CN110764153B - System and method for correcting on-orbit error of hot mirror back lobe of satellite-borne microwave imager - Google Patents
System and method for correcting on-orbit error of hot mirror back lobe of satellite-borne microwave imager Download PDFInfo
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Abstract
The invention provides a system and a method for correcting an on-orbit error of a hot mirror back lobe of a satellite-borne microwave imager, wherein the method comprises the following steps: s1: the hot mirror related parameter module provides parameters for the hot mirror back lobe pointing position acquisition module, the earth radiation quantity acquisition module and the hot mirror back lobe error acquisition module; s2: the hot mirror back lobe pointing position acquisition module acquires the hot mirror back lobe pointing position according to the parameters and transmits the position to the terrestrial radiation amount acquisition module; s3: the earth radiation quantity acquisition module acquires earth radiation quantity corresponding to the pointing position of the hot mirror back lobe according to the parameters and the position, and transmits the earth radiation quantity to the hot mirror back lobe error acquisition module; s4: and the hot mirror back lobe error acquisition module acquires a hot mirror back lobe error according to the parameters and the earth radiation quantity. The method can effectively and accurately obtain the hot mirror back lobe error of the satellite-borne microwave imager in orbit, and is scientific, reasonable and easy to realize.
Description
Technical Field
The invention relates to the technical field of space remote sensing, in particular to a hot mirror back lobe on-orbit error correction system and method for a satellite-borne microwave imager.
Background
The microwave imager can invert parameters such as temperature, wind speed, sea ice, accumulated snow, soil humidity and precipitation by measuring surface and atmospheric radiation information, and is widely applied to the detection field of environments such as atmosphere, ocean and land. Whether the microwave imager can obtain accurate and effective surface brightness temperature remote sensing data during on-orbit operation mainly depends on the calibration precision of the microwave imager. Therefore, in order to obtain accurate and effective remote sensing data of the surface brightness temperature, the calibration precision of the microwave imager needs to be greatly improved.
In the conventional calibration process, the heat source is at a bright temperature (T)BH) Is composed of effective radiant quantity of heat source and effective radiant quantity of heat mirror, TBH＝(1-εH)THS+εHTHMWherein, THSIs the radiant quantity of the heat source, THMIs the radiation quantity of the hot mirror, epsilonHIs the emissivity of the hot mirror. However, the brightness temperature of the heat source is also influenced by the effective radiation quantity received by the hot mirror back lobe on the earth surface, so in order to improve the calibration precision of the microwave imager, it is very necessary to accurately calculate the error caused by the hot mirror back lobe.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a hot mirror back lobe on-orbit error correction system and method for a satellite-borne microwave imager. The technical scheme of the invention is as follows:
an on-orbit error correction system for a hot mirror back lobe of a satellite-borne microwave imager comprises:
the system comprises a hot mirror related parameter acquisition module, a hot mirror back lobe pointing position acquisition module, an earth radiation quantity acquisition module and a hot mirror back lobe error acquisition module;
the hot mirror related parameter module is used for providing the following parameters for the hot mirror back lobe pointing position acquisition module, the earth radiation amount acquisition module and the hot mirror back lobe error acquisition module: the position of the hot mirror, the pointing angle of a hot mirror back lobe, the backward leakage coefficient of the hot mirror back lobe and a hot mirror antenna directional diagram;
the hot mirror back flap pointing position acquisition module: the hot mirror back lobe directional position acquisition module is used for acquiring the hot mirror back lobe directional position according to the position of the hot mirror, the directional angle of the hot mirror back lobe and the hot mirror antenna directional diagram, and transmitting the position to the earth radiation quantity acquisition module;
the earth radiation quantity acquisition module: the hot mirror back lobe error acquisition module is used for acquiring the earth radiation quantity corresponding to the hot mirror back lobe pointing position according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, a hot mirror antenna directional diagram and the hot mirror back lobe pointing position, and transmitting the earth radiation quantity to the hot mirror back lobe error acquisition module;
the hot mirror back lobe error acquisition module: and the system is used for obtaining the radiation quantity received by the hot mirror back lobe, namely the hot mirror back lobe error according to the backward leakage coefficient of the hot mirror back lobe and the earth radiation quantity corresponding to the pointing position of the hot mirror back lobe.
Optionally, the hot mirror back lobe pointing position is a position of the hot mirror back lobe pointing point or pointing surface on the earth.
