CN117969976A - Unmanned aerial vehicle-based short wave antenna gain measurement method - Google Patents
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Abstract
The invention relates to a short wave antenna gain measurement method based on an unmanned aerial vehicle. The method comprises the following steps: integrating the calibrated orthogonal three-ring omnidirectional probe and the spectrometer on an unmanned plane platform to serve as a receiving end, and taking a ground short wave antenna to be measured as a transmitting end; planning a flight path by taking longitude and latitude of a center point of a short wave antenna to be detected as a reference point, carrying out flight measurement by an unmanned aerial vehicle according to the planned flight path, transmitting acquired data to a ground processing module in real time, drawing an antenna pattern, and calculating antenna gain. The invention adopts the calibrated miniaturized orthogonal three-ring omnidirectional probe as the receiving antenna, has wider frequency response and dynamic range, and is matched with a frequency spectrograph to measure the field intensity of a short wave antenna to be measured, thereby calculating the antenna gain and replacing the traditional measuring method of the auxiliary antenna compared with a standard antenna. The technology can be applied to measurement, design and verification of the short wave antenna.
Description
Technical Field
The invention belongs to the technical field of antenna measurement, and relates to a short wave antenna gain measurement method based on an unmanned aerial vehicle, which can be used for obtaining a directional diagram and gain of a short wave antenna.
Background
Because of the huge volume, the short wave antenna has a long far-field distance, the performance of the short wave antenna is greatly influenced by the actual erection environment, and the conventional antenna measuring method cannot effectively measure the pattern and the gain of the short wave antenna at the same time. Through the literature, the test of the short wave antenna is conventionally performed in two steps. The first step is to test the aircraft to obtain the directional diagram of the antenna to be tested, the second step is to lift off the short wave standard antenna to test, and the gain of the antenna to be tested is calculated by comparing the two test results. Because the short-wave standard antenna is large in size, the method is time-consuming and labor-consuming, the consistency is difficult to ensure, and the method is applied to a small number of practical applications.
CN112799027a, "a method and system for calibrating an external field antenna of an unmanned aerial vehicle", provides a method for calibrating horizontal and vertical lobes of a radar antenna by using an unmanned aerial vehicle, but does not provide a measuring method of a directional diagram, and especially cannot provide the gain of the antenna. CN215116531U, an outfield antenna test system, proposes a test system for measuring antenna performance using an unmanned plane platform, the system uses an auxiliary antenna installed on the unmanned plane as a transmitting end, and a ground antenna to be tested as a receiving end. Since the short wave band auxiliary transmitting antenna is difficult to miniaturize, the system cannot be applied to the short wave band antenna measurement, and the patent does not mention a specific measurement method of gain.
Furthermore, the international standard IEEE Std 149-2021 gives a test method for the pattern and gain of short wave antennas using aircraft. According to the method, a dipole antenna fixed on a rotary cradle head is used as an auxiliary antenna, the auxiliary dipole antenna is adjusted through a control cradle head, so that the maximum radiation direction of the auxiliary dipole antenna always points to an antenna to be measured, and the gain is calculated by adopting a standard dipole contrast method. The method is complex and low in reliability, multiple standard dipole antennas covering different frequency bands are required to be manufactured in actual measurement, and the multiple standard dipole antennas are required to be lifted up to a certain height repeatedly for multiple calibration, so that the method is difficult to operate and inconvenient to use in practice.
Disclosure of Invention
The invention aims to provide a convenient, quick and low-cost measurement method for the gain of a short wave antenna based on an unmanned aerial vehicle, which aims to solve the defects in the prior art.
The invention provides a short wave antenna gain measurement method based on an unmanned aerial vehicle, which comprises the following steps:
s1, integrating the calibrated orthogonal three-ring omnidirectional probe and a spectrometer on an unmanned plane platform to serve as a receiving end, and taking a ground short wave antenna to be measured as a transmitting end;
s2, connecting a real-time differential global positioning system (GPS-RTK) with a ground station measurement system;
S3, planning a flight path of unmanned aerial vehicle flight measurement by taking longitude and latitude of a center point of the short wave antenna to be detected as a reference point;
s4, the unmanned aerial vehicle carries out flight measurement according to the planned flight path, the collected data are transmitted to a ground processing module in real time, an antenna pattern is drawn, and the antenna gain is calculated;
the probe in the S1 is composed of three groups of mutually orthogonal electric small loop antennas after calibration, the loop antennas adopt balanced feed, a filter and a multistage amplifier are added at the rear end, and multi-polarization and omnibearing signal receiving is realized through quick switching of a switch.
