CN111948465A - Airborne ultrashort wave antenna directional diagram UAV auxiliary test system - Google Patents
Airborne ultrashort wave antenna directional diagram UAV auxiliary test system Download PDFInfo
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- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/08—Measuring electromagnetic field characteristics
- G01R29/10—Radiation diagrams of antennas
- G01R29/105—Radiation diagrams of antennas using anechoic chambers; Chambers or open field sites used therefor
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/08—Measuring electromagnetic field characteristics
- G01R29/0864—Measuring electromagnetic field characteristics characterised by constructional or functional features
- G01R29/0871—Complete apparatus or systems; circuits, e.g. receivers or amplifiers
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
- G01R29/08—Measuring electromagnetic field characteristics
- G01R29/0864—Measuring electromagnetic field characteristics characterised by constructional or functional features
- G01R29/0892—Details related to signal analysis or treatment; presenting results, e.g. displays; measuring specific signal features other than field strength, e.g. polarisation, field modes, phase, envelope, maximum value
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Abstract
The invention discloses an airborne ultrashort wave antenna directional diagram UAV auxiliary test system, and aims to provide a test method for solving the problem that an outfield aircraft is compatible with a radio frequency link and a radio frequency related to an antenna under a large maneuvering condition. The invention is realized by the following technical scheme: utilize the difference GPS ground mobile station that unmanned aerial vehicle built, unmanned aerial vehicle machine carries the GPS antenna and passes through the synchronous clock module with the frequency reference, embedded module and signal source are sent into respectively to the GPS time, embedded module is according to the GPS time of supplementary unmanned aerial vehicle's machine year flight control system input, the enable signal that the position produced sends into signal source and machine year data link terminal, the signal waveform of the supplementary unmanned aerial vehicle transmission of ground terminal remote control, according to test unmanned aerial vehicle transform height, hover or fly around, the flight strategy of supplementary unmanned aerial vehicle is adjusted in a flexible way to the test revolving stage through ground station terminal, accomplish the directional diagram test of the machine carries the antenna that awaits measuring of different every single move.
Description
Technical Field
The invention relates to the technical field of antenna test, in particular to an ultra-short wave antenna directional pattern test which can be applied to the test and verification of an external field antenna of a large airborne platform and is realized by using a radio remote control device and a self-contained program control device to operate an unmanned aerial vehicle.
Background
Radio technology equipment such as communication, radar, navigation, broadcasting, television and the like, which propagate information by radio waves, require the transmission and reception of radio waves. The antenna is used as an important component of an airborne radio frequency sensor system, the directivity pattern is an important index of the antenna, and the test and verification become important work content in the current engineering model development. In order to achieve the best communication effect, the antenna must have a certain directivity, a high conversion efficiency, and a bandwidth satisfying the system operation. Depending on the task of the radio technology equipment, it is often required that the antenna does not radiate uniformly in all directions or have equal reception capability in all directions, but only radiates or receives radio waves from a specific area, and does not radiate or radiates weakly in other directions, i.e. the antenna is required to have directivity. If the antenna is not directional, for the transmitting antenna, only a small part of the radiated power reaches the required direction, and most of the power is wasted in the direction which is not required; for the receiving antenna, while receiving the required signal, it also receives interference and noise from other directions, even submerging the signal in the interference and noise completely. The accurate test of the antenna directional diagram is related to the radio test of a radio frequency functional link, radio frequency compatibility, radio frequency stealth and the like of a radio frequency system. The principle of measuring the directional diagram is simple, but the problem of many aspects is involved in accurately determining the directional diagram, and the difficulty is high. The GJB-8815 and other standards make specific specifications and requirements for testing and calibrating parameters such as antenna directional diagrams, and an ideal test site is an anechoic chamber, but the site is generally only suitable for high-frequency antenna testing and requires that the use scene of the antenna to be tested is flexible. For a low-frequency antenna, such as a broadcast television tower antenna, the size and the floor space are large, laboratory test activities of the antenna cannot be carried out, a directional pattern of the antenna can be tested only in an open field, and a huge test problem is also faced due to the size problem. The antenna directional diagram is tested in a microwave darkroom, the performance test of a single antenna is basically carried out before installation, and the test of the whole antenna is not carried out in the darkroom generally. The main reason is that the darkroom single antenna test cannot accurately evaluate the distortion influence of the antenna mounting backward direction; as the size of the airborne platform is generally 10m-20m magnitude, part of the airborne platform is larger and cannot adapt to the size of a darkroom dead zone; airborne antennas such as compass, beacon, shortwave, ultrashort wave antennas are low frequency (below 