CN118367329A - Lightweight compact type airborne direction-finding antenna array - Google Patents
Lightweight compact type airborne direction-finding antenna array Download PDFInfo
- Publication number
- CN118367329A CN118367329A CN202410568217.6A CN202410568217A CN118367329A CN 118367329 A CN118367329 A CN 118367329A CN 202410568217 A CN202410568217 A CN 202410568217A CN 118367329 A CN118367329 A CN 118367329A
- Authority
- CN
- China
- Prior art keywords
- antenna array
- radio frequency
- array
- antenna
- hollowed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000011159 matrix material Substances 0.000 claims abstract description 40
- 238000001228 spectrum Methods 0.000 claims abstract description 12
- 235000012431 wafers Nutrition 0.000 claims description 9
- 239000010410 layer Substances 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 6
- 239000011229 interlayer Substances 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 230000035945 sensitivity Effects 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 8
- 238000005516 engineering process Methods 0.000 description 8
- 230000008878 coupling Effects 0.000 description 6
- 238000010168 coupling process Methods 0.000 description 6
- 238000005859 coupling reaction Methods 0.000 description 6
- 238000012544 monitoring process Methods 0.000 description 4
- 230000004044 response Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000001427 coherent effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000007476 Maximum Likelihood Methods 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000010295 mobile communication Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/18—Means for stabilising antennas on an unstable platform
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/285—Aircraft wire antennas
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/50—Structural association of antennas with earthing switches, lead-in devices or lightning protectors
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/52—Means for reducing coupling between antennas; Means for reducing coupling between an antenna and another structure
- H01Q1/521—Means for reducing coupling between antennas; Means for reducing coupling between an antenna and another structure reducing the coupling between adjacent antennas
- H01Q1/523—Means for reducing coupling between antennas; Means for reducing coupling between an antenna and another structure reducing the coupling between adjacent antennas between antennas of an array
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/52—Means for reducing coupling between antennas; Means for reducing coupling between an antenna and another structure
- H01Q1/526—Electromagnetic shields
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Electromagnetism (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
The invention relates to a lightweight compact airborne direction-finding antenna array, which comprises a sealed cavity, wherein an annular hollow bracket is arranged in the sealed cavity, a first antenna array, a second antenna array and a third antenna array are arranged on the annular hollow bracket, the first antenna array, the second antenna array and the third antenna array are sequentially arranged from the outer edge of the annular hollow bracket to the center of the annular hollow bracket, the top of the second antenna array is equal to the top of the first antenna array, the third antenna array is positioned above the first antenna array, a radio frequency matrix switch electrically connected with the first antenna array, the second antenna array and the third antenna array is arranged at the bottom of the sealed cavity, and the first antenna array, the second antenna array, the third antenna array and the radio frequency matrix switch form a three-channel seven-array element space spectrum direction-finding system. The invention has the beneficial effects that: the antenna array can be miniaturized and light, the pneumatic requirement of the machine can be met, the sensitivity is high, and the direction finding accuracy error is small.
Description
Technical Field
The invention relates to the technical field of radio direction finding, in particular to a lightweight compact airborne direction finding antenna array.
Background
At present, the domestic direction-finding antenna array is mainly used for radio monitoring stations and large and medium-sized monitoring vehicles, the antenna array is large in size (more than 1 meter in diameter) and more than 20 kg in weight, and an interferometer direction-finding system is mainly adopted. Antennas are often supported on the ground or roof by towers and supports, several to hundreds of meters from the ground. Even so, the electromagnetic environment of the unmanned aerial vehicle is not comparable to the high altitude, and with the rapid development of unmanned aerial vehicle technology in recent years, the unmanned helicopter is utilized to lift off the monitoring direction-finding equipment so as to obtain a better electromagnetic environment; secondly, the unmanned helicopter platform can be utilized to realize the function of single machine positioning by utilizing the rapid maneuverability of the unmanned helicopter platform; thirdly, through unmanned helicopter platform, can improve the utilization ratio of equipment.
