CN108987923B - Circularly polarized satellite navigation antenna and debugging method - Google Patents
Circularly polarized satellite navigation antenna and debugging method Download PDFInfo
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- CN108987923B CN108987923B CN201810797562.1A CN201810797562A CN108987923B CN 108987923 B CN108987923 B CN 108987923B CN 201810797562 A CN201810797562 A CN 201810797562A CN 108987923 B CN108987923 B CN 108987923B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/48—Earthing means; Earth screens; Counterpoises
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/36—Structural form of radiating elements, e.g. cone, spiral, umbrella; Particular materials used therewith
- H01Q1/38—Structural form of radiating elements, e.g. cone, spiral, umbrella; Particular materials used therewith formed by a conductive layer on an insulating support
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- 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
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
- H01Q15/24—Polarising devices; Polarisation filters
Abstract
The invention discloses a circularly polarized satellite navigation antenna and a debugging method. The satellite navigation antenna comprises an antenna body and at least one group of short circuit structures arranged on the antenna body. The distances between any two groups of short circuit structures and the center point of the antenna body are different; and each group of short circuit structures comprises N short circuit structures, the distance between any two adjacent short circuit structures is greater than or equal to a preset threshold value, and the distance between any short circuit structure and the central point of the antenna body is the same and is smaller than the distance between the feed point of the antenna body and the central point of the antenna body. Therefore, the potential zero point of the satellite navigation antenna can be adjusted by controlling the on-off of each group of short circuit structures, and the impedance matching effect of the satellite navigation antenna can be optimal by adjusting the position of the potential zero point.
Description
Technical Field
The invention relates to the technical field of communication, in particular to a circularly polarized satellite navigation antenna and a debugging method.
Background
The satellite navigation industry is a national strategic high-tech industry, has a very wide application prospect, is the Information industry which develops the fastest globally following cellular mobile communication and internet, and has become a new growth point of the global IT (internet Technology) economy. At the key moment when the Satellite Navigation industry in China is entering the rapid development of industrialization, a set of Global Navigation systems with GPS (Global Positioning System), GLONASS (Global Navigation Satellite System), GALILEO (Galileo Satellite Navigation System) and BDS (Beidou Satellite Navigation System) integrated is expected to be formed within five to ten years.
The communication equipment of the GPS requires that its antenna provide right-hand circular polarization and that the pattern of the radiated power uniformly cover the entire upper hemisphere. Circular polarization is a main propagation method used in a satellite navigation system, and compared with a linear polarization propagation method, there is no limitation in the directions of transmission and reception of electromagnetic waves, and when the circular polarization propagation method is used, the electromagnetic waves generate a faraday rotation effect in an ionosphere, so that the circular polarization has great importance in satellite navigation in recent years.
A terminal antenna of a satellite navigation system generally requires a coverage capability of an approximate hemisphere, a wide antenna beam width, a high low elevation gain, a good circular polarization characteristic and an axial ratio bandwidth, and meanwhile, a specific structure, a size and a performance design should be performed according to the requirements of an application platform.
The satellite navigation antenna is usually made of a metal patch, and because the distance between the feed point and the potential zero point of the satellite navigation antenna affects the distance between the cusp where the two modes intersect in the smith chart and the circle center of the smith chart, if the distance between the feed point and the potential zero point is not reasonable, the distance between the cusp where the two modes intersect in the smith chart and the circle center of the smith chart is easy to be inconsistent with the preset impedance test requirement, and further the impedance matching effect is reduced.
Disclosure of Invention
The embodiment of the invention provides a circularly polarized satellite navigation antenna and a debugging method, and aims to solve the technical problem that the impedance matching effect is reduced due to the unreasonable distance between a feed point and a potential zero point in the prior art.
The embodiment of the invention provides a circularly polarized satellite navigation antenna, which comprises an antenna body and at least one group of short-circuit structures arranged on the antenna body, wherein the short-circuit structures are used for adjusting the position of a zero potential point of the antenna body;
each group of short circuit structures comprises N short circuit structures, and the distance between any two adjacent short circuit structures in the N short circuit structures is greater than or equal to a preset threshold value; the distance between any one of the N short-circuit structures and the central point of the antenna body is the same and is smaller than the distance between the feed point of the antenna body and the central point of the antenna body; the preset threshold is determined according to N, wherein N is an integer greater than or equal to 4;
and the distances between any two groups of short circuit structures in the at least one group of short circuit structures and the central point of the antenna body are different.