300 MHz), and darkrooms have substantially no far field conditions at such low frequency conditions. Therefore, the complete machine test of the antenna is mostly carried out in an external field, and the turret is utilized to simulate the attitude change of the airplane in azimuth and pitch. The current rotary table at home has the capability of rotating in 360 degrees in azimuth, but in the pitching dimension, the rotation is limited by the size and weight of an airplane, the torque of the rotary table can support the maneuvering range of the pitching angle within +/-30 degrees, and meanwhile, the erection height of an antenna at a general auxiliary end is equivalent to that of a testing end, so that the antenna test of an external field complete machine is mainly concentrated in the angular range of 360 degrees in azimuth and +/-30 degrees in pitching. At present, the major impact on the antenna by installation is concentrated on the ultra-short wave band (108-. In the plane flight condition or the small maneuvering condition (the pitching/rolling is less than 20 degrees), the functional link mainly uses the antenna gain within +/-30 degrees of pitching. In the existing external field testing system, the auxiliary end is fixed on the ground or on the mountain head, the influence of multipath is large, the pitching rotation capacity of the rotary table is limited, and the pitching angle testing range cannot exceed 30 degrees. In order to adapt to the performance test of the communication link after the antenna is installed under the condition of large maneuvering of the airplane, the performance of the antenna under the condition of large pitching angle after the antenna is installed needs to be tested, the general pitching angle needs to exceed 60 degrees, and the part of extreme conditions needs to reach 80 degrees. Therefore, a new test means needs to be further developed to meet the antenna performance test under the large-mobility condition, and further verify the functions of the radio frequency link, the radio frequency compatibility, the radio frequency stealth and the like related to the antenna under the large-mobility condition.
With the rapid development of electronic information technology, unmanned aerial vehicles gradually move into the field of vision of the public, and due to the characteristics of lightness, low cost, flexible flight and the like, the unmanned aerial vehicles are widely applied to social production and life, including aerial photography, meteorological observation, agricultural plant protection, electric power line patrol and the like, and are widely concerned by various industries. Therefore, the application of the unmanned aerial vehicle to the antenna test is a new idea and a new subject for solving the measurement and verification of the characteristic parameters of the current low-frequency antenna. The unmanned aerial vehicle is an aircraft flying in a remote control or program control mode and mainly comprises a flight control system, a data link system, a power system, a sensor system and the like. Generally, the two types are fixed wing and rotor wing. The unmanned aerial vehicle can obtain an antenna directional diagram of the antenna to be tested about a pitch angle theta and an azimuth angle phi in a horizontal plane or spherical flight test. The classical short-wave antenna directional diagram is tested by theoretical calculation and a reduced scale model test. With the continuous development of antenna technology, many short-wave antennas are continuously introduced, and due to the ambiguity or uncertainty of the directivity parameters, great inconvenience is brought to the design of communication lines, and the antennas cannot be correctly used. In some cases, the classical short-wave antenna also meets the conditions that the field fluctuation is larger than the standard regulation, or the distance between the classical short-wave antenna and the surrounding antenna is too close to meet the use requirement, and the like. For the measurement of the directivity of the short wave antenna, a balloon or an airplane is used as a carrier, a signal source and a transmitting antenna are carried, and the measurement is carried out along the circumference taking the antenna to be measured as the center. However, these methods are limited by various factors such as cost, time, manpower, weather, etc. In view of these circumstances, a set of fast, advanced and high-precision short-wave antenna testing system is urgently needed to solve the long-standing problem that the directivity index of the short-wave antenna can only be comprehensively judged by a large amount of test data. According to the antenna reciprocity theorem, the tested antenna is used for receiving the radio-frequency signal transmitted by the remote source of the unmanned aerial vehicle, and the received signal is weak because of the far-field test requirement and the light requirement of the signal generation system, the unmanned aerial vehicle flies far and the power of the signal source is limited. Generally, the unmanned aerial vehicle flies horizontally along the plane E or the plane H of the radiation pattern of the tested antenna at a fixed height and approximately in a straight course, and the co-polarization or cross-polarization pattern of the tested antenna at a certain frequency point can be tested and obtained because the dipole antenna of the signal source is linearly polarized in the horizontal flight path of the unmanned aerial vehicle. Firstly, with the increase of the observation angle from the tested antenna to the unmanned aerial vehicle, the distance from the unmanned aerial vehicle to the antenna is gradually increased, so that the space path loss is increased, and the change range directly influences the dynamic range of the ground receiver; secondly, in order to achieve the purpose of testing the directional pattern under a large observation angle, the longer the distance of the unmanned aerial vehicle flying away from the antenna is, the longer the endurance time of the aircraft is required, and only a one-dimensional directional pattern of the antenna can be obtained. Therefore, more complex flight strategies need to be employed.
