CN215644947U - Miniature missile-borne microstrip conformal navigation antenna - Google Patents
Miniature missile-borne microstrip conformal navigation antenna Download PDFInfo
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- CN215644947U CN215644947U CN202122190405.4U CN202122190405U CN215644947U CN 215644947 U CN215644947 U CN 215644947U CN 202122190405 U CN202122190405 U CN 202122190405U CN 215644947 U CN215644947 U CN 215644947U
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Abstract
The utility model discloses a miniaturized missile-borne microstrip conformal navigation antenna, which comprises: the frustum dielectric substrate and the feed network are arranged on the frustum dielectric substrate; a concentric cylinder is removed from the interior of the frustum dielectric substrate, metal layers are electroplated on the inner surface, the outer surface and the upper surface of the frustum dielectric substrate, a metal grounding plate is formed on the metal layer on the inner surface, an upper surface short circuit surface is formed on the metal layer on the upper surface, an annular radiation patch is formed on the metal layer on the outer surface, and the metal grounding plate is connected with the radiation patch on the outer surface through the upper surface short circuit surface; two through holes are formed through the inner surface, the frustum dielectric substrate and the outer surface and serve as antenna feed points, and the inner walls of the two through holes are subjected to metallization treatment; the feed network is connected with the two antenna feed points through a coaxial cable, and provides amplitude and phase excitation required for realizing circular polarization. The antenna provided by the utility model has the advantages of good radiation performance, high gain, small volume, simple structure, easiness in debugging and installation and low cost, and solves the design problem of the high-curvature miniaturized cone surface conformal antenna.
Description
Technical Field
The utility model relates to the technical field of satellite navigation antennas, in particular to a miniaturized missile-borne microstrip conformal navigation antenna.
Background
This section is intended to provide a background or context to the embodiments of the utility model that are recited in the claims. The description herein is not admitted to be prior art by inclusion in this section.
With the establishment and operation of the second-generation Beidou satellite navigation system, the Beidou satellite navigation product can be widely applied to various military platforms. The miniature Beidou satellite navigation device is integrated in the projectile body, so that the accurate and efficient striking capability is realized, and the trend of the miniature and intelligent development of ammunition platforms is achieved. One of the key technologies to achieve this trend is the design of miniaturized missile-borne satellite navigation antennas. Considering the characteristics of the missile platform, the missile-borne satellite navigation antenna must meet the following requirements: miniaturization, high overload resistance, conformality and high performance.
The satellite navigation antenna needs to be strictly designed and manufactured according to the installation structure thereof. Common antenna types are helical antennas, microstrip antennas, antenna arrays, and the like.
In order to meet the requirement of conformal design of the antenna and the missile body, the aerodynamic performance of the antenna is not influenced, the mechanical structure and the strength of the antenna are not damaged, and the internal space of the missile body is saved, the missile-borne satellite navigation antenna mainly adopts a micro-strip antenna array form. A plurality of discrete microstrip patch radiating elements are uniformly arranged along the circumference of the projectile body to form a circular array, and a feed network is used for providing amplitude and phase excitation required by circular polarization, so that omnidirectional radiation within 360-degree range of the circumferential plane of the projectile body is generated, as shown in fig. 1. In addition, some research units select a flexible dielectric plate by utilizing the inherent low-planing-surface characteristic of the microstrip antenna, adopt a plurality of unit antennas to form a one-dimensional linear array, feed the linear array by using a coplanar shunt-feed network, further bend the linear array to be conformal on the surface of the projectile body, and fix the linear array by using screws to form the conformal array, thereby avoiding the interference of the high-speed rotation of the projectile body platform on received signals.
However, the above technical solutions all have problems:
for the scheme of forming the circular ring array by adopting the microstrip panel antenna units, each array element needs to be independently debugged, the workload is large, and the cost is high. And each array element is of a flat plate structure and a non-curved surface structure, so that more projectile body space needs to be occupied, and the application of the array element in a miniaturized space is limited.
For the scheme of bending and conforming the one-dimensional linear array on the surface of the projectile body, the antenna patch and the feed network are processed on the same rectangular medium substrate, the whole array needs to be debugged, each array element cannot be debugged independently, the whole body is pulled to move, the debugging difficulty is high, and the workload is large. In addition, the antenna is mounted by bending the rectangular dielectric plate on the surface of the elastic body and fixing the rectangular dielectric plate by using screws. This can only be achieved by selecting a thinner dielectric sheet material in the case of a larger radius (smaller curvature) of the projectile mounting portion. Otherwise, the antenna is very susceptible to crack damage, which greatly limits its application in miniaturization.
