51 results about "Spaceborne radar" patented technology

The invention discloses a phase-scanning and mechanism-scanning combined airspace searching method based on a spaceborne radar. The method comprises the following steps of: (1) generating a searching wave beam with a fixed shape on an azimuth plane and first initiating the searching direction of an antenna array plane toward an azimuth dimension; (2) carrying out pitching dimension searching wave beam by using a pitching dimension-dimension phased array on the antenna array plane, and implementing pitching dimension airspace searching on a sine space by using characteristics of a phased array antenna wave beam; (3) rotating the antenna array plane to the position of a next azimuth angle; and (4) judging whether an azimuth dimension wave beam direction angle is rotated to a maximum searching azimuth angle direction or not and whether the pitching dimension airspace searching is finished or not; and if so, finishing the searching; and otherwise, carrying out the searching processes of the step (2) and the step (3) in a repeated way. According to the invention, an airspace searching method with different complementary and mixed searching methods as well as combined phase-scanning and mechanism-scanning of the spaceborne radar is achieved; and the phase-scanning and mechanism-scanning combined airspace searching method based on the spaceborne radar, disclosed by the invention, has the advantages of high searching speed, short target capturing time, uneasiness for losing targets, good impact shock resistance, less T / R units and suitability for being used on spaceborne platforms with finite resources.

The present invention discloses a spaceborne radar and ground-based radar reflectivity factor data three dimensional fusion method. According to the present invention, by using the precipitation radar (PR) data of high vertical resolution as the output of a neural network and the ground radar (GR) data of high horizontal resolution and low vertical resolution as the input, a non-linear relationship of a PR and a GR is established, thereby fusing into the three dimensional reflectivity factor data having the high vertical and horizontal resolution. Based on a neural network algorithm, the PR and GR reflectivity factor data three dimensional fusion is carried out to obtain a fine three dimensional structure of an intensity echo which is very important for the later applications, such as the fine detection and tracking of a middle and small-scale convective weather process, the subsequent quantitative rainfall measurement, the radar data assimilation in the middle-scale forecast, etc.

The invention provides a fusion inversion method and device for a sea wave significant wave height field. The method comprises steps as follows: acquiring a significant wave height field which is acquired by a spaceborne radar height gauge and comprises substellar point sea wave significant wave height data as well as a sea surface wind field which is acquired by a spaceborne microwave scatterometer and comprises wide swath sea surface wind speed data; performing conversion calculation processing on the acquired sea surface wind field according to the wind wave growth relation between sea surface wind speeds and sea wave significant wave heights, and obtaining a wind wave field having the same swath as the sea surface wind field; performing correction processing on the wind wave field according to the acquired significant wave height field, and obtaining the sea wave significant wave height field having the same swath as the sea surface wind field; providing the sea surface wind field with wide swath, high precision and high spatial resolution through the spaceborne microwave scatterometer, converting the sea surface wind field acquired by the scatterometer into the wind wave field according to the wind wave growth relation, performing correction processing on the wind wave field through the significant wave height field of the height gauge, and finally, obtaining the significant wave height field with wide swath, high precision and high spatial resolution.

The invention relates to a multifunctional digital signal processor for a skyborne or spaceborne radar altitude gauge, which adopts the technical scheme that an input signal passes through an isolating retainer, and is subjected to sampling through a high-speed A / D sampler under the control of a sequential control unit; a digital I / Q signal is obtained by a digital I / Q processing unit; I / Q data is stored to a data A storage under the control of a storage control unit, and after being stored fully, data of a sub-aperture is processed by a sub-aperture processing unit in a mode of a two-dimensional complex matrix; the output of sub-aperture processing is stored to a data B storage under the control of the storage control unit, and after the data of the sub-aperture is stored fully, subsequent sub-aperture observation data is processed repeatedly and sequentially and is stored to the data B storage continuously; after the data of a set number of the sub-apertures are stored fully, the data is processed by a multi-view processing unit to acquire echo power observation matrixes of resolution footprints in each azimuth finally; and a digital signal processing (DSP) general processor performs maximum likelihood estimation and prediction on each received echo power observation matrix.