Disclosure of Invention
Aiming at the requirement of large pitch angle of the conventional whole machine antenna test and verification, the invention verifies the radio technical indexes such as radio frequency link, radio frequency compatibility, radio frequency stealth and the like related to the antenna under the large-maneuvering condition, adopts an unmanned aerial vehicle to carry out auxiliary test, solves the performance test problem of the airborne antenna under the large-maneuvering flight condition, and provides an airborne ultrashort wave antenna directional diagram auxiliary test system capable of meeting the gain index of the whole machine external field antenna directional diagram under the large-maneuvering flight condition so as to solve the radio test problems of the radio frequency link, the radio frequency compatibility, the radio frequency stealth and the like related to the antenna of the external field whole machine under the large-maneuvering condition.
The technical scheme adopted by the invention for solving the technical problem is as follows: an airborne ultrashort wave antenna pattern UAV assisted test system, comprising: carry out bidirectional communication's ground satellite station terminal with control center, have the difference GPS ground satellite station of antenna, erect the unmanned aerial vehicle auxiliary test system who is equipped with auxiliary test antenna, signal source, its characterized in that: the unmanned aerial vehicle airborne GPS antenna respectively sends frequency reference and GPS time to the embedded module and the signal source through the synchronous clock module, the embedded module sends enabling signals generated according to the GPS time and the position input by the airborne flight control system of the auxiliary unmanned aerial vehicle to the signal source, and simultaneously sends the GPS time, the position and waveform data to the airborne data link terminal; the signal source transmits an auxiliary test signal to the airborne antenna to be tested through an auxiliary test antenna erected on the auxiliary unmanned aerial vehicle, so that the transmission of the auxiliary test signal is completed; ground station terminal utilizes the GPS control module of difference GPS ground station to accomplish supplementary unmanned aerial vehicle real-time position control, data exchange, transmission signal control and synchronization, utilize and receive supplementary airborne data link terminal data, the signal waveform of the supplementary unmanned aerial vehicle transmission of remote control, simultaneously through the vector network analysis appearance that control center links to each other, realize supplementary unmanned aerial vehicle transform height, the flight gesture of hovering or winding, through the automatic nimble flight strategy who adjusts supplementary unmanned aerial vehicle of ground station terminal, carry out the directional diagram test to the airborne antenna that awaits measuring, accomplish the different pitch angle of airborne antenna and directional pattern test under the azimuth.
Compared with the prior art, the invention has the following effects:
the invention adopts the unmanned aerial vehicle to carry out auxiliary test, and the unmanned aerial vehicle is provided with auxiliary test antennas, signal sources and other equipment to finish the emission of auxiliary test signals. The signal waveform is transmitted by the ground terminal data link remote control unmanned aerial vehicle, and the whole antenna test of different pitching angles and azimuth angles is completed by the unmanned aerial vehicle through height change, hovering or flying around. Receiving place test equipment ability, unmanned aerial vehicle auxiliary test system can adjust the flight strategy in a flexible way, satisfies different test requirements, and to the fixed test revolving stage, the aircraft erects the back on the revolving stage, can fly around the revolving stage according to fixed height through unmanned aerial vehicle, tests the antenna performance of all azimuth planes on certain face of pitching, through adjustment flying height, realizes the antenna performance test of different pitch angles. For a two-axis or three-axis rotary table, the unmanned aerial vehicle can adopt a hovering mode, the rotary table rotates through azimuth and pitching to simulate different flight attitudes, the test of the whole antenna is different, the auxiliary test system of the unmanned aerial vehicle is added, the limitation of the capability of the rotary table on the test of the whole antenna is reduced, the performance test of the whole antenna with different azimuth angles and pitching angles is completed, and particularly, the flight height of the unmanned aerial vehicle is flexibly adjusted, and the test state of a large pitching angle can be simulated. By the aid of the unmanned aerial vehicle auxiliary test system, pitching test postures within the range of 0-80 degrees can be simulated, antenna performance tests under the condition of large maneuvering (pitching/rolling maneuvering) are met, and functions of radio frequency links, radio frequency compatibility, radio frequency stealth and the like related to the antenna under the condition of large maneuvering are further verified. Meanwhile, the auxiliary test system of the unmanned aerial vehicle does not need to be configured with a special auxiliary test field and equipment conditions, so that the requirement of the auxiliary end test field is greatly simplified.
