Geosynchronous orbit dual-frequency radar intelligent detection and imaging integrated system design method

Abstract

The invention discloses a geosynchronous orbit double-frequency radar intelligent detection and imaging integrated system design method, which comprises the following steps of: constructing a geosynchronous orbit L-band system wave position selection schematic diagram, and designing a wave position and related parameters; target grouping is realized on the basis of information such as multi-batch target speeds and position time sequences obtained through L-band target detection and tracking; constructing a geosynchronous orbit C wave band system wave position selection schematic diagram, wherein the designed multiple wave positions can fully cover L wave band footprints; c-band wave position intelligent selection is carried out based on grouping information, and high-frequency-band long-time observation of the target is realized; and sparse SAR imaging is carried out on incomplete aperture echo data obtained in tracking observation. According to the invention, on the basis of the designed L / C dual-band wave position, target tracking information of the L band is utilized to group multiple moving targets, indication information is provided for intelligent selection of the wave position of the C band, long-time observation of the moving targets and sparse zoom imaging of supporting the moving targets are realized, and satellite resources are effectively saved.

Description

Technical Field

[0001] This invention belongs to the field of radar system design, specifically relating to a method for designing an integrated intelligent detection and imaging system for a geosynchronous orbit dual-frequency radar. Background Technology

[0002] Traditional radar detects the presence, distance, speed, and direction of a target by transmitting radio waves and receiving the reflected echoes. Long-term target tracking is possible through multiple signal transmissions and receptions. Synthetic Aperture Radar (SAR), on the other hand, is an active, high-resolution imaging radar that can be mounted on aircraft, satellites, spacecraft, and other flight platforms. It provides all-weather, 24 / 7 Earth observation, acquiring target image information and has broad application prospects in disaster prediction, environmental monitoring, and Earth surface mapping.

[0003] Compared to traditional low-Earth orbit SAR, geostationary orbit SAR has advantages such as long operating range (over 36,000 kilometers), wide coverage, and strong staring capability. However, long-distance, high-frequency Earth observation requires high transmission power, which current satellites cannot sustain for extended periods. Compared to SAR systems, traditional detection methods have lower power consumption and can effectively acquire the azimuth and motion information of moving targets, but they cannot acquire target image information for further analysis. Combining traditional radar detection systems with geostationary orbit SAR imaging systems, based on radar detection and tracking information, can provide observation time and location information for high-frequency SAR imaging, effectively saving onboard resources and improving the value of the acquired information. Summary of the Invention

[0004] Purpose of the invention: This invention provides a design method for an integrated intelligent detection and imaging system of geosynchronous orbit dual-frequency radar. It organically combines geosynchronous orbit radar detection and SAR imaging system. Based on the designed L / C dual-band spectral positions, it uses target tracking information of L-band to group multiple moving targets, providing indication information for intelligent selection of C-band spectral positions, realizing long-term observation of moving targets, supporting sparse zoom imaging of moving targets, and effectively saving on-board resources.

[0005] Technical Method: The integrated intelligent detection and imaging system design method for dual-frequency radar in geosynchronous orbit described in this invention includes the following steps:

[0006] (1) Construct a schematic diagram of the L-band system wavelet selection for geosynchronous orbit SAR, design wavelet positions and related parameters, and provide system parameters for L-band target detection and base map imaging;

[0007] (2) Based on the target position and motion information obtained from L-band target detection and tracking, target groups are formed;

[0008] (3) Construct a schematic diagram of C-band system wavelet selection for geosynchronous orbit SAR, and design a C-band multi-wavelet system to fully cover L-band footprints;

[0009] (4) Based on the target grouping information, determine the C-band positions that different grouped targets can experience within the L-band observation range, intelligently select the designed C-band positions, and obtain the parameters of the SAR imaging system;

[0010] (5) Based on the system parameters obtained in step (4) and the target motion information provided in step (2), sparse zoom imaging of C-band moving targets in each target group is realized to obtain high-precision SAR images of the targets.

