CN112346028A - Distributed InSAR satellite azimuth space synchronization on-orbit testing method and system - Google Patents

Distributed InSAR satellite azimuth space synchronization on-orbit testing method and system Download PDF

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CN112346028A
CN112346028A CN202011197192.1A CN202011197192A CN112346028A CN 112346028 A CN112346028 A CN 112346028A CN 202011197192 A CN202011197192 A CN 202011197192A CN 112346028 A CN112346028 A CN 112346028A
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赵迪
刘志铭
丛琳
侯雨生
陈重华
李楠
刘艳阳
陈熙之
卢丹
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Shanghai Institute of Satellite Engineering
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Abstract

The invention provides a distributed InSAR satellite azimuth space synchronization on-orbit testing method and a system, wherein the method comprises the following steps: step 1: calculating azimuth beam pointing AP01 according to the orbit and attitude information of the main satellite; step 2: calculating the azimuth beam pointing to the AP 02; and step 3: judging whether | AP01-AP02| exceeds a threshold; and 4, step 4: calculating azimuth beam pointing direction AP11 according to the auxiliary satellite orbit and attitude information; and 5: calculating a Doppler center AP 12; step 6: judging whether | AP11-AP12| exceeds a threshold; and 7: selecting a test sample pair with | AP01-AP02|, and | AP11-AP12|, wherein the | AP01-AP02|, and the | AP11-AP12| are simultaneously in a threshold range, so that the azimuth space synchronization test result is | AP12-AP02|/AW multiplied by 100%, and AW is the azimuth beam width of the main star; and 8: and calculating the results of all groups of test samples, averaging all groups of calculated values, further reducing random errors and obtaining the final test result. The method can effectively obtain the in-orbit azimuth space synchronization test result of the distributed InSAR satellite.

Description

Distributed InSAR satellite azimuth space synchronization on-orbit testing method and system
Technical Field
The invention relates to the technical field of aerospace systems, in particular to a distributed InSAR satellite azimuth space synchronization on-orbit testing method and system.
Background
Interferometric synthetic aperture radar (InSAR) is an important remote sensing means for obtaining high-precision ground elevation models (DSMs). The method comprises the steps of observing the same area at different viewing angles by using two SAR antennas distributed along a vertical course, carrying out interference processing on two acquired complex SAR images, solving the slope distance difference between the phase center of a main radar antenna and a secondary radar antenna and a target, and further obtaining a DSM (digital surface model) of an observation area. The distributed satellite InSAR system installs two SAR on two flying satellites in formation and simultaneously observes the earth, can overcome the problems of time decoherence and low baseline precision and the like of repeated navigation of the InSAR, and can obtain high-precision DSM. Because the SAR transmitting antenna and the receiving antenna are respectively arranged on different satellite platforms, in order to realize single-satellite SAR imaging and InSAR interferometric measurement, the receiving and transmitting antenna beams must simultaneously cover the same ground irradiation area, and the space synchronization of the double-satellite SAR beams is realized, so that the auxiliary satellite can receive enough echo energy and keep better coherence with the main satellite.
The invention provides an on-orbit testing method of an azimuth space synchronization index aiming at a maximum phase-to-dry method. The distributed InSAR satellite adopting the maximum coherent method has the advantages that the main satellite SAR and the auxiliary satellite SAR work in a front side view module, the SAR azimuth beam width is the same, and the beam directions are all in respective all-zero Doppler planes, as shown in figure 2. The azimuth space synchronization under the maximum coherent method requires that the main satellite and the auxiliary satellite respectively irradiate the wave beams in the same mapping band vertical to the flight direction of the satellite according to respective attitude guidance rules, the residual errors of the Doppler center frequencies of the echo of the main satellite and the auxiliary satellite under the module are small and basically the same, the high Doppler decoherence index is guaranteed, and powerful support is provided for the InSAR system to obtain a high-precision DSM product.