Optionally, the hot mirror back lobe pointing position obtaining module fits the hot mirror back lobe pointing region into an ellipsoid on the ground according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, and the hot mirror antenna directional pattern, so as to obtain the position of the hot mirror back lobe pointing surface on the earth.
Optionally, the hot mirror back lobe pointing position obtaining module obtains a position of the hot mirror back lobe pointing point on the earth according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, and the hot mirror antenna pattern.
Optionally, the hot mirror back lobe error is obtained according to the following formula: t isKL＝η×TE；
Wherein η is the backward leakage coefficient of the hot mirror back lobe, TEAnd the earth radiation quantity corresponding to the pointing position of the hot mirror back lobe.
An on-orbit error correction method for a hot mirror back lobe of a satellite-borne microwave imager is applied to the system and comprises the following steps:
s1: the hot mirror related parameter module provides the following parameters for the hot mirror back lobe pointing position acquisition module, the earth radiation amount acquisition module and the hot mirror back lobe error acquisition module: the position of the hot mirror, the pointing angle of a hot mirror back lobe, the backward leakage coefficient of the hot mirror back lobe and a hot mirror antenna directional diagram;
s2: the hot mirror back lobe pointing position acquisition module acquires a hot mirror back lobe pointing position according to the position of the hot mirror, the pointing angle of the hot mirror back lobe and a hot mirror antenna directional diagram, and transmits the position to the terrestrial radiation quantity acquisition module;
s3: the earth radiation quantity acquisition module acquires earth radiation quantity corresponding to the hot mirror back lobe pointing position according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, a hot mirror antenna directional diagram and the hot mirror back lobe pointing position, and transmits the earth radiation quantity to the hot mirror back lobe error acquisition module;
s4: the hot mirror back lobe error acquisition module acquires the radiant quantity received by the hot mirror back lobe, namely the hot mirror back lobe error according to the backward leakage coefficient of the hot mirror back lobe and the terrestrial radiant quantity corresponding to the pointed position of the hot mirror back lobe.
Optionally, the hot mirror back lobe pointing position is a position of the hot mirror back lobe pointing point or pointing surface on the earth.
Optionally, the hot mirror back lobe pointing position obtaining module fits the hot mirror back lobe pointing region into an ellipsoid on the ground according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, and the hot mirror antenna directional pattern, so as to obtain the position of the hot mirror back lobe pointing surface on the earth.
Optionally, the hot mirror back lobe pointing position obtaining module obtains a position of the hot mirror back lobe pointing point on the earth according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, and the hot mirror antenna pattern.
Optionally, the hot mirror back lobe error is obtained according to the following formula: t isKL＝η×TE；
Wherein η is the backward leakage coefficient of the hot mirror back lobe, TEAnd the earth radiation quantity corresponding to the pointing position of the hot mirror back lobe.
Compared with the prior art, the invention has the following beneficial effects:
the technical scheme of the invention is based on a satellite-borne platform and combined with a domestic system structure of the load of a Fengyun three-number microwave imager, so that the error of the hot mirror back lobe based on the hot mirror back lobe pointing point can be calculated, and the error of the hot mirror back lobe based on the hot mirror back lobe pointing surface can also be calculated.
The technical scheme of the invention is scientific, reasonable and easy to realize, and can solve the problem of accurate calculation of errors caused by a hot mirror back lobe during the on-orbit period of the microwave imager, thereby effectively and accurately eliminating the influence of the errors on the brightness temperature of a heat source, improving the on-orbit calibration precision of the microwave imager, being beneficial to evaluating the actual on-orbit calibration effect of the instrument, being capable of pertinently improving the system calibration scheme and further improving the radiation measurement result of the satellite-borne microwave imager.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural diagram of an on-orbit error correction system for a hot mirror back lobe of a satellite-borne microwave imager according to an embodiment of the present invention;
FIG. 2 is a schematic view of the earth's range covered by the hot mirror back lobe direction in accordance with an embodiment of the present invention;
fig. 3 is a flowchart of an on-orbit error correction method for a hot mirror back lobe of a satellite-borne microwave imager according to an embodiment of the present invention.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Referring to fig. 1 and 2, an on-orbit error correction system for a hot mirror back lobe of a satellite-borne microwave imager includes:
the system comprises a hot mirror related parameter acquisition module, a hot mirror back lobe pointing position acquisition module, an earth radiation quantity acquisition module and a hot mirror back lobe error acquisition module;
the hot mirror related parameter module is used for providing the following parameters for the hot mirror back lobe pointing position acquisition module, the earth radiation amount acquisition module and the hot mirror back lobe error acquisition module: the position of the hot mirror, the pointing angle of the hot mirror back lobe, the backward leakage coefficient of the hot mirror back lobe and the hot mirror antenna directional diagram. The position of the hot mirror is the position of the hot mirror of the microwave imager at the selected time.