According to the invention, through the azimuth/pitching rotation of the rotary table and the hovering/flying around strategy of the unmanned aerial vehicle, the testing capability of the airborne antenna directional diagram in a large-angle range is established, and meanwhile, the problems of overhigh flying height of the unmanned aerial vehicle, attenuation caused by too long testing distance and the like in order to establish a large elevation angle are avoided.
The method is suitable for testing the directional diagram of the large-size airborne and airborne platform antenna, and is particularly suitable for testing the directional diagram of the airborne ultrashort wave omnidirectional antenna under the large-size dynamic condition. Particularly, the directional diagram test of an ultra-short wave antenna directional diagram which is greatly influenced by the installation machine under the condition of large motor-driven condition.
Drawings
Fig. 1 is a schematic block diagram of an unmanned aerial vehicle auxiliary test system built by the invention.
Fig. 2 is a schematic diagram of the antenna pattern test of the unmanned aerial vehicle of fig. 1 under the condition that the unmanned aerial vehicle adopts a fly-around mode to realize a large pitch angle.
Fig. 3 is a schematic diagram of testing an antenna pattern of the unmanned aerial vehicle of fig. 1 under the condition that the unmanned aerial vehicle adopts a hovering mode to realize a large pitch angle.
Detailed Description
See fig. 1. In an embodiment described below, an airborne ultrashort wave antenna pattern UAV assisted test system, comprising: the ground station terminal which carries out bidirectional communication with the control center, the differential GPS ground mobile station with an antenna, and the unmanned aerial vehicle auxiliary test system provided with an auxiliary test antenna and a signal source are erected. The unmanned aerial vehicle airborne GPS antenna respectively sends frequency reference and GPS time to the embedded module and the signal source through the synchronous clock module, the embedded module sends enabling signals generated according to the GPS time and the position input by the airborne flight control system of the auxiliary unmanned aerial vehicle to the signal source, and simultaneously sends the GPS time, the position and waveform data to the airborne data link terminal; the signal source transmits an auxiliary test signal to the airborne antenna to be tested through an auxiliary test antenna erected on the auxiliary unmanned aerial vehicle, so that the transmission of the auxiliary test signal is completed; ground station terminal utilizes the GPS control module of difference GPS ground station to accomplish supplementary unmanned aerial vehicle real time position control, data interchange, transmission signal control and synchronization, utilize and receive supplementary airborne data link terminal data, the signal waveform of the supplementary unmanned aerial vehicle transmission of remote control, simultaneously through the vector network analysis appearance that control center links to each other, through unmanned aerial vehicle transform height, hover or around the flight strategy of the supplementary unmanned aerial vehicle of nimble adjustment, carry out the directional diagram test to the airborne antenna of being surveyed, accomplish the directional diagram test of the airborne antenna of awaiting measuring under different pitch angle and the azimuth.
The unmanned aerial vehicle auxiliary test system provides an aerial standard signal source for the airborne antenna of the tested fixed station, and tests of the antenna directivity pattern are completed. The ground station terminal equipment comprises an antenna to be tested, a receiver, a data acquisition card, a data processing terminal and a differential GPS reference station, and the ground station terminal equipment controls the flight of the auxiliary unmanned aerial vehicle through a ground end data link/a remote controller.