The patent document CN106054185 "a distributed POS-based airborne double-antenna InSAR baseline calculation method" solves the problem of the calculation method of the airborne double-antenna InSAR baseline, and the invention mainly solves the problem of the testing method of the distributed InSAR satellite space synchronization on-orbit operation, and the application direction, the application range and the technical path of the two methods are obviously different.
Based on the analysis of the influence of the space synchronization of the InSAR of the satellite formation on the system performance, Wuhan university newspaper (information science edition), 200710. The main differences are: the patent mainly solves the problem of a testing method for the in-orbit operation of the distributed InSAR satellite space synchronization, and the paper mainly demonstrates the requirement of InSAR elevation measurement on the space synchronization under the formation condition and analyzes the influence of the space synchronization on the elevation measurement precision and resolution of an InSAR system, and has obvious differences in application direction, application range and technical approach.
An interference SAR satellite formation beam synchronization method, Chinese space science and technology, 201005. The main differences are: the patent mainly solves the problem of a testing method for the space synchronization on-orbit operation of a distributed InSAR satellite, and the paper mainly provides an engineering implementation way for completing beam synchronization through satellite formation attitude guidance, and the application direction, the application range and the technical way are obviously different.
A practical space synchronization method of a satellite-machine bistatic SAR, which is used for electronic and information learning and reporting, 200806. The main differences are: the patent mainly solves the problem of a testing method for the space synchronization on-orbit operation of a distributed InSAR satellite, and the paper mainly provides a space synchronization realization way for the beam pointing of a satellite and an airplane receiving and transmitting platform, and the application direction, the application range and the technical way are all obviously different.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a distributed InSAR satellite azimuth space synchronization on-orbit testing method and system.
According to one aspect of the invention, a distributed InSAR satellite azimuth space synchronization on-orbit testing method is provided, which comprises the following steps:
step 1: calculating azimuth beam pointing AP01 according to the orbit and attitude information of the main satellite;
step 2: calculating a Doppler center by using echo data of the observation tropical rainforest region, and calculating azimuth beam pointing AP 02;
and step 3: judging whether the absolute value of AP01-AP02 exceeds a threshold, if so, carrying out next step operation, if so, changing the sample, if not, the section of data does not meet the test requirement;
and 4, step 4: calculating azimuth beam pointing direction AP11 according to the auxiliary satellite orbit and attitude information;
and 5: calculating a Doppler center AP12 by using echo data of the observation tropical rainforest region;
step 6: judging whether the absolute value of AP11-AP12 exceeds a threshold, if so, carrying out next step operation, if so, changing the sample, if not, the section of data does not meet the test requirement;
and 7: selecting a test sample pair with | AP01-AP02|, and | AP11-AP12|, wherein the | AP01-AP02|, and the | AP11-AP12| are simultaneously in a threshold range, so that the azimuth space synchronization test result is | AP12-AP02|/AW multiplied by 100%, and AW is the azimuth beam width of the main star;
and 8: and calculating the results of all groups of test samples, averaging all groups of calculated values, further reducing random errors and obtaining the final test result.
Preferably, in step 1, the AP01 is calculated by setting the satellite yaw angle as ψ and the roll angle as
Figure BDA0002754368630000032
The pitch angle is theta, and the satellite oblique flying angle is alpha, then
AP01＝θcosα-ψsinα。
Preferably, in step 2, the AP02 is calculated by setting the doppler center frequency to fdThe satellite velocity is v and the SAR carrier frequency is fcThe speed of light is c, then
Figure BDA0002754368630000031
Preferably, in the step 2, the areas with rainforest overheating need to be consistent as much as possible during the distributed satellite test, the difference between the areas of the multi-satellite test is required to be not more than 10%, otherwise, the test precision is seriously reduced; the more effective test sample pairs, the higher the test precision, and the effective sample S under the far visual angle is required by the methodfarEffective sample S under intermediate view anglemiddleEffective sample S under myopia anglenearThe precision of the test method can be ensured only by at least 2 groups.
