CN113948846A - Satellite-borne phased array antenna temperature deformation calibration system, measurement system and method - Google Patents
Satellite-borne phased array antenna temperature deformation calibration system, measurement system and method Download PDFInfo
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- CN113948846A CN113948846A CN202111187065.8A CN202111187065A CN113948846A CN 113948846 A CN113948846 A CN 113948846A CN 202111187065 A CN202111187065 A CN 202111187065A CN 113948846 A CN113948846 A CN 113948846A
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/22—Supports; Mounting means by structural association with other equipment or articles
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/16—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
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Abstract
The invention discloses a satellite-borne phased array antenna temperature deformation calibration system, a measurement system and a method thereof, wherein the calibration system comprises: the satellite-borne phased array antenna frame body under different working conditions; the sensor assemblies are positioned on the satellite-borne phased array antenna frame body, and each sensor assembly is used for acquiring 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 body under different working conditions; the main control module is connected with each sensor component and the optical measurement module and used for acquiring preset corresponding relations between parameters and deformation displacement data of the satellite-borne phased array antenna frame body according to parameters of each connecting part under different working conditions and the deformation displacement data of the satellite-borne phased array antenna frame body so as to realize real-time measurement of temperature deformation of the satellite-borne phased array antenna.
Description
Technical Field
The embodiment of the invention relates to the technical field of satellite-borne antennas, in particular to a satellite-borne phased array antenna temperature deformation calibration system, a satellite-borne phased array antenna temperature deformation measurement system and a satellite-borne phased array antenna temperature deformation measurement method.
Background
In a space environment, due to the fact that solar radiation or device heating of a large-scale satellite-borne phased-array antenna generates uniform or non-uniform temperature change, an antenna structure frame can deform to a certain degree, and for an antenna with high precision requirement, structural deformation caused by temperature change can influence system detection or imaging. With the rapid development of aerospace technologies, the requirement on the antenna precision is higher and higher, the antenna size is larger and larger, and the system integration level is higher and higher, so that the heat flux density of the antenna is increased easily, and the structural deformation caused by solar radiation and device heating is more and more serious, so that the problem of system performance reduction is more and more prominent.
At present, most of satellite-borne antennas rely on design to ensure that the temperature deformation is smaller than a certain range so as to meet the needs of a system, and the improvement of structural rigidity or active and passive thermal control is usually adopted, however, the improvement of structural rigidity can bring about the increase of structural mass and increase of emission cost, and the active and passive thermal control can effectively relieve temperature variation and the uneven degree thereof at the input end, but cannot essentially solve the problem.
Disclosure of Invention
The invention provides a temperature deformation calibration system, a temperature deformation measurement system and a temperature deformation measurement method for a satellite-borne phased array antenna, which are used for measuring the temperature deformation of the satellite-borne phased array antenna in real time.
In order to achieve the above object, an embodiment of a first aspect of the present invention provides a system for calibrating temperature deformation of a satellite-borne phased array antenna, including:
the satellite-borne phased array antenna frame body under different working conditions;
the satellite-borne phased array antenna frame comprises a satellite-borne phased array antenna frame body, a plurality of sensor assemblies and a plurality of control modules, wherein the plurality of sensor assemblies are positioned on the satellite-borne phased array antenna frame body, each sensor assembly is used for acquiring parameters of positions on the satellite-borne phased array antenna frame body corresponding to the sensor assembly under different working conditions, and the parameters comprise strain data and temperature data;
the optical measurement module is used for measuring deformation displacement data of the satellite-borne phased array antenna frame body under different working conditions;
the main control module is respectively connected with each sensor assembly and the optical measurement module and used for acquiring preset corresponding relations between parameters and deformation displacement data of the satellite-borne phased array antenna frame body according to parameters of each connecting part and the deformation displacement data of the satellite-borne phased array antenna frame body under different working conditions.
According to one embodiment of the invention, the satellite-borne phased-array antenna frame body comprises a frame body and a plurality of supporting beams positioned in the frame body, wherein two ends of each supporting beam are respectively connected to the frame body to form a plurality of connecting parts; each sensor assembly is located at each connection portion;
the connecting portion are T type connecting portion, the sensor package includes: the strain sensor comprises a first strain sensor, a second strain sensor and a temperature sensor, wherein the first strain sensor is located on a cross beam of the T-shaped connecting portion, the second strain sensor is located on a vertical beam of the T-shaped connecting portion, and the temperature sensor is located at the connecting position of the cross beam of the T-shaped connecting portion and the vertical beam.
In order to achieve the above object, a second aspect of the present invention provides a calibration method for temperature distortion of a satellite-borne phased array antenna, which is implemented based on the aforementioned calibration system for temperature distortion of a satellite-borne phased array antenna, and the calibration method includes the following steps:
acquiring parameters of a plurality of positions on the satellite-borne phased array antenna frame body under different working conditions, wherein the parameters comprise strain data and temperature data;
acquiring deformation displacement data of the space-borne phased array antenna frame body;
according to the parameters of the positions on the satellite-borne phased array antenna frame body under different working conditions and the deformation displacement data of the satellite-borne phased array antenna frame body, acquiring a preset corresponding relation between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body.