The method for acquiring the parameters by the hot mirror related parameter acquisition module comprises the following steps:
the position of the hot mirror is calculated according to the track parameters of the load of the imager, the position and the angle of the hot mirror carried on the load and the like and the geometric structure.
The hot mirror antenna directional diagram, the pointing angle of the hot mirror back lobe and the backward leakage coefficient are obtained through experimental tests, wherein:
the pointing angle of the hot mirror back lobe is obtained by testing the hot mirror antenna in a ground laboratory, and comprises a side view angle of the hot mirror antenna and a half-power angle of the hot mirror antenna back lobe, wherein the side view angle of the hot mirror antenna is that the hot mirror back lobe points (the direction in figure 2)
) And a constant included angle with a load z axis, wherein the half-power angle of the hot mirror antenna back lobe is the half cone angle of the hot mirror antenna back lobe receiving cone.
The backward leakage coefficient of the hot mirror back lobe is obtained by testing the hot mirror antenna in a ground laboratory.
It should be noted that the method for obtaining the parameters is a conventional method for obtaining the parameters in the art, and therefore, the present embodiment is not further developed here. In the present embodiment, the parameters can be considered as known parameters.
The hot mirror back flap pointing position acquisition module: and the hot mirror back lobe directional position acquisition module is used for acquiring the hot mirror back lobe directional position according to the position of the hot mirror, the directional angle of the hot mirror back lobe and the hot mirror antenna directional diagram, and transmitting the position to the earth radiation quantity acquisition module.
The earth radiation quantity acquisition module: the hot mirror back lobe error acquisition module is used for acquiring the earth radiation quantity corresponding to the hot mirror back lobe pointing position according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, the hot mirror antenna directional diagram and the hot mirror back lobe pointing position, and transmitting the earth radiation quantity to the hot mirror back lobe error acquisition module.
The hot mirror back lobe error acquisition module: and the system is used for obtaining the radiation quantity received by the hot mirror back lobe, namely the hot mirror back lobe error according to the backward leakage coefficient of the hot mirror back lobe and the earth radiation quantity corresponding to the pointing position of the hot mirror back lobe.
The pointing position of the hot mirror back lobe is the position of the pointing point or the pointing surface of the hot mirror back lobe on the earth.
The hot mirror back lobe pointing position acquisition module acquires the position of the hot mirror back lobe pointing point on the earth according to the position of the hot mirror, the pointing angle of the hot mirror back lobe and the hot mirror antenna directional diagram.
The hot mirror back lobe pointing position obtaining module fits the hot mirror back lobe pointing region into an ellipsoid on the ground according to the position of the hot mirror, the pointing angle of the hot mirror back lobe and a hot mirror antenna directional diagram, and obtains the position of the hot mirror back lobe pointing surface on the earth.
Referring to fig. 2, P is the point where the satellite is located, Q is the intersatellite point where the satellite is located, and X is the direction of travel of the satellite. The hot mirror is carried on the satellite, the hot mirror is considered to be at a point P, the hot mirror back lobe pointing point is a point E in the figure, the hot mirror back lobe pointing area can be fitted into an ellipse with the circle center O, the point A, the point B, the point C and the point D are all on the ellipse, wherein AC and BD are two axes of the ellipse respectively.
And aiming at the situation of the hot mirror back lobe pointing point, the hot mirror back lobe pointing position acquisition module acquires the position of the hot mirror back lobe pointing point on the earth (point E in figure 2) according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, the hot mirror antenna directional diagram and the geometric structure model, and transmits the position of the pointing point to the earth radiation quantity acquisition module.