The lift-off of the monitoring equipment and the design of the airborne direction-finding antenna array are the serious difficulties, and mainly face the problems of miniaturization and light weight of the antenna array. In order to prevent mutual influence among array elements, the prior antenna array generally distributes each array element on different heights, the staggered layout increases the space height of the antenna array, is inconvenient to realize miniaturization, has small aperture, is easy to cause phase ambiguity, has great influence on direction finding of an interferometer, and particularly has a frequency band below 300 MHz. In addition, the current array antenna device is more and heavy, and a system which is formed by lifting off a single directional antenna and a most log-periodic antenna and adopts a contrast direction-finding system is adopted, so that the direction-finding accuracy error of the direction-finding system is more than 5 degrees, and the error is larger.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides a lightweight compact airborne direction-finding antenna array, which can realize miniaturization and weight reduction of the antenna array, is beneficial to meeting the aerodynamic requirements of an aircraft, and has high sensitivity and small direction-finding accuracy error.
The aim of the invention is achieved by the following technical scheme:
The utility model provides a lightweight compact type airborne direction finding antenna array, including sealed cavity, be equipped with annular fretwork support in the sealed cavity, be equipped with first antenna array on the annular fretwork support, second antenna array and third antenna array, first antenna array, second antenna array and third antenna array are by annular fretwork support outer edge to annular fretwork support center setting gradually, second antenna array top is high with first antenna array top, third antenna array is located first antenna array top, sealed cavity bottom is equipped with the radio frequency matrix switch with equal electric connection of first antenna array, second antenna array and third antenna array, first antenna array, second antenna array, third antenna array and radio frequency matrix switch constitute the seven array element space spectrum direction finding system of three-channel.
Further, the annular hollowed-out support is of an integrated structure made of honeycomb interlayer materials, the annular hollowed-out support comprises three circular hollowed-out plates and supporting plates, the three circular hollowed-out plates are concentric and sequentially arranged from bottom to top, the diameters of the three circular hollowed-out plates are sequentially reduced from bottom to top, the three circular hollowed-out plates are connected and supported in the sealed cavity through the supporting plates, and the first antenna array, the second antenna array and the third antenna array are sequentially arranged on the three circular hollowed-out plates from bottom to top.
Further, the first antenna array comprises seven first dipole antennas with the working frequency bands of 30MHz-1.3GHz, and the first dipole antennas are distributed on the outer edges of the corresponding circular hollowed-out plates in a circumferential array by taking the circle centers of the circular hollowed-out plates as centers.
Further, the second antenna array comprises seven second dipole antennas with the working frequency ranges of 1GHz-3.6GHz, the second dipole antennas are distributed on the outer edges of the corresponding circular hollowed-out plates in a circumferential array mode by taking the circle centers of the circular hollowed-out plates as centers, and the second dipole antennas and the first dipole antennas are arranged in a staggered mode.
Further, the third antenna array comprises seven FPC antennas with the working frequency ranges of 3GHz-8GHz, the FPC antennas are distributed on the outer edges of the corresponding circular hollowed-out plates in a circumferential array mode by taking the circle centers of the circular hollowed-out plates as centers, and the FPC antennas, the first dipole antennas and the second dipole antennas are all arranged in a staggered mode.
Further, the top and the bottom of the first dipole antenna are both provided with hard plate wafers, the surfaces of the hard plate wafers are provided with metal layers, and the first dipole antenna and the hard plate wafers are of hollow structures.
Further, the bottom of the sealing cavity is provided with a flange, a shielding plate is arranged between the flange and the bottom of the sealing cavity, the middle part of the flange is provided with a switch box integrally formed with the flange, and the radio frequency matrix switch is arranged in the switch box.
Further, the radio frequency matrix switch comprises 28 paths of input ends and 3 paths of output ends, the switch box is provided with 21 radio frequency input interfaces positioned in the sealed cavity, the switch box is also provided with 3 radio frequency output interfaces positioned outside the sealed cavity, 1 calibration signal input interface and 1 control interface, the first dipole antenna, the second dipole antenna and the FPC antenna are electrically connected with the input ends of the radio frequency matrix switch through the radio frequency input interfaces, the 3 radio frequency output interfaces are respectively electrically connected with the 3 paths of output ends of the radio frequency matrix switch, and the calibration signal input interfaces and the control interfaces are electrically connected with the radio frequency matrix switch.