SUMMERY OF THE UTILITY MODEL
The embodiment of the utility model provides a miniaturized missile-borne microstrip conformal navigation antenna, which is used for meeting the requirement of high-curvature miniaturized cone-shaped missile body surface conformal, saving missile body space, being not influenced by the motion trail and the posture of a flying body, and realizing stable signal receiving, and comprises the following components: the frustum dielectric substrate and the feed network are arranged on the frustum dielectric substrate;
a concentric cylinder is removed from the interior of the frustum dielectric substrate, metal layers are electroplated on the inner surface, the outer surface and the upper surface of the frustum dielectric substrate, a metal grounding plate is formed on the metal layer on the inner surface, an upper surface short circuit surface is formed on the metal layer on the upper surface, an annular radiation patch is formed on the metal layer on the outer surface, and the metal grounding plate is connected with the radiation patch on the outer surface through the upper surface short circuit surface; two through holes are formed through the inner surface, the frustum dielectric substrate and the outer surface and serve as antenna feed points, and the inner walls of the two through holes are subjected to metallization treatment; the feed network is arranged on the upper surface of the frustum dielectric substrate and connected with the two antenna feed points through coaxial cables, and the feed network provides amplitude and phase excitation required for realizing circular polarization.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts. In the drawings:
fig. 1 is a schematic diagram of a prior art scheme for forming a circular array by using microstrip planar antenna units;
FIG. 2 is a schematic diagram of a miniaturized missile-borne microstrip conformal navigation antenna according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a return loss simulation curve of a miniaturized missile-borne microstrip conformal navigation antenna in an embodiment of the present invention;
FIG. 4 is a schematic diagram of right-hand circularly polarized gain in the main plane of the miniaturized missile-borne microstrip conformal navigation antenna XOZ according to the embodiment of the present invention;
fig. 5 is a schematic diagram of right-hand circularly polarized gain in the YOZ main surface of the miniaturized missile-borne microstrip conformal navigation antenna in the embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the embodiments of the present invention are further described in detail below with reference to the accompanying drawings. The exemplary embodiments and descriptions of the present invention are provided to explain the present invention, but not to limit the present invention.
The utility model aims to meet the design requirements based on a miniaturized missile-borne conformal antenna: 1. the installation space is not more than 30mm multiplied by 45mm multiplied by 30mm, and the space of 23.7mm multiplied by 30mm inside is the space of the projectile body and can not be occupied; 2. the directional diagram is required to be omnidirectional in the horizontal direction; 3. the antenna is high-overload resistant, a technical scheme of a miniaturized missile-borne microstrip conformal navigation antenna is provided according to summary of experience of a plurality of previous projects and a large amount of simulation calculation and test verification, and the antenna is good in radiation performance, high in gain, small in size, simple in structure, easy to debug and install and low in cost. The design problem of the high-curvature miniaturized cone surface conformal antenna is solved.
Fig. 2 is a schematic structural diagram of a miniaturized missile-borne microstrip conformal navigation antenna in an embodiment of the present invention, as shown in fig. 2, the miniaturized missile-borne microstrip conformal navigation antenna includes: the frustum dielectric substrate 1 and the feed network 2;
a concentric cylinder is removed from the interior of the frustum dielectric substrate, metal layers are electroplated on the inner surface 11, the outer surface 12 and the upper surface 13 of the frustum dielectric substrate, a metal grounding plate is formed on the inner surface metal layer, an upper surface short circuit surface is formed on the upper surface metal layer, the metal grounding plate is connected with the outer surface metal layer through the upper surface short circuit surface, and the outer surface metal layer forms an annular radiation patch; two through holes 14 are formed through the inner surface, the frustum dielectric substrate and the outer surface and are used as antenna feed points, and the inner walls of the two through holes are subjected to metallization treatment; the feed network is arranged on the upper surface of the frustum dielectric substrate and connected with the two antenna feed points through a coaxial cable 15, the feed network provides amplitude and phase excitation required for realizing circular polarization, and the polarization state of the feed network can be switched.
In the embodiment of the utility model, the frustum dielectric substrate is of non-uniform thickness, and can be of TAP-2 model or other models.
In the embodiment of the utility model, the maximum radiation direction of the miniaturized missile-borne microstrip conformal navigation antenna is in the direction of an antenna axis.
In the embodiment of the utility model, because the design requirement is that the installation space is not more than 30mm multiplied by 45mm multiplied by 30mm, and the space of the inner part 23.7mm multiplied by 23 mm multiplied by 30mm is not occupied by the space of the projectile body, the size of the frustum medium substrate is designed to be less than 30mm multiplied by 45mm multiplied by 30mm, and the size of a concentric cylinder (which is the space of the equipment in the projectile body) dug in the frustum medium substrate is 23.7mm multiplied by 30 mm. And the miniaturized missile-borne microstrip conformal navigation antenna is resistant to high overload.