Example 1
See fig. 2. The auxiliary antenna adopts omnidirectional antenna to hang in the unmanned aerial vehicle lower part, and ground station terminal is according to the mode of hovering that auxiliary unmanned aerial vehicle adopted, controls auxiliary unmanned aerial vehicle height of hovering and position and as the auxiliary antenna of auxiliary test end through ground unmanned aerial vehicle measurement and control end, controls auxiliary unmanned aerial vehicle transmitting frequency and signal strength through ground control end, tests the directional diagram of the airborne antenna communication that awaits measuring.
The airborne antenna to be tested is connected with the vector network, is installed on the airborne platform, bypasses the rotation center and is perpendicular to the rotating shaft of the table board, and rotates around the axis to do circumferential motion around the automatic turntable to receive signals transmitted by the auxiliary antenna at the auxiliary unmanned aerial vehicle end. The ground unmanned aerial vehicle measurement and control end controls the hovering height and position of the unmanned aerial vehicle, the ground station terminal receives signals transmitted by the auxiliary unmanned aerial vehicle end auxiliary antenna at all angles, the ground station terminal receives test data, the test data of the field intensity-distance relation in an airspace is recorded, field intensity values on all test points are used as normalized calibration parameters, the test data deviated from the track are corrected to a normal track, a central point meeting the requirement of an antenna directional diagram test is calculated, a more accurate antenna direction is obtained, and a directional diagram of the antenna to be tested is drawn.
The unmanned aerial vehicle carries the end to be measured and adopts the rotatory machine of one-dimensional position to be measured antenna, and the test angular domain scope corresponds to the machine-carried platform, adjusts machine and carries the automatic revolving stage every single move angle of end to be measured, and ground station terminal is according to supplementary unmanned aerial vehicle flying height and height of hovering, tests the different angular domain antenna pattern of machine-carried antenna to be measured, can realize the antenna pattern of position qxcomm technology, every single move 0-80 airspace within range.
In consideration of GPS precision, the larger the flight radius is, the smaller the relative error is; considering from the radio wave propagation theory, the antenna directivity should be tested in the far field, about 10 wavelengths away; considering the position of a building beside a flight radius area, the flight radius is determined to be 20 meters. The unmanned aerial vehicle is moved to a position (point A) which is 20 meters away from the antenna, and then the unmanned aerial vehicle flies around the antenna in a circle by taking the point B as the circle center and 20 meters as the radius. The auxiliary unmanned aerial vehicle can always keep the antenna radiation main lobe of the airborne signal source aligned to the measured fixed station antenna during flying, the transmission frequency, the GPS time and the geographical position information of the airborne signal source are controlled and recorded at a certain time interval, and the receiving end software synchronously controls the spectrum analyzer which is positioned at the end of the measured airborne antenna to be measured and reads and records the frequency and the GPS time. When the antenna directivity is tested, the software of the transmitting terminal continuously records the GPS time and the position information; and the receiving end software continuously reads and records the level value received by the spectrum analyzer through the measured antenna, fuses the data of the transmitting end and the receiving end and draws a directional diagram of the measured antenna in polar coordinates.
During testing, the ground-end data link/remote controller controls the auxiliary unmanned aerial vehicle to fly circumferentially around the tested airplane, so that the flying attitude is kept, and the directional main lobe of the auxiliary antenna is always aligned to the tested airborne antenna to be tested; and then controlling the auxiliary unmanned aerial vehicle to carry out circular flight around the airborne antenna to be measured at the horizontal position of the radiation directivity main lobe of the auxiliary antenna by fixing the flight radius, and simultaneously recording the frequency, the GPS position and the time information of the signal source, and the receiving level and the GPS time information of a receiver positioned at the end of the antenna to be measured.
The method comprises the steps of selecting and determining a flight track according to factors such as auxiliary antenna polarization, antenna directional diagram indexes and the like, realizing multiple elevation angles through a plurality of flights at different heights, completing vertical plane directional diagram test, and synchronizing and analyzing the data of a signal source and a receiver by referring to a GPS time stamp so as to draw a horizontal directional diagram of a receiving antenna.