And connecting a real-time differential global positioning system (GPS-RTK) with a ground station measurement system to check the working state of each instrument.
Further, according to the measurement task, measurement equipment such as an omnidirectional probe with a corresponding frequency band is mounted for the unmanned aerial vehicle.
Further, a high-precision positioning receiver is used for collecting the accurate longitude and latitude of the center point of the short wave antenna to be detected, two points A1 and A2 on a straight line passing through the center point are selected, the two points are equidistant from the center point, and the actual longitude and latitude of the center point are calculated through the collected longitude and latitude of the two points.
Center longitude= (a1longitude+a2longitude)/2,
Center latitude= (a1 latitude+a2 latitude)/2.
Further, generating a vertical plane measurement flight path of the unmanned aerial vehicle according to the azimuth angle of the short wave antenna beam to be detected; and generating a flight path measured by the horizontal plane of the unmanned aerial vehicle according to the pitch angle of the antenna beam to be measured, and uploading the flight path to a flight control system of the unmanned aerial vehicle.
Further, the debug antenna factor is matched to the antenna.
Further, the unmanned aerial vehicle performs point-by-point flight measurement and data acquisition according to a planned track in a full-automatic measurement state, and the ground system draws an antenna pattern to be measured in real time.
Further, the distance R (m) between the short wave antenna to be measured and the antenna at the receiving end of the unmanned aerial vehicle and the input power of the ground transmitting antenna are measured(w)。
Further, as known from the basic principle of the antenna, the power density S of the antenna on a sphere with a radius R is
S=G/4πR² （1）
In the above formula, G is the antenna gain. In addition, the relation between the power density of the antenna on the sphere with the radius R and the received electric field strength E can be expressed as
S=E²/η0 （2）
Where η 0 is the spatial wave impedance. Combining the above formulas (1) and (2), the antenna gain G can be obtained as:
G= （3）
input power of the above-mentioned middle antenna Transmit power for signal source/>(W) and insertion loss/>(W) difference, i.e=/>-/>E is the intensity (V/m) of the received electric field in the maximum radiation direction of the antenna to be tested, and the field intensity E is synthesized by three electric field components received by the tricyclic orthogonal antenna.
Compared with the prior art, the invention has the following beneficial effects:
The invention adopts the calibrated miniaturized orthogonal three-ring omnidirectional probe as the receiving antenna, has wider frequency response and dynamic range, is matched with a frequency spectrograph to measure the electric field intensity of the short wave antenna to be measured, directly calculates the antenna gain, and replaces the traditional measuring method for comparing the antenna to be measured with a standard antenna to obtain the antenna gain. The technology can be applied to measurement, design and verification of the short wave antenna.
Drawings
Fig. 1 is a schematic structural diagram of a short wave antenna gain measurement system based on an unmanned aerial vehicle;
Fig. 2 is a physical diagram of an orthogonal tricyclic omni-directional probe in accordance with the present invention;
FIG. 3 is a flow chart of a method for measuring the gain of a short wave antenna based on an unmanned aerial vehicle;
FIG. 4 is a schematic illustration of a vertical plane measurement flight of a drone of the present invention;
fig. 5 is a schematic representation of a unmanned plane level measurement flight of the present invention.
Detailed Description
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The application will be described in detail below with reference to the drawings in connection with embodiments.
The invention will be described in further detail with reference to the accompanying drawings and specific examples.
The method comprises the specific contents that an orthogonal tricyclic omnidirectional standard receiving antenna after calibration and an FSH4 spectrometer are integrated on an unmanned aerial vehicle platform, a ground flight control software programs flight tracks of the unmanned aerial vehicle on a vertical plane and a horizontal plane by taking the longitude and latitude of a short wave antenna center point of an antenna to be tested as a reference point, the unmanned aerial vehicle flies to the test points to hover, data are collected and returned to a ground control system in real time, and a ground processing module draws an antenna pattern and directly calculates antenna gain.