[0011] Furthermore, the implementation process of step (1) is as follows:

[0012] To avoid transmitted pulse interference, the pulse repetition frequency (PRF) must meet the following conditions:

[0013]

[0014]

[0015] in, and These represent the maximum and minimum slant ranges from the SAR satellite to the far and near ends of the mapping strip during the synthetic aperture time. This represents the number of pulse cycles that the target echo takes to reach the radar within the observation area. At the speed of light, This means taking the integer part. The pulse width. For time intervals;

[0016] To avoid the strongest nadir echo affecting the received signal, the PRF should simultaneously meet the following requirements:

[0017]

[0018] in, For satellite altitude, The duration of the nadir echo; to avoid interference from the transmitted pulse and the nadir echo, plot the relationship between the lower angle of view and the pulse repetition frequency as a waveform diagram;

[0019] To avoid the effects of distance and orientation ambiguity, the PRF also needs to satisfy:

[0020]

[0021] in, For satellite platform speed, This refers to the azimuth antenna length. This is for design margin;

[0022] Zebra maps were designed using the maximum and minimum slant ranges from SAR satellites to the far and near ends of the mapping strip during synthetic aperture time.

[0023]

[0024]

[0025]

[0026] in, , , Let be the radius of the Earth in all directions. For satellite coordinates, The nearest and farthest endpoints (the farthest endpoint is indicated when the + sign is used). From a bottom perspective, For beamwidth, The distance from the satellite to the Earth's center. for Distance to the Earth's core For satellite to distance, The plane normal vector of the zero Doppler surface; after obtaining the positions of the near and far endpoints of the observation area, the minimum slant range is obtained by calculating the distance to the satellite. and maximum slope distance .

[0027] Furthermore, the implementation process of step (2) is as follows:

[0028] Based on the L-band target detection and tracking, the position and motion information of multiple targets are continuously acquired, including the slant range and viewing angle of the target to the satellite, the speed and direction of the observed target, and the grouped targets are acquired.

[0029] Furthermore, the targets in the same group possess the following characteristics:

[0030] ① The distance between current targets does not exceed the preset value;

[0031] ②Based on the current target position and target speed, after the set expected movement time, feature ① can still be satisfied;

[0032] ③ The set detection time still satisfies features ① and ②: The setting of the expected movement time is used to predict whether it will enter the coverage area of ​​the same C-band beam, and the setting of the detection time is used to update the target and grouping status.

[0033] Furthermore, the implementation process of step (3) is as follows:

[0034] The latitude and longitude coverage area is selected based on the three-dimensional coverage area of ​​the L-band wavefront. The selection method for this area is as follows:

[0035] ,

[0036] ,

[0037] ,

[0038] in, The coordinates of the boundary points of the beam coverage area. These are the latitude and longitude coordinates of the boundary points. These represent the minimum and maximum latitude and longitude of the boundary point, respectively. These are the latitude and longitude coverage values; to ensure full coverage of the L-band footprint by the C-band wavefront, a redundancy design method is adopted, and the latitude and longitude coverage area is set as a rectangle. Therefore, the latitude and longitude dimensions of the boundary of this area are:

[0039]

[0040] in, These are the start and end values ​​of the set latitude and longitude range, respectively. The set magnification factor; thus, the set rectangular latitude and longitude range encompasses the latitude and longitude range of the L-band wavefront.

[0041] Subsequently, based on the mapping band width of the C-band position, the point spacing of the center illumination point of the C-band position is calculated;

[0042] To reduce the number of wavelets and avoid generating points directly from the rectangular latitude and longitude range boundary, a buffer boundary slightly smaller than the rectangular latitude and longitude range is set, using a scaling factor. The latitude and longitude coordinates of the beam center illumination point can be selected as early as the lowest point of the buffer boundary;

[0043] The latitude and longitude coordinates of the required C-band wavefront center illumination point are uniformly arranged within the latitude and longitude buffer boundary, thereby obtaining its three-dimensional coordinates. Perspective from near and far ends ;

[0044] Calculate the near-side downward angle of each C-band position. Whether a C-band position is a C-band position to be retained can be determined by whether the angle difference between the center downward angle of the C-band position and the L-band position is less than the half beamwidth of the L-band. If it is less, it is retained.

[0045] Furthermore, the point spacing of the C-band wavefront center illumination point is calculated as follows:

[0046]

[0047] in, This represents the maximum point spacing between the centers of illumination of adjacent C-band wavelengths. The spacing is extended by a factor that you set yourself. The time will be just right to achieve full coverage. This refers to the set width of the C-band mapping band.

[0048] Furthermore, the half-beamwidth of the L-band is:

[0049]

[0050] in, Antenna length For carrier frequency.

[0051] Furthermore, the implementation process of step (4) is as follows:

[0052] The center point of each group of targets is calculated using the geometric median, which is the point whose sum of distances to all targets is the shortest. The iterative calculation method is as follows:

[0053]

[0054] in, For the updated center point latitude and longitude, For the first in the group The latitude and longitude of each target This represents the distance between the current center point and all other points.