Preferably, in the step 3, it is determined whether | AP1-AP0| exceeds a threshold, and if echo data of the primary and secondary satellites in the same rainforest area are both within the threshold, the echo data are valid samples, and if any data of the primary and secondary satellites exceed the threshold, the echo data are invalid samples;
the threshold value is set relative to the SAR working frequency band, the satellite attitude guidance rule and the product production level factor, and can be selected by a user according to the actual situation.
According to another aspect of the invention, a distributed InSAR satellite azimuth space synchronization in-orbit test system is provided, which comprises:
module M1: calculating azimuth beam pointing AP01 according to the orbit and attitude information of the main satellite;
module M2: calculating a Doppler center by using echo data of the observation tropical rainforest region, and calculating azimuth beam pointing AP 02;
module M3: judging whether the absolute value of AP01-AP02 exceeds a threshold, if so, carrying out next step operation, if so, changing the sample, if not, the section of data does not meet the test requirement;
module M4: calculating azimuth beam pointing direction AP11 according to the auxiliary satellite orbit and attitude information;
module M5: calculating a Doppler center AP12 by using echo data of the observation tropical rainforest region;
module M6: judging whether the absolute value of AP11-AP12 exceeds a threshold, if so, carrying out next step operation, if so, changing the sample, if not, the section of data does not meet the test requirement;
module M7: selecting a test sample pair with | AP01-AP02|, and | AP11-AP12|, wherein the | AP01-AP02|, and the | AP11-AP12| are simultaneously in a threshold range, so that the azimuth space synchronization test result is | AP12-AP02|/AW multiplied by 100%, and AW is the azimuth beam width of the main star;
module M8: and calculating the results of all groups of test samples, averaging all groups of calculated values, further reducing random errors and obtaining the final test result.
Preferably, in the module M1, the AP01 is calculated by setting the satellite yaw angle ψ and the roll angle ψ
Figure BDA0002754368630000042
The pitch angle is theta, and the satellite oblique flying angle is alpha, then
AP01＝θcosα-ψsinα。
Preferably, in the module M2, the AP02 is calculated by setting the doppler center frequency to fdThe satellite velocity is v and the SAR carrier frequency is fcThe speed of light is c, then
Figure BDA0002754368630000041
Preferably, in the module M2, areas with rainforest overheating zones need to be as consistent as possible during distributed satellite testing, and it is required that the difference between multi-satellite testing areas is not more than 10%, otherwise, the testing accuracy is seriously reduced; the more effective test sample pairs, the higher the test precision, and the effective sample S under the far visual angle is required by the methodfarEffective sample S under intermediate view anglemiddleEffective sample S under myopia anglenearThe precision of the test method can be ensured only by at least 2 groups.
Preferably, in the module M3, it is determined whether | AP1-AP0| exceeds a threshold, and if echo data of the primary and secondary satellites in the same rainforest area are both within the threshold, the sample is an effective sample, and if any data of the primary and secondary satellites exceeds the threshold, the sample is an invalid sample;
the threshold value is set relative to the SAR working frequency band, the satellite attitude guidance rule and the product production level factor, and can be selected by a user according to the actual situation.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention can be used for the in-orbit test work of the distributed InSAR satellite, and provides an in-orbit test means of the azimuth space synchronization index under the maximum coherence method;
2. the method can effectively obtain the in-orbit azimuth space synchronization test result of the maximum phase dry method distributed InSAR satellite;
3. the method has the function of checking the validity of the on-orbit test data, can screen invalid data caused by topographic and geomorphic changes by setting a threshold, and improves the validity and reliability of a test algorithm.
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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 flow chart of processing steps of a distributed InSAR satellite azimuth space synchronization on-orbit testing method;
FIG. 2 is a schematic view of the azimuthal spatial synchronization.
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.