In the embodiment of the invention, the first metal patch and the second metal patch in the antenna body can be communicated through the short-circuit structure, so that the potential zero point in the satellite navigation antenna moves to an area surrounded by a certain group of short-circuit structures from the original center point of the antenna. Furthermore, the antenna body is provided with the plurality of groups of short-circuit structures, and the potential zero point of the satellite navigation antenna is adjusted by controlling the on-off of each group of short-circuit structures, so that the impedance matching effect of the satellite navigation antenna can be optimal by adjusting the position of the potential zero point.
In one possible implementation manner, the distance between any two adjacent short-circuit structures in the N short-circuit structures is the same.
Therefore, the distance between any two adjacent short-circuit structures can be the same, and the symmetry of the satellite navigation antenna can be improved.
In a possible implementation, the antenna body is provided with two or more feed points.
In one possible implementation, N is a multiple of 4.
Therefore, the symmetry of the satellite navigation antenna can be improved.
In a possible implementation manner, a distance between any one of the N short-circuit structures and a central point of the antenna body is calculated by:
the antenna comprises M groups of short-circuit structures, wherein M is an integer greater than or equal to 1; d is the distance between any short circuit structure in the N short circuit structures and the center point of the antenna body; l is the distance between the feed point and the center point of the antenna body.
In one possible implementation, the antenna body includes: the dielectric substrate, a first metal patch arranged on the upper surface of the dielectric substrate and a second metal patch arranged on the lower surface of the dielectric substrate are used for grounding;
each short circuit structure sequentially and vertically penetrates through the first metal patch, the dielectric substrate and the second metal patch.
In a possible implementation manner, the material of the dielectric substrate is ceramic.
In one possible implementation, the shorting structure is a metalized via or a shorting pin.
The embodiment of the invention provides a debugging method of a circularly polarized satellite navigation antenna, which is suitable for the satellite navigation antenna, wherein the satellite navigation antenna comprises at least one group of short-circuit structures, and the method comprises the following steps:
controlling the at least one group of short-circuit structures to be in a disconnected state, and carrying out impedance test on the satellite navigation antenna to obtain a first Smith chart;
determining an initial distance between a cusp where two modes intersect in the first Smith chart and the center of the first Smith chart according to the first Smith chart;
controlling a short-circuit structure of a test group to be in a connected state, carrying out impedance test on the satellite navigation antenna to obtain a second Smith chart, and determining a debugging distance between a cusp where two modes intersect in the second Smith chart and the circle center of the second Smith chart according to the second Smith chart; the test short circuit structure is a first group of short circuit structures in the at least one group of short circuit structures;
and determining the respective on-off states of the at least one group of short circuit structures according to the initial distance, the debugging distance and a preset impedance test requirement.
In the embodiment of the invention, as the antenna body is provided with the plurality of groups of short-circuit structures, the adjustment of the potential zero point of the satellite navigation antenna can be realized by controlling the on-off of each group of short-circuit structures, so that the impedance matching effect of the satellite navigation antenna can be optimal by adjusting the position of the potential zero point.
In a possible implementation manner, determining the on-off state of each of the at least one group of short circuit structures according to the initial distance, the debugging distance, and a preset impedance test requirement includes:
determining whether the debugging distance meets the target distance required by the preset impedance test;
if not, according to the initial distance, the debugging distance and the target distance, re-determining a second group of short-circuit structures from the at least one group of short-circuit structures as the test group short-circuit structures, and returning to the step of controlling the test group short-circuit structures to be in a connected state; until the debugging distance corresponding to the test group short circuit structure accords with the target distance; if the distance between the second group of short-circuit structures and the center point of the antenna body is smaller than the distance between the first group of short-circuit structures and the center point of the antenna body, the first group of short-circuit structures are reset to be in an off state.
An embodiment of the present invention further provides an apparatus, where the apparatus includes:
a memory for storing a software program;
and the processor is used for reading the software program in the memory and executing the debugging method of the circularly polarized satellite navigation antenna described in the various possible implementation modes.
An embodiment of the present invention further provides a computer storage medium, where a software program is stored, and when the software program is read and executed by one or more processors, the method for debugging a circularly polarized satellite navigation antenna described in the foregoing various possible implementation manners is implemented.
Embodiments of the present invention further provide a computer program product containing instructions, which when run on a computer, enable the computer to perform the method for debugging a circularly polarized satellite navigation antenna described in the above various possible implementation manners.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings that are required to be used in the description of the embodiments will be briefly described below.
