CN112346028B - 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 PDFInfo
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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 direction AP01 through the main satellite orbit and the attitude information; step 2: calculating azimuth beam pointing direction AP02; and step 3: judging whether | AP01-AP02| exceeds a threshold; and 4, step 4: calculating azimuth beam pointing direction AP11 through the auxiliary satellite orbit and the attitude information; and 5: calculating a Doppler center AP12; step 6: judging whether | AP11-AP12| exceeds a threshold; and 7: selecting a test sample pair with | AP01-AP02|, and | AP11-AP12| simultaneously in a threshold range, wherein the azimuth space synchronous 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
Technical Field
The invention relates to the technical field of aerospace systems, in particular to a distributed InSAR satellite azimuth space synchronization in-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 wave beams in the same surveying and mapping band vertical to the flight direction of the satellite according to respective attitude guide rules, the residual errors of Doppler center frequencies of the main satellite and the auxiliary satellite under the module are small and basically the same, high Doppler decoherence indexes are guaranteed, and powerful support is provided for an InSAR system to obtain a high-precision DSM product.
The patent document with publication number CN106054185 "an airborne dual-antenna InSAR baseline calculation method based on distributed POS" solves the problem of the calculation method of the airborne dual-antenna InSAR baseline, and the main solution in the present invention is a test method of the distributed InSAR satellite space synchronization in-orbit operation, which has obvious differences in application direction, application range and technical approach.
Based on the analysis of the influence of the space synchronization of the InSAR of the satellite formation on the system performance, wuhan university Schedule (information science edition), 200710. The main differences are: the patent mainly solves the problem of a testing method for in-orbit operation of distributed InSAR satellite space synchronization, and the paper mainly demonstrates the requirements of InSAR elevation measurement on space synchronization under formation conditions and analyzes the influence of space synchronization on 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 in-orbit operation of the distributed InSAR satellite space synchronization, and the thesis mainly provides an engineering realization way for completing beam synchronization through satellite formation attitude guidance, and the application direction, the application range and the technical way have obvious differences.
A practical space synchronization method of a satellite-machine bistatic SAR, 200806, electronic and information science and newspaper. 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 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 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 tropical rainforest area, and calculating azimuth beam pointing AP02;
and step 3: judging whether | AP01-AP02| exceeds a threshold, if so, carrying out next step work, if so, the section of data does not meet the test requirement, and replacing the sample;
and 4, step 4: calculating azimuth beam pointing direction AP11 through the auxiliary satellite orbit and the attitude information;
and 5: calculating a Doppler center AP12 by using echo data of the observation tropical rainforest region;
and 6: judging whether | AP11-AP12| exceeds a threshold, if so, carrying out next step work, and if not, replacing the sample, wherein the section of data does not meet the test requirement;
and 7: selecting a test sample pair with | AP01-AP02|, and | AP11-AP12| simultaneously in a threshold range, wherein the azimuth space synchronous 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
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 f d The satellite velocity is v and the SAR carrier frequency is f c The speed of light is c, then
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 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 method far Effective sample S under intermediate view angle middle Effective sample S under myopia angle near At least 2 groups can ensure the precision of the test method.
Preferably, in step 3, it is determined whether | AP1-AP0| exceeds a threshold, and if the echo data of the primary and secondary satellites to the same rainforest area are within the threshold at the same time, 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.
According to another aspect of the invention, a distributed InSAR satellite azimuth space synchronization in-orbit test system is provided, which comprises:
a module M1: calculating azimuth beam pointing direction AP01 through the main satellite orbit and the attitude information;
a module M2: calculating a Doppler center by using echo data of the tropical rainforest area, and calculating azimuth beam pointing AP02;
a module M3: judging whether | AP01-AP02| exceeds a threshold, if so, carrying out next step work, if so, the section of data does not meet the test requirement, and replacing the sample;
a module M4: calculating azimuth beam pointing direction AP11 through the auxiliary satellite orbit and the attitude information;
a module M5: calculating a Doppler center AP12 by using echo data of the observation tropical rainforest region;
a module M6: judging whether | AP11-AP12| exceeds a threshold, if so, carrying out next step work, and if not, replacing the sample, wherein the section of data does not meet the test requirement;
a module M7: selecting a test sample pair with the absolute values of AP01-AP02 and AP11-AP12 in a threshold range, wherein the azimuth space synchronous test result is absolute values of AP12-AP 02/AW multiplied by 100%, and AW is the azimuth beam width of the main satellite;
a 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 to ψ and the roll angle to
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 f d The satellite velocity is v and the SAR carrier frequency is f c The speed of light is c, then
Preferably, in the module M2, the areas with rainforest overheating need to be as consistent as possible during the distributed satellite test, and 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 method far Effective sample S under intermediate view angle middle Effective sample S under myopia angle near At least 2 groups can ensure the precision of the test method.
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 within the threshold at the same time, 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 variation 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 variations and modifications can be made by persons skilled in the art without departing from the concept of the invention. All falling within the scope of the 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 direction AP01 through the main satellite orbit and the attitude information;
(2) Calculating a Doppler center by using echo data of the tropical rainforest area, and calculating azimuth beam pointing AP02;
(3) Judging whether | AP01-AP02| exceeds a threshold, if so, carrying out next step work, if so, the section of data does not meet the test requirement, and replacing the sample;
(4) Calculating azimuth beam pointing direction AP11 through the auxiliary satellite orbit and the attitude information;
(5) Calculating a Doppler center AP12 by using echo data of the observation tropical rainforest region;
(6) Judging whether | AP11-AP12| exceeds a threshold, if so, carrying out next step work, if so, the section of data does not meet the test requirement, and replacing the sample;
(7) And selecting a test sample pair with the absolute value of AP01-AP02 and the absolute value of AP11-AP12 simultaneously in a threshold range, wherein the azimuth space synchronous test result is absolute value AP12-AP 02/AW multiplied by 100 percent, and AW is the azimuth beam width of the main satellite.