According to an embodiment of the present invention, the obtaining of the preset corresponding relationship between the parameter and the deformation displacement data of the frame body of the space-borne phased array antenna includes:
acquiring a preset corresponding relation between the parameters and deformation displacement data of the satellite-borne phased array antenna frame body by adopting a machine learning method;
or, acquiring multiple preset corresponding relations between the parameters and deformation displacement data of the satellite-borne phased array antenna frame body by adopting a machine learning method, a simulation model correcting method and a mathematical integration method.
According to an embodiment of the invention, the obtaining of the plurality of preset corresponding relations between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body by adopting several methods of a machine learning method, a simulation model correcting method and a mathematical integration method comprises the following steps:
and taking the strain data as independent variables, the deformation displacement data as dependent variables and the temperature data as compensation data, and adopting several methods of a machine learning method, a simulation model correcting method and a mathematical integration method to obtain various preset corresponding relations between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body.
According to an embodiment of the invention, obtaining the preset corresponding relationship between the parameter and the deformation displacement data of the satellite-borne phased array antenna frame body by using a machine learning method comprises:
and taking the strain data and the temperature data as independent variables and the deformation displacement data as dependent variables, and acquiring a preset corresponding relation between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body by adopting a machine learning method.
In order to achieve the above object, a third embodiment of the present invention provides a system for measuring temperature deformation of a satellite-borne phased array antenna, including:
a satellite-borne phased array antenna frame body;
the sensor assemblies are positioned on the satellite-borne phased array antenna frame body and used for acquiring parameters of positions, corresponding to the sensor assemblies, on the satellite-borne phased array antenna frame body, and the parameters comprise strain data and temperature data;
and the data acquisition, analysis and storage module is connected with each sensor assembly and is used for measuring deformation and displacement data of the satellite-borne phased array antenna frame body according to parameters of each connecting part and a pre-stored preset corresponding relation, wherein the preset corresponding relation is the corresponding relation between the parameters and the deformation and displacement data of the satellite-borne phased array antenna frame body, and the preset corresponding relation is obtained by the satellite-borne phased array antenna temperature deformation calibration method.
According to one embodiment of the invention, the satellite-borne phased-array antenna frame body comprises a frame body and a plurality of supporting beams positioned in the frame body, wherein two ends of each supporting beam are respectively connected to the frame body to form a plurality of connecting parts; each sensor assembly is located at each connection portion;
the connecting portion are T type connecting portion, the sensor package includes: the strain sensor comprises a first strain sensor, a second strain sensor and a temperature sensor, wherein the first strain sensor is located on a cross beam of the T-shaped connecting portion, the second strain sensor is located on a vertical beam of the T-shaped connecting portion, and the temperature sensor is located at the connecting position of the cross beam of the T-shaped connecting portion and the vertical beam.
In order to achieve the above object, a fourth aspect of the present invention provides a method for measuring temperature deformation of a satellite-borne phased array antenna, which is implemented based on the system for measuring temperature deformation of a satellite-borne phased array antenna described above, and is characterized by comprising the following steps:
acquiring parameters of a plurality of positions on the space-borne phased array antenna frame body;
and measuring deformation displacement data of the satellite-borne phased array antenna frame body according to the parameters of the positions on the satellite-borne phased array antenna frame body and a pre-stored preset corresponding relation.
According to an embodiment of the present invention, the measuring deformation displacement data of the frame body of the space-borne phased array antenna according to the parameters of each of the connection portions and a preset corresponding relationship includes:
and when the pre-stored preset corresponding relations are various, the deformation displacement data of the satellite-borne phased array antenna frame body is a weighted average of the deformation displacement data measured by the various preset corresponding relations.
According to the temperature deformation calibration system, the temperature deformation measurement system and the temperature deformation measurement method of the satellite-borne phased array antenna, provided by the embodiment of the invention, the calibration system comprises: the satellite-borne phased array antenna frame body under different working conditions; the satellite-borne phased array antenna frame comprises a satellite-borne phased array antenna frame body, a plurality of sensor assemblies and a plurality of control modules, wherein the plurality of sensor assemblies are positioned on the satellite-borne phased array antenna frame body, each sensor assembly is used for acquiring parameters of positions on the satellite-borne phased array antenna frame body corresponding to the sensor assembly under different working conditions, and the parameters comprise strain data and temperature data; the optical measurement module is used for measuring deformation displacement data of the satellite-borne phased array antenna frame body under different working conditions; a main control module which is respectively connected with each sensor component and the optical measurement module and is used for acquiring a preset corresponding relation between parameters and 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, thereby, in the calibration process, an optical measurement module is used for actually measuring deformation displacement data of the satellite-borne phased array antenna frame body under different working conditions, a preset corresponding relation is finally obtained through the actually measured deformation displacement data, the actually measured strain data and the temperature data, finally, the deformation displacement data of the satellite-borne phased array antenna frame are measured through the preset corresponding relation, the actually measured strain data and the actually measured temperature data, and based on the preset corresponding relation, the deformation displacement data of the satellite-borne phased array antenna frame is measured, the preset corresponding relation obtained through actual measurement is closer to reality, so that the finally measured deformation displacement data of the satellite-borne phased array antenna frame is more accurate.