FIG. 1 is a schematic cross-sectional view of a circularly polarized satellite navigation antenna provided in the prior art;
FIG. 2a is a schematic structural diagram of a first metal patch in the prior art;
FIG. 2b is a schematic structural diagram of another first metal patch in the prior art;
FIG. 3 is a perspective view of a circularly polarized satellite navigation antenna provided in the prior art;
FIG. 4 is a schematic diagram of a potential zero point of a satellite navigation antenna;
FIG. 5 is a Smith chart of a prior art circularly polarized satellite navigation antenna;
fig. 6 is a schematic structural diagram of a circular polarization satellite navigation antenna according to an embodiment of the present invention;
FIG. 7 is a schematic structural diagram of another circular polarized satellite navigation antenna according to an embodiment of the present invention;
fig. 8 is a schematic structural diagram of a multi-feeding-point satellite navigation antenna provided in an embodiment of the present invention;
fig. 9 is a schematic flowchart of a method for debugging a circularly polarized satellite navigation antenna according to an embodiment of the present invention;
fig. 10 is a smith chart of a debugged satellite navigation antenna according to an embodiment of the present invention;
fig. 11 is a schematic diagram of an overall flow involved in an embodiment of the present invention.
Detailed Description
The present application will be described in detail below with reference to the accompanying drawings, and the specific operation methods in the method embodiments can also be applied to the apparatus embodiments.
The polarization of the wave describes the time-varying direction of the electric field vector of the electromagnetic wave as it propagates in space. The polarization of electromagnetic waves can be classified into linear polarization, circular polarization, and elliptical polarization according to the trajectory drawn in space per cycle of the electric field intensity vector end point. Linear and circular polarizations can be considered as two special cases of elliptical polarization, respectively. Considering that the satellite transmits circularly polarized electromagnetic waves, the satellite navigation antenna should operate in a circularly polarized state to achieve good polarization matching.
In describing the polarization of a wave, the polarization of the wave is typically analyzed quantitatively using an axis ratio. The axial ratio of the elliptical polarized wave is defined as the ratio of the major axis to the minor axis of the polarized ellipse, and in common, the axial ratio describes the degree of the polarized ellipse circle. When the axial ratio is 0, the electromagnetic wave is a circularly polarized wave, and an ellipticity is small and an elliptically polarized wave with a small axial ratio is also called a circularly polarized wave in engineering.
The embodiment of the invention provides a circularly polarized satellite navigation antenna which can be applied to terminal equipment application platforms of various handsets, base stations, vehicles, aircrafts and the like of a satellite navigation positioning system.
Fig. 1 is a schematic diagram illustrating a cross-section structure of a circularly polarized satellite navigation antenna provided in the prior art. As shown in fig. 1, the satellite navigation antenna 100 includes an antenna body 200; the antenna body 200 may include a dielectric substrate 201, a first metal patch 202, and a second metal patch 203. The first metal patch can be arranged on the upper surface of the dielectric substrate; the second metal patch can be arranged on the lower surface of the dielectric substrate, and the second metal patch can be used for grounding.
Further, in order to optimize the circular polarization effect of the satellite navigation antenna, the prior art generally adopts three ways, namely edge cutting, slot cutting and corner cutting. Fig. 2a illustrates a schematic structure diagram of a first metal patch in the prior art. As shown in fig. 2a, the first metal patch may be adjusted by using a truncated angle mode, that is, the position a shown in fig. 2a may be truncated by using a truncated angle (the truncated angle is an isosceles triangle as much as possible), so that the first metal patch may realize separation of degenerate modes, thereby forming a circular polarized satellite navigation antenna.
Of course, as shown in fig. 2B, fig. 2B exemplarily shows a schematic structural diagram of another first metal patch in the prior art, and the prior art may also perform a corner truncation at the position B shown in fig. 2B, where the position of the particular corner truncation may be determined according to an actual situation, and is not limited specifically.
Fig. 2a is a perspective view of a circular polarized satellite navigation antenna provided in the prior art, which is shown in fig. 3 and is combined with the circular polarized satellite navigation antenna shown in fig. 1. Wherein the satellite navigation antenna further comprises a feeding point 300. The feed point may be a junction point where the antenna and feed energy are transferred to each other. In the prior art, a circular polarization satellite navigation antenna generally adopts a feedback feeding mode, the degree of freedom of selection of a feeding point is relatively high, generally, the edge of the circular polarization antenna has the maximum voltage, the minimum current and the maximum input resistance; the current is maximum at the center, the voltage is minimum, and the input resistance is minimum (close to 0 Ω). Based on this, a position matching with the feeder exists from the center to the edge of the circularly polarized antenna, for example, the feeder is 50 Ω, and a position matching with 50 Ω can be found from the center to the edge, and the position can be used as a feeding point.
