CN111044968A - Device and method for measuring direction finding precision and acting distance of airborne search positioning terminal - Google Patents
Device and method for measuring direction finding precision and acting distance of airborne search positioning terminal Download PDFInfo
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- CN111044968A CN111044968A CN201911408436.3A CN201911408436A CN111044968A CN 111044968 A CN111044968 A CN 111044968A CN 201911408436 A CN201911408436 A CN 201911408436A CN 111044968 A CN111044968 A CN 111044968A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S3/00—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received
- G01S3/02—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received using radio waves
- G01S3/023—Monitoring or calibrating
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Abstract
The invention discloses a device and a method for measuring direction-finding precision and action distance of an airborne searching and positioning terminal, which are based on a differential directional locator and are derived through a structural design and a test principle, so that the synchronous measurement of the direction-finding precision and the action distance of the searching and positioning terminal is realized; meanwhile, the dynamic performance of the airborne search positioning terminal can be measured, the accuracy of direction finding precision measurement is improved, and the measurement error is smaller than 1 degree; meanwhile, the working performance of the equipment under the postures of pitching, rolling and the like of the airplane can be simulated and tested, and the test results of the antenna of the equipment at different installation positions of the belly and the back of the airplane can be automatically converted, so that a reliable and effective verification method is provided for a ground simulation test of an airborne search terminal before scientific research and installation, and the product development period can be effectively shortened; through the ground simulation use scene, discover early and solve and equip latent service problem, improve flight test throughput.
Description
Technical Field
The invention belongs to the technical field of electronic measurement, and particularly relates to a device and a method for measuring the direction-finding precision and the acting distance of an airborne search positioning terminal, which are used for accurately measuring the direction-finding precision and the acting distance of airborne search positioning terminal equipment in an outdoor environment.
Background
The airborne search positioning terminal is an incoming wave signal transmitted by a measurement target, is mainly used for airborne navigation equipment for air-ground/air-sea search and rescue, air-ground auxiliary homing and air-air convergence guidance, and generally works in an ultrashort wave frequency band. The active airborne searching and positioning terminal mainly comprises an airborne lifesaving radio station and an ultrashort wave direction finder. In order to measure the main technical properties of the device (direction finding accuracy, range), a reliable test method and test apparatus are required. At present, in order to complete the test of the direction-finding accuracy and the acting distance of an airborne search positioning terminal, the method mainly includes the following three methods:
one method is to adopt an internal field detector to check the direction-finding precision of the device through the near-field radiation of a symmetrical antenna, and the method cannot check the action distance of the device, simulate the actual use scene and reflect the actual use effect of an external field, such as the influence of environmental conditions such as an electromagnetic environment, direction-finding height difference and the like.
The second method is to perform direction finding on an emission source within a range of visual range through a mechanical turntable provided with an antenna of the device to be tested, observe a direction finding result through a device debugging interface, and perform functional inspection on the device.
The last method is that the outfield adopts a handheld GPS locator and a magnetic compass device to respectively obtain the longitude and latitude position information, the course angle and the like of a discrete static test point and a target point, and the theoretical azimuth and distance are obtained through manual calculation and are compared with the measured value of the device.
Disclosure of Invention
In order to solve the problems, the invention aims to provide a device and a method for measuring the direction-finding precision and the acting distance of an airborne searching and positioning terminal, and the device and the method are based on a differential GPS directional locator, and realize the synchronous measurement of the direction-finding precision and the acting distance of the searching and positioning terminal through structural design and derivation of a test principle; meanwhile, the dynamic performance of the airborne search positioning terminal can be measured, the accuracy of direction finding precision measurement is improved, and the measurement error is smaller than 1 degree.
In order to achieve the above object, the present invention adopts the following technical solutions.