Further, the 21 radio frequency input interfaces are distributed around a central circumferential array of the switch box.
Further, 3 adjustable gain low noise amplifiers, 7 synthesizers and 7 one-to-four switches are further arranged in the switch box, the first dipole antenna and the second dipole antenna are connected to the input ends of the radio frequency matrix switch through radio frequency input interfaces, each FPC antenna corresponds to 1 synthesizer and 1 one-to-four switch, the FPC antenna is connected to the input end of the corresponding one-to-four switch through the radio frequency input interface, 1 output end of one-to-four switch is connected to the input end of the radio frequency matrix switch, the other 3 output ends of one-to-four switch are respectively connected to the input end of the corresponding synthesizer and the input ends of two synthesizers adjacent to the corresponding synthesizer, the output ends of the synthesizers are connected to the input ends of the radio frequency matrix switch, the 3 output ends of the radio frequency matrix switch are respectively connected to the input ends of the 3 adjustable gain low noise amplifiers, and the output ends of the 3 adjustable gain low noise amplifiers are respectively connected to the 3 radio frequency output interfaces.
Compared with the prior art, the invention has the following beneficial effects:
1. The invention solves the difficult problems of miniaturization and light weight of the direction-finding antenna array, and enables the direction-finding antenna array to meet the requirement of the machine and to be successfully used on the machine.
2. The invention solves the electric coupling problem of the dense array technology, reduces the space height requirement relative to the prior staggered array mode by the same-layer staggered array technology, enables the direction-finding antenna array technology to be feasible on the flying platform, simultaneously meets the airborne aerodynamic requirement, and reduces the influence of the large-scale external antenna array on the aerodynamic structure of the flying platform.
3. The invention realizes the separation of coherent same-frequency signals through the three-channel seven-array element space spectrum direction-finding system, and has smaller volume and lighter mass than the existing five-channel and nine-channel space spectrum direction-finding system.
4. The invention can realize the control of the directional diagram of the array elements, can change the sensitivity and the size of the directional diagram of the array elements, and changes the sharpness of the directional diagram by combining the array elements, thereby reducing the coupling among dense array elements and further reducing the influence caused by the coupling through a robust algorithm.
Drawings
FIG. 1 is a schematic view of the external structure of the present invention;
FIG. 2 is a schematic view of the overall internal structure of the sealed cavity of the present invention;
FIG. 3 is a schematic front view showing the internal structure of the sealed cavity in the invention;
FIG. 4 is a schematic top view showing the internal structure of the sealed cavity of the present invention;
FIG. 5 is a schematic view of the bottom structure of the seal chamber of the present invention;
FIG. 6 is a diagram showing the comparison of the synthesized array element and the conventional single omni-directional array element;
fig. 7 is a schematic diagram showing the comparison of the array element response of the synthesized array element and the prior single omni-directional array element.
In the figure: 1. sealing the cavity; 2. a round hollowed-out plate; 3. a support plate; 4. a first dipole antenna; 5. a second dipole antenna; 6. an FPC antenna; 7. a flange; 8. a shielding plate; 9. a switch box; 10. a radio frequency input interface; 11. a radio frequency output interface; 12. a calibration signal input interface; 13. and a control interface.
Detailed Description
The present invention will be further described with reference to the accompanying drawings, but the scope of the present invention is not limited to the following.
A lightweight compact airborne direction-finding antenna array is provided, wherein a first antenna array, a second antenna array and a third antenna array are arranged in a sealed cavity 1, three sets of antenna array elements are provided, and the three sets of antenna array elements can cover VHF/UHF common frequency bands. As shown in fig. 1, the top of the sealed cavity 1 is streamline, and its specific external dimension is Φ720×350mm, and its weight is 5.6kg. In order to achieve miniaturization and light weight of the whole structure and simultaneously prevent the problem of electric coupling of interlayer interference caused by mutual influence among array elements, the invention adopts an array arrangement mode of staggered layers to lay out a first antenna array, a second antenna array and a third antenna array, and three sets of array elements are arranged in a sealed cavity 1 through an annular hollow bracket, and a radio frequency matrix switch is combined to enable the first antenna array, the second antenna array, the third antenna array and the radio frequency matrix switch to form a three-channel seven-array element space spectrum direction finding system.