Drawings
FIG. 1 is a schematic structural diagram of a satellite-borne phased array antenna temperature deformation calibration system according to an embodiment of the invention;
FIG. 2 is a schematic diagram of a connection part in a satellite-borne phased array antenna temperature deformation calibration system according to an embodiment of the invention;
FIG. 3 is a flowchart of a method for calibrating temperature deformation of a satellite-borne phased array antenna according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a system for measuring temperature deformation of a satellite-borne phased array antenna according to an embodiment of the present invention;
fig. 5 is a flowchart of a method for measuring temperature deformation of a satellite-borne phased array antenna according to an embodiment of the present invention;
fig. 6 is a schematic diagram of a calibration measurement process of temperature deformation of a satellite-borne phased array antenna according to an embodiment of the invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.
For temperature deformation control of a large-scale satellite-borne phased-array antenna, currently, methods such as structural rigidity improvement or active and passive thermal control are mostly adopted for realizing the temperature deformation control, but the following problems exist:
the structural rigidity is improved, so that the structural mass is increased, and the emission cost is greatly increased; and is not realizable in design with some systems quality tightly controlled;
for structural temperature deformation, active and passive thermal control can effectively relieve temperature variation and the non-uniform degree thereof at the input end, but cannot essentially solve the problem; and at present, the thermal design already takes temperature deformation as one of the key control factors of the design, and the capacity is further improved at a very large cost, which is almost unacceptable.
At present, the following methods are mainly used for structural deformation in other engineering fields:
based on optical displacement direct measurement, the method is not suitable for a shielded scene, equipment is usually erected outside a measured structural part for measurement, and the method is not suitable for real-time temperature deformation measurement of a large satellite-borne phased array antenna;
the method has certain difficulty in algorithm, acceleration-speed-displacement integration generates large errors in a long time, timing calibration is needed, and the method is not feasible for low-frequency, quasi-static and static deformation measurement.
Therefore, the embodiment of the invention provides a satellite-borne phased array antenna temperature deformation calibration system, a measurement system and a method thereof, and aims to solve the problems.
Fig. 1 is a schematic structural diagram of a satellite-borne phased array antenna temperature deformation calibration system according to an embodiment of the present invention.
As shown in fig. 1, the system for calibrating temperature deformation of the satellite-borne phased array antenna comprises:
the satellite-borne phased array antenna frame body 1 under different working conditions;
the sensor assemblies 4 are positioned on the satellite-borne phased array antenna frame body, each sensor assembly 4 is used for acquiring parameters of the position, corresponding to the sensor assembly, on the satellite-borne phased array antenna frame body under different working conditions, and the parameters comprise strain data and temperature data;
the optical measurement module 5 is used for measuring deformation displacement data of the satellite-borne phased array antenna frame body 1 under different working conditions;
the main control module 6 is connected with each sensor component 4 and the optical measurement module 5 respectively, and is used for acquiring preset corresponding relations between parameters and deformation displacement data of the satellite-borne phased array antenna frame body 1 according to the parameters of each connecting part 3 under different working conditions and the deformation displacement data of the satellite-borne phased array antenna frame body 1.
It should be noted that the frame body 1 of the satellite-borne phased array antenna under different working conditions means that the satellite-borne phased array antenna is under different thermal conditions in a mode of a warm box or a heating plate, and under different thermal conditions, the satellite-borne phased array antenna has different deformation responses. The arrangement position of each sensor component 4 can be located at any position of the satellite-borne phased-array antenna frame body 1, and the installation position of each sensor component 4 under different working conditions is guaranteed to be the same.
For example, there are N different thermal conditions, so that in each thermal condition, each sensor element 4 located in the space-borne phased array antenna frame body 1 will measure a set of parameters, and the optical measurement module 5 will also measure a set of deformation displacement data, so that there are N different thermal conditions, and further, N sets of parameters and N sets of deformation displacement data will be finally obtained, and the main control module 6 can obtain the corresponding relationship between the N sets of parameters and the N sets of deformation displacement data by using a relevant mathematical method according to the finally obtained N sets of parameters and N sets of deformation displacement data. For example, the parameters include strain data x1 and temperature data x2, and the strain displacement data is y, so that the function relationship obtained by the main control module 6 is y ═ f (x1, x2), and a preset corresponding relationship f is finally obtained through N sets of parameters and N sets of strain displacement data.