The measuring device for the direction-finding precision and the acting distance of the airborne searching and positioning terminal comprises
The antenna device comprises a support frame, wherein a support platform is arranged at the upper end of the support frame, a bearing seat is fixed on the support platform, a bearing is matched on the bearing seat, a rotating shaft is vertically arranged in the bearing, an installation disc is hinged to the upper end of the rotating shaft, and an antenna of equipment to be tested is installed on the installation disc; a pitch angle adjusting mechanism is arranged between the mounting disc and the rotating shaft;
when the device antenna to be tested is a circular-like antenna, the device antenna to be tested is arranged in the center of the mounting disc, and the first GPS antenna and the second GPS antenna are symmetrically arranged on two sides of the device antenna to be tested in the diameter direction of the mounting disc;
when the device antenna to be tested is a knife-shaped antenna, a pair of knife-shaped antennas are symmetrically arranged relative to the diameter direction of the mounting disc, and the first GPS antenna and the second GPS antenna are symmetrically arranged relative to the midpoint of a phase center connecting line of the pair of knife-shaped antennas;
the differential directional locator is used for measuring the current position information and course information of the antenna of the equipment to be measured, the theoretical azimuth angle of the target relative to the course of the antenna of the equipment to be measured, the phase center of the antenna of the equipment to be measured and the position information of the target;
the device antenna to be tested is an airborne searching and positioning terminal, the position information is longitude and latitude information, and 0 degree of the device antenna to be tested points to a first GPS antenna; the quasi-circular antenna is a cylindrical antenna array or an annular cavity antenna.
Further, every single move adjustment mechanism contains card and many gears latch, the card is articulated with the pivot, many gears latch and mounting disc bottom surface fixed connection, the card cooperatees with many gears latch for adjust and fix the angle of pitch of the equipment antenna that awaits measuring.
Further, the distance between the phase center of the first GPS antenna and the phase center of the second GPS antenna is greater than 1.2 m.
Further, when the antenna of the device to be tested is a circular antenna, a round hole is formed in the center of the installation turntable, a concave basin is installed at the position of the round hole in a matched mode, and the antenna of the device to be tested is installed in the concave basin.
Furthermore, the bottom surface of the concave basin is hinged with the rotating shaft.
Further, the edge of the mounting disc is provided with a hinge.
Further, the support frame is a triangular support frame.
Furthermore, the support frame is a four-corner support frame, and each support rod of the four-corner support frame is provided with an installation screw hole.
Further, the differential directional locator is a differential GPS directional locator, a differential Beidou directional locator or a differential GPS/Beidou dual-frequency directional locator.
Furthermore, the differential directional locator is connected with an upper computer through an RS232 serial port.
(II) the method for measuring the direction-finding precision and the acting distance of the airborne searching and positioning terminal comprises the following steps:
wherein the included angle α is an included angle relative to the north;
the position information of the target is the longitude and latitude of the target;
and 3, calculating the theoretical orientation gamma of the target relative to the heading of the aircraft as follows:
γ＝β-α+360°(β＜α)，
γ＝β-α(β＞α)；
the value ranges of α, β and gamma are (0-359 degrees), when the antenna of the equipment to be tested is installed, the antenna points to the first GPS antenna at 0 degree and points to the second GPS antenna at 180 degrees;
and 7, simulating the change of the pitching angle of the airplane through the pitching angle adjusting mechanism, and repeating the steps 1-6 to obtain the direction-finding precision and the acting distance under different pitching angles of the airplane.
Compared with the prior art, the invention has the beneficial effects that:
(1) the invention is based on the differential directional locator, and realizes the synchronous measurement of the direction-finding precision and the acting distance of the searching and positioning terminal through structural design and the derivation of a test principle; meanwhile, the dynamic performance of the airborne search positioning terminal can be measured, the accuracy of direction finding precision measurement is improved, and the measurement error is smaller than 1 degree.
(2) The invention effectively solves the problem that the direction-finding precision and the acting distance of the airborne search positioning terminal can not be accurately, synchronously and dynamically measured in an external field environment, can simulate and test the working performance of equipment in the postures of pitching, rolling and the like of an airplane, and automatically converts the test results of the antenna of the equipment at different installation positions of the belly and the back of the airplane, thereby providing a reliable and effective verification method for the ground simulation test of the airborne search terminal before scientific research and installation, and effectively shortening the product development period; through the ground simulation use scene, discover early and solve and equip latent service problem, improve flight test throughput.
(3) The measuring device has the advantages of simple operation steps, conventional and few types of required test tools and instruments, visual display of test results, good real-time performance, synchronous storage and recording of test data, and convenience for further analysis after testing.
Drawings
The invention is described in further detail below with reference to the figures and specific embodiments.