The present invention relates to an advanced spaceborne Synthetic Aperture Radar (SAR) system and method that can provide high resolution measurements of the Earth or planetary surface, overcoming limitations in conventional SAR systems, and reduce development costs. The present invention utilizes advanced and innovative techniques, such as software defined waveforms, digital beamforming (DBF) and reconfigurable hardware, to provide radar capabilities not possible with conventional radar instruments, while reducing the radar development cost. The SAR system architecture employs a modular, low power, lightweight design approach to meet stringent spaceborne radar instrument requirements. Thus, the present invention can enable feasible Earth and planetary missions that address a vast number survey goals, including the measurement of ecosystem structure and extent, surface and sub-surface topography, subsurface stratigraphy, soil freeze-thaw, ice sheet composition and extent, glacier depth, and surface water, among many others.

A radar altimeter system-level testing method, using an echo simulator to form a closed-loop test system, to test the radar altimeter's height measurement function, wave height test function, and system AGC adaptive adjustment function, so as to test the system-level measurement function of the radar altimeter A comprehensive verification is carried out, which solves the system-level verification problem of the spaceborne radar altimeter under the whole star condition. The method of the present invention utilizes the echo simulator to form a closed-loop test system, changes the input of the radar altimeter system through the setting of the echo simulator and the adjustment of the attenuator, and interprets the final test result of the radar altimeter, and the test result reflects the complete working logic of the radar altimeter, achieving The purpose of radar altimeter system level verification.

The invention discloses a satellite-borne radar rainfall correction method based on active and passive microwave joint detection, and the method comprises the steps: correcting the deviation between active radar observation data and passive radiometer observation data in the presence of rainfall through employing numerical prediction background field historical data and observation historical data; performing space-time matching on the corrected active radar observation data, the corrected passive radiometer observation data and the numerical forecasting background field atmosphere three-dimensional space distribution information; using the numerical forecasting background field atmosphere three-dimensional space distribution information as prior information, and using the corrected activeradar observation data and the corrected passive radiometer observation data for calculation to obtain an optimal analysis atmosphere cloud and rain profile; and calculating a related rainfall correction coefficient of the active radar according to the optimal analysis atmospheric cloud and rain profile. The method is suitable for various satellite-borne radar systems and passive microwave instruments, and the precision of the rainfall correction coefficient can be guaranteed.

The invention discloses a thermal control device for a spaceborne radar transmitting and receiving chip assembly, comprising: the transmitting and receiving chip assembly [4] is installed in the heat pipe area of ​​a honeycomb plate; the space between the transmitting and receiving chip assembly [4] and the honeycomb plate is filled with thermally conductive fillers ; The outer surface is sprayed with radiation coating; on the corresponding side, an electric heater [3] and a loop heat pipe LHP evaporator [8] are pasted; a temperature sensing element [6] is installed on the transmitting and receiving chip assembly [4], connected by a wire to the input end of the control device [13]; the output lines of the control device [13] are respectively connected with the LHP evaporator [8] and the electric heater [3]; the exterior of the honeycomb panel is equipped with heat insulating material; the back of the heat insulating material An LHP radiator [9] is installed on the sunny side; the LHP radiator [9] is connected with a heat pipe through a pipeline. The invention solves the problems of heat dissipation and temperature consistency when the transmitting and receiving chip assembly [4] is working, and heat preservation when not working, and achieves beneficial effects such as stable control, strong adaptability, and good temperature consistency.