[0055] Based on the calculated center positions of each group, the distance to the center illumination point of each C-band wave position is calculated, and the minimum value is selected as the appropriate C-band wave position for that group of targets.

[0056] Beneficial Effects: Compared with the prior art, the beneficial effects of this invention are as follows: 1. The geosynchronous orbit dual-frequency radar intelligent detection and imaging integrated system proposed in this invention organically combines radar detection and SAR imaging, providing a runtime opportunity for high-frequency SAR observation based on low-frequency target detection and tracking results, thus reducing the energy consumption pressure of long-term high-frequency imaging by SAR satellites; 2. The geosynchronous orbit dual-frequency radar intelligent detection and imaging integrated system inherits the advantages of wide beam coverage of L-band and high-precision imaging of C-band, and on this basis, improves the effectiveness of high-frequency SAR observation by utilizing L-band detection. Attached Figure Description

[0057] Figure 1 This is a flowchart of the present invention;

[0058] Figure 2 A schematic diagram of L-band oscillation selection for geostationary orbit SAR;

[0059] Figure 3 A schematic diagram of C-band oscillation selection for geostationary orbit SAR;

[0060] Figure 4 To generate the result image of the C-band wavefront center illumination point;

[0061] Figure 5 A schematic diagram of intelligent band position selection after target grouping; where (a) is a schematic diagram of intelligent band position selection for C-band; and (b) is a C-band beam coverage diagram. Detailed Implementation

[0062] The present invention will now be described in further detail with reference to the accompanying drawings.

[0063] like Figure 1 As shown, this invention provides a design method for an integrated intelligent detection and imaging system for a dual-frequency radar in geosynchronous orbit, specifically including the following steps:

[0064] Step 1: Construct a schematic diagram of the geosynchronous orbit L-band system wavelet selection, design wavelets and related parameters, and provide system parameters for L-band target detection and base map imaging.

[0065] First, to avoid transmit pulse interference, the pulse repetition frequency (PRF) must meet the following conditions:

[0066]

[0067]

[0068] in, and These represent the maximum and minimum slant distances from the SAR satellite to the far and near ends of the mapping strip, respectively, throughout the entire observation period. This represents the number of pulse cycles that the target echo takes to reach the radar within the observation area. At the speed of light, This means taking the integer part. The duration of the pulse. This refers to the pulse protection time.

[0069] Secondly, to avoid the strongest nadir echo affecting the received signal, the PRF should simultaneously satisfy the following:

[0070]

[0071] in, For satellite altitude, The duration of the nadir echo is given; to avoid interference from the transmitted pulse and the nadir echo, the relationship between the lower angle of view and the pulse repetition frequency is plotted as a waveform diagram.

[0072] Finally, to avoid the effects of distance and orientation ambiguity, PRF also needs to satisfy:

[0073]

[0074] in, For satellite platform speed, This refers to the azimuth antenna length. This is for design margin.

[0075] Zebra maps were designed using the maximum and minimum slant ranges from SAR satellites to the far and near ends of the mapping strip during synthetic aperture time.

[0076]

[0077]

[0078]

[0079] in, , , Let be the radius of the Earth in all directions. For satellite coordinates, The nearest and farthest endpoints (the farthest endpoint is indicated when the + sign is used). From a bottom perspective, L-band beamwidth The distance from the satellite to the Earth's center. for Distance to the Earth's core For satellite to distance, The plane normal vector of the zero Doppler surface.

[0080] After obtaining the near and far endpoints of the observation area, the minimum slant range is obtained by calculating the distance to the satellite. and maximum slope distance Using the maximum and minimum slant range zebra diagram design method can more accurately determine the interference range of the transmitted pulse and the nadir echo, and obtain a more accurate schematic diagram of system wave position selection.

[0081] Step 2: L-band target detection and tracking will continuously provide the position and motion information of the observed targets, including the slant range and viewing angle from the target to the satellite, the magnitude and direction of the observed target's velocity, etc. Based on this information, targets are grouped to provide indications for C-band intelligent position selection. Targets in the same group should have the following characteristics:

[0082] ① The current distance between targets does not exceed the set C-band wavefront coverage range (or set value).

[0083] ②Based on the current target position and target speed, feature ① can still be satisfied after the set expected movement time.

[0084] ③The detection time set still satisfies features ① and ②.

[0085] The expected motion time setting is used to predict whether targets will enter the same C-band beam coverage area, while the detection time setting is used to update the target and grouping status. Based on these three features, effective grouping of multiple targets can be achieved, allowing for the subsequent allocation of appropriate C-band beam positions to each group.

[0086] Step 3: Construct a schematic diagram of the wavefront selection for the geosynchronous orbit SAR C-band system. The designed multi-wavefront configuration can fully cover the L-band footprint, providing parameter support for high-resolution C-band imaging.

[0087] First, select the latitude and longitude coverage area based on the three-dimensional coverage area of ​​the L-band wavefront designed in step 1. The selection method for this area is as follows:

[0088]

[0089]

[0090]

[0091] in, The coordinates of the boundary points of the beam coverage area. These are the latitude and longitude coordinates of the boundary points. These represent the minimum and maximum latitude and longitude of the boundary point, respectively. These are the latitude and longitude coverage values. To ensure full coverage of the L-band footprint by the C-band wavefront, a redundant design scheme is adopted, and the latitude and longitude coverage area is set as a rectangle. Therefore, the latitude and longitude dimensions of the boundary of this area are:

[0092]

[0093] in, These are the start and end values ​​of the set latitude and longitude range, respectively. This is the set magnification factor. Therefore, the set rectangular latitude and longitude range encompasses the latitude and longitude range of the L-band wavefront.

[0094] Subsequently, based on the mapping band width of the C-band position, the point interval of the center illumination point of the C-band position is calculated as follows:

[0095]

[0096] in, This represents the maximum point spacing between the centers of illumination of adjacent C-band wavelengths. The spacing is extended by a factor that you set yourself. The time will be just right to achieve full coverage. This refers to the set width of the C-band mapping band.

[0097] Secondly, to minimize the number of wavelets and avoid generating points directly from the rectangular latitude and longitude range boundary, a buffer boundary slightly smaller than the rectangular latitude and longitude range needs to be set. The setting method is similar to the process of setting the start and end values ​​of the latitude and longitude range, using a scaling factor. The latitude and longitude coordinates of the beam center illumination point can be selected as early as the lowest point of the buffer boundary.

[0098] Based on the above settings, the latitude and longitude coordinates of the required C-band wavefront center illumination point can be uniformly arranged within the latitude and longitude buffer boundary, thereby obtaining its three-dimensional coordinates. Perspective from near and far ends The calculation method is similar to the calculation method for the maximum and minimum slope distances at the far and near ends of the surveying zone in step 1.

[0099] Finally, the near-side downward angle of view for each C-band position was calculated. Whether a C-band position is a required C-band position can be determined by checking if the angular difference between its center downward angle and the L-band position is less than the L-band half-beamwidth. If it is less, it is retained. The L-band half-beamwidth is calculated as follows:

[0100]

[0101] in, Antenna length For carrier frequency.

[0102] Step 4: Based on the target grouping information from Step 2, determine the possible C-position locations of different target groups within the L-band observation range, intelligently select the designed C-band multi-positions, and achieve long synthetic aperture time continuous observation of the same target group based on position switching. The specific method is as follows:

[0103] First, calculate the center point position of each group of targets using the geometric median, which is the point where the sum of distances to all targets is shortest. The iterative calculation method is as follows:

[0104]

[0105] in, For the updated center point latitude and longitude, For the first in the group The latitude and longitude of each target This represents the distance between the current center point and all other points.

[0106] Based on the calculated center positions of each group, the distance to the center illumination point of each C-band wave position is calculated, and the minimum value is selected to intelligently match a suitable C-band wave position for that group of targets.

[0107] Step 5: Based on the C-band wave position parameters matched in Step 4 and the information such as the velocity and position of the moving target obtained in Step 2, sparse SAR imaging can be performed on the incomplete aperture echo data obtained in the tracking observation. As the acquisition and observation time increases, the resolution of the observed moving target will also improve, thereby obtaining the zoom imaging results of the observed moving target.

[0108] The following section uses a set of typical geostationary orbit satellite parameters as an example to introduce the integrated intelligent detection and imaging system of dual-frequency radar in geostationary orbit, thus facilitating understanding. According to... Figure 2 , Figure 3 The schematic diagram of the system wavelet selection shown in the figure calculates the relevant parameters. Taking the L-band single wavelet as an example, the calculated parameters of the geosynchronous orbit L / C dual-band system are shown in Table 1.

