line between the sun and artificial lambert's sphere and between satellite remote sensor to be calibrated and artificial lambert's sphere
Line angle thetaj, irradiation level at satellite remote sensor entrance pupil can be reached by thus obtaining artificial lambert's sphere reflected solar radiation
Ekj, the corresponding pixel position k and gray value DN of artificial lambert's sphere picture pointkj；
(6) under conditions of keeping φ constant, step (5) is repeated, the n times for obtaining pixel k measure corresponding gray value DNkj
With entrance pupil irradiation level Ekj, with reference to the background signal value DN of pixelk0, linear response relationship is established by least square method, obtains picture
The Absolute Radiometric Calibration Coefficients G of first kk,
Requirement of step (1) Satellite calibration to signal energy be：Satellite remote sensor can receive artificial lambert
The solar energy of sphere reflection, and the signal voltage that the detector in satellite remote sensor generates is located at detector saturation signal electricity
Between the 20%~80% of pressure value.
Artificial lambert's sphere is aluminum sphere, and surface is coated with blanc fixe by adhesive.
The present invention compared with prior art the advantages of be：
(1) the method for the present invention introduces remote sensor, reference source position indirectly using lambert's sphere using solar radiation as reference source
Outside whole system, the optical element in entire light path can be calibrated, can also be full of remote sensor aperture, meet full light
Road, full aperture are distributed matched radiation calibration requirement with solar spectrum；
(2) the method for the present invention uses the in-orbit direct reflected solar radiation of lambert's sphere, has broken away from atmospheric conditions and ground
The limitation of target property avoids the uncertainty that the environmental factors such as air, ground target introduce in solar radiation relays link,
Improve in-orbit absolute radiometric calibration precision；
(3) the method for the present invention establishes unified space optics radiation benchmark by disposing lambert's sphere in space, can
To realize normalization monitoring to satellite remote sensor, the rdaiation response variation of satellite remote sensor is corrected in time, improves satellite remote sensor
In-orbit radiation calibration response efficiency；
(4) the method for the present invention can carry out calibration by using in-orbit lambert's sphere, it is easy to accomplish, without in satellite sheet
Body installs additional calibration instrument equipment, is conducive to mitigate the burden of existing Optical remote satellite On-Star system.
Description of the drawings
Fig. 1 is the FB(flow block) of the method for the present invention；
Fig. 2 is the solar radiant energy TRANSFER MODEL schematic diagram of the present invention；
Fig. 3 is the characteristic parameter schematic diagram of the present invention；
Fig. 4 is relation of lambert's sphere reflected signal DN values with deep space background signal DN values of the present invention.
Specific embodiment
As shown in Figure 1, being the FB(flow block) of the method for the present invention, key step is as follows：
(1) radiation pattern is discharged by carrier rocket radiation pattern or satellite and emits artificial lambert's ball into space
Body, diameter and the orbital position of sphere meet requirement of the satellite calibration to signal energy；
Satellite requirement of the calibration to signal energy receives sphere reflected sunlight energy for satellite remote sensor, in remote sensor
Detector generate signal voltage be located between the 20%~80% of detector saturation signal voltage value.
Artificial lambert's sphere has the uniform spherome close to Lambertian characteristics for surface, and a kind of embodiment therein is
Barium sulfate lambert's sphere, barium sulfate lambert sphere are made of the method for spraying.First by uniform aluminum spherome surface sand
Paper polishes, and blanc fixe and milky white adhesive is mixed and made into the aluminum spherome surface that half paste is equably sprayed on polishing, after dry
Artificial lambert's sphere can be obtained.
(2) parameter of satellite remote sensor to be calibrated is set, the time of integration, gain and series is made to be protected in entire calibration process
It holds constant.
(3) attitude maneuver is carried out to satellite, satellite remote sensor to be calibrated is made to be directed toward deep space background, it is distant to obtain satellite to be calibrated
Sensor is imaged the gray value of pixel, carries out n times (n >=1, number is more, and precision is higher) and measures, the pixel measured every time
Gray value DNk0i, wherein, k is the position (value range of k is the sum from 1 to remote sensor pixel) of remote sensor pixel, and i is survey
The number of amount, i=1,2,3......, n after n times are measured, calculate the background letter of satellite remote sensor pixel k to be calibrated
Number average value DNk0
(4) using the transmission of Satellite Tool Kit STK emulation solar radiant energies, establish comprising satellite, lambert's sphere and too
The scene of sun draws the period under the conditions of the position relationship between satellite, lambert's sphere and sun three meets calibration, too
The TRANSFER MODEL of positive radiation energy as shown in Fig. 2, in Fig. 2, lambert's sphere by after the solar radiant energy received to external reflection, it is distant
The radiation energy that sensor reception is reflected by lambert's sphere.