Example 2
See fig. 3. Supplementary unmanned aerial vehicle adopts around flying the mode. The ground station terminal machine carries the receiving antenna who waits to survey the end and adopts fixed mode, according to the flight radius who satisfies far field condition, set for supplementary unmanned aerial vehicle as the center and wind around being surveyed the aircraft according to fixed flight radius and fly with regard to automatic revolving stage, control supplementary unmanned aerial vehicle flying height, supplementary antenna transmitting frequency and transmitted signal intensity, the simultaneous control loading signal source fly around receiving antenna, through adjusting supplementary unmanned aerial vehicle flying height and flight radius, realize being surveyed different angle territory antenna directional diagrams tests of unmanned aerial vehicle complete machine antenna.
The ground station terminal airborne to-be-measured end calculates the angle of each point deviating from the main lobe axis of the receiving antenna according to the auxiliary unmanned aerial vehicle circling radius and the distance between the receiving point and the circling center point, then finds out the deviation between the received field intensity value and the field intensity value received in the maximum direction according to the radiation directivity pattern of the receiving antenna, accumulates the deviation to the field intensity received by the receiving point, uses the field intensity value received by each point on the circling circumference as a reduced calibration parameter, compensates by using the field intensity value as a reference value, corrects and determines a correction value and performs reduction processing to obtain the flight directional pattern of the antenna phase center and the rotation center. But also greatly reduces errors and flight difficulty caused by various cables.
The present invention has been described in detail with reference to the accompanying drawings, but it is to be understood that the above-described embodiments are only preferred embodiments of the present invention, and not limiting, and it will be apparent to those skilled in the art that various changes and modifications may be made therein, such as extending the testing frequency range of the present invention, and any modifications, equivalents, improvements and the like, which are within the spirit and principle of the present invention, are intended to be included within the scope of the appended claims.
Claims (10)
1. An airborne ultrashort wave antenna pattern UAV assisted test system, comprising: carry out bidirectional communication's ground satellite station terminal with control center, have the difference GPS ground satellite station of antenna, erect the unmanned aerial vehicle auxiliary test system who is equipped with auxiliary test antenna, signal source, its characterized in that: the unmanned aerial vehicle airborne GPS antenna respectively sends frequency reference and GPS time to the embedded module and the signal source through the synchronous clock module, the embedded module sends enabling signals generated according to the GPS time and the position input by the airborne flight control system of the auxiliary unmanned aerial vehicle to the signal source, and simultaneously sends the GPS time, the position and waveform data to the airborne data link terminal; the signal source transmits an auxiliary test signal to the airborne antenna to be tested through an auxiliary test antenna erected on the auxiliary unmanned aerial vehicle, so that the transmission of the auxiliary test signal is completed; ground station terminal utilizes the GPS control module of difference GPS ground station to accomplish supplementary unmanned aerial vehicle real-time position control, data exchange, transmission signal control and synchronization, utilize and receive supplementary airborne data link terminal data, the signal waveform of the supplementary unmanned aerial vehicle transmission of remote control, simultaneously through the vector network analysis appearance that control center links to each other, realize supplementary unmanned aerial vehicle transform height, the flight gesture of hovering or winding, through the automatic nimble flight strategy who adjusts supplementary unmanned aerial vehicle of ground station terminal, carry out the directional diagram test to the airborne antenna that awaits measuring, accomplish the different pitch angle of airborne antenna and directional pattern test under the azimuth.
2. The airborne ultrashort wave antenna pattern UAV assisted test system of claim 1, wherein: the unmanned aerial vehicle auxiliary test system provides an aerial standard signal source for the airborne antenna of the tested fixed station, and tests of the antenna directivity pattern are completed.
3. The airborne ultrashort wave antenna pattern UAV assisted test system of claim 1, wherein: the ground station terminal equipment comprises an antenna to be tested, a receiver, a data acquisition card, a data processing terminal and a differential GPS reference station, and the ground station terminal equipment controls the flight of the auxiliary unmanned aerial vehicle through a ground end data link/a remote controller.
4. The airborne ultrashort wave antenna pattern UAV assisted test system of claim 1, wherein: the auxiliary antenna adopts omnidirectional antenna to hang in auxiliary unmanned aerial vehicle lower part, and ground station terminal is according to the mode of hovering that auxiliary unmanned aerial vehicle adopted, controls auxiliary unmanned aerial vehicle height of hovering and position and the auxiliary antenna as the auxiliary test end through ground unmanned aerial vehicle measurement and control end, controls auxiliary unmanned aerial vehicle transmitting frequency and signal strength through the ground control end, tests the directional diagram of the airborne antenna communication that awaits measuring.