FIG. 1 is a three-dimensional view of a test apparatus in an embodiment of the invention;
FIG. 2 is a top three-dimensional view of FIG. 1;
FIG. 3 is a three-dimensional view of FIG. 2 after installation of the quasi-circular antenna;
FIG. 4 is a three-dimensional view of FIG. 2 with the blade antenna installed;
FIG. 5 is a three-dimensional view of a testing device in accordance with another embodiment of the present invention;
FIG. 6 is a top three-dimensional view of FIG. 5 with the quasi-circular antenna installed;
FIG. 7 is a top three-dimensional view of FIG. 5 with the blade antenna installed;
FIG. 8 is a schematic diagram of the connection of the testing apparatus in the embodiment of the present invention;
FIG. 9 is a schematic diagram of a test apparatus in an embodiment of the invention;
fig. 10 is a schematic view of a display interface of the upper computer.
In the above figures, 1 support frame; 101 supporting a platform; 2, a differential directional locator; 3, bearing seats; 4, a rotating shaft; 5, mounting a disc; 6, an antenna of the equipment to be tested; a circular antenna of type 601; 602 a blade antenna; 7 a first GPS antenna; 8 a second GPS antenna; 9, a pitch angle adjusting mechanism; 901 cards; 902 multi-gear latch; 10, a concave basin; and 11, a hinge.
Detailed Description
The embodiments and effects of the present invention will be described in further detail below with reference to the accompanying drawings.
Example 1
Referring to fig. 1-8, the device and method for measuring the direction-finding accuracy and the acting distance of an airborne search positioning terminal comprises a support frame 1 and a differential directional locator 2, wherein a support platform 101 is arranged at the upper end of the support frame 1, a bearing block 3 is fixed on the support platform 101, a bearing is matched on the bearing block 3, a rotating shaft 4 is vertically arranged in the bearing, an installation disc 5 is hinged to the upper end of the rotating shaft 4, and an antenna 6 of equipment to be measured is installed on the installation disc 5; a pitch angle adjusting mechanism 9 is arranged between the mounting disc 5 and the rotating shaft 4;
when the device antenna 6 to be tested is the quasi-circular antenna 601, the device antenna 6 to be tested is arranged at the center of the mounting disc 5, and the first GPS antenna 7 and the second GPS antenna 8 are symmetrically arranged on two sides of the device antenna 6 to be tested in the diameter direction of the mounting disc 5; as shown in fig. 3 and 6, when the antenna 6 of the device under test is the blade antenna 602, the pair of blade antennas 602 are symmetrically arranged with respect to the diameter direction of the mounting plate 5, and the first GPS antenna 7 and the second GPS antenna 8 are symmetrically arranged with respect to the midpoint of the connecting line of the phase centers of the pair of blade antennas 602; and the differential directional locator 2 is used for measuring the current position information and course information of the antenna 6 of the equipment to be measured, the theoretical azimuth angle of the target relative to the course of the antenna 6 of the equipment to be measured, the phase center of the antenna 6 of the equipment to be measured and the position information of the target.
In the above embodiment, the support frame 1 and the support platform 101 are used for ensuring the stability of the measuring device, the bearing block 3 is matched with a bearing, the rotating shaft 4 is vertically arranged in the bearing, the upper end of the rotating shaft 4 is hinged with the mounting disc 5, the mounting disc 5 is provided with the antenna 6 of the device to be measured, the rotating shaft 4 rotates to drive the mounting disc 5 to rotate, and then each antenna on the mounting disc horizontally rotates; the upper end of the rotating shaft 4 is hinged with a mounting disc 5, a pitch angle adjusting mechanism 9 is arranged between the mounting disc 5 and the rotating shaft 4, the pitch angle of the mounting disc 5 is adjusted through the pitch angle adjusting mechanism 9, and then the pitch angle of the antenna 6 of the device to be tested is changed, so that the condition of the aircraft under different pitch angle postures is simulated for testing.
As shown in fig. 3 and 6, when the device antenna 6 to be tested is a quasi-circular antenna 601, the device antenna 6 to be tested is disposed at the center of the mounting plate 5, and the first GPS antenna 7 and the second GPS antenna 8 are symmetrically disposed at two sides of the device antenna 6 to be tested in the diameter direction of the mounting plate 5; as shown in fig. 4 and 7, when the device antenna 6 to be tested is a blade antenna 602, a pair of blade antennas 602 are symmetrically arranged with respect to the diameter direction of the mounting plate 5, and the first GPS antenna 7 and the second GPS antenna 8 are symmetrically arranged with respect to the midpoint of the connecting line of the phase centers of the pair of blade antennas 602; the differential directional locator 2 receives the position and orientation information of the first GPS antenna 7 and the second GPS antenna 8 through the antenna interface. The current position information and course information of the antenna 6 of the equipment to be tested, the theoretical azimuth angle of the target relative to the course of the antenna 6 of the equipment to be tested, the phase center of the antenna 6 of the equipment to be tested and the position information of the target can be obtained through calculation.