It is understood that the optical measurement module 5 may be a laser or a grating ruler, etc. that can perform deformation displacement measurement. The positions of the sensor components 4 can be the same as or different from the positions, measured by the optical measurement module 5, of the satellite-borne phased array antenna frame body 1, and the optical measurement module 5 can also directly measure deformation displacement data of the positions, where the sensor components 4 are arranged, of the satellite-borne phased array antenna frame body 1 and can also measure deformation displacement data of other points except the positions, where the sensor components 4 are arranged, of the satellite-borne phased array antenna frame body 1. The present invention is not particularly limited in this regard.
The number of the points where the sensor assemblies 4 are arranged may be the same as or different from the number of the position points on the satellite-borne phased array antenna frame body 1 measured by the optical measurement module 5, that is, the number of the points where the sensor assemblies 4 are arranged is, for example, m, and the number of the position points on the satellite-borne phased array antenna frame body 1 measured by the optical measurement module 5 may be m or not, which is not limited in this respect. Finally, the main control module 6 only needs to acquire the preset corresponding relation f by acquiring the N groups of parameters and the N groups of deformation displacement data through a relevant mathematical method. It can be understood that the more the number of the points at which the sensor assembly 4 is arranged, the more the optical measurement module 5 measures the more the position points, and the more the finally obtained preset correspondence f reflects the deformation of the satellite-borne phased array antenna frame body 1. The number of actual process sensor assemblies 4 depends on the material cost, and the data of the position points measured by the optical measuring module 5 depends on the time cost.
The preset corresponding relation f can be obtained by a machine learning method, a simulation model correction method and a mathematical integration method in the following ways. When the preset corresponding relation f is obtained by using a machine learning method, the strain data and the temperature data can be used as independent variables, the deformation displacement data can be used as dependent variables, a function is constructed, and the preset corresponding relation f is obtained through training. The machine learning method can be KNN, a support vector machine, a neural network method and the like. When the preset corresponding relation f is obtained by using a machine learning method, temperature data can be used as compensation data to compensate strain data, finally, the compensated strain data is used as an independent variable, deformation displacement data is used as a dependent variable to construct a function, and the preset corresponding relation f is obtained through training.
When the correction simulation model method and the mathematical integral method are used for obtaining, the temperature data can be used as compensation data to compensate strain data, finally, the compensated strain data is used as an independent variable, the deformation displacement data is used as a dependent variable, a function is constructed, and the preset corresponding relation f is obtained through training.
It can be understood that after the temperature data is compensated for the strain data, or the temperature data and the strain data are both directly used as independent variables to obtain the corresponding relation, so that the temperature drift problem of the strain sensor is solved, and the final corresponding relation f is more accurate.
According to an embodiment of the invention, as shown in fig. 1 and fig. 2, the satellite-borne phased array antenna frame body 1 includes a frame body, and a plurality of support beams 2 located in the frame body, wherein two ends of each support beam 2 are respectively connected to the frame body to form a plurality of connecting portions 3; each of the sensor assemblies 4 is located at each of the connection portions 3;
connecting portion 3 is T type connecting portion, and sensor assembly 4 includes: the strain sensor comprises a first strain sensor 41, a second strain sensor 42 and a temperature sensor 43, wherein the first strain sensor 41 is positioned on a cross beam of the T-shaped connecting part, the second strain sensor 42 is positioned on a vertical beam of the T-shaped connecting part, and the temperature sensor 43 is positioned at the connecting position of the cross beam and the vertical beam of the T-shaped connecting part.
Through the above setting mode, the first strain sensor 41 can detect strain data on the beam of the satellite-borne phased array antenna frame body 1, the second strain sensor 42 can detect strain data on the vertical beam of the satellite-borne phased array antenna frame body 1, and the temperature sensor 43 can detect temperature data at the connecting part 3. Therefore, sensors are arranged at positions, which are easy to deform, of the satellite-borne phased array antenna frame body 1, and strain data and temperature data which can reflect deformation of the satellite-borne phased array antenna frame body 1 most are obtained. In other embodiments, the sensor assembly 4 may be disposed between two connecting portions 3, and the present invention is not particularly limited thereto. That is to say, in this embodiment, the sensor assemblies 4 are all arranged at the positions of the connection portions 3 on the satellite-borne phased array antenna frame body 1, so that after the satellite-borne phased array antenna frame body 1 is heated, the strain at the connection portions 3 is large, the sensor assemblies 4 can easily acquire strain data, and the positions of the connection portions 3 should be changed to reflect a change of the satellite-borne phased array antenna frame body 1.