Specifically, as shown in fig. 2-4, the first antenna array, the second antenna array and the third antenna array are installed on the annular hollow support, and the first antenna array, the second antenna array and the third antenna array are sequentially arranged from the outer edge of the annular hollow support to the center of the annular hollow support, wherein the top of the second antenna array is equal to the top of the first antenna array in height, and the third antenna array is located above the first antenna array. The radio frequency matrix switch is arranged at the bottom of the sealed cavity 1 and is electrically connected with the first antenna array, the second antenna array and the third antenna array.
As shown in fig. 2 and 3, the annular hollow support is an integral structure made of honeycomb interlayer materials, and comprises a circular hollow plate 2 and a support plate 3. The circular hollowed-out plates 2 are arranged in three, the three circular hollowed-out plates 2 are concentric and sequentially arranged from bottom to top, the diameters of the three circular hollowed-out plates 2 are sequentially reduced from bottom to top, the three circular hollowed-out plates 2 are connected through the support plate 3 and supported in the sealed cavity 1, and the first antenna array, the second antenna array and the third antenna array are sequentially fixed on the three circular hollowed-out plates 2 from bottom to top.
As shown in fig. 4, the first antenna array includes seven first dipole antennas 4 with a working frequency band of 30MHz-1.3GHz, and the first dipole antennas 4 are distributed on the outer edges of the corresponding circular hollowed-out plates 2 in a circumferential array with the center of the circular hollowed-out plates 2 as the center. The first antenna array adopts a spatial spectrum estimation direction-finding system to reduce phase ambiguity brought by the aperture of the antenna, thereby effectively reducing the diameter of the antenna. The frequency band adopts DML (Determinacy Maximum Likelihood) algorithm in space spectrum estimation direction-finding technology, although the calculation amount related to two-dimensional search is large, the estimation accuracy is high, the anti-interference capability is high, the influence caused by phase ambiguity is small, and the root mean square error of the direction-finding accuracy in the frequency band is 2 degrees.
As shown in fig. 4, the second antenna array includes seven second dipole antennas 5 with the working frequency band of 1GHz-3.6GHz, the second dipole antennas 5 are distributed on the outer edges of the corresponding circular hollowed-out plates 2 in a circumferential array with the center of the circular hollowed-out plates 2 as the center, and the second dipole antennas 5 and the first dipole antennas 4 are staggered. The frequency band usually adopts a MUSIC (Multiple Signal Classification ) algorithm in a spatial spectrum estimation technology, the direction finding is accurate, the calculated direction finding degree is fast, and when the coherent signal is subjected to direction finding, a DML algorithm is adopted, and the root mean square error of the direction finding accuracy in the frequency band is 1 degree.
As shown in fig. 4, the third antenna array includes seven FPC antennas 6 with working frequency ranges of 3GHz-8GHz, the FPC antennas 6 are distributed on the outer edges of the corresponding circular hollow plates 2 in a circumferential array with the center of the circular hollow plates 2 as the center, and the FPC antennas 6, the first dipole antennas 4 and the second dipole antennas 5 are all staggered. The frequency band adopts an interferometer algorithm, has small calculated amount and quick direction indication, is beneficial to tracking a moving target, and has the direction-finding accuracy root mean square error of 1 degree in the frequency band.