In the embodiment of the present invention, the center frequency of the antenna operation is: 1268.52MHz, free space wavelength λ0Approximately equal to 236mm, and the diameters of the upper bottom surface and the lower bottom surface of the frustum medium substrate are respectively about 0.125 lambda through conversion0And 0.18 lambda0The length of the frustum medium substrate bus is about 0.13 lambda0. Considering that the installation space of the antenna is very small and the curvature of the elastomer at the installation part is large (the diameter D & lt lambda & gt)0) According to the theory and engineering realization of the microstrip antenna, a conformal array form cannot be adopted, and only the microstrip loop antenna can be selected for realization.
According to the basic theory of microstrip antennas, the antenna patch length should be one-half of the operating wavelength (0.5 λ)g). Using epsilon in designing the antenna taking into account the size constraints of the mounting platformrHigh dielectric constant dielectric material of 10.2, and the antenna size is further reduced by providing a short circuit surface on the patch top end face, and the final radiating patch length is reduced to about 0.26 lambdag。
The annular radiating patch is determined according to the following formula:
wherein, L is the length of the microstrip patch; f. of0For the center frequency of antenna operation, C is the speed of light, about 3X 108m/s；εrIs the dielectric constant.
The height of the metal layer on the outer surface as the annular radiation patch is adjustable, so that the metal layer is used for adjusting the working frequency of the miniaturized missile-borne microstrip conformal navigation antenna, and the metal layer can be 26mm, for example.
In the embodiment of the utility model, a dielectric layer with non-uniform thickness is adopted, and the thickness is increasedThe thickness of the dielectric layer at the bottom of the antenna is used for improving the radiation performance of the antenna. According to the theory of microstrip antenna, if the diameter D of the elastomer and the working wavelength lambda0The relation between them satisfies D < 0.5 lambda0Then, one feeding point is adopted to realize the omnidirectional coverage of the antenna. In order to meet the requirement of circular polarization of a satellite navigation system, two antenna feed points are designed to be spaced by 90 degrees on the circumference of a frustum dielectric substrate, the diameters of the two antenna feed points are 1mm, and the distance between the two antenna feed points and the upper end face of the frustum dielectric substrate is 3.8 mm.
A broadband power division phase-shifting feed network is designed to provide amplitude and phase excitation required by circular polarization for a double-fed point. The feed network is connected with the two antenna feed points through two 50 ohm standard coaxial cables with the same length.
In the embodiment of the utility model, the feed network is a circuit board which can provide amplitude and phase excitation required for realizing circular polarization. The polarization of the feed network is adjustable.
The feed network can be arranged on the upper surface of the frustum dielectric substrate.
In the embodiment of the utility model, the manufacturing process of the miniaturized missile-borne microstrip conformal navigation antenna comprises the following steps: firstly, selecting a dielectric material with corresponding parameters, and obtaining a dielectric substrate meeting the requirements through machining. And plating metal layers on the surfaces of the dielectric substrate by adopting surface electroplating treatment. The working frequency of the antenna can be conveniently adjusted by adjusting the position of the feed point and the height of the antenna radiation patch. The whole antenna is completely realized by a common machining process, and has the advantages of simple manufacture, convenient debugging, insensitivity to machining errors and low cost.
As can be seen from fig. 3, the resonant center frequency of the antenna unit is 1268MHz, the operating bandwidth exceeds 20MHz, and the Beidou satellite navigation B3 frequency band can be completely covered.
As can be seen from fig. 4, in the XOZ main plane, the maximum radiation direction main polarization (right-hand circular polarization) gain of the antenna element is about 3.4dBi (as shown in m 1), and has a relatively symmetrical directional pattern. The Half Power Beam Width (HPBW) of the designed antenna is about 110 degrees, and stable signal receiving can be realized.
As can be seen from fig. 5, in the YOZ main plane, the maximum radiation direction main polarization (right-hand circular polarization) gain of the antenna element is about 3.4dBi (as shown in m 1), and has a relatively symmetrical directional pattern. The Half Power Beam Width (HPBW) of the designed antenna is about 110 degrees, and stable signal receiving can be realized.
Compared with the existing implementation schemes of various missile-borne satellite navigation antennas, the miniature missile-borne microstrip conformal navigation antenna provided by the utility model has the following advantages:
1. the novel miniaturized missile-borne microstrip conformal navigation antenna has the advantages of a low profile of the microstrip antenna, does not occupy the internal space of a missile body, and solves the design problem of the high-curvature miniaturized cone surface conformal antenna.