Fig. 3 is a flowchart of a method for calibrating temperature deformation of a satellite-borne phased array antenna according to an embodiment of the present invention. As shown in fig. 3, the calibration method is implemented based on the above satellite-borne phased array antenna temperature deformation calibration system, and includes the following steps:
s101, obtaining parameters of a plurality of positions on the satellite-borne phased array antenna frame body under different working conditions, wherein the parameters comprise strain data and temperature data;
s102, acquiring deformation displacement data of the satellite-borne phased array antenna frame body;
s103, acquiring preset corresponding relations between parameters and deformation displacement data of the satellite-borne phased array antenna frame body according to the parameters of the positions on the satellite-borne phased array antenna frame body under different working conditions and the deformation displacement data of the satellite-borne phased array antenna frame body.
It should be noted that the frame body 1 of the satellite-borne phased array antenna under different working conditions means that the satellite-borne phased array antenna is under different thermal conditions in a mode of a warm box or a heating plate, and under different thermal conditions, the satellite-borne phased array antenna has different deformation responses. The arrangement position of each sensor component 4 can be located at any position of the satellite-borne phased-array antenna frame body 1, and the installation position of each sensor component 4 under different working conditions is guaranteed to be the same.
For example, there are N different thermal conditions, so that in each thermal condition, each sensor element 4 located in the space-borne phased array antenna frame body 1 will measure a set of parameters, and the optical measurement module 5 will also measure a set of deformation displacement data, so that there are N different thermal conditions, and further, N sets of parameters and N sets of deformation displacement data will be finally obtained, and the main control module 6 can obtain the corresponding relationship between the N sets of parameters and the N sets of deformation displacement data by using a relevant mathematical method according to the finally obtained N sets of parameters and N sets of deformation displacement data. For example, the parameters include strain data x1 and temperature data x2, and the strain displacement data is y, so that the function relationship obtained by the main control module 6 is y ═ f (x1, x2), and a preset corresponding relationship f is finally obtained through N sets of parameters and N sets of strain displacement data.
Wherein the number of the deformation displacement data in each group is the same. The number of the strain data and the temperature data in each group of parameters is the same. However, the number of the deformation displacement data in each set may be the same as or different from the number of the strain data and the temperature data in each set, and the present invention is not particularly limited thereto.
According to an embodiment of the invention, obtaining the preset corresponding relationship between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body comprises:
acquiring a preset corresponding relation between parameters and deformation displacement data of a satellite-borne phased array antenna frame body by adopting a machine learning method;
or, acquiring multiple preset corresponding relations between the parameters and deformation displacement data of the satellite-borne phased array antenna frame body by adopting a machine learning method, a simulation model correcting method and a mathematical integration method.
According to an embodiment of the invention, the obtaining of the plurality of preset corresponding relations between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body by adopting several methods of a machine learning method, a simulation model correcting method and a mathematical integration method comprises the following steps:
and taking the strain data as independent variables, the deformation displacement data as dependent variables and the temperature data as compensation data, and adopting several methods of a machine learning method, a simulation model correcting method and a mathematical integration method to obtain various preset corresponding relations between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body.
When the preset corresponding relation f is obtained by using a machine learning method, a simulation model correcting method and a mathematical integration method, temperature data can be used as compensation data to compensate strain data, finally, the compensated strain data is used as an independent variable, deformation displacement data is used as a dependent variable to construct a function, and the preset corresponding relation f is obtained through training. After the temperature data is compensated for the strain data, the temperature drift problem of the strain sensor is solved, and the final corresponding relation f is more accurate.
Each method can obtain a preset corresponding relationship, and in an actual use situation, the obtained deformation displacement data can be weighted and averaged by using the preset corresponding relationship obtained by one method or using multiple preset corresponding relationships.
According to one embodiment of the invention, the step of obtaining the preset corresponding relation between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body by adopting a machine learning method comprises the following steps:
and taking the strain data and the temperature data as independent variables and the deformation displacement data as dependent variables, and acquiring a preset corresponding relation between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body by adopting a machine learning method.
When the preset corresponding relation f is obtained by using a machine learning method, the strain data and the temperature data can be used as independent variables, the deformation displacement data can be used as dependent variables, a function is constructed, and the preset corresponding relation f is obtained through training. The machine learning method can be KNN, a support vector machine, a neural network method and the like.
It can be understood that the temperature data and the strain data are both directly used as independent variables to obtain the corresponding relation, so that the temperature drift problem of the strain sensor is solved, and the final corresponding relation f is more accurate.