Calibration condition includes the visible condition of geometry and the visible condition of sensor, and two conditions must simultaneously meet.Geometry can
See that condition is blocked for line of the satellite with lambert's sphere therebetween from the earth.The visible condition of sensor is in for lambert's sphere
Outside ground shadow, lambert's sphere can reflected solar radiation can so as to fulfill observation be imaged.
(5) a certain imaging moment point is arbitrarily chosen from the period for meeting calibration condition, attitude maneuver is carried out to satellite,
Make direction lambert's sphere of satellite remote sensor to be calibrated, the detector in satellite remote sensor can obtain lambert's sphere reflection sun
Radiate getable signal.By remote sensor observation lambert's sphere azimuth, i.e., the line between remote sensor and lambert's sphere and
The angle in remote sensor entrance pupil direction is denoted as φ.
(6) imaging moment point moment, the position relationship between satellite, lambert's sphere and sun three are obtained.Lambert's sphere
It is transmitted to after the certain tracks of space, it is necessary to estimate the in-orbit position of lambert's sphere by ground survey mode, obtains satellite to bright
Three characteristic parameters inscribed during primary spheroid imaging, the relative distance L including lambert's sphere and the sun1(j), lambert's sphere is with treating
Calibrate the relative distance L at satellite remote sensor entrance pupil2(j), line between the sun and lambert's sphere and satellite remote sensing to be calibrated
The angle theta of line between device and lambert's spherej.The signal of characteristic parameter is as shown in Figure 3.
(7) the irradiation level E at solar radiation arrival lambert's sphere is calculated by equation belowj。
Wherein：
E (λ) reaches the spectral irradiance at lambert's sphere, unit Wm for solar radiation-2·μm-1；
λ1、λ2The spectral coverage lower and upper limit of remote sensor respectively to be calibrated；
R is solar radius, R=6.9599 × 108m；
J is pendulous frequency.
M (λ) is spectral radiant exitance (the unit Wm of the sun-2·μm-1), solar source can be equivalent into temperature
For the radiation black matrix of 5900K, according to Planck radiation law, the spectral radiant exitance of the sun is represented byIn formula, λ is wavelength, c1For the first black body radiation constant (c1=
3.741844×104W·m-2·μm4), c2For the second black body radiation constant (c2=14388 μm of K), T is thermodynamic temperature (T
=5900K).
(8) the irradiation level E at satellite remote sensor entrance pupil is calculated by equation belowkj。
Wherein：
ρ is the surface reflectivity of lambert's sphere；
f(θj) the angle factor between reflected energy and projectile energy, it is built by carrying out optics to space sphere target
Mould is obtained：
Wherein, d is lambert's sphere diameter；
(9) lambert's sphere is Point Target, after lambert's spheroid imaging, obtains the position of its formed picture point on the detector
Put with gray value size, be denoted as k, DN respectivelykj.The relation such as figure of lambert's sphere reflected signal DN values and deep space background signal DN values
Shown in 4, in situation shown in figure, image point position k=15, picture point gray value DNkj=B.