The method is characterized in that an orthogonal three-ring omnidirectional probe after calibration is used as an auxiliary receiving antenna, the probe consists of three groups of mutually orthogonal small electric ring antennas after calibration, the ring antennas adopt balanced feed, a filter and a multistage amplifier are added at the rear end, and multi-polarization and omnibearing signal receiving is realized through quick switching of a switch. The orthogonal three-ring omnidirectional probe has a wider dynamic range, flat frequency response and smaller size, is matched with a spectrometer to measure the electric field intensity of a short wave antenna to be measured, directly calculates the antenna gain, and replaces the traditional measuring method that the antenna to be measured can be compared with a standard antenna to obtain the antenna gain.
Referring to fig. 1, a schematic structure of a short wave antenna gain measurement system based on an unmanned aerial vehicle according to the present invention is shown. The system comprises an onboard test system and a ground test system.
The airborne test system consists of an unmanned aerial vehicle subsystem, an airborne control module, a spectrometer, an airborne data transmission and an omnidirectional antenna. The unmanned aerial vehicle subsystem is a six-rotor unmanned aerial vehicle flight platform carrying test equipment, the airborne control module realizes the function of collecting field intensity data by controlling the frequency spectrograph and the omnidirectional antenna, and the airborne data transmission function is to carry out wireless data transmission with the ground test system.
The ground test system consists of a ground processing module, a signal source, a power amplifier, an antenna to be tested, a ground station module, an RTK and ground data transmission. The ground station module and the RTK are responsible for the control and positioning of the unmanned aerial vehicle subsystem, and the ground processing module transmits signals through a control signal source, a power amplifier and an antenna to be tested, and on the other hand, the ground processing module has an important role in real-time data processing.
Figure 2 is a physical diagram of an orthogonal tri-ring omni-directional probe of the present invention. The orthogonal three-ring omnidirectional probe consists of three groups of mutually orthogonal electric small-ring antennas after calibration, the electric small-ring antennas adopt balanced feed, a filter and a multistage amplifier are added at the rear end, and multi-polarization and omnibearing signal reception is realized through quick switching of a switch. The orthogonal three-ring omnidirectional probe antenna is calibrated to ensure the stability and accuracy of the performance. The balanced feed design helps to reduce interference and noise, thereby improving signal quality. The filters and multistage amplifiers at the back end can enhance the sharpness and strength of the signal so that the probe can capture more accurate data. The switch is used for rapidly switching different polarization directions, so that the probe can realize multi-polarization and omnibearing signal receiving and analysis.
Fig. 3 is a flowchart of a short wave antenna gain measurement method based on an unmanned aerial vehicle. The unmanned aerial vehicle-based short wave antenna gain measurement method comprises the following specific steps:
(1) Setting up a real-time differential global positioning system (GPS-RTK) and connecting with a ground station of a measurement system, and checking the working state of the RTK and displaying various parameters of an unmanned aerial vehicle of the ground station;
(2) Carrying an omnidirectional probe of a corresponding frequency band on the unmanned aerial vehicle according to the measurement task;
(3) And acquiring the longitude and latitude of the center point of the short wave antenna by using a high-precision positioning receiver. Selecting two points A1 and A2 on a straight line passing through the center point, wherein the two points are equidistant from the center point, and calculating the actual longitude and latitude of the center point according to the acquired longitude and latitude of the two points, wherein the central longitude= (A1 longitude+A2 longitude)/2, and the central latitude= (A1 latitude+A2 latitude)/2;
(4) Measuring the pitch angle of the short wave antenna to be measured by using a high-precision positioning receiver;
(5) The flight path of the unmanned aerial vehicle on the vertical plane and the horizontal plane is planned according to the azimuth angle and the pitch angle of the short wave antenna, and the flight path comprises the steps of setting data such as the flight height, the course angle, the speed, the radius of the round flight, the circle center (namely, the longitude and the latitude of the central point of the short wave antenna) and the like of the unmanned aerial vehicle; generating a planned track text file, importing the planned track text file and uploading the planned track text file to the unmanned aerial vehicle, and carrying out flight test by the unmanned aerial vehicle according to the planned track, and comparing whether the planned track is consistent with the uploaded track;
(6) Moving the unmanned aerial vehicle to an open field, and debugging a ground-end remote control program and an unmanned aerial vehicle-end airborne equipment data transmission link and a control link; setting signal source power and modulating antenna factors; rotating the unmanned aerial vehicle to enable the direction angle of the omnidirectional antenna to be changed, collecting data, and comparing whether measured values at different positions are changed or not; after the state debugging is finished, determining a frequency point fi to be measured, i=1 and 2 … N of which the direction diagram and the gain need to be measured; i is the serial number of the frequency points to be detected, and N is the total number of the frequency points to be detected;
(7) Checking whether magnetic interference exists or not, and whether each indicator lamp is normal or not;
(8) The unmanned aerial vehicle performs point-by-point flight measurement according to a planned track in a full-automatic measurement state, acquires data, and the ground system draws an antenna pattern to be measured in real time.