The invention discloses a spaceborne radar data processing and controlling device based on a VPX bus. Two identical processing computers are adopted for a data processing system and a controlling system, and each processing computer comprises two isomorphic PowerPC 440 cores. The two systems form two working modes through the four isomorphic PowerPC 440 cores. According to the parallel mode, the four isomorphic PowerPC 440 cores independently work, but interconnection channels are formed between the four isomorphic PowerPC 440 cores through interconnection communication buses. According to the fault-tolerance mode, the four isomorphic PowerPC 440 cores carry out fault tolerance in a four-mode redundancy mode. The device aims at achieving the purposes of high spaceborne radar data processing point flight path processing capacity, coordinate transformation of radar information data, trace point and flight path rough correlation, trace point and temporary flight path correlation, flight path correlation, trace point fusion and flight path filtering, and short prediction processing time and solving the problem that the spaceflight use environment is severe.

The invention discloses a thermal control system for a plane phased array antenna with high power and high heat flow in double-side view, which includes a transmitting and receiving chip assembly and a pre-embedded area of ​​a phase-change heat pipe installed in a structural honeycomb plate, and the phase-change heat pipe adopts aluminum ammonia The phase-change heat pipe plays a role of equalizing and suppressing the temperature rise of the transmitting and receiving chip components; there is a heat-conducting filler between the transmitting and receiving chip components and the embedded heat pipe area of ​​the honeycomb plate to increase the contact heat conduction between the transmitting and receiving chip components and the phase-change heat pipe . The invention solves the problems of heat dissipation, temperature consistency, heat preservation when not working, and the like when the space-borne radar transmitting and receiving chip assembly is working under the condition of double side view, high power and high heat flow.

The invention relates to an InSAR deformation monitoring method based on spatial constraint, which comprises the following steps of: conducting data acquisition and preprocessing, namely, acquiring an original single-view complex image through a spaceborne radar satellite, and performing image registration and geocoding by using an external DEM to enable all the images to be positioned in a same coordinate framework; selecting an optimal main image from all the images under the same coordinate frame, and forming differential interference pairs by the optimal main image and other images respectively; based on the differential interference pair, selecting and obtaining high-coherence points; performing phase unwrapping processing on the high-coherence points to obtain unwrapped phases of the high-coherence points; for the unwrapping phase, inversing a deformation sequence by using spatial constraint, so as to obtain an initial deformation phase; and carrying out atmospheric error separation on the initial deformation phase to obtain a final deformation phase, namely deformation monitoring information. Compared with the prior art, the method is based on the time sequence InSAR technology, the spatial constraint is reasonably added, and the high-precision deformation sequence can be efficiently and reliably recovered.

The invention discloses a real-time compensation decoupling method for spacecraft platform disturbance by a spaceborne radar. The method includes that when the spaceborne radar searches, a three-axis stabilization rate gyroscope real-timely detects changing amount and changing direction of a spacecraft platform attitude angle; the changing amount and the changing direction of the spacecraft platform attitude angle are subjected to transformation of coordinates to obtain changing amount and changing direction of a spaceborne radar attitude angle; when the changing amount of the spaceborne radar attitude angle exceeds a preset threshold value, the spaceborne radar sets a searching compensatory angle; the value of the searching compensatory angle is the changing amount of the spaceborne radar attitude angle; the compensation direction of the searching compensatory angle is vertical to the searching direction of the spaceborne radar and opposite to the changing direction of the spaceborne radar attitude angle; a servo mechanism of the spaceborne radar performs real-time compensation controlling on the spaceborne radar attitude angle according to the searching compensatory angle. According to the real-time compensation decoupling method and a compensation decoupling system for spacecraft platform disturbance by the spaceborne radar, own resources of a spacecraft platform are utilized, real-time compensation of the servo mechanism of the spaceborne radar is achieved, valuable volume, weight, and power consumption resources of a spacecraft can not be occupied, and resources are saved.