Based on the structure of the annular hollowed-out support and the installation layout of the three sets of antenna array elements, the annular hollowed-out support is high in strength and light in weight, and has the strength and weight requirements, so that the overall weight of the airborne direction-finding antenna array is reduced while the three sets of antenna array elements are more compactly installed; through the staggered array technology of the same layer, the space height requirement is reduced, the overall structure is more compact, the miniaturization requirement is met, the direction-finding antenna array technology is feasible on the flight platform, the airborne pneumatic requirement is met, and the influence of the large-scale external antenna array on the pneumatic structure of the flight platform is reduced. In addition, when the antenna array is used on an air-based platform, the incidence of the information source is kept at an angle, and interlayer interference is naturally reduced due to the change of the incidence environment.
As shown in fig. 1, 4 and 5, a flange 7 is fixed at the bottom of the sealed cavity 1, a shielding plate 8 is arranged between the flange 7 and the bottom of the sealed cavity 1, a switch box 9 integrally formed with the flange 7 is arranged in the middle of the flange 7, and a radio frequency matrix switch is arranged in the switch box 9; the radio frequency matrix switch comprises 28 paths of input ends and 3 paths of output ends, the switch box 9 is provided with 21 radio frequency input interfaces 10 which are positioned in the sealed cavity 1, the switch box 9 is also provided with 3 radio frequency output interfaces 11, 1 calibration signal input interface 12 and 1 control interface 13 which are positioned outside the sealed cavity 1, the first dipole antenna 4, the second dipole antenna 5 and the FPC antenna 6 are electrically connected with the input ends of the radio frequency matrix switch through the radio frequency input interfaces 10, the 3 radio frequency output interfaces 11 are electrically connected with the 3 paths of output ends of the radio frequency matrix switch respectively, and the calibration signal input interfaces 12 and the control interfaces 13 are electrically connected with the radio frequency matrix switch.
In order to further reduce the overall weight of the airborne direction-finding antenna array and make the structure more compact, hard plate wafers are fixed at the top and bottom of the first dipole antenna 4, the surfaces of the hard plate wafers are coated with metal layers, and the first dipole antenna 4 and the hard plate wafers are of hollow structures; meanwhile, as shown in fig. 4 and 5, the switch box 9 is integrally connected with the flange 7, so that the space at the joint of the switch box 9 and the machine body is fully utilized through the integrated design, 21 radio frequency input interfaces 10 are distributed around the central circumference array of the switch box 9, and the height of the whole switch is shortened and the length of a radio frequency connecting wire is shortened through the circumference arrangement of the radio frequency interfaces.
In order to control the directional diagram of the array elements and reduce the coupling among the dense array elements, the invention is also provided with 3 gain-adjustable low-noise amplifiers, 7 synthesizers and 7 one-to-four switches in the switch box 9. The first dipole antenna 4 and the second dipole antenna 5 are connected to the input end of the radio frequency matrix switch through the radio frequency input interface 10, so that the signal paths of the first antenna array and the second antenna array are through signals; each FPC antenna 6 corresponds to 1 synthesizer and 1 one-to-four switch, the FPC antenna 6 is connected to the input end of the corresponding one-to-four switch through the radio frequency input interface 10, the 1 output end of the one-to-four switch is connected to the input end of the radio frequency matrix switch, the other 3 output ends of the one-to-four switch are respectively connected to the input end of the corresponding synthesizer and the input ends of two synthesizers adjacent to the corresponding synthesizer, the output end of the synthesizers is connected to the input end of the radio frequency matrix switch, so that the signal path of the third antenna array is a through signal, the signal path of the third antenna array can be switched to a synthesized signal, the 3 output ends of the radio frequency matrix switch are respectively connected to the input ends of 3 adjustable gain low noise amplifiers, and the output ends of the 3 adjustable gain low noise amplifiers are respectively connected to 3 radio frequency output interfaces 11. The calibration signal enters the radio frequency matrix switch through the calibration signal input interface 12, is divided into 28 paths at the radio frequency matrix switch and is connected with 28 paths of input ends of the radio frequency matrix switch, so that the channel error of the 28 paths of input signals is obtained; the control signal enters the radio frequency matrix switch through the control interface 13, and then the radio frequency matrix switch is controlled.