The invention provides a distributed InSAR satellite azimuth space synchronization on-orbit testing method, as shown in FIG. 1, in the embodiment, the specific implementation steps are as follows:
(1) calculating azimuth beam pointing AP01 according to the orbit and attitude information of the main satellite;
(2) calculating a Doppler center by using echo data of the observation tropical rainforest region, and calculating azimuth beam pointing AP 02;
(3) judging whether the absolute value of AP01-AP02 exceeds a threshold, if so, carrying out next step operation, if so, changing the sample, if not, the section of data does not meet the test requirement;
(4) calculating azimuth beam pointing direction AP11 according to the auxiliary satellite orbit and attitude information;
(5) calculating a Doppler center AP12 by using echo data of the observation tropical rainforest region;
(6) judging whether the absolute value of AP11-AP12 exceeds a threshold, if so, carrying out next step operation, if so, changing the sample, if not, the section of data does not meet the test requirement;
(7) selecting a test sample pair with | AP01-AP02|, and | AP11-AP12|, wherein the | AP01-AP02|, and the | AP11-AP12| are simultaneously in a threshold range, so that the azimuth space synchronization test result is | AP12-AP02|/AW multiplied by 100%, and AW is the azimuth beam width of the main star.
(8) And calculating the results of all groups of test samples, averaging all groups of calculated values, further reducing random errors and obtaining the final test result.
It should be specially noted that the setting of the threshold value is related to many factors such as the SAR working frequency band, the satellite attitude guidance law, the product production level, etc., and can be selected by the user according to the actual situation.
Taking the german TanDEM-X system as an example, the main information is shown in table 1:
TABLE 1 TanDEM-X satellite System information
Figure BDA0002754368630000051
Figure BDA0002754368630000061
Taking amazon tropical rainforest regions near the equator in brazil as an example, the pointing measurement accuracy (i.e., AP01, AP11 accuracy) is 0.01 °; the Doppler center estimation precision is 30Hz, and the calculation precision is converted to about 0.0025 degrees from AP02 and AP 12; therefore, the threshold value can be set to be 0.015 degrees, the invention is applied to a German TanDEM-X system, the test precision of a single group of test samples can reach (0.0025 degrees +0.0025 degrees) to 0.33 degrees multiplied by 100 percent to 1.5 percent, the random error can be further reduced by averaging the test results of a plurality of groups of effective samples, and the test precision is expected to be further improved.
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. A distributed InSAR satellite azimuth space synchronization on-orbit testing method is characterized by comprising the following steps:
step 1: calculating azimuth beam pointing AP01 according to the orbit and attitude information of the main satellite;
step 2: calculating a Doppler center by using echo data of the observation tropical rainforest region, and calculating azimuth beam pointing AP 02;
and step 3: judging whether the absolute value of AP01-AP02 exceeds a threshold, if so, carrying out next step operation, if so, changing the sample, if not, the section of data does not meet the test requirement;
and 4, step 4: calculating azimuth beam pointing direction AP11 according to the auxiliary satellite orbit and attitude information;
and 5: calculating a Doppler center AP12 by using echo data of the observation tropical rainforest region;
step 6: judging whether the absolute value of AP11-AP12 exceeds a threshold, if so, carrying out next step operation, if so, changing the sample, if not, the section of data does not meet the test requirement;
and 7: selecting a test sample pair with | AP01-AP02|, and | AP11-AP12|, wherein the | AP01-AP02|, and the | AP11-AP12| are simultaneously in a threshold range, so that the azimuth space synchronization test result is | AP12-AP02|/AW multiplied by 100%, and AW is the azimuth beam width of the main star;
and 8: and calculating the results of all groups of test samples, averaging all groups of calculated values, further reducing random errors and obtaining the final test result.
2. The distributed InSAR satellite azimuth-space synchronization on-orbit testing method of claim 1, wherein in the step 1, the AP01 is calculated by setting the satellite yaw angle to ψ and the roll angle to
Figure FDA0002754368620000011
The pitch angle is theta, and the satellite oblique flying angle is alpha, then
AP01＝θcosα-ψsinα。
3. The distributed InSAR satellite azimuth-space synchronization in-orbit testing method of claim 2, wherein in the step 2, the AP02 is calculated by setting the Doppler center frequency to fdThe satellite velocity is v and the SAR carrier frequency is fcThe speed of light is c, then
Figure FDA0002754368620000012
4. The distributed InSAR satellite azimuth space synchronization on-orbit testing method according to claim 3, characterized in that in the step 2, the areas with rainforest overheating need to be as consistent as possible during the distributed satellite testing, the difference between the multi-satellite testing areas is required to be not more than 10%, otherwise the testing precision is seriously reduced; the more effective test sample pairs, the higher the test precision, and the effective sample S under the far visual angle is required by the methodfarEffective sample S under intermediate view anglemiddleEffective sample S under myopia anglenearThe precision of the test method can be ensured only by at least 2 groups.