The invention provides a spaceborne radar clock drifting on-orbit correction method based on an active calibrator. The spaceborne radar clock drifting on-orbit correction method based on the active calibrator comprises the steps that spaceborne radar pulse signals are tracked, received and transmitted through the active calibrator, the clock drifting distance of spaceborne radar is obtained by comparing an active calibrator distance parabola and a spaceborne radar distance parabola, and real-time quantitative monitoring of the operating state of a spaceborne radar clock is achieved based on the clock drifting distance of the spaceborne radar. According to the spaceborne radar clock drifting on-orbit correction method based on the active calibrator, the clock drifting distance of the spaceborne radar is measured accurately with an independent method for the first time, testing can be conducted in any position within the coverage of wave beams of the spaceborne radar and at any time when the spaceborne radar is in transit according to the method, the space-time flexibility is high, and the requirement for absolute timing reference for the active calibrator does not exist due to the fact that the pulse intervals are received by the active calibrator on the ground to serve as analysis data; meanwhile, path errors caused by the air when the spaceborne radar signals are transmitted are eliminated, and the clock drifting distance of the spaceborne radar can be measured accurately in real time.

The invention discloses a stepping compensation low-cost phased array antenna architecture and a design method thereof, relates to the technical field of spaceborne radar antennas in the spaceflight field, and solves the problems of poor sub-array level phased array scanning capability, high scanning grating lobe and serious gain loss of a spaceborne radar antenna in the spaceflight field. The stepping compensation low-cost phased array antenna architecture comprises n antenna sub-arrays, n transceiving assemblies and a power division synthesis network; and each antenna subarray comprises a wave beam stepping shifter and m basic radiation units, each wave beam stepping shifter comprises m output ends, the input ends of the n wave beam stepping shifters are connected with the output ends ofthe n transceiving assemblies, the m output ends of the wave beam stepping shifters are connected with the input ends of the m basic radiation units respectively, and the input ends of the n transceiving assemblies are respectively connected with the corresponding output ends of the power division synthesis network. The scanning gain loss is greatly reduced, the scanning range can be expanded, the flexibility of a satellite-borne information system is improved, and the antenna architecture can be widely applied to a high-speed satellite communication system and a high-resolution radar imagingsystem.

The invention provides a method for determining an LFM waveform of a distributed spaceborne radar based on different frequency modulation slopes of the same bandwidth. A linear frequency modulation signal of the same carrier frequency, the same time width and the same bandwidth is equally divided into two segments on the time axis, each segment is modulated by using a different frequency modulation slope k, a transmitting signal model of different frequency modulation slopes of the distributed system radar is established to analyze the influence of differences of the frequency modulation slopes on the waveform orthogonality and Doppler sensitivity, autocorrelation, cross-correlation and Doppler tolerance and other parameters of the transmitting waveform are set via theoretical analysis, double-segment transmitting waveform parameters of each radar unit are determined, the quasi-orthogonality and low Doppler sensitivity between multiple double-slope LFM signals are achieved at last, andthe demands of the distributed system radar for the transmitting waveform are met without increasing the bandwidth of the radar system. The method provided by the invention is simple in operation, and can be used for significantly improving the orthogonality of the transmitting waveform of the distributed spaceborne radar system, and reducing the crosstalk between the radar units and the requirements of the distributed system for the system bandwidth B.

The invention provides a preparation method of an anisotropic composite material for a spaceborne radar antenna panel, and relates to a preparation method of a composite material for a spaceborne radar antenna panel. In the prior art, the existing composite material for spaceborne radar antenna panels can not concurrently meet a transverse tensile strength and longitudinal tensile strength, and has characteristics of poor comprehensive mechanical property and not high density. A purpose of the present invention is to solve problems in the prior art. The preparation method comprises: coating an aluminum nitride suspension on the surface of fibers, fixing into a bundle, injecting an aluminum alloy solution to impregnate, and spraying a cooling liquid to rapidly cool to obtain the composite material. The anisotropic composite material has characteristics of high density, high longitudinal tensile strength maintaining, high longitudinal thermal conductivity maintaining, transverse tensile strength increase, transverse thermal conductivity increase, and excellent comprehensive performance, and can be used in the field of spaceborne radar antenna panels and preparations thereof.

