49 results about "Antenna temperature" patented technology

The invention discloses a SAW (surface acoustic wave)-based passive temperature tag which comprises a substrate, an interdigital transducer, a tag antenna, a temperature reflecting grating and an ID (identification)-tag reflecting grating. The ID tag reflecting grating is used for identifying the detected objects by the SAW on the reflecting substrate, and the substrate is provided with the interdigital transducer used for take charging to the electro-acoustic conversion of signals. According to the SAW-based passive temperature tag, a transmitting and receiving antenna is used for transmitting and receiving radio-frequency signals, the ID-tag reflecting grating is used for identifying the detected objects by the SAW on the reflecting substrate, and the temperature reflecting grating is used for measuring temperature by the SAW on the reflecting substrate. A reader is used for reading the ID information and the temperature data which are stored in the passive temperature tag, and the data is processed in an intermediate-frequency signal processing plate. With regard to the determination of the position of the echo baseband pulse signals, the centroid position replaces the peak position, therefore, the amount of computation is reduced, and the precision is improved.

The invention discloses a gain-and-direction-orientated structure thermal deformation compensation method for a satellite-borne active phase control array antenna. The method comprises the steps of determining structural parameters, material attributes and electromagnetic parameters of the antenna; determining antenna environment thermal load; calculating antenna temperature field distribution under sunshine; determining T / R assembly thermal power consumption; calculating antenna temperature field distribution under the T / R assembly thermal power consumption; performing temperature field superposition and calculating the thermal deformation of the antenna structure; extracting position offset in the array element geometric center; calculating the additional error of the array element space phase; determining the amplitude and phase distribution of array element excitation current; calculating the electrical performance of the antenna; judging whether gain and direction are both satisfied simultaneously or not; and calculating the antenna ideal main beam directed unit vector, the adjusting amount of the array element space phase, and the phase current of the compensated array element excitation current. The compensation method provided by the invention is combined with a phase adjusting method, so that the electrical performance compensation to the deformed satellite-borne active phase control array antenna is realized; the problem of antenna electrical performance degradation caused by structural thermal deformation is solved; and the normal operation of the antenna can be ensured.

The invention discloses a temperature control method of a wave-absorbing external heat flow simulation system for a large-scale spacecraft microwave antenna vacuum thermal test, surface temperature of a wedge inside a wave-absorbing box is used as a controlled object, and a thin film heater on the outer surface of the wave-absorbing box serves as a heater, thereby realizing temperature control of an antenna arranged inside the wave-absorbing box. According to the method, on the basis of a multistage PID algorithm, a stable-state and dynamic model of wave-absorbing material surface temperature-antenna surface arrived heat flow is established to set ratio parameters, integral parameters and differential parameters at different temperatures; algorithm target curves are given in a segmented manner; a fuzzy control algorithm is adopted to improve the balancing speed of the controlled object; and a neural network model is introduced to predict the test piece surface temperature. The temperature control method of the wave-absorbing external heat flow simulation system for the large-scale spacecraft microwave antenna vacuum thermal test realizes uniformity and high-efficiency and high-precision control of antenna temperature in a large-scale spacecraft microwave antenna thermal test, is suitable for a large-scale microwave antenna vacuum thermal test, improves test effectiveness and coverage of the test, and is also suitable for a vacuum thermal test of a spacecraft equipped with a large-scale microwave antenna.

The invention discloses an antenna cross polarization correction method applicable to a satellite-borne polarized related completely-polarized microwave radiometer. The method comprises the following steps of: re-deducing an antenna temperature equation comprising four Strokes parameters, obtaining a 4*4 cross polarization M matrix by adopting an antenna temperature simulation technology, and finally realizing antenna cross polarization correction for a completely-polarized radiometer which runs on a track. The method is different from cross polarization correction which is performed in an antenna design and optimization stage and is applicable to final correction of the radiometer running on the track. By the method, the antenna cross polarization correction for the satellite-borne polarized related completely-polarized microwave radiometer is realized.