Aiming at the situation of the hot mirror back lobe pointing surface, the hot mirror back lobe pointing position acquisition module projects the half-power cone of the hot mirror back lobe to the earth surface according to the position of the hot mirror, the constant side viewing angle of the hot mirror antenna, the half-power angle of the hot mirror antenna back lobe and other parameters, and the projection surface is fitted into an elliptical surface, so that the position of the hot mirror back lobe pointing surface on the earth is obtained. As shown in fig. 2, O is the center of the ellipse, and the point a, the point B, the point C and the point D are all on the ellipse, where AC and BD are two axes of the ellipse respectively, and according to the geometric model, the position of the hot mirror back lobe pointing surface on the earth is obtained, and the position of the pointing surface is transmitted to the earth radiation amount obtaining module.
The earth radiation quantity obtaining module is used for calculating earth radiation quantity corresponding to a hot mirror back lobe pointing point or a pointing surface according to a hot mirror antenna directional diagram transmitted by a hot mirror related parameter calculating module, a pointing point or a pointing surface position transmitted by the hot mirror back lobe pointing position obtaining module and back lobe total energy ratio coefficients corresponding to different angles of a hot mirror antenna back lobe calculated according to the hot mirror antenna directional diagram, calculating the earth radiation quantity corresponding to the hot mirror back lobe pointing point or the pointing surface according to remote sensing data (in the embodiment, the data are known data) of a satellite-borne microwave imager by multiplying the remote sensing radiation quantity of different pointing points by the energy ratio coefficient of the corresponding back lobe angle, and transmitting the earth radiation quantity to the hot mirror back lobe error obtaining module.
It should be noted that the calculation method involved in the process of acquiring the amount of earth radiation is a conventional method in the art, so the embodiment is not further developed here.
The hot mirror back lobe error refers to the earth radiation received by the hot mirror back lobe, the radiation is caused by a backward leakage coefficient (eta) of the hot mirror back lobe, and the radiation brightness temperature can cause the increase of the on-orbit heat source brightness temperature of the microwave imager and influence the on-orbit calibration of the microwave imager. Back flap error (T) of the hot mirrorKL) Obtained according to the following formula:
TKL＝η×TE；
wherein η is the backward leakage coefficient of the hot mirror back lobe, TEPointing the hot mirror back flapThe amount of terrestrial radiation corresponding to the location.
Referring to fig. 2 and 3, an on-orbit error correction method for a hot mirror back lobe of a satellite-borne microwave imager is applied to the system and comprises the following steps:
s1: the hot mirror related parameter module provides the following parameters for the hot mirror back lobe pointing position acquisition module, the earth radiation amount acquisition module and the hot mirror back lobe error acquisition module: the position of the hot mirror, the pointing angle of the hot mirror back lobe, the backward leakage coefficient of the hot mirror back lobe and the hot mirror antenna directional diagram.
The method for acquiring the parameters by the hot mirror related parameter acquisition module comprises the following steps:
the position of the hot mirror is calculated according to the track parameters of the load of the imager, the position and the angle of the hot mirror carried on the load and the like and the geometric structure.
The hot mirror antenna directional diagram, the pointing angle of the hot mirror back lobe and the backward leakage coefficient are obtained through experimental tests, wherein:
the pointing angle of the hot mirror back lobe is obtained by testing the hot mirror antenna in a ground laboratory, and comprises a side view angle of the hot mirror antenna and a half-power angle of the hot mirror antenna back lobe, wherein the side view angle of the hot mirror antenna is that the hot mirror back lobe points (the direction in figure 2)
) And a constant included angle with a load z axis, wherein the half-power angle of the hot mirror antenna back lobe is the half cone angle of the hot mirror antenna back lobe receiving cone.
The backward leakage coefficient of the hot mirror back lobe is obtained by testing the hot mirror antenna in a ground laboratory.
It should be noted that the method for obtaining the parameters is a conventional method for obtaining the parameters in the art, and therefore, the present embodiment is not further developed here. In the present embodiment, the parameters can be considered as known parameters.
S2: the hot mirror back lobe directional position acquisition module acquires the hot mirror back lobe directional position according to the position of the hot mirror, the directional angle of the hot mirror back lobe and a hot mirror antenna directional diagram, and transmits the position to the earth radiation quantity acquisition module.
S3: the earth radiation quantity acquisition module acquires earth radiation quantity corresponding to the hot mirror back lobe directional position according to the position of the hot mirror, the directional angle of the hot mirror back lobe, the hot mirror antenna directional diagram and the hot mirror back lobe directional position, and transmits the earth radiation quantity to the hot mirror back lobe error acquisition module.