The invention discloses a satellite-borne radar switching interface module, which is characterized in that an external power supply is connected with a 5V power supply interface chip through a VPX bus to supply power to the module, an anti-radiation device reads data self-configuration of a PROM, reads more than two parts of data of FLASH to configure an FPGA device, refreshes configuration of the FPGA device at regular time, monitors the state of the FPGA device and reads BIT information of the FPGA device. According to the FPGA device, the FPGA device is connected with a VPX bus through a CAN interface chip or an RS485 interface chip, external data is transmitted to the FPGA device through the VPX bus to be analyzed and recognized and transmitted to a next processing node, high-speed transmission of the data is achieved, and the triple modular redundancy and dynamic refreshing technology is adopted to reinforce radiation resistance, adapt to the space environment and reduce the influence of FPGA logic and FLASH overturning; and a data transmission link and a control instruction are adopted, software uploading is achieved, and ground software updates satellite-borne radar switching interface module software online.

The invention discloses a GNSS-based radar height finding system and a using method thereof. The system comprises a signal hardware receiver and a server, wherein the signal hardware receiver is provided with three channels, respectively, a GNSS channel, a main radar channel and an auxiliary radar channel; each channel sequentially comprises an antenna assembly, a low-noise amplifier assembly, a frequency mixer assembly, a first-stage microwave signal source assembly, a band pass filter assembly, a power amplifier assembly, a second-stage microwave signal source assembly, a low pass filter assembly, a quadrature demodulator assembly, and an analog-to-digital converter assembly according to a signal passing direction. Signals of the three channels pass through the analog-to-digital converter assemblies and then together enter a data collector assembly. A data acquisition control software module, a signal pretreatment software module, a two-dimensional imaging software module and a coherent processing software module are loaded on the server. The system of the invention can solve technical limitations of single observation angle, expensive employment, long revisit period and the like in the current spaceborne radar height finding system.

The invention discloses a method for evaluating the performance of a ship radar in an interference environment, comprising: a first step of radar and interference source antenna emission modeling; a second step of electromagnetic signal transmission modeling; a third step of target and background echo scattering modeling; a fourth step of electromagnetic signal transmission modeling and antenna receiving signal modeling; a fifth step of radar receiver modeling; a sixth step of obtaining a video signal output by the model; and a seventh step of processing data and evaluating the performance ofa radar, wherein an evaluation algorithm is established, video output data of the radar is processed, and the performance of the radar is evaluated. The method of the invention has the beneficial effects that: the method provides a complete ship radar performance evaluation model, which can analyze and evaluate the performance of the ship radar in the interference environment; because the modelingis performed at a signal level and in zero intermediate frequency, a simulation model does not depend on frequency and device parameters of a radar receiving channel, so that the model has universality and high efficiency; a ship platform and other platforms have common characteristics and can evaluate the performances of land, airborne and spaceborne radars.

The invention discloses a satellite-borne SAR imaging real-time processing method based on multiple servers and multiple GPUs, and the method comprises the steps: firstly reading satellite-borne SAR radar echo data on any CPU host end, and dividing the radar echo signal data to a plurality of CPU host ends through the password-free communication among the CPU host ends; reading corresponding radar echo signal data parameters and information of a plurality of GPU equipment ends at each CPU host end, and setting the thread count of the CPU host end; then, enabling each GPU equipment end to read satellite-borne SAR radar echo data divided for the azimuth direction, a distributed memory and a plurality of echoes of radar echo signals from the corresponding CPU host end; finally, achieving range pulse compression of a plurality of echoes at the GPU equipment end, and achieving BP imaging; and after BP images on all GPU equipment ends are obtained, writing the BP images into a radar echo data processing file, and analyzing an imaging result.