5. The airborne ultrashort wave antenna pattern UAV assisted test system of claim 1, wherein: the airborne antenna to be tested is connected with the vector network, is installed on the airborne platform, bypasses the rotation center and is perpendicular to the rotating shaft of the table board, and rotates around the axis to do circumferential motion around the automatic turntable to receive signals transmitted by the auxiliary antenna at the auxiliary unmanned aerial vehicle end.
6. The airborne ultrashort wave antenna pattern UAV assisted test system of claim 1, wherein: the method comprises the steps that an unmanned aerial vehicle measurement and control end controls the hovering height and the hovering position of the unmanned aerial vehicle, a ground station terminal receives signals transmitted by an auxiliary unmanned aerial vehicle end auxiliary antenna at all angles, the ground station terminal receives test data, the test data of the field intensity-distance relation in an airspace are recorded, field intensity values on all test points are used as normalized calibration parameters, the test data deviated from a track are corrected to a normal track, a central point meeting the requirement of an antenna directional diagram test is calculated, a more accurate antenna direction is obtained, and a directional diagram of an antenna to be tested is drawn.
7. The airborne ultrashort wave antenna pattern UAV assisted test system of claim 1, wherein: the unmanned aerial vehicle carries the end to be measured and adopts the rotatory machine of one-dimensional position to be measured antenna, and the test angular domain scope corresponds to the machine-carried platform, adjusts machine and carries the automatic revolving stage every single move angle of end to be measured, and ground station terminal is according to supplementary unmanned aerial vehicle flying height and height of hovering, tests the different angular domain antenna directional diagrams of machine-carried antenna to be measured, realizes the antenna directional diagram in the position qxcomm technology, every single move 0-80 airspace range.
8. The airborne ultrashort wave antenna pattern UAV assisted test system of claim 1, wherein: the method comprises the steps that an auxiliary unmanned aerial vehicle always keeps an antenna radiation main lobe of an airborne signal source aligned to a tested fixed station antenna during flying, the transmission frequency, the GPS time and the geographical position information of the airborne signal source are controlled and recorded at certain time intervals, receiving end software synchronously controls a spectrum analyzer located at the end of an antenna to be tested of the tested aircraft, the frequency and the GPS time are read and recorded, and during antenna directivity testing, the transmitting end software continuously records the GPS time and the position information; and the receiving end software continuously reads and records the level value received by the spectrum analyzer through the measured antenna, fuses the data of the transmitting end and the receiving end and draws a directional diagram of the measured antenna in polar coordinates.
9. The airborne ultrashort wave antenna pattern UAV assisted test system of claim 1, wherein: the ground end data link/remote controller controls the auxiliary unmanned aerial vehicle to fly circumferentially around the tested airplane, so that the flying attitude is kept, and the directional main lobe of the auxiliary antenna is always aligned to the tested airborne antenna to be tested; then, the auxiliary unmanned aerial vehicle is controlled to carry out circular flight around the airborne antenna to be measured with a fixed flight radius and at the horizontal position of the radiation directivity main lobe of the auxiliary antenna, and the frequency, the GPS position and the time information of a signal source, the receiving level of a receiver positioned at the end of the antenna to be measured and the GPS time information are recorded at the same time; the flight track is selected and determined according to the factors of auxiliary antenna polarization and antenna directional diagram indexes, a plurality of elevation angles are realized after a plurality of flights at different heights, the vertical plane directional diagram test is completed, the data of the signal source and the data of the receiver are synchronized and analyzed by referring to the GPS time stamp, and the horizontal directional diagram of the receiving antenna can be drawn.
10. The airborne ultrashort wave antenna pattern UAV assisted test system of claim 1, wherein: the ground station terminal airborne to-be-measured end calculates the angle of each point deviating from the main lobe axis of the receiving antenna according to the auxiliary unmanned aerial vehicle circling radius and the distance between the receiving point and the circling center point, then finds out the deviation between the received field intensity value and the field intensity value received in the maximum direction according to the radiation directivity pattern of the receiving antenna, accumulates the deviation to the field intensity received by the receiving point, uses the field intensity value received by each point on the circling circumference as a reduced calibration parameter, compensates by using the field intensity value as a reference value, corrects and determines a correction value and performs reduction processing to obtain the flight directional pattern of the antenna phase center and the rotation center.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112799027A (en) * | 2020-12-31 | 2021-05-14 | 中国电子科技集团公司第十四研究所 | Calibration test method and system for outfield antenna of unmanned aerial vehicle |
| CN114184852A (en) * | 2021-11-30 | 2022-03-15 | 南京理工大学 | Antenna directional pattern active and passive combined type measuring system based on aerial platform |
| CN114924132A (en) * | 2022-03-10 | 2022-08-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle electromagnetic compatibility measuring device and method thereof |
| CN115655247A (en) * | 2022-10-12 | 2023-01-31 | 中国航空工业集团公司西安飞机设计研究所 | Radio compass data processing method for ultrashort wave interference |
| CN116526126A (en) * | 2023-06-29 | 2023-08-01 | 天津天羿科技有限公司 | Relay data link antenna device, communication method, electronic device, and storage medium |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103631250A (en) * | 2013-02-07 | 2014-03-12 | 中国科学院光电研究院 | Method for implementing ground test on tracking precision of pitch axis of antenna |
| CN104133121A (en) * | 2014-07-09 | 2014-11-05 | 中国电子科技集团公司第二十二研究所 | Automatic test method for directional diagram of short-wave large-scale antenna array |
| 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 |
| CN109975621A (en) * | 2019-04-11 | 2019-07-05 | 西安电子科技大学 | A kind of multi-rotor unmanned aerial vehicle large-scale antenna scene pattern measurement system and method |
| CN111537807A (en) * | 2020-03-31 | 2020-08-14 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Method for assisting in testing antenna directional diagram in large-maneuvering flight state by unmanned aerial vehicle |
| CN111624414A (en) * | 2020-05-09 | 2020-09-04 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Method for assisting in testing antenna directional diagram in large-maneuvering flight state by unmanned aerial vehicle |
-
2020
- 2020-07-30 CN CN202010747231.4A patent/CN111948465A/en not_active Withdrawn
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103631250A (en) * | 2013-02-07 | 2014-03-12 | 中国科学院光电研究院 | Method for implementing ground test on tracking precision of pitch axis of antenna |
| CN104133121A (en) * | 2014-07-09 | 2014-11-05 | 中国电子科技集团公司第二十二研究所 | Automatic test method for directional diagram of short-wave large-scale antenna array |
| 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 |
| CN109975621A (en) * | 2019-04-11 | 2019-07-05 | 西安电子科技大学 | A kind of multi-rotor unmanned aerial vehicle large-scale antenna scene pattern measurement system and method |
| CN111537807A (en) * | 2020-03-31 | 2020-08-14 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Method for assisting in testing antenna directional diagram in large-maneuvering flight state by unmanned aerial vehicle |
| CN111624414A (en) * | 2020-05-09 | 2020-09-04 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Method for assisting in testing antenna directional diagram in large-maneuvering flight state by unmanned aerial vehicle |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112799027A (en) * | 2020-12-31 | 2021-05-14 | 中国电子科技集团公司第十四研究所 | Calibration test method and system for outfield antenna of unmanned aerial vehicle |
| CN114184852A (en) * | 2021-11-30 | 2022-03-15 | 南京理工大学 | Antenna directional pattern active and passive combined type measuring system based on aerial platform |
| CN114184852B (en) * | 2021-11-30 | 2024-06-11 | 南京理工大学 | Aerial platform-based antenna pattern active and passive combined type measurement system |
| CN114924132A (en) * | 2022-03-10 | 2022-08-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle electromagnetic compatibility measuring device and method thereof |
| CN115655247A (en) * | 2022-10-12 | 2023-01-31 | 中国航空工业集团公司西安飞机设计研究所 | Radio compass data processing method for ultrashort wave interference |
| CN115655247B (en) * | 2022-10-12 | 2024-06-11 | 中国航空工业集团公司西安飞机设计研究所 | Radio compass data processing method for ultrashort wave interference |
| CN116526126A (en) * | 2023-06-29 | 2023-08-01 | 天津天羿科技有限公司 | Relay data link antenna device, communication method, electronic device, and storage medium |
| CN116526126B (en) * | 2023-06-29 | 2023-10-24 | 天津天羿科技有限公司 | Relay data link antenna device, communication method, electronic device, and storage medium |
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