The gain of the adjustable gain low noise amplifier is controllable, and the adjustable gain low noise amplifier has three gears of 0db, 10db and 20db, when 0db is selected, the adjustable gain low noise amplifier is in an off state, and at the moment, the directional diagram of the whole antenna array is equivalent to a passive array, and has good consistency; when 10db and 20db are selected, the adjustable gain low noise amplifier is in an amplifying state, and the directional diagram of the whole antenna array is equivalent to an active array, compared with a passive array, the directions are expanded simultaneously, and the sensitivity of the array element is increased.
For the signals of 3G-8G, when the amplifier is at 20db or the direction-finding jitter is too large, the signal path can be switched to the synthesized signal through the synthesizer, the direction-finding algorithm is changed from a 3-channel spatial spectrum or a related interferometer to a 2-channel related interferometer, and the directional pattern of the whole antenna array is sharpened compared with the passive array, so that the sensitivity of the array elements or the signal-to-noise ratio of the signals are increased.
As shown in fig. 6, a is a single omni-directional array element form without using a synthesizer in the prior art, and each directional array element has the same polarity; b is the form of the synthesized array element when the signal path is switched to the synthesized signal through the synthesizer.
As shown in fig. 7, c is the response of the conventional single omni-directional element within the range of 0 o-360o, and d is the response of the element within the range of 0 o-360o. It can be seen that the main resolution strength and the auxiliary resolution strength of the single omni-directional array element are the same, so that the dense array elements have larger coupling, and the main resolution strength of the synthesized array elements is enhanced, and the auxiliary resolution is weakened.
The light-weight compact type airborne direction-finding antenna array supports a 3-channel interferometer and a spatial spectrum direction-finding system, is suitable for mounting large and medium unmanned aerial vehicles, can be used as a ring in a communication signal detection subsystem to be mounted on the unmanned aerial vehicle through practical testing and application, and further forms an electromagnetic spectrum detection unmanned helicopter, and can rapidly, efficiently and accurately position a mobile communication vehicle.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (10)
1. A lightweight compact airborne direction finding antenna array is characterized in that: including sealed cavity (1), be equipped with annular fretwork support in sealed cavity (1), be equipped with first antenna array on the annular fretwork support, second antenna array and third antenna array, first antenna array, second antenna array and third antenna array are set gradually by annular fretwork support outer edge to annular fretwork support center, second antenna array top is high with first antenna array top equi, third antenna array is located first antenna array top, sealed cavity (1) bottom is equipped with the radio frequency matrix switch with the equal electric connection of first antenna array, second antenna array and third antenna array, first antenna array, second antenna array, third antenna array and radio frequency matrix switch constitute the seven array element space spectrum direction finding systems of three-channel.
2. The lightweight compact airborne directional antenna array of claim 1, characterized in that: the annular hollowed-out support is of an integrated structure made of honeycomb interlayer materials, the annular hollowed-out support comprises round hollowed-out plates (2) and supporting plates (3), the round hollowed-out plates (2) are arranged to be three, the three round hollowed-out plates (2) are concentric and sequentially arranged from bottom to top, the diameters of the three round hollowed-out plates (2) are sequentially reduced from bottom to top, the three round hollowed-out plates (2) are connected and supported in the sealing cavity (1) through the supporting plates (3), and the first antenna array, the second antenna array and the third antenna array are sequentially arranged on the three round hollowed-out plates (2) from bottom to top.
3. The lightweight compact airborne directional antenna array of claim 2, characterized in that: the first antenna array comprises seven first dipole antennas (4) with the working frequency range of 30MHz-1.3GHz, and the first dipole antennas (4) are distributed on the outer edges of the corresponding circular hollowed-out plates (2) in a circumferential array by taking the circle centers of the circular hollowed-out plates (2) as centers.
4. A lightweight compact airborne directional antenna array according to claim 3, characterized in that: the second antenna array comprises seven second dipole antennas (5) with the working frequency ranges of 1GHz-3.6GHz, the second dipole antennas (5) are distributed on the outer edges of the corresponding circular hollowed-out plates (2) in a circumferential array mode by taking the circle centers of the circular hollowed-out plates (2) as centers, and the second dipole antennas (5) and the first dipole antennas (4) are arranged in a staggered mode.