The invention provides a spaceborne radar altimeter method and system. The method comprises the following steps: setting a coding signal pulse sequence as a periodic transmission sequence, and enabling any pulses to be in an orthogonal relation; setting a pulse repetition frequency on the zebra map, and enabling the set pulse repetition frequency to control nadir echo and interference side high area echo to be received by a radar receiver at the same time, wherein the waveform of radar emission signals corresponding to the nadir echo and the interference side high area echo is different; obtaining bottom-looking radar altimeter echoes and side-looking radar altimeter echoes with time aliasing based on the setting of the coded signal pulse sequence and the setting of the pulse repetition frequency, wherein the bottom-looking radar altimeter echoes and the side-looking radar altimeter echoes obtained at the same moment are orthogonal; and based on the acquired time-aliasing echo of the bottom-looking radar altimeter and the time-aliasing echo of the side-looking radar altimeter, extracting echo signals of the bottom-looking radar altimeter and echo signals of the side-looking radar altimeter respectively so as to realize the height measurement function of the bottom-looking altimeter and the side-looking altimeter.

The embodiment of the invention provides a multi-satellite formation radar timing synchronization method, device and equipment and a storage medium, which are applied to a multi-satellite formation spaceborne radar system. The spaceborne radar system comprises a primary satellite radar and at least one auxiliary satellite radar. The method comprises the following steps: acquiring relative time difference information between a second pulse signal output by a global navigation satellite system (GNSS) receiver of a primary satellite and a second pulse signal output by a GNSS receiver of any auxiliary satellite in at least one auxiliary satellite; according to the relative time difference information, performing time synchronization on the second pulse signal of the primary satellite and the second pulse signal of any auxiliary satellite; generating a timing signal of the main satellite radar and a timing signal of any auxiliary satellite radar based on the pulse per second signal after time synchronization. Based on the radar timing synchronization method provided by the invention, the time synchronization of the timing signals of the spaceborne radar system of the multi-satellite formation can be realized.

The invention discloses a phase-scanning and mechanism-scanning combined airspace searching method based on a spaceborne radar. The method comprises the following steps of: (1) generating a searching wave beam with a fixed shape on an azimuth plane and first initiating the searching direction of an antenna array plane toward an azimuth dimension; (2) carrying out pitching dimension searching wave beam by using a pitching dimension-dimension phased array on the antenna array plane, and implementing pitching dimension airspace searching on a sine space by using characteristics of a phased array antenna wave beam; (3) rotating the antenna array plane to the position of a next azimuth angle; and (4) judging whether an azimuth dimension wave beam direction angle is rotated to a maximum searching azimuth angle direction or not and whether the pitching dimension airspace searching is finished or not; and if so, finishing the searching; and otherwise, carrying out the searching processes of the step (2) and the step (3) in a repeated way. According to the invention, an airspace searching method with different complementary and mixed searching methods as well as combined phase-scanning and mechanism-scanning of the spaceborne radar is achieved; and the phase-scanning and mechanism-scanning combined airspace searching method based on the spaceborne radar, disclosed by the invention, has the advantages of high searching speed, short target capturing time, uneasiness for losing targets, good impact shock resistance, less T / R units and suitability for being used on spaceborne platforms with finite resources.

The invention discloses a GNSS-based radar height finding system and a using method thereof. The system comprises a signal hardware receiver and a server, wherein the signal hardware receiver is provided with three channels, respectively, a GNSS channel, a main radar channel and an auxiliary radar channel; each channel sequentially comprises an antenna assembly, a low-noise amplifier assembly, a frequency mixer assembly, a first-stage microwave signal source assembly, a band pass filter assembly, a power amplifier assembly, a second-stage microwave signal source assembly, a low pass filter assembly, a quadrature demodulator assembly, and an analog-to-digital converter assembly according to a signal passing direction. Signals of the three channels pass through the analog-to-digital converter assemblies and then together enter a data collector assembly. A data acquisition control software module, a signal pretreatment software module, a two-dimensional imaging software module and a coherent processing software module are loaded on the server. The system of the invention can solve technical limitations of single observation angle, expensive employment, long revisit period and the like in the current spaceborne radar height finding system.