S4: the hot mirror back lobe error acquisition module acquires the radiant quantity received by the hot mirror back lobe, namely the hot mirror back lobe error according to the backward leakage coefficient of the hot mirror back lobe and the terrestrial radiant quantity corresponding to the pointed position of the hot mirror back lobe.
The pointing position of the hot mirror back lobe is the position of the pointing point or the pointing surface of the hot mirror back lobe on the earth.
The hot mirror back lobe pointing position acquisition module acquires the position of the hot mirror back lobe pointing point on the earth according to the position of the hot mirror, the pointing angle of the hot mirror back lobe and the hot mirror antenna directional diagram.
The hot mirror back lobe pointing position obtaining module fits the hot mirror back lobe pointing region into an ellipsoid on the ground according to the position of the hot mirror, the pointing angle of the hot mirror back lobe and a hot mirror antenna directional diagram, and obtains the position of the hot mirror back lobe pointing surface on the earth.
Referring to fig. 2, P is the point where the satellite is located, Q is the intersatellite point where the satellite is located, and X is the direction of travel of the satellite. The hot mirror is carried on the satellite, the hot mirror is considered to be at a point P, the hot mirror back lobe pointing point is a point E in the figure, the hot mirror back lobe pointing area can be fitted into an ellipse with the circle center O, the point A, the point B, the point C and the point D are all on the ellipse, wherein AC and BD are two axes of the ellipse respectively.
And aiming at the situation of the hot mirror back lobe pointing point, the hot mirror back lobe pointing position acquisition module acquires the position of the hot mirror back lobe pointing point on the earth (point E in figure 2) according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, the hot mirror antenna directional diagram and the geometric structure model, and transmits the position of the pointing point to the earth radiation quantity acquisition module.
Aiming at the situation of the hot mirror back lobe pointing surface, the hot mirror back lobe pointing position acquisition module projects the half-power cone of the hot mirror back lobe to the earth surface according to the position of the hot mirror, the constant side viewing angle of the hot mirror antenna, the half-power angle of the hot mirror antenna back lobe and other parameters, and the projection surface is fitted into an elliptical surface, so that the position of the hot mirror back lobe pointing surface on the earth is obtained. As shown in fig. 2, O is the center of the ellipse, and the point a, the point B, the point C and the point D are all on the ellipse, where AC and BD are two axes of the ellipse respectively, and according to the geometric model, the position of the hot mirror back lobe pointing surface on the earth is obtained, and the position of the pointing surface is transmitted to the earth radiation amount obtaining module.
The earth radiation quantity obtaining module is used for calculating earth radiation quantity corresponding to a hot mirror back lobe pointing point or a pointing surface according to a hot mirror antenna directional diagram transmitted by a hot mirror related parameter calculating module, a pointing point or a pointing surface position transmitted by the hot mirror back lobe pointing position obtaining module and back lobe total energy ratio coefficients corresponding to different angles of a hot mirror antenna back lobe calculated according to the hot mirror antenna directional diagram, calculating the earth radiation quantity corresponding to the hot mirror back lobe pointing point or the pointing surface according to remote sensing data (in the embodiment, the data are known data) of a satellite-borne microwave imager by multiplying the remote sensing radiation quantity of different pointing points by the energy ratio coefficient of the corresponding back lobe angle, and transmitting the earth radiation quantity to the hot mirror back lobe error obtaining module.
It should be noted that the calculation method involved in the process of acquiring the amount of earth radiation is a conventional method in the art, so the embodiment is not further developed here.