The invention relates to a passive millimeter wave focal plane image formation device, belonging to the field of passive millimeter wave image formation device and aiming to solve the problem of limited pixel and low image formation resolution faced by the existing image formation device. The device comprises N-numbered feed sources and N-numbered millimeter wave radiometer channels; the N-numbered feed sources are arranged on the focal plane of focusing antenna in the form of linear array; each millimeter wave radiometer channel is composed of a radio-frequency amplifier, a radio-frequency filter, a frequency mixer and an A / D converter which are connected in series in sequence; N-numbered intermediate frequency digital signals are transmitted to a computer for carrying out self-correlation and mutual correlation processing, the computer obtains antenna temperature Tai and interferometry temperature Tcij, the computer then processes the antenna temperature Tai to obtain pixel value Ti and inserts the interferometry temperature Tcij between pixel value Ti and Tj to mutually form an focal plane image. In the invention, coherent image formation and incoherent image formation are effectively combined, so that the number of pixels of the image is increased and spatial resolution of image formation is improved.

The invention belongs to the technical field of electric power insulating equipment detection, and particularly relates to an insulator dirt detecting method and device. The method comprises the steps that the relational expression among the antenna temperature, the environment temperature, the atmosphere humidity, the equivalent salt density and the equivalent dust density is established; the antenna temperature, the environment temperature and the atmosphere humidity are detected and substituted into the relational expression; double circulation increasing with the iterative step being eta 1 is carried out on the equivalent salt density and the equivalent dust density, and the minimum mean square error between the antenna temperature and the antenna temperature output through formula iteration is calculated; precise double circulation iteration with the iterative step being eta 1 / 10 is carried out, and when the error is minimal, the final equivalent salt density and the final equivalent dust density are obtained. The device comprises a microwave radiometer, a temperature sensor, a humidity sensor, a central processing unit, a memorizer, a display screen, operation buttons, a battery, a signal line and a power line. The insulator dirt degree is online detected in a non-contact mode, and the insulator dirt detecting method and device have the advantages of being high in precision, fast in detection, convenient to use and the like.

The invention relates to the technical field of antennas, in particular to a thermal deformation real-time forecast method for an axial symmetry reflector antenna. Temperature measuring data and temperature simulation data are combined, and the thermal deformation real-time forecast method for the axial symmetry reflector antenna is put forward. Accordingly, an antenna temperature field is acquired accurately in real time, the real-time forecast for the thermal deformation of the reflector antenna is achieved, and the influence of the thermal deformation of the reflector antenna to electrical properties of the reflector antenna is reduced in real time. The thermal deformation real-time forecast method for the axial symmetry reflector antenna is used for the real-time forecast of the temperature field and the thermal deformation of the axial symmetry reflector antenna in a project.

The invention discloses a foundation antenna temperature compensation method, which mainly solves the problem of nonideal electric performance caused by electric performance compensation by aiming at gravity deformation in the prior art. The method is realized through the following steps that (1) the foundation reflecting surface antenna parameters are obtained, and the parameters are used for calculating the sun direct illuminating point position of an antenna; (2) an antenna panel is divided into M*N blocks, and the antenna panel block region with the sun direct illumination point is determined; (3) an antenna hot deformation sub surface position compensation regulation table is built, the sub surface position compensation regulation table is inquired through the real-time weather condition, and six kinds of 36 fitting parameters of the current block under extreme conditions are obtained; (4) the six kinds of fitting parameters are subjected to grouping interpolation, the interpolation results are used for calculation to obtain the antenna heat deformation sub surface position compensation regulation quantity, and the antenna temperature compensation is completed. The foundation antenna temperature compensation method has the advantages that the antenna deformation caused by the temperature field can be compensated in real time, the electric performance is improved, and the method can be used for the temperature deformation electric performance real-time compensation of foundation antennas of ground communication antennas, radio telescopes and the like.

The invention discloses a space mesh reflector antenna temperature load analysis method based on an electromechanical coupling model. The method comprises the specific steps of 1, inputting antenna geometric parameters, material parameters and electric parameters; 2, building an antenna structure finite element model; 3, building an antenna heat finite element model; 4, setting a boundary condition; 5, selecting a track; 6, calculating a temperature field; 7, loading temperature field loads; 8, calculating thermal deformation; 9, outputting thermal deformation displacement; 10, calculating facet phase errors; 11, adopting an electromechanical coupling model for calculating an antenna far field electric field; 12, judging whether the electric performance meets the requirement or not; 13, outputting an antenna structural design scheme or 14, updating antenna parameters, and the step 1 continues to be executed. Based on the electromechanical coupling model, temperature load analysis is performed on the space mesh reflector antenna, space mesh reflector antenna electric performance analysis and electromechanical integration optical design can be guided.

The present invention relates to a method and apparatus which corrects antenna noise temperature in antenna back lobes, for earth-observing microwave instruments on satellites in orbit, to counter signal contamination from celestial bodies. The antenna back lobe signal correction is computer-program-modeled with only a few static and only a few dynamic inputs, and for a given set of parameters (i.e., orbital altitude, pointing characteristics (e.g., nadir or cross-scanning or conical-scanning), frequency selectivity of the receiver / detector) produces a few output files which are then combined by the program to predict the back lobe signal correction which is to be applied.

The invention discloses a satellite-bone active phased-array antenna structure lightweight design method based on electromechanical coupling.The method comprises the steps that antenna structure parameters, material properties, thermal parameters and electromagnetic parameters are determined; aluminum honeycomb physical property parameters and geometrical parameters are extracted; an antenna array element phase center is determined; an antenna thermal model is established, thermal loads and boundary conditions are exerted, and antenna temperature field distribution in a space environment is calculated; an antenna structure finite element model is established, temperature loads and structural constraint are exerted, and antenna array plane thermal deformation is calculated; array element phase center nodal displacement is extracted; an antenna radiation pattern is calculated based on an electromechanical coupling model, and a first side lobe level of a deformed antenna is calculated; whether the result is out of the tolerance range or not is judged; the aluminum honeycomb geometrical parameters are modified, and a satellite-bone active phased-array antenna lightweight structure scheme is obtained.According to the satellite-bone active phased-array antenna structure lightweight design method based on electromechanical coupling, mutual effects of a mechanical field, an electric field and a thermal field of the antenna are considered comprehensively, structure lightweight design is achieved on the premise that the electrical requirements of the antenna are guaranteed, and the method is used for guiding the satellite-bone active phased-array antenna structure design.

The invention discloses a method for determining heat power consumption of a satellite-borne active phased-array antenna assembly based on electromechanical coupling. The method includes the steps that a structure parameter, a material attribute and an electromagnetic parameter of an antenna are determined; a heat parameter of the T / R assembly is determined; the antenna array element phase center is determined; an antenna heat model is set up, heat load and boundary conditions are applied, and the antenna temperature field distribution in a space environment is calculated; the heat unit type is converted; an antenna structure finite element model is set up, a temperature load and structural constraint are applied, and antenna array face heat deformation is calculated; an antenna phase reference point is determined, array element phase center node displacement is extracted, and gain loss of the deformed antenna is calculated based on an electromechanical coupling model; whether the gain loss exceeds the allowed range or not is judged, and the heat parameter of the T / R assembly is modified; the maximum value of heat power consumption of the T / R assembly is determined. Heat power consumption of the satellite-borne active phased-array antenna assembly can be effectively determined, design of the satellite-borne active phased-array antenna assembly is guided, and assembly position layout can be guided according to antenna structure temperature field distribution.

Temperature measurement systems (20) include a temperature sensor (22) and an electronic signal interrogator (24). The temperature sensor (22) has a transponder (26) equipped with an antenna (28), and a separate parasitic antenna (32) with a temperature-sensitive transducer (34, 68-74, 78a-84a), while the interrogator (24) has a transmitter (42) and antenna (40). The sensor (22) is designed to be placed in thermal contact with an object to be temperature-measured, with the interrogator (24) placed in proximity to the object. The systems (20) may be used with food servingware domes (88, 114), which can be preheated and placed over a food-bearing plate to maintain the temperature of the food.

The invention discloses a real-time monitoring microwave dicke radiometer based on a reference load temperature and belongs to the field of microwave passive remote sensing. The radiometer comprises a dicke input switch, wherein a first end of the dicke input switch is sequentially connected with a radio frequency and intermediate frequency amplifying circuit, a square law detector, a low frequency amplifier, a synchronous detector, a low pass filter and a data collecting and processing module, a second end of the dicke input switch is switched between a reference load and an antenna under the driving of a switch signal generator, and a temperature measuring circuit is arranged on the reference load and connected with the data collecting and processing module. The reference load of the microwave dicke radiometer is not required to be kept in a constant temperature state, only the temperature measuring circuit is used for monitoring the temperature changes of the reference load in real time, the monitored variable quantity of the temperature of the reference load is plugged into a radiometer scaling equation for modification, and an antenna temperature of the measured scene is obtained. According to the real-time monitoring microwave dicke radiometer based on the reference load temperature, the measuring accuracy is improved and the structure of the existing microwave dicke radiometers is simplified.

The invention discloses a rapid constructing method for temperature of a reflector antenna based on structural thermal analogy. The method comprises the steps that a structural scheme of the reflectorantenna, a layout scheme of temperature sensors and a distribution temperature information database of an antenna temperature field are determined; the antenna is divided into N annular domains; thedirectional pitching angle of the antenna and the angle between solar rays and a reflector are determined; the number and positions of the temperature sensors in the annular domains are determined, and actual numerical values under the current working condition are extracted; a temperature field of the annular domains is determined; an initial temperature field and an initial temperature value ofthe annular domains under the current working condition are calculated; analogic coefficienTS of the annular domains of the antenna are calculated, the initial temperature field is revised and the actual temperature field of the annular domains is reconstructed; whether or not a variable i is greater than N is determined, and the actual temperature field of the reflector antenna is reconstructed.The method has the advantages of being simple in calculation method and smaller in calculation amount, a large amount of time spent on simulating a finite element model is avoided, rapidness of acquiring the actual temperature field of a reflector antenna structure is ensured, and the method facilitates improvement of antenna reflector accuracy and comprehensive performance of the antenna.

The invention discloses an electromechanical integration optimization design method for a space mesh antenna under the action of a temperature load. The design method comprises the specific steps of (1) inputting geometric parameters, material parameters and electric parameters of the antenna; (2) building a structural finite element model of the antenna; (3) building a thermal finite element model of the antenna; (4) setting a boundary condition; (5) selecting an orbit; (6) calculating a temperature field; (7) loading a temperature field load; (8) calculating thermal deformation; (9) outputting a thermal deformation displacement; (10) calculating an ideal far electric field of the antenna; (11) approximately calculating a change quantity of the far electric field of the antenna; (12) calculating the far electric field of the antenna; (13) judging whether electric performance meets a requirement or not; (14) outputting an antenna structure design scheme; and (15) updating the antenna parameters. According to the design method, the electric performance of the space mesh antenna under the action of the temperature load is analyzed by adopting the approximate calculation method, and the electromechanical integration optimization design of the antenna structure is realized.

The invention provides a spaceborne salinometer cold space external calibration method and device, and relates to the satellite observation field. The method includes the steps: according to the land specific gravity in an antenna antical lobe view field of a spaceborne salinometer, determining a preselected area suitable for cold space external calibration; according to preset observation data corresponding to an antenna main lobe of the spaceborne salinometer, determining a time window suitable for cold space external calibration, wherein the observation data include space radiation, solar radiation and moon radiation; according to a cold space external calibration satellite actual running orbit corresponding to the preselected area and the time window, calculating a standard antenna temperature; and carrying out statistical processing on the standard antenna temperature and the actually measured antenna temperature of the spaceborne salinometer, to obtain a cold space external calibration coefficient for correcting the salinometer observation brightness temperature deviation. The method can perform external calibration on the salinometer regularly to obtain the instrument calibration coefficient, and is used for correcting the deviation of the observed brightness temperature obtained by the salinometer; and moreover, the method systemically solves the problem of the spaceborne salinometer cold space calibration in China.

The invention relates to a calibration system and method for a microwave weather observation instrument. The calibration system for the microwave weather observation instrument is mainly composed of a microwave absorber, a heat insulation box and an air layer. On the basis of accurate theoretical analysis, the antenna temperature TB of an antenna opening face of an output series radiometer of the calibration system is obtained, then the voltage V output by a microwave radiometer is measured, a calibration equation is fitted through two or more sets of antenna temperature TB data and voltage V data, and calibration is carried out on the microwave weather observation instrument. According to the calibration system, selection and characteristic tests of key materials are achieved, and the problem that the calibration accuracy is affected due to the fact that a brightness temperature output face is frosted at low temperature is solved. On the basis of the calibration system, the calibration method is introduced, the microwave weather observation instrument not only can accurately conduct two-point linear calibration, but also can conduct multi-point calibration so as to check whether the linearity of the observation instrument is good or not.

The invention provides an antenna window assembly and a design method thereof, which are suitable for a long-time aerothermal environment. The simulation and design of one-dimensional heat insulationof antenna window assembly are carried out, and the theoretical thickness of heat insulation layer and the theoretical thickness of heat insulation port frame at the center of the aerodynamic outlinesurface of antenna window assembly are obtained. Combined with the process feasibility of the heat shield frame and the thickness of the heat shield layer, the thickness of the aerodynamic outline, the face position and the thickness of the heat shield layer of the antenna window assembly are determined. Replace the hollowout of the contact area between the heat shielding port frame and the peripheral heat shielding structure with four support columns. Using 3D modeling software, the 3D digital model of antenna window assembly is established. Temperature field simulation software is used to establish a three-dimensional temperature field simulation model, and the temperature distribution of antenna window assembly is obtained. Optimize the insulation thickness of the antenna window assembly until the temperature meets the antenna temperature requirements.

The invention discloses a real-time monitoring microwave dicke radiometer based on a reference load temperature and belongs to the field of microwave passive remote sensing. The radiometer comprises a dicke input switch, wherein a first end of the dicke input switch is sequentially connected with a radio frequency and intermediate frequency amplifying circuit, a square law detector, a low frequency amplifier, a synchronous detector, a low pass filter and a data collecting and processing module, a second end of the dicke input switch is switched between a reference load and an antenna under the driving of a switch signal generator, and a temperature measuring circuit is arranged on the reference load and connected with the data collecting and processing module. The reference load of the microwave dicke radiometer is not required to be kept in a constant temperature state, only the temperature measuring circuit is used for monitoring the temperature changes of the reference load in real time, the monitored variable quantity of the temperature of the reference load is plugged into a radiometer scaling equation for modification, and an antenna temperature of the measured scene is obtained. According to the real-time monitoring microwave dicke radiometer based on the reference load temperature, the measuring accuracy is improved and the structure of the existing microwave dicke radiometers is simplified.

The invention discloses a radio frequency front-end analog compensation circuit, which comprises a first amplifier (1), a second amplifier (2), an isolator (3), an antenna (4), a temperature sensor (5) and a differential arithmetic unit (6), and is characterized in that the temperature sensor (5) is arranged at the periphery of the second amplifier (2) and is used for acquiring temperature changein real time; a radio frequency signal passes through the first amplifier (1) and the second amplifier (2) and then is radiated out through the isolator (3) and the antenna (4). Along with the increase of the working time, the temperature of the amplifier module is increased due to the heat consumption generated by the second amplifier (2), the voltage value acquired by the temperature sensor (5)is changed, and the grid bias voltage of the second amplifier (2) is compensated through the change result obtained by differential operation of the variable quantity of the temperature sensor (5) through the differential arithmetic unit (6). The circuit can sense the temperature change of a heat source in real time, correspondingly adjusts circuit gain, is large in control range, and is high in real-time performance.

The invention discloses a gain-and-direction-orientated structure thermal deformation compensation method for a satellite-borne active phase control array antenna. The method comprises the steps of determining structural parameters, material attributes and electromagnetic parameters of the antenna; determining antenna environment thermal load; calculating antenna temperature field distribution under sunshine; determining T / R assembly thermal power consumption; calculating antenna temperature field distribution under the T / R assembly thermal power consumption; performing temperature field superposition and calculating the thermal deformation of the antenna structure; extracting position offset in the array element geometric center; calculating the additional error of the array element space phase; determining the amplitude and phase distribution of array element excitation current; calculating the electrical performance of the antenna; judging whether gain and direction are both satisfied simultaneously or not; and calculating the antenna ideal main beam directed unit vector, the adjusting amount of the array element space phase, and the phase current of the compensated array element excitation current. The compensation method provided by the invention is combined with a phase adjusting method, so that the electrical performance compensation to the deformed satellite-borne active phase control array antenna is realized; the problem of antenna electrical performance degradation caused by structural thermal deformation is solved; and the normal operation of the antenna can be ensured.

The invention provides a method for measuring an antenna temperature field under incomplete information, which is used for solving the problem of low measurement accuracy of the antenna temperature field in the prior art, and comprises the following steps of: (1) establishing an antenna model to be measured and a virtual model corresponding to the antenna model to be measured (2) obtaining a POD mode of the antenna model to be measured; (3) calculating a temperature field of the antenna to be measured; (4) obtaining target data Ht and source data Hs; (5) calculating target data Ht and imitation source data Hs'; (6) obtaining a training data equation H; (7) establishing a temperature field calculation pseudo-prediction model ptau; (8) calculating an antenna temperature field. According to the method, the influence of measurement errors on temperature field calculation is considered, and the calculation precision is improved.

The invention relates to a brightness temperature correction method based on microwave radiometer antenna temperature detection, and belongs to the technical field of microwave radiometer calibration.The working wave band of a microwave radiometer carried by a satellite in a calibration method is in a microwave wave band of 1-1000GHz, and the 3dB beam width of an antenna main beam is less than 0.25 degrees; the calibration method comprises the following steps of step 1, installing a temperature monitoring device on each of an antenna main reflection surface A, auxiliary reflection surfaces BCand a satellite body D; step 2, analyzing the radiation energy ratio of the antenna main reflection surface, the auxiliary reflection surfaces and the satellite body in respective observation ranges;and step 3, calculating the atmospheric brightness temperature TT received by a receiver. The method is high in precision, low in cost and convenient to popularize, and is suitable for being used asa satellite-borne large-caliber antenna microwave radiometer calibration method.

Temperature measurement systems (20) include a temperature sensor (22) and an electronic signal interrogator (24). The temperature sensor (22) has a transponder (26) equipped with an antenna (28), and a separate parasitic antenna (32) with a temperature-sensitive transducer (34, 68-74, 78a-84a), while the interrogator (24) has a transmitter (42) and antenna (40). The sensor (22) is designed to be placed in thermal contact with an object to be temperature-measured, with the interrogator (24) placed in proximity to the object. The systems (20) may be used with food servingware domes (88, 114), which can be preheated and placed over a food-bearing plate to maintain the temperature of the food.

The invention provides an active phased-array relay antenna temperature control device, and relates to the technical field of spacecraft thermal control. The device comprises an equipment group, an antenna waveguide, a heat pipe and a heat dissipation plate, the heat dissipation plate is installed on the reverse side of the antenna waveguide and forms an accommodating space, and the equipment group is installed on the reverse side of the antenna waveguide and is arranged in the accommodating space. An accommodating cavity is formed in the reverse side of the antenna waveguide, the heat pipe isinstalled in the accommodating cavity, and white paint is sprayed to the front side and the reverse side of the antenna waveguide. Through spraying the white paint on the front side of the active phased-array relay antenna waveguide, adding the heat dissipation plate on the nightside, arranging the heat pipe in the concave cavity and other measures, the on-orbit temperature control problem of theactive phased-array relay antenna is solved, the heat dissipation efficiency is greatly improved, the temperature control problem of the antenna is effectively solved, the temperature requirements under different external heat flow conditions can be met, the process is simple, implementation is easy, and the cost is low.