5. The distributed InSAR satellite azimuth-direction space synchronization on-orbit testing method according to claim 4, characterized in that in the step 3, it is judged whether | AP1-AP0| exceeds a threshold, the echo data of the primary and secondary satellites to the same rainforest area are both within the threshold, and are valid samples, and if any data of the primary and secondary satellites exceeds the threshold, they are invalid samples; the threshold value is set relative to the SAR working frequency band, the satellite attitude guidance rule and the product production level factor, and can be selected by a user according to the actual situation.
6. A distributed InSAR satellite azimuth space synchronization in-orbit test system is characterized by comprising:
module M1: calculating azimuth beam pointing AP01 according to the orbit and attitude information of the main satellite;
module M2: calculating a Doppler center by using echo data of the observation tropical rainforest region, and calculating azimuth beam pointing AP 02;
module M3: judging whether the absolute value of AP01-AP02 exceeds a threshold, if so, carrying out next step operation, if so, changing the sample, if not, the section of data does not meet the test requirement;
module M4: calculating azimuth beam pointing direction AP11 according to the auxiliary satellite orbit and attitude information;
module M5: calculating a Doppler center AP12 by using echo data of the observation tropical rainforest region;
module M6: judging whether the absolute value of AP11-AP12 exceeds a threshold, if so, carrying out next step operation, if so, changing the sample, if not, the section of data does not meet the test requirement;
module M7: selecting a test sample pair with | AP01-AP02|, and | AP11-AP12|, wherein the | AP01-AP02|, and the | AP11-AP12| are simultaneously in a threshold range, so that the azimuth space synchronization test result is | AP12-AP02|/AW multiplied by 100%, and AW is the azimuth beam width of the main star;
module M8: and calculating the results of all groups of test samples, averaging all groups of calculated values, further reducing random errors and obtaining the final test result.
7. The distributed InSAR satellite azimuth-space synchronization in-orbit testing system of claim 6, wherein in the module M1, the AP01 is calculated by setting the satellite yaw angle to ψ and the roll angle to
Figure FDA0002754368620000022
The pitch angle is theta, and the satellite oblique flying angle is alpha, then
AP01＝θcosα-ψsinα。
8. The distributed InSAR satellite orientation-space synchronization in-orbit testing system of claim 7, wherein in the module M2, the AP02 is calculated by setting the Doppler center frequency to fdThe satellite velocity is v and the SAR carrier frequency is fcThe speed of light is c, then
Figure FDA0002754368620000021
9. The distributed InSAR satellite azimuth space synchronization in-orbit testing system of claim 8, wherein in the module M2, areas with rainforest overheating need to be consistent as much as possible during distributed satellite testing, the difference between multi-satellite testing areas is required to be not more than 10%, otherwise, the testing precision is seriously reduced; the more effective test sample pairs, the higher the test precision, and the effective sample S under the far visual angle is required by the methodfarEffective sample S under intermediate view anglemiddleEffective sample S under myopia anglenearThe precision of the test method can be ensured only by at least 2 groups.
10. The distributed InSAR satellite azimuth-direction spatial synchronization on-orbit testing system of claim 9, wherein in the module M3, it is determined whether | AP1-AP0| exceeds a threshold, and the echo data of the primary and secondary satellites to the same rainforest area are both within the threshold, which is a valid sample, and if any data of the primary and secondary satellites exceeds the threshold, which is an invalid sample; the threshold value is set relative to the SAR working frequency band, the satellite attitude guidance rule and the product production level factor, and can be selected by a user according to the actual situation.
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