The differential directional locator is a differential GPS directional locator, a differential Beidou directional locator or a differential GPS/Beidou dual-frequency directional locator; the quasi-circular antenna is a cylindrical antenna array or an annular cavity antenna.
Referring to fig. 1, according to an embodiment of the present invention, the pitch adjustment mechanism includes a clamping plate 901 and a multi-gear clamping tooth 902, the clamping plate 901 is hinged to the rotating shaft 4, the multi-gear clamping tooth 902 is fixedly connected to the bottom surface of the mounting plate 5, and the clamping plate 901 is matched with the multi-gear clamping tooth 902 to adjust and fix the pitch angle of the mounting plate 5.
In the above embodiment, the fixed end card on the card 901 is connected to different gears of the multi-gear latch 902, and connection arcs with different lengths are formed between the rotating shaft 4 and the bottom surface of the mounting disc, so that the pitch angle of the mounting disc 5 and the antenna 6 of the device to be tested thereon is adjusted, and the test performance of the test device in different pitching postures of the aircraft can be simulated.
Referring to fig. 2-7, according to one embodiment of the present invention, the distance between the phase center of the first GPS antenna 7 and the phase center of the second GPS antenna 8 is not less than 1.2 m.
In the above embodiment, the distance between the phase center of the first GPS antenna 7 and the phase center of the second GPS antenna 8 is the baseline length R, and the theoretical orientation accuracy of the differential GPS positioning device 2 is 2/R, so that the distance range is set so as to ensure the direction finding accuracy of the device, and the baseline length is generally determined to be 1.5m in accordance with the actual installation conditions (the width of the test vehicle) and the convenience of installation operation.
Referring to fig. 1-2, according to an embodiment of the present invention, when the device antenna 6 to be tested is a circular-like antenna 601, a circular hole is formed in the center of the mounting plate, a concave basin 10 is mounted at the circular hole in a matching manner, and the device antenna 6 to be tested is mounted in the concave basin 10; the bottom surface of the concave basin 10 is hinged with the rotating shaft 4.
In the above embodiment, the arrangement of the concave basin 10 enables the device to be suitable for different types of quasi-circular airborne search positioning terminal antennas, such as quasi-circular antennas like a cylindrical antenna array and an annular cavity antenna, which are convenient to install. For a blade antenna, it may be mounted directly to mounting plate 5 by means of quick release screws.
Referring to fig. 1-2, according to one embodiment of the present invention, hinges 11 are provided at the edges of the mounting plate 5.
In the above embodiment, the hinge 11 is provided at the edge of the mounting plate 5 for easy carrying after folding.
Referring to fig. 3, the support frame 1 is a tripod support frame 1 according to an embodiment of the present invention.
In the above embodiment, the supporting frame 1 is the triangular supporting frame 1, so that the test can be conveniently carried out in a near field, a high point or a static state, the measurement can be carried out only by supporting the triangular supporting frame 1 on the ground, and the portable and mobile measurement device is convenient to carry and move.
Referring to fig. 1-2, according to an embodiment of the present invention, the supporting frame 1 is a quadrangular supporting frame 1, and each supporting rod of the quadrangular supporting frame 1 is provided with a mounting screw hole.
In the above embodiment, the device is conveniently installed on the top of the medium-sized multipurpose communication test vehicle by the bolts penetrating through the installation screw holes, and can provide stable power supply for instruments and equipment by depending on the self-provided power supply of the test vehicle, and the measurement test can be completed under the static or driving state of the vehicle.
Referring to fig. 8, according to an embodiment of the present invention, the differential directional locator 2 is connected to an upper computer through an RS232 serial port.
In the above embodiment, the upper computer is used to complete the real-time display, storage and working state control of the relevant test information. The main functions of the upper computer comprise positioning and orientation result display, theoretical relative azimuth and action distance calculation, equipment test result and test error calculation, test data recording and the like. The display and control function interface is shown in fig. 10.