2. The novel antenna realizes omnidirectional radiation within 360-degree range of the circumferential plane of the projectile body, is not influenced by the motion track and the posture of the flying body, and can realize stable reception of signals.
3. The novel antenna is simple in structure, and in the design process, the required performance can be obtained only by adjusting the position of the feed point and the length of the patch. The structural parameters are few, and the time for design optimization is greatly shortened.
4. The novel antenna is simple and convenient in manufacturing process and can be realized by adopting a common machining process. Is insensitive to error and convenient to debug.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (12)
1. A miniaturized missile-borne microstrip conformal navigation antenna, comprising: the frustum dielectric substrate and the feed network are arranged on the frustum dielectric substrate;
a concentric cylinder is removed from the interior of the frustum dielectric substrate, metal layers are electroplated on the inner surface, the outer surface and the upper surface of the frustum dielectric substrate, a metal grounding plate is formed on the metal layer on the inner surface, an upper surface short circuit surface is formed on the metal layer on the upper surface, an annular radiation patch is formed on the metal layer on the outer surface, and the metal grounding plate is connected with the radiation patch on the outer surface through the upper surface short circuit surface; two through holes are formed through the inner surface, the frustum dielectric substrate and the outer surface and serve as antenna feed points, and the inner walls of the two through holes are subjected to metallization treatment; the feed network is arranged on the upper surface of the frustum dielectric substrate and connected with the two antenna feed points through coaxial cables, and the feed network provides amplitude and phase excitation required for realizing circular polarization.
2. The miniaturized missile-borne microstrip conformal navigation antenna of claim 1, wherein the frustum dielectric substrate is of non-uniform thickness.
3. The miniaturized missile-borne microstrip conformal navigation antenna of claim 1, wherein the outer dimension of the frustum dielectric substrate is less than 30mm x 45mm x 30mm, and the miniaturized missile-borne microstrip conformal navigation antenna resists high overload.
4. The miniaturized missile-borne microstrip conformal navigation antenna of claim 1, wherein a maximum radiation direction of the miniaturized missile-borne microstrip conformal navigation antenna is in an antenna axis direction.
5. The miniaturized missile-borne microstrip conformal navigation antenna of claim 1, wherein the two antenna feed points are arranged at 90 ° intervals on the circumference of the frustum dielectric substrate.
6. The miniaturized missile-borne microstrip conformal navigation antenna according to claim 1, wherein the feed network is a circuit board for providing amplitude and phase excitation required for realizing circular polarization.
7. The miniaturized missile-borne microstrip conformal navigation antenna of claim 1, wherein the polarization state of the feed network is switchable.
8. The miniaturized missile-borne microstrip conformal navigation antenna of claim 1, wherein the feed network is mounted on an upper surface of a frustum dielectric substrate.
9. The miniaturized missile-borne microstrip conformal navigation antenna according to claim 1, wherein the feed network is connected with two antenna feed points through two standard coaxial cables of 50 ohms and equal length.
10. The miniaturized missile-borne microstrip conformal navigation antenna of claim 1, wherein the outer surface metal layer is height-adjustable for adjusting an operating frequency of the miniaturized missile-borne microstrip conformal navigation antenna.
11. The miniaturized missile-borne microstrip conformal navigation antenna of claim 1, wherein the annular radiating patch size is determined according to the following formula:
wherein, L is the length of the microstrip patch; f. of0Is the center frequency of antenna operation, C is the speed of light, 3 × 108m/s；εrIs the dielectric constant.
12. The miniaturized missile-borne microstrip conformal navigation antenna of claim 1, wherein the length of the annular radiating patch is 0.26 λgWherein λ isgIs the operating wavelength of the microstrip antenna.
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| CN202122190405.4U CN215644947U (en) | 2021-09-10 | 2021-09-10 | Miniature missile-borne microstrip conformal navigation antenna |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113644402A (en) * | 2021-09-10 | 2021-11-12 | 中国信息通信研究院 | Miniature missile-borne microstrip conformal navigation antenna |
| CN113644402B (en) * | 2021-09-10 | 2024-06-21 | 中国信息通信研究院 | Miniaturized missile-borne microstrip conformal navigation antenna |
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2021
- 2021-09-10 CN CN202122190405.4U patent/CN215644947U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113644402A (en) * | 2021-09-10 | 2021-11-12 | 中国信息通信研究院 | Miniature missile-borne microstrip conformal navigation antenna |
| CN113644402B (en) * | 2021-09-10 | 2024-06-21 | 中国信息通信研究院 | Miniaturized missile-borne microstrip conformal navigation antenna |
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