Fig. 4 is a schematic structural diagram of a system for measuring temperature deformation of a satellite-borne phased array antenna according to an embodiment of the present invention. As shown in fig. 4, the measuring system includes:
a satellite-borne phased-array antenna frame body 11;
the sensor assemblies 14 are located on the satellite-borne phased array antenna frame body 11, each sensor assembly 14 is used for acquiring parameters of a position on the satellite-borne phased array antenna frame body corresponding to the sensor assembly, and the parameters comprise strain data and temperature data;
the data acquisition, analysis and storage module 61 is connected to each sensor component 14, and is configured to measure deformation displacement data of the satellite-borne phased array antenna frame body 11 according to a parameter of each connection portion 31 and a preset corresponding relationship, where the preset corresponding relationship is a corresponding relationship between the parameter and the deformation displacement data of the satellite-borne phased array antenna frame body 11, and the preset corresponding relationship is obtained by a previous calibration method for temperature deformation of a satellite-borne phased array antenna.
According to an embodiment of the invention, the satellite-borne phased-array antenna frame body 11 comprises a frame body and a plurality of supporting beams 21 positioned in the frame body, wherein two ends of each supporting beam 21 are respectively connected to the frame body to form a plurality of connecting parts 31; each of the sensor assemblies 14 is located at each of the connections 31;
the connection portion 31 is a T-shaped connection portion, and the sensor unit 14 includes: the strain sensor comprises a first strain sensor, a second strain sensor and a temperature sensor, wherein the first strain sensor is located on a cross beam of the T-shaped connecting portion, the second strain sensor is located on a vertical beam of the T-shaped connecting portion, and the temperature sensor is located at the connecting position of the cross beam of the T-shaped connecting portion and the vertical beam.
It should be noted that the preset corresponding relationship is obtained by the calibration method of the foregoing embodiment, and during actual measurement, only the sensor component 14 needs to be installed on the satellite-borne phased array antenna frame body 11, the position where the sensor component 14 is installed needs to be consistent with the position where the sensor component 4 is installed in the calibration system, and the installation number also needs to be consistent. Therefore, when the satellite-borne phased array antenna frame body 11 operates in orbit, the data acquisition, analysis and storage module 61 can measure the deformation displacement data of the satellite-borne phased array antenna frame body 11 according to the parameters of each connecting part 31 and the pre-stored preset corresponding relation. The deformation displacement data of the satellite-borne phased array antenna frame body 11 under various working conditions are actually measured by the optical measurement module used in the calibration method, and then after various parameters of the satellite-borne phased array antenna frame body 11 during in-orbit operation are actually measured, the deformation displacement data can be obtained through the preset corresponding relation f. Therefore, the satellite upper computer 71 adjusts the electrical compensation data of the satellite antenna according to the deformation displacement data, and guarantees system performance.
The data acquisition, analysis and storage module 61 has functions of data acquisition, AD conversion, data processing, data analysis, data storage, database, algorithm implementation, data interaction, and the like.
Fig. 5 is a flowchart of a method for measuring temperature deformation of a satellite-borne phased array antenna according to an embodiment of the present invention. The measurement method is realized based on the former satellite-borne phased array antenna temperature deformation measurement system, and as shown in fig. 5, the measurement method comprises the following steps:
s201, acquiring parameters of a plurality of positions on the satellite-borne phased array antenna frame body;
s202, measuring deformation displacement data of the satellite-borne phased array antenna frame body according to the parameters of the positions on the satellite-borne phased array antenna frame body and a preset corresponding relation which is prestored.
According to an embodiment of the present invention, measuring deformation displacement data of a satellite-borne phased array antenna frame body according to parameters of a plurality of positions on the satellite-borne phased array antenna frame body and a preset corresponding relationship includes:
and when the pre-stored preset corresponding relations are multiple, the deformation displacement data of the satellite-borne phased array antenna frame body is a weighted average of the deformation displacement data measured by the multiple preset corresponding relations.
It should be noted that when only one preset corresponding relationship is prestored in the data acquisition, analysis and storage module 61, the deformation displacement data of the satellite-borne phased array antenna frame body can be obtained only through the corresponding relationship; and when the pre-stored preset corresponding relations are multiple, the deformation displacement data of the satellite-borne phased array antenna frame body is a weighted average value of the deformation displacement data measured by the multiple preset corresponding relations. The weight distribution can be distributed according to the precision of each preset corresponding relation, the preset corresponding relation with high precision distributes the balance weight, and the preset corresponding relation with low precision distributes the balance weight lightly.
Fig. 6 is a schematic diagram of a calibration measurement process of temperature deformation of a satellite-borne phased array antenna according to an embodiment of the invention.
When the ground data acquisition calibration is carried out, data of a strain sensor, data of a temperature sensor and optical measurement data are input, data storage is output (namely, the strain data, the temperature data and deformation displacement data are stored), then, the strain data, the temperature data and the deformation displacement data are input in a ground analysis part, an algorithm (namely, a preset corresponding relation) is output by combining a calculation method, data of the strain sensor and data of the temperature sensor are input and stored in an in-orbit operation part, deformation calculation (deformation displacement data) is obtained by combining the stored strain data and temperature data according to the algorithm, and finally, the deformation calculation (deformation displacement data) is uploaded to a satellite upper computer, the satellite upper computer stores the deformation displacement data and adjusts electrical compensation data of a satellite antenna according to the deformation displacement data.