And the upper computer receives and displays the current position information and the current course information of the carrier through a 232 serial port of the differential directional locator 2. When target position information is input to the upper computer, the geographic position of the target, the theoretical position of the target relative to the carrier and the distance between the target and the carrier can be automatically calculated and displayed;
the upper computer receives and displays the actual measurement direction of the equipment through a 232 serial port of the host computer of the equipment to be measured, and completes operation control of the working mode of the equipment and the like;
and the upper computer can obtain the direction-finding error of the antenna 6 of the equipment to be measured by synchronously comparing and calculating the theoretical direction and the actual-measured direction.
The device is adopted to carry out an outfield test, the mounting disc of the antenna turntable is formed by cutting and processing a finished aluminum plate with the thickness of 1mm, and the rotating shaft and the mounting base are both completed by adopting an aluminum block processing center. And opening holes in the antenna mounting plate according to the outline dimensions and the mounting mode of the Beidou/GPS antenna and the equipment to be tested.
The specific shape, size and fastening mode of the antenna turntable are not limited to the shown appearance and size, and the antenna turntable can be in other forms with the same working mode.
Example 2
Referring to fig. 8-9, for a certain emission source, i.e. a target, the method for measuring the direction-finding accuracy and the range of the airborne search positioning terminal of the present invention comprises the following steps:
wherein the included angle α is an included angle relative to the north;
the position information of the target is the longitude and latitude of the target;
and 3, calculating the theoretical orientation gamma of the target relative to the heading of the aircraft as follows:
γ＝β-α+360°(β＜α)，
γ＝β-α(β＞α)；
the value ranges of α, β and gamma are (0-359 degrees), when the antenna of the equipment to be tested is installed, the antenna of the equipment to be tested points to the first GPS antenna at 0 degree, and points to the second GPS antenna 8 at 180 degrees;
and 7, simulating the change of the pitching angle of the airplane through the pitching angle adjusting mechanism, and repeating the steps 1-5 to obtain the direction-finding precision and the acting distance under different pitching angles of the airplane.
For the test device, according to the antenna installation position (the machine back or the machine belly) of the antenna 6 of the equipment to be tested, an upper antenna or a lower antenna is selected, and a test result is converted, so that the test condition under the installation environment is simulated.
The specific conversion process is as follows:
(1) orientation calculation
a)γ＝Atan2[cos(lat1)×sin(lat2)-sin(lat1)×cos(lat2)×cos(lon2-lon1)，sin(lon2-lon1)×cos(lat2)]；
Wherein γ is a radian system, Atan2 is a four-quadrant arctan function, (lat1, lon1), (lat2, lon2) are position information (radian system) of an antenna and a target of the device to be tested, namely longitude and latitude information, respectively;
b) converting gamma into an angle system by using a DEGREE radian conversion function, wherein the converted gamma belongs to (-180 DEGREEs and 180 DEGREEs);
c) and converting gamma into a value range of 0-359 degrees by using an MOD (modified MOD) remainder function, namely gamma is MOD (gamma +360 degrees and 360 degrees).
(2) Distance of action calculation
D ═ arcos [ sin (lat1) × sin (lat2) + cos (lat1) × cos (lat2) × cos (lon2-lon1) ] × 6371, where D is km.
One specific embodiment of the test apparatus of the present invention is given below:
as shown in FIG. 1, the mounting plate 5 is an aluminum plate having a diameter of 1500mm and a thickness of 1.5mm, and weighs about 14 kg. Cutting off the edge part at a position 350mm away from the edge of the mounting disc 5, and additionally installing a hinge 11 with the same size for folding so as to facilitate carrying; 2 GPS antennas are fixedly arranged on the mounting disc 5 in the diameter direction; the hollow portion is used for mounting the device under test antenna 6. The mounting plate 5 is designed with a planar opening and a sunken concave basin 10 to meet the mounting requirements of different types of antennas.
The bottom of the mounting disc 5 is provided with a mounting bracket which is about 2.5kg in weight and is connected with the mounting disc 5 with the diameter of 1500mm by screws, and the bottom of the mounting bracket is connected with a rotating shaft 4 which is about 2.2kg in weight; the rotating shaft 4 is hinged with the mounting plate 5.