5. The lightweight compact airborne directional antenna array of claim 4, characterized in that: the third antenna array comprises seven FPC antennas (6) with the working frequency ranges of 3GHz-8GHz, the FPC antennas (6) are distributed on the outer edges of the corresponding circular hollowed-out plates (2) by taking the circle centers of the circular hollowed-out plates (2) as the central circumferential array, and the FPC antennas (6), the first dipole antennas (4) and the second dipole antennas (5) are all staggered.
6. A lightweight compact airborne directional antenna array according to claim 3, characterized in that: the top and the bottom of the first dipole antenna (4) are both provided with hard plate wafers, the surfaces of the hard plate wafers are provided with metal layers, and the first dipole antenna (4) and the hard plate wafers are of hollow structures.
7. The lightweight compact airborne directional antenna array of claim 5, characterized in that: the bottom of the sealing cavity (1) is provided with a flange (7), a shielding plate (8) is arranged between the flange (7) and the bottom of the sealing cavity (1), the middle part of the flange (7) is provided with a switch box (9) integrally formed with the flange (7), and the radio frequency matrix switch is arranged in the switch box (9).
8. The lightweight compact airborne directional antenna array of claim 7, characterized in that: the radio frequency matrix switch comprises 28 paths of input ends and 3 paths of output ends, the switch box (9) is provided with 21 radio frequency input interfaces (10) which are positioned in the sealed cavity (1), the switch box (9) is also provided with 3 radio frequency output interfaces (11) which are positioned outside the sealed cavity (1), 1 calibration signal input interfaces (12) and 1 control interface (13), the first dipole antenna (4), the second dipole antenna (5) and the FPC antenna (6) are electrically connected with the input ends of the radio frequency matrix switch through the radio frequency input interfaces (10), the 3 radio frequency output interfaces (11) are electrically connected with the 3 paths of output ends of the radio frequency matrix switch respectively, and the calibration signal input interfaces (12) and the control interfaces (13) are electrically connected with the radio frequency matrix switch.
9. The lightweight compact airborne directional antenna array of claim 8, characterized in that: the 21 radio frequency input interfaces (10) are distributed around the central circumferential array of the switch box (9).
10. The lightweight compact airborne directional antenna array of claim 8, characterized in that: the switch box (9) is internally provided with 3 adjustable gain low noise amplifiers, 7 synthesizers and 7 one-to-four switches, the first dipole antenna (4) and the second dipole antenna (5) are connected with the input ends of the radio frequency matrix switches through radio frequency input interfaces (10), each FPC antenna (6) corresponds to 1 synthesizer and 1 one-to-four switch, each FPC antenna (6) is connected with the input ends of the corresponding one-to-four switches through the radio frequency input interfaces (10), 1 output end of one-to-four switch is connected with the input ends of the radio frequency matrix switches, the other 3 output ends of one-to-four switch are respectively connected with the input ends of the corresponding synthesizers and the input ends of two synthesizers adjacent to the corresponding synthesizers, the 3 output ends of the radio frequency matrix switches are respectively connected with the input ends of the 3 adjustable gain low noise amplifiers, and the output ends of the 3 adjustable gain low noise amplifiers are respectively connected with the 3 radio frequency output interfaces (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410568217.6A CN118367329A (en) | 2024-05-09 | 2024-05-09 | Lightweight compact type airborne direction-finding antenna array |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410568217.6A CN118367329A (en) | 2024-05-09 | 2024-05-09 | Lightweight compact type airborne direction-finding antenna array |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118367329A true CN118367329A (en) | 2024-07-19 |
Family
ID=91880174