(9) And analyzing and sorting the measured data, and calculating parameters such as beam direction, beam width, antenna gain and the like of the frequency point to be measured of the antenna.
From the basic principle of the antenna, the power density S of the antenna on a sphere with radius R is:
S=G/4πR² （1）
In the above formula, G is the antenna gain. The power density of an antenna on a sphere of radius R can in turn be expressed as the spatial field strength E:
S=E²/η0 （2）
Wherein η 0 is the space wave impedance, and the above formulas (1) and (2) are combined to obtain the gain of the short wave antenna:
G= （3）
input power of the above-mentioned middle antenna Transmit power for signal source/>(W) and insertion loss/>(W) difference, i.e=/>-/>E is the intensity (V/m) of the received electric field in the maximum radiation direction of the antenna to be tested, and the field intensity E is synthesized by three electric field components received by the tricyclic orthogonal antenna.
The unmanned aerial vehicle flight measurement comprises flight measurement of a vertical plane and a horizontal plane of an antenna to be measured.
Fig. 4 is a schematic diagram of a vertical plane measurement flight of an unmanned aerial vehicle, wherein the vertical plane flight measurement of the unmanned aerial vehicle is to plan a flight measurement track of the unmanned aerial vehicle on a vertical plane of an azimuth angle according to the azimuth angle of a short wave antenna beam to be measured. The unmanned aerial vehicle performs data acquisition during fixed-point flight measurement, and transmits the measured data back to the ground test system in real time through the data transmission module, the ground test processes the measured data and draws a directional diagram of the short-wave antenna, and further performance indexes such as the gain of the short-wave antenna can be obtained.
Fig. 5 is a schematic illustration of unmanned plane horizontal plane flight measurement according to the present invention, wherein unmanned plane horizontal plane flight measurement is to plan a flight path of the unmanned plane on the horizontal plane according to the azimuth angle and pitch angle of the antenna beam. The maximum field intensity value and the corresponding pitching angle on the beam vertical plane can be determined by analyzing the data acquired by the vertical plane, and when the horizontal plane flight measurement is carried out at the height corresponding to the pitching angle, the unmanned plane measurement acquisition system carries out flight measurement according to the flight path and acquires the data, and after the measurement is completed, the unmanned plane automatically returns. By analyzing the data, a horizontal plane direction diagram and an azimuth angle corresponding to the maximum value can be obtained.
It should be noted that the foregoing detailed description is exemplary and is intended to provide further explanation of the application. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application. As used herein, the singular is intended to include the plural unless the context clearly indicates otherwise. Furthermore, it will be further understood that the terms "comprises" and/or "comprising," when used in this specification, specify the presence of stated features, steps, operations, devices, components, and/or groups thereof.
Furthermore, the terms "comprise" and "have," as well as any variations thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those elements but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
Spatially relative terms, such as "above … …," "above … …," "upper surface on … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations "above … …" and "below … …". The device may also be positioned in other different ways, such as rotated 90 degrees or at other orientations, and the spatially relative descriptors used herein interpreted accordingly.