Compared with the traditional method of limiting the temperature deformation of the antenna structure by improving the structural rigidity or actively and passively controlling heat and the like, the method has the following main advantages and effects:
the method gets rid of the limitation of simply limiting temperature deformation, adopts the thought of measurement-feedback-compensation, has strong designability, and can solve the difficult problems which can not be realized in the current design;
the structural mass is increased by improving the structural rigidity through the traditional design, and the method only needs to add one set of measuring system no matter the scale of the antenna, the mass of the sensor per se can be relatively ignored, and the advantages are more obvious for the antenna with larger scale;
the current active and passive thermal control temperature limitation reaches a certain bottleneck, the capability of the antenna is almost impossible to be further improved, temperature change and temperature unevenness to a certain degree are inevitable, and the method can release the pressure of antenna thermal design to a certain degree on the premise that the thermal control ensures that a device does not fail;
the method is based on strain measurement and combines optical measurement in a calibration stage: compared with direct measurement based on optical displacement, the method effectively avoids the problem of shielding; the method can directly carry out contact measurement on the sensor on the antenna frame, and has high reliability; compared with measurement based on an acceleration sensor, the method avoids the problems of error generated by acceleration-speed-displacement integration, timing calibration and the like, and can perform low-frequency, quasi-static and static structural deformation measurement; compared with the method based on strain measurement, the method combines the calibration data of optical measurement, and the algorithm has strong designability.
The method can mix various algorithms, finally calculates the structural deformation in a weighted average mode, has the characteristic of strong robustness, and can add the measured data to the database in the in-orbit running process, so that the algorithm model can self-learn, and the performance is continuously improved.
In summary, according to the calibration system, the measurement system and the method for temperature deformation of the space-borne phased array antenna provided by the embodiment of the invention, the calibration system includes: the satellite-borne phased array antenna frame body under different working conditions; the satellite-borne phased array antenna frame comprises a satellite-borne phased array antenna frame body, a plurality of sensor assemblies and a plurality of control modules, wherein the plurality of sensor assemblies are positioned on the satellite-borne phased array antenna frame body, each sensor assembly is used for acquiring parameters of positions on the satellite-borne phased array antenna frame body corresponding to the sensor assembly under different working conditions, and the parameters comprise strain data and temperature data; the optical measurement module is used for measuring deformation displacement data of the satellite-borne phased array antenna frame body under different working conditions; a main control module which is respectively connected with each sensor component and the optical measurement module and is used for acquiring a preset corresponding relation between parameters and 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, thereby, in the calibration process, an optical measurement module is used for actually measuring deformation displacement data of the satellite-borne phased array antenna frame body under different working conditions, a preset corresponding relation is finally obtained through the actually measured deformation displacement data, the actually measured strain data and the temperature data, finally, the deformation displacement data of the satellite-borne phased array antenna frame are measured through the preset corresponding relation, the actually measured strain data and the actually measured temperature data, and based on the preset corresponding relation, the deformation displacement data of the satellite-borne phased array antenna frame is measured, the preset corresponding relation obtained through actual measurement is closer to reality, so that the finally measured deformation displacement data of the satellite-borne phased array antenna frame is more accurate.
It is to be noted that the foregoing is only illustrative of the preferred embodiments of the present invention and the technical principles employed. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.
Claims (10)
1. The utility model provides a satellite-borne phased array antenna temperature deformation calibration system which characterized in that includes:
the satellite-borne phased array antenna frame body under different working conditions;
the satellite-borne phased array antenna frame comprises a satellite-borne phased array antenna frame body, a plurality of sensor assemblies and a plurality of control modules, wherein the plurality of sensor assemblies are positioned on the satellite-borne phased array antenna frame body, each sensor assembly is used for acquiring parameters of positions on the satellite-borne phased array antenna frame body corresponding to the sensor assembly under different working conditions, and the parameters comprise strain data and temperature data;
the optical measurement module is used for measuring deformation displacement data of the satellite-borne phased array antenna frame body under different working conditions;
the main control module is respectively connected with each sensor assembly and the optical measurement module and used for acquiring preset corresponding relations between parameters and deformation displacement data of the satellite-borne phased array antenna frame body according to parameters of each connecting part and the deformation displacement data of the satellite-borne phased array antenna frame body under different working conditions.
2. The system for calibrating temperature deformation of the satellite-borne phased array antenna according to claim 1, wherein the satellite-borne phased array antenna frame body comprises a frame body and a plurality of supporting beams positioned in the frame body, and two ends of each supporting beam are respectively connected to the frame body to form a plurality of connecting parts; each sensor assembly is located at each connection portion;
the connecting portion are T type connecting portion, the sensor package includes: the strain sensor comprises a first strain sensor, a second strain sensor and a temperature sensor, wherein the first strain sensor is located on a cross beam of the T-shaped connecting portion, the second strain sensor is located on a vertical beam of the T-shaped connecting portion, and the temperature sensor is located at the connecting position of the cross beam of the T-shaped connecting portion and the vertical beam.