(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
Taking amazon rainforest regions near the equator in brazil as an example, the pointing measurement precision (i.e., the precision of AP01 and AP 11) is 0.01 °; the Doppler center estimation precision is 30Hz, and the calculation precision is converted to about 0.0025 degrees between AP02 and AP12; 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% =1.5%, 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 direction AP01 through the main satellite orbit and the attitude information;
step 2: calculating a Doppler center by using echo data of the tropical rainforest region, and calculating azimuth beam pointing AP02 by using data observed by a main satellite;
and 3, step 3: judging whether the absolute value of AP01-AP02 exceeds a threshold, if so, carrying out next step work, and if so, replacing the sample, wherein the echo data does not meet the test requirement;
and 4, step 4: calculating azimuth beam pointing direction AP11 through the auxiliary satellite orbit and the attitude information;
and 5: calculating a Doppler center by using echo data of the observation tropical rainforest region, and calculating azimuth beam pointing AP12 by using auxiliary observation data;
step 6: judging whether | AP11-AP12| exceeds a threshold, if so, carrying out next step work, and if not, replacing the sample, wherein the echo data does not meet the test requirement;
and 7: selecting a test sample pair with | AP01-AP02|, and | AP11-AP12| simultaneously in a threshold range, wherein the azimuth space synchronous test result is | AP12+ AP02|/AW multiplied by 100%, and AW is the azimuth beam width of the main star;
and step 8: calculating the results of each group of test samples, averaging the calculated values of each group, further reducing random errors and obtaining a final test result;
in the step 2, the areas with rainforests are consistent in overheating areas during distributed satellite testing, and the difference of multi-satellite testing areas is required to be not more than 10%.
2. According to claimThe method for testing the azimuth-direction space synchronization in-orbit of the distributed InSAR satellite in the claim 1 is characterized in that in the step 1, the AP01 is calculated by setting the yaw angle of the satellite to be psi and the roll angle to be roll angle
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 on-orbit testing method of claim 2, wherein in the step 2, the AP02 is calculated by setting Doppler center frequency to f d The satellite velocity is v and the SAR carrier frequency is f c The speed of light is c, then
4. The distributed InSAR satellite azimuth-direction space synchronization on-orbit testing method according to claim 3, wherein the more effective test sample pairs, the higher the testing accuracy, the more effective samples S under a far view angle are required far Effective sample S under intermediate view angle middle Effective sample S under myopia angle near At least 2 groups each can guarantee the test accuracy.
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 satellite to the same rainforest area are simultaneously within the threshold, and the samples are valid samples, and if any data of the primary satellite exceeds the threshold, the samples 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:
a module M1: calculating azimuth beam pointing AP01 according to the orbit and attitude information of the main satellite;
a module M2: calculating a Doppler center by using echo data of the tropical rainforest region, and calculating azimuth beam pointing AP02 by using data observed by a main satellite;
a module M3: judging whether the absolute value of AP01-AP02 exceeds a threshold, if so, carrying out next step work, and if so, replacing the sample, wherein the echo data does not meet the test requirement;
a module M4: calculating azimuth beam pointing direction AP11 through the auxiliary satellite orbit and the attitude information;
a module M5: calculating a Doppler center by using echo data of the observation tropical rainforest region, and calculating azimuth beam pointing AP12 by using auxiliary observation data;
a module M6: judging whether | AP11-AP12| exceeds a threshold, if so, carrying out next step work, if so, the echo data does not meet the test requirement, and replacing the sample;
a module M7: selecting a test sample pair with | AP01-AP02|, and | AP11-AP12| simultaneously in a threshold range, wherein the azimuth space synchronous test result is | AP12+ AP02|/AW multiplied by 100%, and AW is the azimuth beam width of the main star;
a module M8: calculating the results of each group of test samples, averaging the calculated values of each group, further reducing random errors and obtaining the final test result;
in the module M2, the areas with rainforests and overheating areas are consistent during distributed satellite testing, and the difference of multi-satellite testing areas is required to be not more than 10%.
7. The distributed InSAR satellite azimuth-direction space synchronization in-orbit testing system of claim 6, wherein in the module M1, the AP01 is calculated by setting the satellite yaw angle as ψ and the roll angle as
Pitch angle theta, satellite tilt angleDegree is alpha, then
AP01＝θcosα-ψsinα。
8. The distributed InSAR satellite azimuth-space synchronization in-orbit testing system of claim 7, wherein in the module M2, the AP02 is calculated by setting Doppler center frequency to f d The satellite velocity is v and the SAR carrier frequency is f c The speed of light is c, then
9. The distributed InSAR satellite azimuth-direction space-synchronous in-orbit testing system of claim 8, wherein the more effective test sample pairs, the higher the testing accuracy, the more effective samples S at a far view angle are required far Effective sample S under medium viewing angle middle Effective sample S under myopia angle near At least 2 groups each can guarantee the test accuracy.
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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