(10) under conditions of keeping φ constant, step (5)~(9) are repeated, the n times for obtaining pixel k measure corresponding ash
Angle value DNkjWith entrance pupil irradiation level Ekj.With reference to the background signal value DN of pixelk0, linear response is established by least square method and is closed
System, obtains the Absolute Radiometric Calibration Coefficients G of pixel kk, specific formula is as follows：
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (3)
1. a kind of Optical remote satellite absolute radiation calibration method based on space lambert's sphere, it is characterised in that including walking as follows
Suddenly：
(1) radiation pattern is discharged by carrier rocket radiation pattern or satellite and emits artificial lambert's sphere into space,
The diameter of sphere meets requirement of the satellite calibration to signal energy with orbital position；Artificial lambert's sphere has for surface
Close to the uniform spherome of Lambertian characteristics；
(2) parameter of satellite remote sensor to be calibrated is set, the time of integration, gain and series is made to be kept not in entire calibration process
Become；
(3) attitude maneuver is carried out to satellite, satellite remote sensor to be calibrated is made to be directed toward deep space background, obtains satellite remote sensor to be calibrated
The gray value of pixel is imaged, carries out n times measurement, the gray value DN of the pixel k measured every time altogetherk0i, wherein n >=1, k are distant
The position of sensor pixel, the value range of k are the sums from 1 to remote sensor pixel, and i is the number of measurement, i=1,2,
3......,n；After n times are measured, the background signal average value DN of satellite remote sensor pixel k to be calibrated is calculatedk0,
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<mi>i</mi>
<mo>=</mo>
<mi>n</mi>
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</munderover>
<msub>
<mi>DN</mi>
<mrow>
<mi>k</mi>
<mn>0</mn>
<mi>i</mi>
</mrow>
</msub>
<mo>;</mo>
</mrow>
(4) establish and include the scene of satellite, artificial lambert's sphere and the sun, emulate the transmission of solar radiation energy, obtain satellite,
Position relationship between artificial lambert's sphere and sun three meets the period of calibration condition；The calibration condition includes several
What visible condition and visible condition of sensor, the visible condition of geometry for satellite and the line of artificial lambert's sphere therebetween from
The earth blocks, and the visible condition behaviour of sensor is made lambert's sphere and is in outside ground shadow, and artificial lambert's sphere can reflect sun spoke
Penetrating can be imaged so as to fulfill observation；
(5) a certain imaging moment point is chosen from the period for meeting calibration condition, attitude maneuver is carried out to satellite, is made to be calibrated
The entrance pupil normal of satellite remote sensor is directed toward lambert's sphere, and the azimuth that remote sensor is observed to artificial lambert's sphere is denoted as φ, obtains
The relative distance L of artificial lambert's sphere and the sun1(j), artificial lambert's sphere at satellite remote sensor entrance pupil to be calibrated it is opposite away from
From L2(j), line between the sun and artificial lambert's sphere and the company between satellite remote sensor to be calibrated and artificial lambert's sphere
The angle theta of linej, irradiation level E at satellite remote sensor entrance pupil can be reached by thus obtaining artificial lambert's sphere reflected solar radiationkj,
The corresponding pixel position k and gray value DN of artificial lambert's sphere picture pointkj, j is pendulous frequency；
(6) under conditions of keeping φ constant, step (5) is repeated, the n times for obtaining pixel k measure corresponding gray value DNkjWith enter
Pupil irradiation level Ekj, with reference to the background signal value DN of pixelk0, linear response relationship is established by least square method, obtains pixel k
Absolute Radiometric Calibration Coefficients Gk,
<mrow>
<msub>
<mi>G</mi>
<mi>k</mi>
</msub>
<mo>=</mo>
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<mi>j</mi>
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<mo>&lsqb;</mo>
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<mo>(</mo>
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<mi>DN</mi>
<mrow>
<mi>k</mi>
<mi>j</mi>
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<mo>-</mo>
<msub>
<mi>DN</mi>
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<mi>k</mi>
<mn>0</mn>
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<mo>)</mo>
</mrow>
<mo>&CenterDot;</mo>
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<mi>E</mi>
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<mi>k</mi>
<mi>j</mi>
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</mrow>
<mrow>
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<mi>j</mi>
<mo>=</mo>
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<mi>E</mi>
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<mi>j</mi>
</mrow>
<mn>2</mn>
</msubsup>
</mrow>
</mfrac>
<mo>.</mo>
</mrow>
2. a kind of Optical remote satellite absolute radiation calibration method based on space lambert's sphere according to claim 1,
It is characterized in that：Requirement of step (1) Satellite calibration to signal energy be：Satellite remote sensor can receive artificial bright
The solar energy of primary sphere reflection, and the signal voltage that the detector in satellite remote sensor generates is located at detector saturation signal
Between the 20%~80% of voltage value.
3. a kind of Optical remote satellite absolute radiometric calibration side based on space lambert's sphere according to claim 1 or 2
Method, it is characterised in that：Artificial lambert's sphere is aluminum sphere, and surface is coated with blanc fixe by adhesive.
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| CN115524016B (en) * | 2022-09-01 | 2023-04-11 | 国家卫星气象中心(国家空间天气监测预警中心) | Correction method for relative calibration to absolute calibration of black body on satellite of satellite remote sensor |
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