[0109] Table 1 Comparison of parameters of dual-frequency band systems in geosynchronous orbit

[0110]

[0111] As shown in Table 1, the downward viewing angle coverage of the C-band position is greater than or equal to that of the L-band observation area. The L-band position can be covered by multiple C-band positions. Its azimuth resolution is significantly improved due to the advantages of the high-frequency band, and both the azimuth ambiguity and range ambiguity are below -25dB, which meets the design requirements of the classic SAR system.

[0112] Figure 4 To generate the resulting map of the C-band beam center illumination point, the red line represents the defined rectangular latitude and longitude range boundary, the pinkish-purple dashed line represents the buffer boundary line, the blue dots represent the beam center illumination point positions, and the green line represents the expected coverage range of each beam. The conditions set here are to achieve full coverage, and the width of the C-band mapping strip is set to 100km. Therefore, the coverage radius of each point is 50km, and the maximum interval between adjacent points is 70.7km, achieving full coverage of the L-band latitude and longitude range.

[0113] Figure 5 This diagram illustrates the intelligent band position selection after target grouping. The large yellow solid circle represents the L-band band position coverage area, and the green solid circle represents the C-band band position coverage area. It is evident that the C-band observation range completely covers the L-band coverage. Each central illumination point is... Figure 4 Provided and filtered. Figure 5As shown in (b), Group 1 consists of multiple targets moving from north to south across a wide angle of view, while Group 2 consists of multiple targets moving from west to east across a narrow angle of view. Since maritime targets move at high speeds, the positions of high-orbit satellites can be approximated as constant. Therefore, the wavefronts required for the wide angles of view for targets in Groups 1 and 2 are as follows: Figure 5 As shown in (a), it can be seen that the viewing angle range under the wave position coverage of group 1 is large, while the viewing angle of group 2 changes very little, both of which meet the wave position selection requirements.

[0114] In summary, the integrated intelligent detection and imaging system of geosynchronous orbit dual-frequency radar organically combines geosynchronous orbit radar detection and SAR imaging systems. Based on the designed L / C dual-band spectral design, it uses target detection and tracking information from the L-band to group multiple moving targets, providing indication information for intelligent spectral selection in the C-band. This enables long-term observation of moving targets, supports sparse zoom imaging of moving targets, and effectively saves onboard resources.

[0115] The embodiments described above are merely examples of several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the scope of protection of the present invention.

Claims

1. A design method for an integrated intelligent detection and imaging system of a dual-frequency radar in geosynchronous orbit, characterized in that, Includes the following steps: (1) Construct a schematic diagram of the L-band system wavelet selection for geosynchronous orbit SAR, design wavelet positions and related parameters, and provide system parameters for L-band target detection and base map imaging; (2) Based on the target position and motion information obtained from L-band target detection and tracking, target groups are formed; (3) Construct a schematic diagram of C-band system wavelet selection for geosynchronous orbit SAR, and design a C-band multi-wavelet system to fully cover L-band footprints; (4) Based on the target grouping information, determine the C-band positions that different grouped targets can experience within the L-band observation range, intelligently select the designed C-band positions, and obtain the parameters of the SAR imaging system; (5) Based on the system parameters obtained in step (4) and the target motion information provided in step (2), sparse zoom imaging of C-band moving targets in each target group is realized to obtain high-precision SAR images of the targets.

2. The integrated intelligent detection and imaging system design method for geosynchronous orbit dual-frequency radar according to claim 1, characterized in that, The implementation process of step (1) is as follows: To avoid transmitted pulse interference, the pulse repetition frequency (PRF) must meet the following conditions: in, and These represent the maximum and minimum slant ranges from the SAR satellite to the far and near ends of the mapping strip during the synthetic aperture time. This represents the number of pulse cycles that the target echo takes to reach the radar within the observation area. At the speed of light, This means taking the integer part. The pulse width. For time intervals; To avoid the strongest nadir echo affecting the received signal, the PRF should simultaneously meet the following requirements: in, For satellite altitude, The duration of the nadir echo; to avoid interference from the transmitted pulse and the nadir echo, plot the relationship between the lower angle of view and the pulse repetition frequency as a waveform diagram; To avoid the effects of distance and orientation ambiguity, the PRF also needs to satisfy: in, For satellite platform speed, This refers to the azimuth antenna length. This is for design margin; Zebra maps were designed using the maximum and minimum slant ranges from SAR satellites to the far and near ends of the mapping strip during synthetic aperture time. in, , , Let be the radius of the Earth in all directions. For satellite coordinates, The nearest and farthest endpoints (the farthest endpoint is indicated when the + sign is used). From a bottom perspective, For beamwidth, The distance from the satellite to the Earth's center. for Distance to the Earth's core For satellite to distance, The plane normal vector of the zero Doppler surface; after obtaining the positions of the near and far endpoints of the observation area, the minimum slant range is obtained by calculating the distance to the satellite. and maximum slope distance .