However, the circular polarization satellite navigation antenna in the prior art is relatively fixed due to the position of the feeding point. The potential zero point of the satellite navigation antenna is generally located at the center point of the satellite navigation antenna. Fig. 4 is a schematic diagram of a potential zero point of the satellite navigation antenna, where an arrow in fig. 4 may indicate a magnitude of an electric field, and the electric field is 0 at a position of a center point of the satellite navigation antenna, and accordingly, a potential of the position is 0, and it can also be seen from fig. 4 that the center point of the satellite navigation antenna is the potential zero point. In this way, a certain distance exists between the feeding point and the potential zero point, and since the center point of the satellite navigation antenna and the position of the feeding point are fixed, the distance between the feeding point and the potential zero point is relatively fixed. Fig. 5 shows a smith chart of a prior art circularly polarized satellite navigation antenna. As can be seen from fig. 5, there is a certain distance between the center and the position of the cusp where the two modes of the smith chart intersect, and the impedance matching effect of the satellite navigation antenna is not optimal.
Based on this, fig. 6 exemplarily shows a schematic structural diagram of a circularly polarized satellite navigation antenna provided by an embodiment of the present invention, which is used for solving the problem that the impedance matching effect is reduced due to the unreasonable distance between the feed point and the potential zero point. As shown in fig. 6, the satellite navigation antenna 100 may include an antenna body 200 and at least one set of shorting structures, such as a first set of shorting structures 401 and a second set of shorting structures 402 shown in fig. 6. Wherein, each group of short circuit structures can be arranged on the antenna body.
Similar to the structure of the satellite navigation antenna shown in fig. 1, in the embodiment of the present invention, the antenna body 200 may also include a dielectric substrate 201, a first metal patch 202 disposed on an upper surface of the dielectric substrate, and a second metal patch 203 disposed on a lower surface of the dielectric substrate. Accordingly, each group of short-circuit structures (or each short-circuit structure in each group of short-circuit structures) may sequentially vertically pass through the first metal patch, the dielectric substrate, and the second metal patch.
Further, the dielectric substrate may be made of various materials, for example, ceramic, a PCB, and the like, and is not limited specifically.
In the embodiment of the invention, the first metal patch and the second metal patch in the antenna body can be communicated through the short-circuit structure, so that the potential zero point in the satellite navigation antenna moves to an area surrounded by a certain group of short-circuit structures from the original center point of the antenna. Furthermore, the antenna body is provided with the plurality of groups of short-circuit structures, and the potential zero point of the satellite navigation antenna is adjusted by controlling the on-off of each group of short-circuit structures, so that the impedance matching effect of the satellite navigation antenna can be optimal by adjusting the position of the potential zero point.
Further, the distance between any two groups of short circuit structures and the center point of the antenna body is different. As shown in fig. 6, the distance between the first group of short-circuit structures 401 and the center point of the antenna body (i.e., the point O in fig. 6) is D1, and the distance between the second group of short-circuit structures 402 and the center point of the antenna body (i.e., the point O in fig. 6) is D2, where D1 ≠ D2.
Taking the first group of short-circuit structures 401 as an example, the group of short-circuit structures may include N short-circuit structures, where N is an integer greater than or equal to 4, and further N may be a multiple of 4. For example, taking N-4 as an example, as shown in fig. 7, a schematic structural diagram of another circular polarization satellite navigation antenna provided in the embodiment of the present invention is shown. First set of shorting structures 401 may include 4 shorting structures, shorting structure 4011, shorting structure 4012, shorting structure 4013, and shorting structure 4014, respectively.
Further, the distance between any two adjacent short-circuit structures in the N short-circuit structures may be greater than or equal to a preset threshold; wherein the preset threshold may be determined according to N. Furthermore, the distance between any two adjacent short-circuit structures in the N short-circuit structures may be the same, for example, when N is 4, the angle between any two short-circuit structures and the central point of the antenna body is 90 °, so that the distance between any two adjacent short-circuit structures is the same, and the symmetry of the satellite navigation antenna can be improved.
Furthermore, the distance between any one of the N short-circuit structures and the center point of the antenna body is the same and smaller than the distance between the feed point of the antenna body and the center point of the antenna body. Namely, distances between the short-circuit structure 4011, the short-circuit structure 4012, the short-circuit structure 4013, and the short-circuit structure 4014 shown in fig. 6 and the center point of the antenna body are all equal.
Further, the distance between any one of the N short-circuit structures and the center point of the antenna body can be calculated by formula (1).