The invention belongs to the technical field of satellite-borne synthetic aperture radar data processing, and particularly relates to a building extraction method based on lifting track radar data. According to the method, a satellite-borne synthetic aperture radar is used for obtaining an orbit ascending radar image and an orbit descending radar image at the time interval of 6 days, and the method for extracting the building based on the satellite-borne radar data is established through radiometric calibration, terrain correction, thermal noise elimination, entropy calculation and orbit weighting, incident angle correction, orbit ascending and descending maximum value synthesis and histogram threshold processing. According to the method, the dependence of building extraction on ground samples is reduced, the operation load is reduced compared with an identification method based on machine learning, the problem of building scattering information distortion caused by monorail radar observation is solved, identification errors caused by space speckle noise, image incidence angles and radiation differences are reduced, and the identification accuracy is improved. The method can be applied to the fields of land resource monitoring, urban planning management and the like, and achieves 87% precision in urban building identification cases.

The invention provides a fusion inversion method and device for a sea wave significant wave height field. The method comprises steps as follows: acquiring a significant wave height field which is acquired by a spaceborne radar height gauge and comprises substellar point sea wave significant wave height data as well as a sea surface wind field which is acquired by a spaceborne microwave scatterometer and comprises wide swath sea surface wind speed data; performing conversion calculation processing on the acquired sea surface wind field according to the wind wave growth relation between sea surface wind speeds and sea wave significant wave heights, and obtaining a wind wave field having the same swath as the sea surface wind field; performing correction processing on the wind wave field according to the acquired significant wave height field, and obtaining the sea wave significant wave height field having the same swath as the sea surface wind field; providing the sea surface wind field with wide swath, high precision and high spatial resolution through the spaceborne microwave scatterometer, converting the sea surface wind field acquired by the scatterometer into the wind wave field according to the wind wave growth relation, performing correction processing on the wind wave field through the significant wave height field of the height gauge, and finally, obtaining the significant wave height field with wide swath, high precision and high spatial resolution.

The invention discloses a novel method for eliminating direction ambiguity of earth surface deformation of a satellite interference radar, which comprises the following steps of: solving a variance by using a distance relationship between a phase difference between a plurality of satellite interference radar image pairs and orbits, combining a weighted least square method and using different coherence phase probability density distribution functions; and taking an inverse matrix of the variance matrix as a weighting matrix, and determining the surface water horizontal and vertical motion deformation. According to the method, the multi-beam or lifting-rail multi-mode spaceborne radar interferogram is fused, so that the interference of system errors on the surface deformation observed by the satellite interference radar is eliminated, and the precision of obtaining the three-dimensional surface deformation observed by the satellite interference radar is improved; the method can be applied to real-time dynamic and macroscopic large-scale monitoring of real earth surface three-dimensional deformation such as land subsidence and landslide to provide reliable technical support.

The embodiment of the invention provides a composite terrain feature simulation method and device and an electronic device, and the method comprises the steps: building a geological feature database and a digital elevation information database of a composite terrain, carrying out the orbit modeling of a satellite where a satellite-borne radar is located, and determining the conversion relation ofall coordinate systems of the satellite; determining an irradiation area of a radar beam of the satellite-borne early warning radar on the surface of the earth; and dividing an irradiation area according to the clutter scattering resolution to obtain a scattering unit; according to the target longitude and latitude corresponding to the scattering unit, obtaining geologic characteristics and elevation information of the scattering unit from a geologic characteristic database and a digital elevation information database respectively; and based on the geological characteristics and the elevationinformation of each scattering unit and the relative position relationship between each scattering unit and the radar, calculating the backward scattering coefficient of each scattering unit by adopting a calculation model, and taking the longitude and latitude, the geological characteristics, the elevation information and the backward scattering coefficient of each scattering unit as the composite terrain characteristics under the irradiation area.