3. The integrated intelligent detection and imaging system design method for geosynchronous orbit dual-frequency radar according to claim 1, characterized in that, The implementation process of step (2) is as follows: Based on the L-band target detection and tracking, the position and motion information of multiple targets are continuously acquired, including the slant range and viewing angle of the target to the satellite, the speed and direction of the observed target, and the grouped targets are acquired.

4. The integrated intelligent detection and imaging system design method for geosynchronous orbit dual-frequency radar according to claim 3, characterized in that, The targets in the same group have the following characteristics: ① The distance between current targets does not exceed the preset value; ②Based on the current target position and target speed, after the set expected movement time, feature ① can still be satisfied; ③ The set detection time still satisfies features ① and ②: The setting of the expected movement time is used to predict whether it will enter the coverage area of ​​the same C-band beam, and the setting of the detection time is used to update the target and grouping status.

5. The integrated intelligent detection and imaging system design method for geosynchronous orbit dual-frequency radar according to claim 1, characterized in that, The implementation process of step (3) is as follows: The latitude and longitude coverage area is selected based on the three-dimensional coverage area of ​​the L-band wavefront. The selection method for this area is as follows: ， ， ， in, The coordinates of the boundary points of the beam coverage area. These are the latitude and longitude coordinates of the boundary points. These represent the minimum and maximum latitude and longitude of the boundary point, respectively. These are the latitude and longitude coverage values; to ensure full coverage of the L-band footprint by the C-band wavefront, a redundancy design method is adopted, and the latitude and longitude coverage area is set as a rectangle. Therefore, the latitude and longitude dimensions of the boundary of this area are: in, These are the start and end values ​​of the set latitude and longitude range, respectively. The set magnification factor; thus, the set rectangular latitude and longitude range encompasses the latitude and longitude range of the L-band wavefront. Subsequently, based on the mapping band width of the C-band position, the point spacing of the center illumination point of the C-band position is calculated; To reduce the number of wavelets and avoid generating points directly from the rectangular latitude and longitude range boundary, a buffer boundary slightly smaller than the rectangular latitude and longitude range is set, using a scaling factor. The latitude and longitude coordinates of the beam center illumination point can be selected as early as the lowest point of the buffer boundary; The latitude and longitude coordinates of the required C-band wavefront center illumination point are uniformly arranged within the latitude and longitude buffer boundary, thereby obtaining its three-dimensional coordinates. Perspective from near and far ends ; Calculate the near-side downward angle of each C-band position. Whether a C-band position is a C-band position to be retained can be determined by whether the angle difference between the center downward angle of the C-band position and the L-band position is less than the half beamwidth of the L-band. If it is less, it is retained.

6. The integrated intelligent detection and imaging system design method for geosynchronous orbit dual-frequency radar according to claim 5, characterized in that, The point interval of the C-band wavefront center illumination point is calculated as follows: in, This represents the maximum point spacing between the centers of illumination of adjacent C-band wavelengths. The spacing is extended by a factor that you set yourself. The time will be just right to achieve full coverage. This refers to the set width of the C-band mapping band.

7. The integrated intelligent detection and imaging system design method for geosynchronous orbit dual-frequency radar according to claim 5, characterized in that, The half-beamwidth of the L-band is: in, Antenna length For carrier frequency.

8. The integrated intelligent detection and imaging system design method for geosynchronous orbit dual-frequency radar according to claim 1, characterized in that, The implementation process of step (4) is as follows: The center point of each group of targets is calculated using the geometric median, which is the point whose sum of distances to all targets is the shortest. The iterative calculation method is as follows: in, For the updated center point latitude and longitude, For the first in the group The latitude and longitude of each target This represents the distance between the current center point and all other points. Based on the calculated center positions of each group, the distance to the center illumination point of each C-band wave position is calculated, and the minimum value is selected to intelligently match a suitable C-band wave position for that group of targets.

Images