The pitch angle adjusting mechanism is used for controlling the pitch angle of the mounting disc 5 so as to simulate the change of the pitch angle of the airplane. The adjustable angle can be manually adjusted, and can also be accurately adjusted by adopting a stepping motor, and the adjustment range is 0-20 degrees. The mounting disc 5 is made of aluminum plates through cutting and processing, the rotating shaft 4 and the mounting base are made of aluminum blocks through a processing center, no complex and special-shaped parts exist, and the production line is good. And (5) perforating the antenna mounting disc 5 according to the antenna shape and the mounting mode of the equipment to be tested.
The support frame 1 of the present invention can be modified according to the installation conditions of the test vehicle.
The performance of a certain type ultrashort wave locator is tested in a suburban combined area by adopting the device. The accompanying and testing equipment is a handheld lifesaving radio station (emission source), the equipment to be tested is a certain type ultrashort wave direction finder, the accompanying and testing equipment and the test point have the altitude difference of 60m, the distance of 22km and the test frequency point of 245.5MHz, and the testing device is erected on the roof. Through tests, the relative orientation is changed respectively according to the modes of rotating the antenna disc under the static condition of the vehicle, driving the vehicle in a dynamic curve and the like, the current theoretical orientation and distance of the target and the orientation and direction-finding errors thereof measured by the ultrashort wave direction finder can be read in real time through display and control software, the measured data can be recorded in real time, the expected test target is realized, and the test aim is achieved.
The use method of the device comprises the following steps:
the working process of the device comprises the following steps:
(a) the test apparatus is connected as shown in fig. 8, confirming that the device under test antenna 6 is pointing "zero" to the first GPS antenna 7.
(b) Opening the differential directional positioning equipment, connecting the data communication interface to the upper computer, starting up for about 1min,
(c) confirming that the test interface obtains longitude and latitude information and course angle information of the current position;
(d) inputting longitude and latitude information of a target point through a display control computer of an upper computer, and automatically calculating the current distance; setting working parameters of the equipment to be tested through a display control computer;
(e) the direction finding result is read through the display control interface, the static performance index of the equipment is measured, and the direction finding precision can be directly read;
(f) after the static working state is confirmed to be normal, the mounting disc 5 is controlled to rotate through manual operation or a motor, namely the relative direction of the target is changed, and the direction tracking change condition and the real-time direction-finding precision are observed through a display control computer;
(g) adjusting the inclination of the mounting disc 5 to simulate the pitching or rolling postures of the airplane, and testing the working performance of the equipment in different postures;
the tester can download and store the test data as required for further analysis.
The above description is only for the specific embodiments of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive of the changes or substitutions within the technical scope of the present invention, and all the changes or substitutions should be covered within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (10)
1. Measurement device of location terminal direction finding precision and working distance is searched to airborne, its characterized in that includes:
the antenna device comprises a support frame, wherein a support platform is arranged at the upper end of the support frame, a bearing seat is fixed on the support platform, a bearing is matched on the bearing seat, a rotating shaft is vertically arranged in the bearing, an installation disc is hinged to the upper end of the rotating shaft, and an antenna of equipment to be tested is installed on the installation disc; a pitch angle adjusting mechanism is arranged between the mounting disc and the rotating shaft;
when the device antenna to be tested is a circular-like antenna, the device antenna to be tested is arranged in the center of the mounting disc, and the first GPS antenna and the second GPS antenna are symmetrically arranged on two sides of the device antenna to be tested in the diameter direction of the mounting disc;
when the device antenna to be tested is a knife-shaped antenna, a pair of knife-shaped antennas are symmetrically arranged relative to the diameter direction of the mounting disc, and the first GPS antenna and the second GPS antenna are symmetrically arranged relative to the midpoint of a phase center connecting line of the pair of knife-shaped antennas;
the differential directional locator is used for measuring the current position information and course information of the antenna of the equipment to be measured, the theoretical azimuth angle of the target relative to the course of the antenna of the equipment to be measured, the phase center of the antenna of the equipment to be measured and the position information of the target;
the device antenna to be tested is an airborne searching and positioning terminal, the position information is longitude and latitude information, and 0 degree of the device antenna to be tested points to a first GPS antenna; the quasi-circular antenna is a cylindrical antenna array or an annular cavity antenna.
2. The device for measuring the direction-finding accuracy and the acting distance of the airborne searching and positioning terminal as claimed in claim 1, wherein the pitching adjusting mechanism comprises a clamping piece and a multi-gear clamping tooth, the clamping piece is hinged to the rotating shaft, the multi-gear clamping tooth is fixedly connected with the bottom surface of the mounting plate, and the clamping piece is matched with the multi-gear clamping tooth and used for adjusting and fixing the pitching angle of the antenna of the device to be tested.