In the above detailed description, reference is made to the accompanying drawings, which form a part hereof. In the drawings, like numerals typically identify like components unless context indicates otherwise. The illustrated embodiments described in the detailed description, drawings, and claims are not meant to be limiting. Other embodiments may be utilized, and other changes may be made, without departing from the spirit or scope of the subject matter presented herein.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. The unmanned aerial vehicle-based short wave antenna gain measurement method is characterized by comprising the following steps of:
S1, integrating the calibrated orthogonal three-ring omnidirectional probe and a spectrometer on an unmanned plane platform to serve as a receiving end, and taking a ground short wave antenna to be measured as a transmitting end;
s2, connecting a real-time differential global positioning system GPS-RTK with a ground station measurement system;
S3, planning a flight path of unmanned aerial vehicle flight measurement by taking longitude and latitude of a center point of the short wave antenna to be detected as a reference point;
s4, the unmanned aerial vehicle carries out flight measurement according to the planned flight path, data acquired by the unmanned aerial vehicle are transmitted to the ground processing module in real time, an antenna pattern is drawn, and the antenna gain is calculated.
2. The unmanned aerial vehicle-based short wave antenna gain measurement method of claim 1, wherein S1 comprises:
The orthogonal three-ring omnidirectional probe consists of three groups of mutually orthogonal electric small-ring antennas after calibration, the electric small-ring antennas adopt balanced feed, a filter and a multistage amplifier are added at the rear end, and multi-polarization and omnibearing signal reception is realized through quick switching of a switch.
3. The unmanned aerial vehicle-based short wave antenna gain measurement method of claim 1, wherein S3 comprises:
The longitude and latitude of the center point of the short wave antenna to be detected are acquired by using a high-precision positioning receiver, two points A1 and A2 on the straight line passing through the center point are selected, the two points are equidistant from the center point, the actual longitude and latitude of the center point is calculated by the acquired longitude and latitude of the two points,
Center longitude= (a1longitude+a2longitude)/2,
Center latitude= (a1 latitude+a2 latitude)/2.
4. The unmanned aerial vehicle-based short wave antenna gain measurement method of claim 1, wherein the S4 calculation of the antenna gain comprises:
from the basic principle of the antenna, the power density S of the antenna on a sphere with radius R is:
S=G/4πR² （1）
The relationship between the power density of the antenna on the spherical surface with the radius R and the received electric field strength E is expressed as:
S=E²/η0 （2）
the antenna gains are derived from the above formulas (1) and (2) as follows:
G= （3）
in the above formula, G is the antenna gain, eta 0 is the space wave impedance, R is the distance (m) between the short wave antenna to be detected and the antenna at the receiving end of the unmanned aerial vehicle, and the input power of the antenna Transmit power for signal source/>(W) and insertion loss/>(W) difference, i.e./> =-/>E is the intensity (V/m) of the received electric field in the maximum radiation direction of the antenna to be tested, and the field intensity E is synthesized by three electric field components received by the tricyclic orthogonal antenna.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108254630A (en) * | 2018-02-07 | 2018-07-06 | 西安星网天线技术有限公司 | A kind of short-wave antenna directional diagram and the measuring system and method for gain |
| CN114384332A (en) * | 2021-12-25 | 2022-04-22 | 中国电波传播研究所（中国电子科技集团公司第二十二研究所） | Method for testing short wave antenna polarization directional diagram |
| CN115150008A (en) * | 2022-06-21 | 2022-10-04 | 北京中测国宇科技有限公司 | Outfield base station antenna pattern and radio frequency test system and method based on unmanned aerial vehicle |
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| CN108254630A (en) * | 2018-02-07 | 2018-07-06 | 西安星网天线技术有限公司 | A kind of short-wave antenna directional diagram and the measuring system and method for gain |
| CN114384332A (en) * | 2021-12-25 | 2022-04-22 | 中国电波传播研究所（中国电子科技集团公司第二十二研究所） | Method for testing short wave antenna polarization directional diagram |
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