The invention discloses a method and device for measuring material radiance based on a millimeter wave. The method includes the steps that (10), high temperature material measurement is performed, specifically, the radiation characteristics and temperature of a black body material are measured by the millimeter wave; (20), low temperature material measurement is performed, specifically, the radiation characteristics and temperature of liquid nitrogen are measured by the millimeter wave; (30) target material measurement is performed, specifically, the radiation characteristics and temperature of a target material is measured by the millimeter wave; (40), antenna temperature calibration is performed, specifically, the temperature of the black body material and the temperature of the liquid nitrogen are used for calibrating the antenna temperature; and (50), radiation brightness temperature inversion is performed, specifically, the radiance of the target material is obtained by inversionbased on the antenna temperature. The device includes an antenna (1) with a wave band of 3mm / 8mm, a radio frequency low noise amplifier (2), a detector (3), a low frequency amplifier (4), a thermometer module (5), a calibration device (6) and a data processing module (7). According to the method and device for measuring the material radiance based on the millimeter wave, the system size is small,operation is simple and measurement is fast and accurate.

The invention provides a detection method for insulator contaminants in a power system. According to the invention, the radiation brightness temperature of insulator contaminants is measured through a microwave radiometer, and the radiation brightness temperature characteristic is taken as a main parameter for measuring the contamination grade. The method provided in the invention makes use of the microwave radiometer to measure a target, inverses the radiation brightness temperature of the measured target according to different antenna temperatures of the measured target, and then judges the contamination degree of the insulator.

The invention discloses a phased-array antenna electrical performance compensation method and system based on temperature field reconstruction, and belongs to the technical field of radar antennae, and the method comprises the steps: carrying out the temperature field transient simulation, actual measurement and temperature reconstruction of a phased-array antenna through an antenna temperature field measurement method under incomplete information; carrying out a temperature drift characteristic experiment on the phased-array antenna component to obtain a transmission parameter curve at a discrete temperature; adopting a vector fitting method to fit a frequency response function of transmission parameters changing along with frequency and temperature at each test temperature; introducing an extreme learning machine algorithm to establish a mathematical model among frequency, temperature, frequency response function poles and residues; and taking the measured frequency and temperature of the phased-array antenna as input variables, obtaining a pole and a residue of a frequency response function, determining the amplitude and the phase of excitation current, and carrying out electrical performance compensation. The method and system can be used for compensating the electrical performance of the phased-array antenna influenced by the temperature, so that the phased-array antenna reaches the optimal working state.

The invention discloses a satellite-borne phased-array antenna temperature deformation calibration system, a measurement system and a method. The calibration system comprises satellite-borne phased-array antenna frame bodies under different working conditions, multiple sensor assemblies, an optical measurement module and a main control module, wherein the multiple sensor assemblies are located on the satellite-borne phased-array antenna frame bodies, and each sensor assembly is used for collecting parameters of the position on the satellite-borne phased-array antenna frame body corresponding to the sensor assembly under different working conditions; the optical measurement module is used for measuring deformation displacement data of the satellite-borne phased-array antenna frame bodies under different working conditions; and the main control module is connected with each sensor assembly and the optical measurement module, and is used for obtaining a preset corresponding relation between the parameters and the deformation displacement data of the satellite-borne phased-array antenna frame body according to the parameters of each connecting part under different working conditions and the deformation displacement data of the satellite-borne phased-array antenna frame body, so that the temperature deformation of the satellite-borne phased-array antenna can be measured in real time.