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410568217.6A Pending CN118367329A (en) | 2024-05-09 | 2024-05-09 | Lightweight compact type airborne direction-finding antenna array |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN118367329A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103887613A (en) * | 2014-03-06 | 2014-06-25 | 广州海格通信集团股份有限公司 | Passive direction-finder antenna array of phase interferometer and phase interferometer |
| WO2018036009A1 (en) * | 2016-08-26 | 2018-03-01 | 深圳前海科蓝通信有限公司 | Intelligent antenna device and intelligent antenna communication system |
| CN112072270A (en) * | 2020-07-20 | 2020-12-11 | 成都大公博创信息技术有限公司 | Integrated rapid deployment monitoring direction-finding equipment |
| CN216980850U (en) * | 2022-04-27 | 2022-07-15 | 成都华日通讯技术股份有限公司 | Integrated multipurpose unmanned aerial vehicle disturbance detecting equipment |
| US11489267B1 (en) * | 2021-06-07 | 2022-11-01 | Southwest Research Institute | Cylindrical continuous-slot antenna made from discrete wrap-around antenna elements |
-
2024
- 2024-05-09 CN CN202410568217.6A patent/CN118367329A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103887613A (en) * | 2014-03-06 | 2014-06-25 | 广州海格通信集团股份有限公司 | Passive direction-finder antenna array of phase interferometer and phase interferometer |
| WO2018036009A1 (en) * | 2016-08-26 | 2018-03-01 | 深圳前海科蓝通信有限公司 | Intelligent antenna device and intelligent antenna communication system |
| CN112072270A (en) * | 2020-07-20 | 2020-12-11 | 成都大公博创信息技术有限公司 | Integrated rapid deployment monitoring direction-finding equipment |
| US11489267B1 (en) * | 2021-06-07 | 2022-11-01 | Southwest Research Institute | Cylindrical continuous-slot antenna made from discrete wrap-around antenna elements |
| CN216980850U (en) * | 2022-04-27 | 2022-07-15 | 成都华日通讯技术股份有限公司 | Integrated multipurpose unmanned aerial vehicle disturbance detecting equipment |
Non-Patent Citations (1)
| Title |
|---|
| 李明: "一种基于高速开关阵列的测向算法", 《电子信息对抗技术》, 31 December 2017 (2017-12-31) * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111541052B (en) | Antenna array system and current plate array wavelength scaling antenna aperture | |
| CN109030961B (en) | Method for testing vertical radiation field pattern of target antenna | |
| US7193561B2 (en) | Phase controlled antennae for data transmission between mobile devices | |
| CN111585042B (en) | Multi-beam dielectric lens antenna and manufacturing method thereof | |
| CN107728137A (en) | A kind of Passive Radar System of multi-antenna array switching | |
| CN208255424U (en) | A kind of low latitude unmanned plane passive detection positioning system | |
| CN116299589B (en) | Satellite-borne ultra-small GNSS occultation detector | |
| CN107069196A (en) | S/L frequency range flat board self-tracking antennas | |
| EP3754786A1 (en) | Tapered wall radome | |
| CN112986921A (en) | Side lobe suppression method of broadband digital receiving array | |
| WO2007055710A2 (en) | Electronic pitch over mechanical roll antenna | |
| CN114421117A (en) | Satellite-borne multi-band integrated receiving antenna | |
| CN207664223U (en) | A kind of dual-linear polarization antenna | |
| CN118367329A (en) | Lightweight compact type airborne direction-finding antenna array | |
| CN111883919B (en) | Full-angle-domain air networking type self-adaptive antenna design method | |
| Futatsumori et al. | Design and measurement of W-band offset stepped parabolic reflector antennas for airport surface foreign object debris detection radar systems | |
| CN217561727U (en) | Radar and unmanned aerial vehicle | |
| CN202585702U (en) | Novel seven-antenna-element circular array for multiple direction-finding modes | |
| CN107978840B (en) | Dual-polarized antenna feed source array assembly | |
| CN115856766A (en) | Sum and difference beam direction finding method based on log periodic antenna | |
| CN115586546A (en) | Multi-mode forwarding type navigation deception jamming system for receiving and forwarding in full airspace | |
| CN212162069U (en) | Multi-beam dielectric lens antenna | |
| CN115037352A (en) | Noise reduction method for satellite beam alignment enhancement | |
| CN113562156A (en) | Ultra-wide-band lightweight airborne direction finding array of unmanned aerial vehicle | |
| CN205583153U (en) | High -gain broadband circular polarized antenna |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |