CN217562813U - Circular seven-element detection antenna array configuration - Google Patents
Circular seven-element detection antenna array configuration Download PDFInfo
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- CN217562813U CN217562813U CN202220678560.2U CN202220678560U CN217562813U CN 217562813 U CN217562813 U CN 217562813U CN 202220678560 U CN202220678560 U CN 202220678560U CN 217562813 U CN217562813 U CN 217562813U
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Abstract
The utility model provides a circular seven yuan of antenna array configurations of listening, include: a mounting platform A and 7 antenna array elements B; the mounting platform A is of a pneumatic appearance structure and comprises a lower base plate A1 and a fairing A2, the lower base plate A1 is fixedly mounted between the 21 st frame and the 27 th frame of the belly of the airplane through the fairing A2, and the lower base plate A1 is of a circular structure; and the 7 antenna array elements B are uniformly arranged on the end surface of the lower bottom plate A1 along the circumferential direction of the circular structure. The utility model discloses technical scheme has solved the aerial configuration of aviation machine carried electron direction finding system, owing to receive aircraft platform overall dimension's restriction, the antenna array element B size and the very limited problem of quantity that use.
Description
Technical Field
The application relates to the technical field of general appearance of airplanes, in particular to a circular seven-element detection antenna array configuration.
Background
The aviation airborne electronic direction finding system has the advantages of large action range, long detection distance, capability of realizing single-machine target positioning and the like.
The antenna configuration of the aviation airborne electronic direction finding system is limited by the overall dimension of an airplane platform, so that effective space for laying antenna arrays can be provided, and the size and the number of antenna array elements (B) allowed to be used are very limited; in addition, the metal skin structure of the fuselage can cause the change of the amplitude-phase characteristics of the direction-finding antenna, and the difficulty and the complexity of the configuration of the airborne direction-finding antenna array are increased.
SUMMERY OF THE UTILITY MODEL
The utility model aims at: the utility model provides a circular seven yuan of antenna array configurations of listening to solve the aerial aircraft and carry the antenna configuration of electron direction finding system, owing to receive aircraft platform overall dimension's restriction, antenna array element B size and the very limited problem of quantity that use.
The technical scheme of the utility model is that: the embodiment of the utility model provides an antenna array configuration is listened to circular seven yuan, include: a mounting platform A and 7 antenna array elements B;
the mounting platform A is of a pneumatic appearance structure and comprises a lower base plate A1 and a fairing A2, the lower base plate A1 is fixedly mounted between the 21 st frame and the 27 th frame of the belly of the airplane through the fairing A2, and the lower base plate A1 is of a circular structure; and the 7 antenna array elements B are uniformly arranged on the end surface of the lower bottom plate A1 along the circumferential direction of the circular structure.
Optionally, in the circular seven-element detection antenna array configuration described above,
the fairing A2 with the aerodynamic appearance structure of the mounting platform A is oval; alternatively, the first and second liquid crystal display panels may be,
the fairing A2 with the aerodynamic configuration structure of the mounting platform A is arranged to be a symmetrical structure along the symmetrical plane of the machine body.
Optionally, in the circular seven-element detection antenna array configuration described above,
the mounting platform A is characterized in that a lower base plate A1 protrudes out of the lower zero longitudinal preset height of the belly, the diameter of the lower base plate A1 meets the requirement of the minimum mounting size of 7 antenna array elements B which are uniformly mounted in the circumferential direction, and the circle center of the lower base plate A1 is located at the preset distance behind the 23 th frame of the belly.
Optionally, in the circular seven-element detection antenna array configuration described above,
the aerodynamic shape of the installation platform A is obtained through rectification modification, the installation platform A spans between 7-8 long girders on two sides of a symmetrical plane of the machine body, and the lower bottom plate A1 is smoothly connected with the side wall of the installation platform A.
Optionally, in the circular seven-element detection antenna array configuration described above,
every antenna array element B sets up to rod antenna, rod antenna's installation base diameter is greater than body of rod diameter.
Optionally, in the circular seven-element detection antenna array configuration described above,
the mounting platform a further comprises: the fairing comprises a circumferential framework A3 arranged along the circumferential direction of a fairing A2, a lower bottom plate A1 and the circumferential framework A3 are connected through bolts, the circumferential framework A3, the fairing A2 and a belly skin are connected through rivets, and a circumferential reinforcing plate is additionally arranged outside the belly skin of a connecting area;
the lower bottom plate A1 and the fairing A2 of the mounting platform A are of an integrated structure formed by aluminum alloy integrated machining, and the periphery framework A3 is of a riveting combination structure and a belly skin which adopt a plate bending piece and an upright post.
Optionally, in the circular seven-element detective antenna array configuration described above, the mounting platform a further includes:
the symmetry sets up on lower plate A1, and with stringer parallel arrangement's 2 at least auxiliary longerons A4, auxiliary longeron A4 is located 4 stringer of organism symmetry both sides respectively.
Optionally, in the circular seven-element detective antenna array configuration described above, the mounting platform a further includes:
and the process quick-release opening cover A5 is arranged at the center of the lower bottom plate A1 and is used for installing and maintaining the antenna array element B.
Optionally, in the circular seven-element detective antenna array configuration described above, the lengths of the 7 cables used by the 7 antenna elements B are equal.
The utility model has the advantages that: the embodiment of the utility model provides an antenna array configuration is listened to circular seven yuan lays the installation to antenna array element B through considering certain medium-sized aircraft structure characteristic, and furthest has utilized the aircraft back surface overall dimension, utilizes organism middle section and wing space, has obtained an interferometer that is fit for airborne installation condition is circular seven yuan and has listened antenna array configuration. The circular seven-element detection antenna array configuration is applied to an aviation airborne electronic direction finding system, compared with the antenna configuration of the existing aviation airborne electronic direction finding system, the direction finding system has strong capability of inhibiting phase distortion formed by the airborne antenna affected by a metal skin, and the problem of high-precision direction finding of airborne direction finding equipment in the actual environment can be well solved. The embodiment of the utility model provides a technical scheme of antenna array configuration is listened to round seven units has following beneficial effect:
1) The method provides a new alternative of a circular layout configuration for arranging a multi-element detection antenna array (containing seven elements) on the surface of the airplane body;
2) The seven-element detection antenna array and the body appearance are integrated into a whole, so that the problem that the layout size of the antenna array is limited by the body structure is solved;
3) The local airflow separation is reduced through the rectification shape-modifying design of the antenna array mounting platform;
4) The high-precision and quick direction finding of 100 MHz-1350 MHz is realized on the airplane;
5) Under the condition of meeting the detection working frequency, 360-degree direction-finding full coverage is realized.
Drawings
The accompanying drawings are included to provide a further understanding of the technical aspects of the present invention, and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention, and do not constitute a limitation on the technical aspects of the invention.
Fig. 1 is a schematic structural diagram of a circular seven-element detection antenna array configuration according to the present invention;
fig. 2 is a schematic view of an installation structure of an antenna array element B in a circular seven-element detecting antenna array configuration according to an embodiment of the present invention;
fig. 3 is a schematic view of another mounting structure of an antenna array element B in a circular seven-element detecting antenna array configuration according to an embodiment of the present invention;
fig. 4 is a front view of the arrangement of antenna elements provided in the embodiment of fig. 3;
fig. 5 is a schematic diagram of another view of the arrangement of the antenna elements provided in the embodiment shown in fig. 4.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
The problems that the size and the number of antenna elements B existing in the antenna configuration in the aviation airborne electronic direction finding system already described in the background art are very limited and the like are solved.
According to the design requirements of the whole aircraft antenna layout, the mission use and the whole aircraft electromagnetic compatibility of a certain type of aircraft, 1 100 MHz-1350 MHz seven-element circular detection antenna array is arranged at the 21 st to 27 th frames of the belly of the certain type of aircraft to form a circular seven-element detection antenna array configuration. The embodiment of the utility model provides a seven units are listened antenna layout configuration and are adopted the pneumatics of totality and organism structure integration integrated design, under the limited circumstances of organism structure overall arrangement size, realized that 100MHz ~ 1350MHz direction finding precision is high, fast, satisfying under listening operating frequency and 360 degrees direction finding full coverage conditions, solved direction finding precision and arrived the contradiction that the azimuth does not have fuzzy scope.
The present invention provides that several specific embodiments below may be combined with each other, and the same or similar concepts or processes may not be repeated in some embodiments.
Fig. 1 is the utility model provides a structural schematic diagram of antenna array configuration is listened to circular seven yuan, fig. 2 is the cross-sectional view of the C-C face of antenna array configuration is listened to circular seven yuan that the embodiment that fig. 1 shows provided, the utility model discloses the antenna array configuration is listened to circular seven yuan that the embodiment provided includes: a mounting platform A and 7 antenna elements B.
As shown in fig. 1 and 2, the mounting platform a is configured to be an aerodynamic configuration structure, and includes a lower base plate A1 and a fairing A2, and is fixedly mounted between the 21 st frame and the 27 th frame of the aircraft belly through the fairing A2, the number 22-27 with a circular frame in fig. 1 represents the corresponding frame number of the aircraft belly, and the lower base plate A1 is a circular structure; and the 7 antenna array elements B are uniformly arranged on the end surface of the lower bottom plate A1 along the circumferential direction of the circular structure. As shown in fig. 3, which is a bottom view of an arrangement scheme of antenna elements in a circular seven-element detection antenna array configuration provided by an embodiment of the present invention, fig. 4 is a front view of an arrangement form of the antenna elements provided by the embodiment shown in fig. 3, and fig. 5 is a schematic diagram of another view angle of the arrangement form of the antenna elements provided by the embodiment shown in fig. 4.
The utility model discloses in the implementation of the embodiment, mounting platform A have aerodynamic configuration structure radome fairing A2 can set up to the ellipse.
In another implementation of the embodiment of the present invention, the fairing A2 with aerodynamic configuration of the installation platform a is configured as a symmetrical structure along the symmetry plane of the machine body, such as the symmetrical structure shown in fig. 1.
Referring to fig. 1 and fig. 2, in the concrete structure of the circular seven-element detecting antenna array configuration provided by the embodiment of the present invention, the lower bottom plate A1 protrudes from the belly of the mounting platform a to be a certain vertical height, for example, 85mm, the diameter of the lower bottom plate A1 is satisfied with the minimum mounting dimension of the circumferential uniform mounting of the 7 antenna array elements B, the circle center of the lower bottom plate A1 is located a certain distance, for example, 150mm, behind the 23 rd frame of the belly.
The embodiment of the utility model provides an in concrete the realization, mounting platform A's pneumatic appearance can be for figuring the obtaining through the rectification, mounting platform A spanes between each 7 ~ 8 stringers in organism plane of symmetry both sides, and goes up bottom plate A1 and the smooth linking of mounting platform A lateral wall.
In the embodiment of the present invention, each of the antenna elements B is configured as a rod antenna, and the diameter of the mounting base of the rod antenna is larger than the diameter of the rod body.
The embodiment of the utility model provides an antenna array configuration is listened to circular seven units lays the installation through considering certain medium-sized aircraft structure characteristic to antenna array element B, and furthest has utilized the back of the body surface overall dimension, utilizes organism middle section and wing space, has obtained the antenna array configuration is listened to circular seven units of interferometer that is fit for machine year installation condition. Compared with the antenna configuration of the existing aviation airborne electronic direction finding system, the circular seven-element detecting antenna array configuration is applied to the aviation airborne electronic direction finding system, so that the direction finding system has stronger capability of inhibiting phase distortion formed by the airborne antenna affected by the metal skin, and the problem of high-precision direction finding of airborne direction finding equipment in the actual environment can be better solved.
As shown in fig. 2, in an implementation manner of the embodiment of the present invention, the installation platform a may further include: along the week circle skeleton A3 that radome fairing A2 circumference set up, lower plate A1 passes through bolted connection with week circle skeleton A3, adopts rivet connection between week circle skeleton A3, radome fairing A2 and the ventral skin, and the ventral skin outside of joining region has increased the hoop reinforcing plate.
In this implementation, mounting platform A's lower plate A1 and radome fairing A2 add the integrative structure who forms for adding through the whole machine of aluminum alloy, and week circle skeleton A3 is for adopting the riveting integrated configuration and the ventral skin of bent piece plus the stand of board.
Optionally, the utility model discloses mounting platform A can also include:
the symmetry sets up on lower plate A1, and with stringer parallel arrangement's 2 at least auxiliary longerons A4, auxiliary longeron A4 is located 4 stringer of organism symmetry both sides respectively.
Optionally, the utility model discloses mounting platform A can also include:
and the process quick-release opening cover A5 is arranged at the center of the lower bottom plate A1 and is used for installing and maintaining the antenna array element B. Additionally, the embodiment of the present invention provides a length of 7 cables that 7 antenna elements B can adopt is equal.
The following describes a specific implementation of the circular seven-element detection antenna array configuration provided by the embodiment of the present invention by using a specific embodiment.
According to the requirement of installing the antenna of the mission system, a mounting platform A of 1 round seven-element detection antenna array (100 MHz-1350 MHz) is arranged at the lower part of a 21-27 frame of the aircraft belly. In a specific structure, the circle center of the mounting platform A is 150mm behind a belly 23 frame, the diameter of the mounting platform A is 1400mm, and the circle center protrudes out of the lower part of the belly and is 85mm in length. In order to reduce airflow separation, the installation platform is subjected to rectification shape modification, the installation platform A is arranged between 21-27 frames and is positioned between 7-8 long trusses on two sides of a symmetrical plane of the machine body, the length of the installation platform A is about 2300mm, the width of the installation platform A is about 1550mm, and the side walls of the installation platform A are smoothly connected with the lower bottom plate.
In this embodiment, the antenna element B is composed of 7 rod antennas, the diameter of the bottom of the antenna is 90mm, the diameter of the rod is 56mm, and the height is 326mm.
The lower bottom surface of the antenna mounting platform A is a horizontal plane which is 85mm away from the lower zero longitudinal position of the airplane body, and the center of the horizontal plane is 150mm behind the 23 frames of the airplane symmetry plane. A lower bottom plate A1 and a fairing A2 of an antenna array mounting platform A are made of aluminum alloy integrated machine processing pieces so as to guarantee the requirements of strength and flatness of the antenna array mounting platform A, a circumferential framework A3 is connected with a lower wall plate of a machine body through riveting combination pieces of bent plate processing pieces and upright posts and used for fixedly supporting the lower bottom plate, and fairings A2 are arranged at the front and the rear of the antenna array mounting platform A. The lower bottom plate A1 of the antenna mounting platform A is connected with the circumferential framework A3 through bolts, the circumferential framework A3, the fairing A2 and the fuselage skin are connected through rivets, and a delta 1.2mm annular reinforcing plate is added outside the fuselage skin in a connection area.
In order to ensure the bearing strength of the antenna mounting platform A and the fairing A2, two auxiliary longitudinal beams A4 are additionally arranged in the antenna mounting platform A and the fairing A2 for reinforcement, the auxiliary longitudinal beams A4 are positioned at the 4 long girders at the two sides of the symmetrical plane of the machine body, the adaptability of the left and right 4 long girders between 21 frames and 27 frames of the machine body is correspondingly changed, and a plate bending piece is additionally arranged for reinforcement.
At the center of an antenna mounting platform A
The lower bottom plate A1 is provided with 7 equal-angle supporting plate nuts for mounting the antenna, and the center of the platform is provided with
For artistic covering capThe use and maintenance of the antenna.
The surface of the mounting platform A is flat and smooth, and has good conductivity, and the direct current resistance between the mounting surface and the machine body is less than 0.1 omega.
And performing airtight and watertight treatment between the antenna element B and the body installation surface.
In order to meet the requirement on the consistency of phases in the direction-finding use, 7 cables used by 7 antenna elements B are designed with equal length.
The embodiment of the utility model provides a technical scheme that antenna array configuration was listened to circular seven yuan has following beneficial effect:
1) The method provides a new alternative of a circular layout configuration for arranging a multi-element detection antenna array (containing seven elements) on the surface of the airplane body;
2) The seven-element detection antenna array and the body appearance are integrated, so that the problem that the layout size of the antenna array is limited by the body structure is solved;
3) The local airflow separation is reduced through the rectification shape-modifying design of the antenna array mounting platform;
4) The high-precision and quick direction finding of 100 MHz-1350 MHz is realized on an airplane;
5) Under the condition of meeting the detection working frequency, the 360-degree direction-finding full coverage is realized.
Although the embodiments of the present invention have been described above, the description is only for the convenience of understanding the present invention, and the present invention is not limited thereto. The present invention is not limited to the above embodiments, but may be modified in various forms and details without departing from the spirit and scope of the present invention.
Claims (9)
1. A circular seven element sensing antenna array configuration comprising: the antenna comprises a mounting platform (A) and 7 antenna elements (B);
the mounting platform (A) is of a pneumatic appearance structure and comprises a lower base plate (A1) and a fairing (A2), the lower base plate (A1) is fixedly mounted between a 21 st frame and a 27 th frame of an airplane belly through the fairing (A2), and the lower base plate (A1) is of a circular structure; and the 7 antenna array elements (B) are uniformly arranged on the end surface of the lower bottom plate (A1) along the circumferential direction of the circular structure.
2. The circular seven-element phased array antenna configuration of claim 1,
the fairing (A2) with the aerodynamic configuration structure of the mounting platform (A) is arranged to be oval; alternatively, the first and second liquid crystal display panels may be,
the fairing (A2) with the aerodynamic configuration structure of the mounting platform (A) is arranged to be a symmetrical structure along the symmetrical plane of the machine body.
3. The circular seven-element detection antenna array configuration of claim 2,
the mounting platform is characterized in that a lower base plate (A1) in the mounting platform (A) protrudes out of the lower zero longitudinal preset height of the belly, the diameter of the lower base plate (A1) meets the minimum mounting size of 7 antenna array elements (B) which are uniformly mounted in the circumferential direction, and the circle center of the lower base plate (A1) is located behind the 23 th frame of the belly for a preset distance.
4. The circular seven-element detection antenna array configuration according to any one of claims 1 to 3,
the pneumatic appearance of the installation platform (A) is obtained by rectification and modification, the installation platform (A) spans between 7-8 long girders on two sides of a symmetrical plane of the machine body, and the lower bottom plate (A1) is smoothly connected with the side wall of the installation platform (A).
5. The circular seven-element detection antenna array configuration of any one of claims 1 to 3,
each antenna array element (B) is set to be a rod-shaped antenna, and the diameter of an installation base of the rod-shaped antenna is larger than that of the rod body.
6. The circular seven-element detection antenna array configuration of any one of claims 1 to 3,
the mounting platform (a) further comprises: the lower bottom plate (A1) is connected with the circumferential framework (A3) through bolts, the circumferential framework (A3), the fairing (A2) and the belly skin are connected through rivets, and a circumferential reinforcing plate is additionally arranged outside the belly skin of the connecting area;
the lower bottom plate (A1) and the fairing (A2) of the mounting platform (A) are of an integrated structure formed by an aluminum alloy integrated machine, and the periphery framework (A3) is of a riveting combination structure and a belly skin which adopt plate bending pieces and upright posts.
7. The circular seven-element phased array configuration according to claim 6, wherein said mounting platform (A) further comprises:
the symmetrical 2 at least auxiliary longitudinal beams (A4) that set up on lower plate (A1) and with stringer parallel arrangement, auxiliary longitudinal beam (A4) are located the 4 stringer of organism plane of symmetry both sides respectively.
8. The circular seven-element detection antenna array configuration according to any one of claims 1 to 3, wherein the mounting platform (A) further comprises:
and the process quick-release opening cover (A5) is arranged at the center of the lower bottom plate (A1) and is used for installing and maintaining the antenna array element (B).
9. The circular seven-element detective antenna array configuration of any of claims 1-3, wherein said 7 antenna elements (B) employ 7 cables of equal length.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202220678560.2U CN217562813U (en) | 2022-03-25 | 2022-03-25 | Circular seven-element detection antenna array configuration |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202220678560.2U CN217562813U (en) | 2022-03-25 | 2022-03-25 | Circular seven-element detection antenna array configuration |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116953681A (en) * | 2023-09-20 | 2023-10-27 | 成都智芯雷通微系统技术有限公司 | Spherical phased array radar |
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2022
- 2022-03-25 CN CN202220678560.2U patent/CN217562813U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116953681A (en) * | 2023-09-20 | 2023-10-27 | 成都智芯雷通微系统技术有限公司 | Spherical phased array radar |
| CN116953681B (en) * | 2023-09-20 | 2023-12-12 | 成都智芯雷通微系统技术有限公司 | Spherical phased array radar |
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