3. The apparatus as claimed in claim 1, wherein the distance between the phase center of the first GPS antenna and the phase center of the second GPS antenna is greater than 1.2 m.
4. The device for measuring the direction-finding accuracy and the acting distance of an airborne searching and positioning terminal as claimed in claim 1, wherein when the device antenna to be measured is a circular-like antenna, a circular hole is formed in the center of the mounting plate, a concave basin is mounted at the circular hole in a matched manner, and the device antenna to be measured is mounted in the concave basin.
5. The device for measuring the direction-finding accuracy and the acting distance of the airborne searching and positioning terminal as claimed in claim 4, wherein the bottom surface of the concave basin is hinged with the rotating shaft.
6. The device for measuring the direction-finding accuracy and the acting distance of an airborne searching and positioning terminal as claimed in claim 1, wherein the edge of the mounting plate is provided with a hinge.
7. The apparatus of claim 1, wherein the supporting frame is a triangular frame.
8. The device for measuring the direction-finding accuracy and the acting distance of the airborne searching and positioning terminal as claimed in claim 1, wherein the supporting frame is a four-corner supporting frame, and each supporting rod of the four-corner supporting frame is provided with a mounting screw hole.
9. The device for measuring the direction-finding accuracy and the acting distance of the airborne search positioning terminal according to claim 1, wherein the differential orientation locator is connected with an upper computer through an RS232 serial port.
10. The method for measuring the direction finding precision and the acting distance of the airborne search positioning terminal is characterized by comprising the following steps of:
step 1, acquiring a clockwise included angle α between a phase center line of an antenna of equipment to be tested and an earth meridian where the phase center is located through a differential directional locator;
wherein the included angle α is an included angle relative to the north;
step 2, acquiring an included angle β between the longitude where the connecting line of the target and the phase center are located and the north relative to the ground through the phase center of the antenna of the device to be tested and the position information of the target;
the position information of the target is the longitude and latitude of the target;
and 3, calculating the theoretical orientation gamma of the target relative to the heading of the aircraft as follows:
γ＝β-α+360°(β＜α)，
γ＝β-α(β＞α)；
the value ranges of α, β and gamma are (0-359 degrees), when the antenna of the equipment to be tested is installed, the antenna points to the first GPS antenna at 0 degree and points to the second GPS antenna at 180 degrees;
step 4, measuring the actual measurement direction of the target relative to the carrier by the antenna of the device to be measured;
step 5, calculating the difference between the theoretical direction gamma of the target relative to the course of the carrier and the measured direction of the target relative to the carrier measured by the antenna of the equipment to be measured, namely the direction-finding error of the antenna of the equipment to be measured; obtaining the acting distance of the antenna of the equipment to be tested according to the phase center of the antenna of the equipment to be tested and the position information of the target;
step 6, continuously rotating the antenna mounting disc to control the variation and the variation speed of the relative azimuth, thereby completing the continuous direction finding of the target relative to the carrier within the range of 360 degrees;
and 7, simulating the change of the pitching angle of the airplane through the pitching angle adjusting mechanism, and repeating the steps 1-6 to obtain the direction-finding precision and the acting distance under different pitching angles of the airplane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911408436.3A CN111044968A (en) | 2019-12-31 | 2019-12-31 | Device and method for measuring direction finding precision and acting distance of airborne search positioning terminal |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111983550A (en) * | 2020-08-27 | 2020-11-24 | 航天科工微电子系统研究院有限公司 | Radio direction finding precision test method based on GPS |
| CN112817024A (en) * | 2020-12-30 | 2021-05-18 | 陕西烽火电子股份有限公司 | Airborne search positioning device and method based on Beidou-ultrashort wave-photoelectric sensing |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111983550A (en) * | 2020-08-27 | 2020-11-24 | 航天科工微电子系统研究院有限公司 | Radio direction finding precision test method based on GPS |
| CN111983550B (en) * | 2020-08-27 | 2024-04-12 | 航天科工微电子系统研究院有限公司 | GPS-based radio direction finding precision testing method |
| CN112817024A (en) * | 2020-12-30 | 2021-05-18 | 陕西烽火电子股份有限公司 | Airborne search positioning device and method based on Beidou-ultrashort wave-photoelectric sensing |
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