The hot mirror back lobe error refers to the earth radiation received by the hot mirror back lobe, the radiation is caused by a backward leakage coefficient (eta) of the hot mirror back lobe, and the radiation brightness temperature can cause the increase of the on-orbit heat source brightness temperature of the microwave imager and influence the on-orbit calibration of the microwave imager. Back flap error (T) of the hot mirrorKL) Obtained according to the following formula:
TKL＝η×TE；
wherein η is the backward leakage coefficient of the hot mirror back lobe, TEAnd the earth radiation quantity corresponding to the pointing position of the hot mirror back lobe.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. The utility model provides a satellite-borne microwave imager hot mirror back lobe is error correction system in orbit which characterized in that includes:
the system comprises a hot mirror related parameter acquisition module, a hot mirror back lobe pointing position acquisition module, an earth radiation quantity acquisition module and a hot mirror back lobe error acquisition module;
the hot mirror related parameter module is used for providing the following parameters for the hot mirror back lobe pointing position acquisition module, the earth radiation amount acquisition module and the hot mirror back lobe error acquisition module: the position of the hot mirror, the pointing angle of a hot mirror back lobe, the backward leakage coefficient of the hot mirror back lobe and a hot mirror antenna directional diagram;
the hot mirror back flap pointing position acquisition module: the hot mirror back lobe directional position acquisition module is used for acquiring the hot mirror back lobe directional position according to the position of the hot mirror, the directional angle of the hot mirror back lobe and the hot mirror antenna directional diagram, and transmitting the position to the earth radiation quantity acquisition module;
the earth radiation quantity acquisition module: the hot mirror back lobe error acquisition module is used for acquiring the earth radiation quantity corresponding to the hot mirror back lobe pointing position according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, a hot mirror antenna directional diagram and the hot mirror back lobe pointing position, and transmitting the earth radiation quantity to the hot mirror back lobe error acquisition module;
the hot mirror back lobe error acquisition module: and the system is used for obtaining the radiation quantity received by the hot mirror back lobe, namely the hot mirror back lobe error according to the backward leakage coefficient of the hot mirror back lobe and the earth radiation quantity corresponding to the pointing position of the hot mirror back lobe.
2. The system of claim 1, wherein the hot mirror back lobe pointing position is a position on earth of the hot mirror back lobe pointing point or pointing surface.
3. The system of claim 2, wherein the hot mirror back lobe direction position obtaining module fits the hot mirror back lobe direction area to an ellipsoid on the ground according to the position of the hot mirror, the direction angle of the hot mirror back lobe, and the hot mirror antenna pattern, and obtains the position of the hot mirror back lobe direction surface on the earth.
4. The system of claim 2, wherein the hot mirror back lobe pointing position obtaining module obtains the position of the hot mirror back lobe pointing point on the earth according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, and the hot mirror antenna pattern.
5. The system of claim 1, wherein the hot mirror back lobe error is obtained according to the following equation:
TKL＝η×TE；
wherein η is the backward leakage coefficient of the hot mirror back lobe, TEAnd the earth radiation quantity corresponding to the pointing position of the hot mirror back lobe.
6. An on-orbit error correction method for a hot mirror back lobe of a satellite-borne microwave imager, which is applied to the system as claimed in any one of claims 1 to 5, and comprises the following steps:
s1: the hot mirror related parameter module provides the following parameters for the hot mirror back lobe pointing position acquisition module, the earth radiation amount acquisition module and the hot mirror back lobe error acquisition module: the position of the hot mirror, the pointing angle of a hot mirror back lobe, the backward leakage coefficient of the hot mirror back lobe and a hot mirror antenna directional diagram;
s2: the hot mirror back lobe pointing position acquisition module acquires a hot mirror back lobe pointing position according to the position of the hot mirror, the pointing angle of the hot mirror back lobe and a hot mirror antenna directional diagram, and transmits the position to the terrestrial radiation quantity acquisition module;
s3: the earth radiation quantity acquisition module acquires earth radiation quantity corresponding to the hot mirror back lobe pointing position according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, a hot mirror antenna directional diagram and the hot mirror back lobe pointing position, and transmits the earth radiation quantity to the hot mirror back lobe error acquisition module;
s4: the hot mirror back lobe error acquisition module acquires the radiant quantity received by the hot mirror back lobe, namely the hot mirror back lobe error according to the backward leakage coefficient of the hot mirror back lobe and the terrestrial radiant quantity corresponding to the pointed position of the hot mirror back lobe.
7. The method of claim 6, wherein the hot mirror back lobe pointing position is a position on the earth of the hot mirror back lobe pointing point or pointing plane.
8. The method of claim 7, wherein the hot mirror back lobe pointing position obtaining module fits the hot mirror back lobe pointing region to an ellipsoid on the ground according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, and the hot mirror antenna pattern, and obtains the position of the hot mirror back lobe pointing surface on the earth.
9. The method of claim 7, wherein the hot mirror back lobe pointing position obtaining module obtains the position of the hot mirror back lobe pointing point on the earth according to the position of the hot mirror, the pointing angle of the hot mirror back lobe, and the hot mirror antenna pattern.
10. The method of claim 6, wherein the hot mirror back lobe error is obtained according to the following equation:
TKL＝η×TE；
wherein η is the backward leakage coefficient of the hot mirror back lobe, TEAnd the earth radiation quantity corresponding to the pointing position of the hot mirror back lobe.
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