CN113589055B - Automatic index testing method for full airspace phased array measurement and control system based on unmanned aerial vehicle platform - Google Patents
Automatic index testing method for full airspace phased array measurement and control system based on unmanned aerial vehicle platform Download PDFInfo
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Abstract
The invention discloses an automatic test method for indexes of a full-airspace phased array measurement and control system based on an unmanned aerial vehicle platform. The automatic test method has the advantages that: complex infrastructure is not needed, the method is suitable for the requirements of outfield testing, and the testing cost is reduced; the method has the advantages that the automatic test of the indexes of the full-airspace phased array measurement and control system is realized, compared with the traditional scheme, the operation flow is simplified, the test difficulty is reduced, and the test efficiency and the test precision are improved; the automatic test of the phased array system index can be realized by controlling the flight track of the unmanned aerial vehicle, and finally, the test result is stored according to the beam pointing angle, so that the preparation is made for the subsequent test task.
Description
Technical Field
The invention belongs to the field of measurement and control of an aircraft test target range, and particularly relates to an automatic index testing method of a full airspace phased array measurement and control system based on an unmanned aerial vehicle platform.
Background
The system is an important subsystem of the range flight test, and the external field test of the telemetry and remote control system belongs to key nodes in the system for measuring and controlling the range of the aircraft test. According to the test requirements and the traditional test scheme, when the quality factor (G/T value) and the equivalent omnidirectional radiation power (EIRP value) of the full-airspace phased array system are tested, a tower test mode is generally adopted, namely a calibration tower is erected to test the tested system (as shown in figures 1 and 2).
When testing the system quality factor (G/T value) and the equivalent omnidirectional radiation power (EIRP value) under the external field test condition, two problems exist: firstly, a task outfield is generally free of tower calibration and other high-rise buildings, and does not have tower calibration conditions; secondly, the selected measuring instruments all need manual operation, the flow is complex, and the automatic test requirements cannot be met.
Disclosure of Invention
When the full airspace phased array measurement and control system is used for performing the outfield test, in order to reduce the requirement on test facilities, so that the full airspace phased array measurement and control system is suitable for the outfield test environment, and the test comprehensiveness and automation level are improved, the invention provides an automatic test method for full airspace phased array measurement and control system indexes (namely equivalent omnidirectional radiation power (EIRP value) and receiving quality factor (G/T value)) based on an unmanned aerial vehicle platform.
The test scheme of the present invention mainly comprises the test of the reception quality factor (G/T value) (shown in fig. 3) and the equivalent omni-directional radiation power (EIRP value) (shown in fig. 4). The method mainly comprises the following three steps:
(one) determining test conditions
Mainly comprises the contents of field conditions, equipment reference conditions, limiting conditions in test and the like.
(II) designing flight trajectory
1. Determining beam coverage
First, the beam coverage is determined according to the specific shape of the full spatial domain phased array antenna, here exemplified by a hemispherical conformal phased array antenna. The projection of the sub-airspace covered by the phased array antenna through beam forming on the surface of the phased array antenna is approximately a circle when seen from the normal tangent plane of the hemispherical conformal phased array antenna, the coverage area of the sub-airspace is not more than psi DEG in azimuth/pitch angle, and after the coverage area exceeds the area, the contribution degree of antenna units on two sides to the antenna beam gain is small, as shown in fig. 5-1.
2. Unmanned aerial vehicle traversing point design
Since the beam gain of a phased array antenna is sensitive to pitch angle, the radius of the antenna beam projection forming circle is smaller in the low elevation range than in the high elevation range, so that the covered circle is denser. Therefore, when the flight path of the unmanned aerial vehicle is designed, the influence of low elevation angle and high elevation angle on the traversing points is considered while each sub-airspace is ensured to be traversed, namely, the azimuth and the pitch angle of the low elevation angle and the high elevation angle traversing points are separately designed.
Because the projection of an effective beam forming area on the surface of the phased array is approximately a circle, in order to ensure the coverage of the phased array antenna on the whole airspace, a plurality of circles are selected to be circumscribed on the surface of the phased array antenna for coverage, so that an approximately equivalent result is achieved. A specific method of covering the circle is shown in fig. 5-2.
In order to simplify the calculation process, a circular inscribed equilateral triangle is used for covering the surface of the phased array, and in order to cover more area as possible, the bottom edge of the triangle is closely attached to the contact position of the hemispherical conformal phased array antenna and the ground. The radius of a hemispherical phased array antenna is known as R, and the coverage area of the phased array antenna projected on the surface of the phased array antenna through a sub-airspace covered by beam forming does not exceed phi DEG in azimuth/pitch angle. The low elevation angle portion is set as x (x is less than or equal to psi), the radius of the circumscribed small circle is r=tan (x/2) x R, and the side length of the inscribed triangle of the small circle is s=2×r×cos (30 °); the high elevation angle portion is set to y (x < y. Ltoreq. ψ), the radius of the circumscribed small circle is r1=tan (y/2) ×r, and the side length of the inscribed triangle of the small circle is s1=2×r1×cos (30 °). In order to ensure the coverage of the overhead airspace, no matter how many rows are divided according to the pitch angle, a small circle is arranged at the normal tangent line part (E=90°) of the highest point, the radius of the small circle is equal to the radius of the small circle circumscribed by the high elevation angle part, and the side length of the inscribed triangle of the small circle is equal to the side length of the inscribed triangle circumscribed by the high elevation angle part.
As shown in the first row of fig. 5-2, the first three triangle groups are divided into one group (two circles are formed by taking a and B as the circle centers) by taking 3/2 of the side lengths of the inscribed triangle as the unit, and according to the method, one more common triangle area between every two groups needs to be covered, namely one more circle. The total number of rows to be traversed is M, each row can be divided into n m groups at most through numerical simulation calculation, the number of triangles which can be arranged at most in each row (namely the number of circle centers of inscribed triangles) is q m＝nm×2+(nm -1, so that the azimuth angle degree required to be traversed in one row is delta m＝360/qm+360/qm×[0qm -1, the pitch angle theta m of the circle center of each inscribed triangle is obtained through space geometry calculation,In summary, the coordinates of each traversal point are (δ m,θm), where m=1, …, M.
(III) test procedure
1. Reception quality factor (G/T value) test (as shown in FIG. 6)
(1) Preparation process
Step 1: a full airspace phased array measurement and control system (hereinafter referred to as a measured system) is stopped on a flat open field level, and is powered up and automatically leveled;
Step 2: the antenna is lifted, the coordinates of the phase center point of the antenna of the tested system are calibrated, and test software is bound;
Step 3: powering up equipment on the unmanned aerial vehicle, setting output power St and frequency Fg of a beacon machine, and outputting an S frequency band signal through a calibration antenna;
step 4: according to the pre-calibrated transmission feeder line insertion loss Lt and the calibrated antenna gain Gt, calculating to obtain the EIRP of beacon transmission;
EIRP＝St-Lt+Gt (1-1)
in the formula, EIRP is equivalent omnidirectional radiation power of the calibration tower, st is transmission signal power of the calibration tower, lt is feeder loss of the calibration tower, and Gt is gain of a transmission antenna of the calibration tower;
Step 5: the unmanned aerial vehicle ground control terminal sends the unmanned aerial vehicle real-time positioning coordinates to test software, and the test software calculates the distance Dg between the unmanned aerial vehicle and the tested system according to the tested system antenna phase center coordinates;
Step 6: the tested system controls the antenna beam to point to cold air, the gain modulation of a receiving link is maximum, the received signal is calibrated, the measured noise power spectral density is N 0, and the noise power spectral density is bound into test software;
step 7: and binding the polarization loss Lp, the atmosphere and the multipath loss La into test software according to the calibration antenna, the polarization mode and the pitch angle of the antenna to be tested.
(2) Tracking process
Step 1: the tested system controls the wave beam to aim at the beacon of the unmanned plane;
step 2: observing the angle error demodulation condition, and ensuring the normal angle error demodulation;
step 3: and if the beam is always aligned with the corresponding beacon, the unmanned aerial vehicle is flown.
(3) Test procedure
Step 1: the testing software controls the frequency spectrograph, calibrates the received signal, measures the signal power Sg, and calculates the signal-to-noise ratio Sg/N 0;
Step 2: the test software calculates the linear distance between the coordinates of the system to be tested and the real-time positioning information of the unmanned aerial vehicle, and calculates the space transmission loss Lg of the signal according to the frequency used by the test;
Lg＝32.45+20lgFg(MHz)+20lgDg(km) (1-2)
Step 3: the test software calculates the G/T value at this angle, at this frequency using the following equation:
G/T＝Sg/N0-EIRP+Lg+La+Lp+k (1-3)
Where k is the boltzmann constant.
Step 4: selecting a plurality of traversal points in the flight path of the unmanned aerial vehicle, and repeating the testing steps (1) - (3) to obtain G/T values of the tested system at the plurality of traversal points;
Step 5: the test software stores the system G/T values with the beam pointing angles (elevation and azimuth) as an index.
2. Equivalent omnidirectional radiation power (EIRP value) test (as shown in fig. 7)
(1) Preparation work
Step 1: stopping the tested system on a flat open field level, powering up and automatically leveling;
Step 2: the antenna is lifted, the phase center coordinates of the antenna of the tested system are calibrated, and test software is bound;
step 3: the unmanned aerial vehicle is provided with a power meter, and signals are received through a calibration antenna;
Step 4: the unmanned aerial vehicle ground control terminal sends unmanned aerial vehicle real-time positioning data to test software, and the test software calculates the distance De between the unmanned aerial vehicle and the tested system according to the phase center coordinates of the tested system antenna;
Step 5: binding the calibration antenna gain Gr, the feeder line loss Lr between the calibration antenna and the power meter into test software;
Step 6: and binding the polarization loss Lp, the atmosphere and the multipath loss La into test software according to the calibration antenna, the polarization mode and the pitch angle of the antenna to be tested.
(2) Tracking process
Step 1: the tested system controls the wave beam to aim at the beacon of the unmanned plane;
step 2: observing the angle error demodulation condition, and ensuring the normal angle error demodulation;
step 3: and if the beam is always aligned with the corresponding beacon, the unmanned aerial vehicle is flown.
(3) Test procedure
Step 1:
a) Setting the local oscillation source transmitting local oscillation of the clock as low local oscillation 2150MHz, corresponding to L frequency band transmitting, and setting the L frequency band frequency as F1;
b) Setting the local oscillation source transmitting local oscillation of the clock to be high local oscillation 2450MHz, and setting the S frequency band transmitting corresponding to the S frequency band frequency to be F2;
Step 2: the tested system controls the antenna beam to point to the unmanned aerial vehicle, the test software sets an output power value, the tested system outputs a single carrier wave, and the signal power is a medium-strength signal;
Step 3: after a power meter on the unmanned aerial vehicle receives the signal, adjusting the output power of a tested system to be maximum, transmitting the real-time signal power Se measured by the power meter back to the unmanned aerial vehicle control terminal through a reverse link, and finally transmitting the real-time signal power to test software through a test network by the unmanned aerial vehicle control terminal;
Step 4: calculating the space transmission loss Le of the signal by using the measured system coordinates, the unmanned plane coordinates and the frequency for testing by using test software;
step5: calculating the EIRP value of the system at the angle and the frequency by using the following formula;
EIRP＝Se+Le+La+Lp+Lr-Gr (1-5)
Step 6: selecting a plurality of traversal points in the flight process of the unmanned aerial vehicle, stably tracking the unmanned aerial vehicle by an antenna, and repeating the steps (2) - (5) to obtain EIRP values of the tested system at the plurality of traversal points;
Step 7: the system EIRP value is stored in the test software with the beam pointing angle as an index.
The invention has the advantages that:
1. Complex infrastructure is not needed, the method is suitable for the requirements of outfield testing, and the testing cost is reduced;
2. the method has the advantages that the automatic test of the indexes of the full-airspace phased array measurement and control system is realized, compared with the traditional scheme, the operation flow is simplified, the test difficulty is reduced, and the test efficiency and the test precision are improved;
3. The automatic test of the phased array system index can be realized by controlling the flight track of the unmanned aerial vehicle, and finally, the test result is stored according to the beam pointing angle, so that the preparation is made for the subsequent test task.
Drawings
Fig. 1 is a diagram of a conventional reception quality factor (G/T value) test method.
Fig. 2 is a conventional equivalent omni-directional radiated power (EIRP value) test method.
Fig. 3 is a diagram showing a method for testing a reception quality factor (G/T value) according to the present invention.
Fig. 4 is a method for testing the equivalent omni-directional radiated power (EIRP value) designed by the present invention.
Fig. 5-1 is a schematic view of an antenna beam projection in the present invention.
Fig. 5-2 is a plot of the circumscribed small circle of a hemispherical conformal phased array antenna of the present invention.
Fig. 6 is a flow chart of a method for testing the reception quality factor (G/T value) according to the present invention.
Fig. 7 is a flow chart of an equivalent omni-directional radiated power (EIRP value) test method designed in accordance with the present invention.
Fig. 8 is a schematic diagram of the relationship between radius and small circle of a hemispherical conformal phased array antenna of the present invention.
Detailed Description
The automatic test method for the index of the full-airspace phased array measurement and control system is divided into three parts of determining test conditions, designing flight path and implementing test steps on the basis of calculating the G/T value and the EIRP value of a coordinate point on a flight path of an unmanned aerial vehicle on the basis of planning the flight path of the unmanned aerial vehicle according to the problems of high requirements on time and facilities, insufficient coverage, complex test flow and the like in the external field test of the telemetry and remote control system, and finally, key performance indexes are obtained by calculation, so that important basis is provided for the external field test of the full-airspace phased array telemetry and remote control system.
Examples:
The test equipment comprises a set of full airspace phased array measurement and control system, an unmanned aerial vehicle, a set of reference station and a set of unmanned aerial vehicle ground control terminal.
(One) determining test conditions
An unmanned aerial vehicle with a GPS positioning function is carried with an S-band beacon machine, a calibration antenna;
A set of ground control terminals capable of establishing communication and control links with unmanned aerial vehicles.
(II) designing flight trajectory
1. Determining beam coverage
Taking a hemispherical conformal phased array antenna as an example, the coverage of the antenna beam does not exceed psi=60 in azimuth/elevation angle.
2. Unmanned aerial vehicle traversing point design
And (3) selecting a circular inscribed equilateral triangle to cover the surface of the phased array, wherein the bottom surface of the triangle is clung to the contact position of the hemispherical conformal phased array antenna and the ground. Hemispherical phased array antennas are known with a radius r=1m. The low elevation part (first row) is set to x=30°, the radius r of the small circle is approximately 0.27m, and the side length s of the inscribed triangle is approximately 0.46m; the high elevation section is set to y=40°, the small circle radius r1≡0.36m, and the side length s1≡0.63m of the inscribed triangle (as shown in fig. 8). In order to ensure the coverage of the overhead airspace, no matter how many rows are divided according to the pitch angle, a small circle is arranged on the normal tangent line part E=90° of the highest point, and the radius of the small circle and the side length of the inscribed triangle of the small circle are the same as those of the high elevation angle part.
After the small circles cover the hemispherical surface, the small circles are divided into groups by taking 3/2 inscribed triangle side lengths as units for each row, and according to the method, one more common triangle area needs to be covered between every two groups, and one more common triangle area needs to be accumulated. The number of the most arranged equilateral triangles in each row is q 1＝26、q2＝11、q3＝5、q4＝2、q5 =1 through numerical simulation calculation, and the total number of rows to be traversed is M=5.
Through calculation, the first row of the hemispherical conformal phased array antenna is provided with 26 triangles at most, the center point of the triangle is taken as the unmanned plane traversing point, and the azimuth angle and the pitch angle are respectively as follows ：(13.8,7.5)(27.6,7.5)(41.4,7.5)(55.2,7.5)(69,7.5)(82.8,7.5)(96.6,7.5)(110.4,7.5)(124.2,7.5)(138,7.5)(151.8,7.5)(165.6,7.5)(179.4,7.5)(193.2,7.5)(207,7.5)(220.8,7.5)(234.6,7.5)(248.4,7.5)(262.2,7.5)(276,7.5)(289.8,7.5)(303.6,7.5)(317.4,7.5)(331.2,7.5)(345,7.5)(358.8,7.5);
The hemispherical conformal phased array antenna is provided with a second row of at most 11 triangles, the center point of the triangle is used as an unmanned aerial vehicle traversing point, and the azimuth angle and the pitch angle are respectively as follows ：(32.7,26.1)(65.4,26.1)(98.1,26.1)(130.8,26.1)(163.5,26.1)(196.2,26.1)(228.9,26.1)(261.6,26.1)(294.3,26.1)(327,26.1)(359.7,26.1);
The hemispherical conformal phased array antenna is characterized in that a maximum of 5 triangles are arranged in a third row, a triangle center point is used as an unmanned aerial vehicle traversing point, and an azimuth angle and a pitch angle are respectively as follows: (72,53.1) (144,53.1) (216,53.1) (288,53.1) (360,53.1);
The hemispherical conformal phased array antenna is characterized in that a fourth row of hemispherical conformal phased array antennas is provided with 2 triangles at most, a triangle center point is used as an unmanned aerial vehicle traversing point, and azimuth angles and pitch angles are respectively as follows: (180,80.1) (360,80.1);
The hemispherical conformal phased array antenna is characterized in that a fifth row of hemispherical conformal phased array antennas is provided with at most 1 triangle, a triangle center point is used as an unmanned aerial vehicle traversing point, and azimuth angles and pitch angles are as follows: (0,90).
(III) implementation of the test procedure
1. Reception quality factor (G/T value) test
(1) Preparation process
Step 1: the tested system (L= 87.49539 B= 41.72695 H=1165) is stopped on a field level of the flat open, and is powered up and automatically leveled;
Step 2: the antenna is lifted, the coordinates of the phase center point of the antenna of the tested system are calibrated, and test software is bound;
step 3: powering up equipment on the unmanned aerial vehicle, setting output power St of a beacon machine, and outputting an S frequency band signal through a calibration antenna, wherein the frequency point is Fg= 2206.25MHz;
Step 4: according to the previously calibrated transmission feeder line insertion loss lt=3.3 dBW and the calibrated antenna gain gt=15 dBW, the EIRP= -72.6 of beacon transmission is calculated by the following formula;
EIRP＝St-Lt+Gt (1-1)
In the formula, ERIP is equivalent omnidirectional radiation power of the calibration tower, st is transmission signal power of the calibration tower, lt is insertion loss of a feeder line of the calibration tower, and Gt is gain of a transmission antenna of the calibration tower;
step 5: the unmanned aerial vehicle ground control terminal sends unmanned aerial vehicle real-time positioning data to test software, and the test software calculates the distance Dg between the unmanned aerial vehicle and the tested system according to the phase center coordinates of the tested system antenna;
Step 6: the tested system controls the antenna beam to point to cold air, the gain modulation of a receiving link is maximum, the received signal is calibrated, the measured noise power spectral density is N 0, and the noise power spectral density is bound into test software;
Step 7: according to the calibration antenna, the polarization mode and the pitch angle of the antenna to be measured, the polarization loss lp=3 dBW, and the atmospheric and multipath loss La=1 dBW are bound into test software.
(2) Tracking process
Step 1: the tested system controls the wave beam to aim at the beacon of the unmanned plane;
step 2: observing the angle error demodulation condition, and ensuring the normal angle error demodulation;
step 3: and if the beam is always aligned with the corresponding beacon, the unmanned aerial vehicle is flown.
(3) Test procedure
Step 1: the testing software controls the frequency spectrograph, calibrates the received signal, measures the signal power Sg, and calculates the signal-to-noise ratio Sg/N 0;
Step 2: the test software calculates the linear distance between the coordinates of the system to be tested and the real-time positioning information of the unmanned aerial vehicle by utilizing the coordinates of the system to be tested and the real-time positioning information of the unmanned aerial vehicle, and calculates the space transmission loss Lg of the signal by utilizing the following formula according to the frequency used by the test;
Lg＝32.45+20lgFg(MHz)+20lgDg(km) (1-2)
step 3: the test software calculates the G/T value at that angle, at that frequency, using the following equation.
G/T＝Sg/N0-EIRP+Lg+La+Lp+k (1-3)
Where K is boltzmann constant, k= -228.6dBW/Hz/K;
Step 4: selecting a plurality of traversal points in the flight path of the unmanned aerial vehicle, and repeating the testing steps (1) - (3) to obtain G/T values of the tested system at the plurality of traversal points;
Step 5: the test software stores the system G/T values with the beam pointing angles (elevation and azimuth) as an index.
(4) Data recording
After the unmanned aerial vehicle is tested around the tested system, the following traversal points are screened from the positioning coordinates forwarded to the test software by the unmanned aerial vehicle control terminal and stored, as shown in the table 1-1.
Table 1-1G/T value test key traversal Point coordinate List
The beacon operating frequency point fg= 2206.25MHz and the receiving system quality factor (G/T value) test record is shown in table 1-2.
Table 1-2 table of figures of merit test records for receiving system
2. Equivalent omnidirectional radiation power (EIRP value) test
(1) Preparation process
Step 1: the tested system (L= 87.49539 B= 41.72695 H=1165) is stopped on a field level of the flat open, and is powered up and automatically leveled;
Step 2: the antenna is lifted, the phase center coordinates of the antenna of the tested system are calibrated, and test software is bound;
Step 3: the unmanned aerial vehicle is provided with a power meter, and signals are received through the calibration antenna.
Step 4: and the unmanned aerial vehicle ground control terminal sends the unmanned aerial vehicle real-time positioning data to test software, and the test software calculates the distance De between the unmanned aerial vehicle and the tested system according to the phase center coordinates of the tested system antenna.
Step 5: when the frequency of the transmitted signal of the tested system is f1=1765 MHz, the corresponding calibration antenna gain is gr=15 dBW; when the frequency of the transmitted signal of the tested system is F2=2025 MHz, the corresponding calibration antenna gain is Gr=16.5 dBW, and the feeder line loss Lr=3 dBW between the calibration antenna and the power meter is bound into test software;
Step 6: according to the calibration antenna, the polarization mode and the pitch angle of the antenna to be tested, the polarization loss lp=3 dBW and the atmospheric and multipath loss La=1 are bound into test software.
(2) Tracking process
Step 1: the tested system controls the wave beam to aim at the beacon of the unmanned plane;
step 2: observing the angle error demodulation condition, and ensuring the normal angle error demodulation;
step 3: and if the beam is always aligned with the corresponding beacon, the unmanned aerial vehicle is flown.
(3) Test procedure
Step 1:
a) Setting the local oscillation source transmitting local oscillation of the clock as low local oscillation 2150MHz, and setting the frequency as F1=1765 MHz corresponding to L frequency band transmitting;
b) Setting the local oscillation source emission local oscillation of the clock to be high local oscillation 2450MHz, and setting the frequency to be F2=2025 MHz corresponding to S frequency band emission;
Step 2: the tested system controls the antenna beam to point to the unmanned aerial vehicle, the test software sets an output power value, the tested system outputs a single carrier wave, and the signal power is a medium-strength signal;
step 3: after a power meter on the unmanned aerial vehicle receives the signal, adjusting the output power of a tested system to be maximum, transmitting the real-time signal power Se measured by the power meter back to the unmanned aerial vehicle control terminal through a reverse link, and finally transmitting the real-time signal power to the tested system through a test network by the unmanned aerial vehicle control terminal;
Step 4: calculating the space transmission loss Le of the signal by using the tested system coordinates, the unmanned plane coordinates and the frequency F1/F2 for testing by using the testing software;
step5: calculating the EIRP value of the system at the angle and the frequency by using the following formula;
EIRP＝Se+Le+La+Lp+Lr-Gr (1-4)
Step 6: selecting a plurality of traversal points in the flight process of the unmanned aerial vehicle, stably tracking the unmanned aerial vehicle by an antenna, and repeating the steps (2) - (5) to obtain EIRP values of the tested system at the plurality of traversal points;
Step 7: the system EIRP value is stored in the test software with the beam pointing angle as an index.
(4) Data recording
The tested system uses L frequency band transmitting signals, and after the unmanned aerial vehicle winds the tested system, the following traversing points are screened from the positioning coordinates forwarded to the test software by the unmanned aerial vehicle control terminal and stored, as shown in tables 1-3.
Tables 1-3EIRP value test key traversal Point coordinate List
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The operating frequency point of the tested system is 1765MHz, and the test record of the equivalent omnidirectional radiation power (EIRP value) is shown in tables 1-4.
Tables 1-4 equivalent omnidirectional radiation power test record table (f1=1765 MHz)
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And the tested system uses an S frequency band to transmit signals, and after the unmanned aerial vehicle winds the tested system, the unmanned aerial vehicle control terminal screens out the determined traversal points from the positioning coordinates forwarded to the test software for storage, as shown in tables 1-3.
The operating frequency point of the tested system is 2025MHz, and the test record of the equivalent omnidirectional radiation power (EIRP value) is shown in tables 1-5.
Tables 1-5 equivalent omnidirectional radiation power test record table (f2=2025mhz)
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The above embodiments are only illustrative of the method steps of the present invention and their core ideas, and are not intended to limit the present invention. Modifications and variations may be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the invention. Accordingly, it is intended that all equivalent modifications and variations of the invention be covered by the claims of this invention, which are within the skill of those skilled in the art, can be made without departing from the spirit and scope of the invention disclosed herein.
Claims (1)
1. The automatic index testing method for the full airspace phased array measurement and control system based on the unmanned aerial vehicle platform is characterized by comprising the following steps of:
s1, determining test conditions: the system comprises field conditions, equipment test conditions and limiting conditions in test, wherein the test equipment comprises a set of full airspace phased array measurement and control system, an unmanned aerial vehicle with an S-band beacon machine, a calibration antenna and a GPS positioning function, a set of reference stations and a set of unmanned aerial vehicle ground control terminal capable of establishing communication and control links with the unmanned aerial vehicle;
s2, designing a flight track:
(1) Determining beam coverage: aiming at a hemispherical conformal full airspace phased array antenna, the coverage area of the phased array antenna projected on the surface of the phased array antenna through a sub airspace covered by beam forming does not exceed psi DEG in azimuth/pitch angle;
(2) Unmanned aerial vehicle traversing point design
Covering the surface of the hemispherical conformal phased array antenna by using a circular inscribed equilateral triangle, so that the bottom edge of the triangle is clung to the contact position of the hemispherical conformal phased array antenna and the ground, wherein for a low elevation angle part, the radius of an inscribed small circle is r=tan (x/2) x R, the side length of the inscribed triangle of the small circle is s=2×r×cos (30 degrees), and for a high elevation angle part, the radius of the circumscribed small circle is r1=tan (y/2) x R, the side length of the inscribed triangle of the small circle is s1=2×r1×cos (30 degrees), wherein R is the radius of the hemispherical conformal phased array antenna, x is the angle of the low elevation angle part, x is less than or equal to psi, y is the angle of the high elevation angle part, and x < y is less than or equal to psi; setting a small circle for the normal tangent line part of the highest point of the hemispherical conformal phased array antenna surface, wherein the radius of the small circle is equal to the radius of the circumscribed small circle of the high elevation part, and the side length of the inscribed triangle of the small circle is equal to the side length of the inscribed triangle of the circumscribed small circle of the high elevation part;
After covering the hemispherical conformal phased array antenna surface, dividing each row of small circles into a group by taking 3/2 inscribed triangle side length as a unit, adding one more public triangle area between every two groups, accumulating one more circumscribed small circle in the area, and obtaining each row of maximally divisible n m groups by numerical simulation calculation, wherein the maximally arrangeable inscribed triangle number of each row is q m＝nm×2+(nm -1); the azimuth angle degree to be traversed in each row is delta m＝360/qm+360/qm×[0qm -1, and then the pitch angle of the circle center point of each inscribed triangle in each row is obtained through space geometry calculation The coordinate of each traversing point is (delta m,θm), wherein m=1, …, M and M are the rows to be traversed on the hemispherical conformal phased array antenna surface;
S3, respectively testing the receiving quality factor and the equivalent radiation omnidirectional power of the full-space-domain phased array measurement and control system
The reception quality factor test includes the following sub-steps:
(1) Preparation process
Step 1: stopping the full airspace phased array measurement and control system on a flat open field level, powering up and automatically leveling;
Step 2: the antenna is lifted, the coordinates of the phase center point of the antenna of the tested system are calibrated, and test software is bound;
Step 3: powering up equipment on the unmanned aerial vehicle, setting output power St and frequency Fg of a beacon machine, and outputting an S frequency band signal through a calibration antenna;
step 4: according to the pre-calibrated transmission feeder line insertion loss Lt and the calibrated antenna gain Gt, the EIRP of the beacon transmission is calculated by the following formula;
EIRP＝St-Lt+Gt
wherein EIRP is equivalent omnidirectional radiation power of the calibration tower, st is transmission signal power of the calibration tower, lt is feeder loss of the calibration tower, and Gt is gain of a transmission antenna of the calibration tower;
Step 5: the unmanned aerial vehicle ground control terminal sends the unmanned aerial vehicle real-time positioning coordinates to test software, and the test software calculates the distance Dg between the unmanned aerial vehicle and the tested system according to the tested system antenna phase center coordinates;
Step 6: the tested system controls the antenna beam to point to cold air, the gain modulation of a receiving link is maximum, the received signal is calibrated, the measured noise power spectral density is N 0, and the noise power spectral density is bound into test software;
Step 7: binding the polarization loss Lp, the atmosphere and the multipath loss La into test software according to the calibration antenna, the polarization mode of the antenna to be tested and the pitch angle;
(2) Tracking process
Step 1: the tested system controls the wave beam to aim at the beacon of the unmanned plane;
step 2: observing the angle error demodulation condition, and ensuring the normal angle error demodulation;
step 3: if the beam is always aligned with the corresponding beacon, the unmanned aerial vehicle is flown;
(3) Test procedure
Step 1: the testing software controls the frequency spectrograph, calibrates the received signal, measures the signal power Sg, and calculates the signal-to-noise ratio Sg/N 0;
Step 2: the test software calculates the linear distance between the coordinates of the system to be tested and the real-time positioning information of the unmanned aerial vehicle by utilizing the coordinates of the system to be tested and the real-time positioning information of the unmanned aerial vehicle, and calculates the space transmission loss Lg of the signal by utilizing the following formula according to the frequency used by the test;
Lg＝32.45+20lgFg(MHz)+20lgDg(km)；
Step 3: the test software calculates the G/T value at this angle, at this frequency using the following equation:
G/T＝Sg/N0-EIRP+Lg+La+Lp+k
k in the formula is Boltzmann constant;
Step 4: selecting a plurality of traversal points in the flight path of the unmanned aerial vehicle, and repeating the testing sub-steps (1) - (3) to obtain G/T values of the tested system at the plurality of traversal points;
step 5: the test software stores the G/T value of the tested system by taking the beam pointing angle as an index;
the equivalent omnidirectional radiation power test comprises the following substeps:
(1) Preparation work
Step 1: stopping the full airspace phased array measurement and control system on a flat open field level, powering up and automatically leveling;
Step 2: the antenna is lifted, the phase center coordinates of the antenna of the tested system are calibrated, and test software is bound;
step 3: the unmanned aerial vehicle is provided with a power meter, and signals are received through a calibration antenna;
Step 4: the unmanned aerial vehicle ground control terminal sends unmanned aerial vehicle real-time positioning data to test software, and the test software calculates the distance De between the unmanned aerial vehicle and the tested system according to the phase center coordinates of the tested system antenna;
Step 5: binding the calibration antenna gain Gr, the feeder line loss Lr between the calibration antenna and the power meter into test software;
step 6: binding the polarization loss Lp, the atmosphere and the multipath loss La into test software according to the calibration antenna, the polarization mode of the antenna to be tested and the pitch angle;
(2) Tracking process
Step 1: the tested system controls the wave beam to aim at the beacon of the unmanned plane;
step 2: observing the angle error demodulation condition, and ensuring the normal angle error demodulation;
step 3: if the beam is always aligned with the corresponding beacon, the unmanned aerial vehicle is flown;
(3) Test procedure
Step 1:
a) Setting the local oscillation source transmitting local oscillation of the clock as low local oscillation 2150MHz, corresponding to L frequency band transmitting, and setting the L frequency band frequency as F1;
b) Setting the local oscillation source transmitting local oscillation of the clock to be high local oscillation 2450MHz, and setting the S frequency band transmitting corresponding to the S frequency band frequency to be F2;
Step 2: the tested system controls the antenna beam to point to the unmanned aerial vehicle, the test software sets an output power value, the tested system outputs a single carrier wave, and the signal power is a medium-strength signal;
Step 3: after a power meter on the unmanned aerial vehicle receives the signal, adjusting the output power of a tested system to be maximum, transmitting the real-time signal power Se measured by the power meter back to the unmanned aerial vehicle control terminal through a reverse link, and finally transmitting the real-time signal power to test software through a test network by the unmanned aerial vehicle control terminal;
Step 4: using the measured system coordinates, unmanned plane coordinates and test frequency, the test software calculates the space transmission loss Le of the signal by using the following formula;
Le＝32.45+20lgF1(MHz)+20lgDe(km)
Le＝32.45+20lgF2(MHz)+20lgDe(km)
Step 5: the EIRP value of the tested system at the angle and the frequency is calculated by using the following steps;
EIRP＝Se+Le+La+Lp+Lr-Gr
step 6: selecting a plurality of traversal points in the flight process of the unmanned aerial vehicle, stably tracking the unmanned aerial vehicle by an antenna, and repeating the steps 2-5 to obtain EIRP values of the tested system at the plurality of traversal points;
Step 7: the system EIRP value is stored in the test software with the beam pointing angle as an index.
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