3. A temperature deformation calibration method for a satellite-borne phased array antenna is realized based on the temperature deformation calibration system for the satellite-borne phased array antenna as claimed in claim 1 or 2, and comprises the following steps:
acquiring parameters of a plurality of positions on the satellite-borne phased array antenna frame body under different working conditions, wherein the parameters comprise strain data and temperature data;
acquiring deformation displacement data of the space-borne phased array antenna frame body;
according to the parameters of the positions on the satellite-borne phased array antenna frame body under different working conditions and the deformation displacement data of the satellite-borne phased array antenna frame body, acquiring a preset corresponding relation between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body.
4. The method for calibrating temperature deformation of the spaceborne phased array antenna according to claim 3, wherein the step of obtaining the preset corresponding relation between the parameters and deformation displacement data of the spaceborne phased array antenna frame body comprises the following steps:
acquiring a preset corresponding relation between the parameters and deformation displacement data of the satellite-borne phased array antenna frame body by adopting a machine learning method;
or, acquiring multiple preset corresponding relations between the parameters and deformation displacement data of the satellite-borne phased array antenna frame body by adopting a machine learning method, a simulation model correcting method and a mathematical integration method.
5. The method for calibrating temperature deformation of the spaceborne phased array antenna according to claim 4,
the method for acquiring the multiple preset corresponding relations between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body comprises the following steps of:
and taking the strain data as independent variables, the deformation displacement data as dependent variables and the temperature data as compensation data, and adopting several methods of a machine learning method, a simulation model correcting method and a mathematical integration method to obtain various preset corresponding relations between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body.
6. The method for calibrating temperature deformation of the spaceborne phased array antenna according to claim 4, wherein the step of obtaining the preset corresponding relation between the parameters and the deformation displacement data of the spaceborne phased array antenna frame body by adopting a machine learning method comprises the following steps:
and taking the strain data and the temperature data as independent variables and the deformation displacement data as dependent variables, and acquiring a preset corresponding relation between the parameters and the deformation displacement data of the satellite-borne phased array antenna frame body by adopting a machine learning method.
7. A system for measuring temperature deformation of a satellite-borne phased array antenna is characterized by comprising:
a satellite-borne phased-array antenna frame body,
the sensor assemblies are positioned on the satellite-borne phased array antenna frame body and used for acquiring parameters of positions, corresponding to the sensor assemblies, on the satellite-borne phased array antenna frame body, and the parameters comprise strain data and temperature data;
the data acquisition, analysis and storage module is connected with each sensor assembly and used for measuring deformation and displacement data of the satellite-borne phased array antenna frame body according to parameters of each connecting part and a preset corresponding relation, wherein the preset corresponding relation is the corresponding relation between the parameters and the deformation and displacement data of the satellite-borne phased array antenna frame body, and the preset corresponding relation is obtained by the satellite-borne phased array antenna temperature deformation calibration method according to any one of claims 3 to 6.
8. The system for measuring temperature deformation of the satellite-borne phased array antenna according to claim 7, wherein the satellite-borne phased array antenna frame body comprises a frame body and a plurality of supporting beams positioned in the frame body, and two ends of each supporting beam are respectively connected to the frame body to form a plurality of connecting parts; each sensor assembly is located at each connection portion;
the connecting portion are T type connecting portion, the sensor package includes: the strain sensor comprises a first strain sensor, a second strain sensor and a temperature sensor, wherein the first strain sensor is located on a cross beam of the T-shaped connecting portion, the second strain sensor is located on a vertical beam of the T-shaped connecting portion, and the temperature sensor is located at the connecting position of the cross beam of the T-shaped connecting portion and the vertical beam.
9. A temperature deformation measurement method of a satellite-borne phased array antenna is realized based on the temperature deformation measurement system of the satellite-borne phased array antenna according to claim 7 or 8, and is characterized by comprising the following steps:
acquiring parameters of a plurality of positions on the space-borne phased array antenna frame body;
and measuring deformation displacement data of the satellite-borne phased array antenna frame body according to the parameters of the positions on the satellite-borne phased array antenna frame body and a pre-stored preset corresponding relation.
10. The method for measuring the temperature deformation of the spaceborne phased array antenna according to claim 9, wherein the step of measuring the deformation displacement data of the spaceborne phased array antenna frame body according to the parameters of the plurality of positions on the spaceborne phased array antenna frame body and the preset corresponding relation which is prestored comprises the following steps:
and when the pre-stored preset corresponding relations are various, the deformation displacement data of the satellite-borne phased array antenna frame body is a weighted average of the deformation displacement data measured by the various preset corresponding relations.
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