The antenna comprises M groups of short circuit structures, wherein M is an integer greater than or equal to 1; d is the distance between any one of the N short-circuit structures and the center point of the antenna body; and L is the distance between the feed point and the central point of the antenna body.
Similarly, as shown in fig. 7, the second group of short-circuit structures 402 may also include 4 short-circuit structures, which are respectively a short-circuit structure 4021, a short-circuit structure 4022, a short-circuit structure 4023, and a short-circuit structure 4024. In particular, the specific structure of the second group of short-circuit structures may refer to the first group of short-circuit structures, which will not be described in detail herein.
In the embodiment of the present invention, the short-circuit structure may have various forms, for example, the short-circuit structure may be a metalized via, or may also be a short-circuit pin, which is not limited specifically. The short-circuit structure can be used as a metalized via hole, and an electric graver can be used for controlling the on-off of the metalized via hole, for example, the metal layer on the inner wall of the metalized via hole is scraped by the electric graver, so that the metalized via hole can be in an off state.
In other possible embodiments, there may be multiple feed points in the satellite navigation antenna. Fig. 8 is a schematic structural diagram of a multi-feeding-point satellite navigation antenna according to an embodiment of the present invention. The satellite navigation antenna may include two feed points, such as feed point 301 and feed point 302 shown in fig. 8. Further, at least one set of short-circuit structures may also be disposed between the feeding point 301 (or the feeding point 302) and the central point of the antenna, which is described above specifically and will not be described in detail herein.
Based on the satellite navigation antenna described above, fig. 9 exemplarily shows a schematic flow diagram corresponding to a method for debugging a circularly polarized satellite navigation antenna provided by an embodiment of the present invention, and as shown in fig. 9, the method specifically includes the following steps:
And step 903, controlling the short-circuit structure of the test group to be in a connected state, carrying out impedance test on the satellite navigation antenna to obtain a second Smith chart, and determining the debugging distance between a sharp point where two modes intersect in the second Smith chart and the circle center of the second Smith chart according to the second Smith chart.
And 904, determining the respective on-off states of the at least one group of short circuit structures according to the initial distance, the at least one debugging distance and a preset impedance test requirement.
In the embodiment of the invention, as the antenna body is provided with the plurality of groups of short-circuit structures, the adjustment of the potential zero point of the satellite navigation antenna can be realized by controlling the on-off of each group of short-circuit structures, so that the impedance matching effect of the satellite navigation antenna can be optimal by adjusting the position of the potential zero point.
Specifically, in step 901 and step 902, at least one set of short-circuit structures are controlled to be in an open state, in other words, the potential zero point of the satellite navigation antenna is located at the center point of the antenna. Thus, after the antenna is impedance tested, the resulting first smith chart may refer to the chart shown in fig. 5 above. From fig. 5, an initial distance (i.e., L shown in fig. 5) between a cusp of the first smith chart at which the two modes intersect and a center of the first smith chart may be determined0)。
In step 903, the test short structure is a first group of short structures in the at least one group of short structures. For example, as shown in fig. 7, for example, the first group of short circuit structures 401 may be set as a test group short circuit structure, and the first group of short circuit structures 401 is controlled to be in a connected state, that is, each short circuit structure (i.e., the short circuit structure 4011, the short circuit structure 4012, the short circuit structure 4013, and the short circuit structure 4014) in the first group of short circuit structures is in a connected state, so that the potential zero point of the satellite navigation antenna illustrated in fig. 7 moves from the central point of the antenna to an area surrounded by the short circuit structure 4011, the short circuit structure 4012, the short circuit structure 4013, and the short circuit structure 4014.
Furthermore, the connection state of the test group short-circuit structure can be controlled in various ways, for example, if the short-circuit structure is a metalized via hole, an electric graver can be used for scraping off the metal layer on the inner wall of the metalized via hole, and the metalized via hole can be in a disconnected state.
Further, when the short-circuit structure of the test set is in a connected state, the impedance test can be performed on the satellite navigation antenna again, so that a second smith chart can be obtained. As shown in fig. 10, a smith chart of a debugged satellite navigation antenna according to an embodiment of the present invention. From fig. 10, the tuning distance (i.e., L shown in fig. 10) between the cusp of the second smith chart where the two modes intersect and the center of the first smith chart can be determined1)。
In step 904, the on-off state of each of the at least one group of short circuit structures can be determined according to the initial distance, the debugging distance and the preset impedance test requirement. Specifically, whether the debugging distance meets a preset target distance required by the impedance test or not can be determined, and if yes, the first group of short-circuit structures can be controlled to be in a connected state; if not, re-determining a second group of short-circuit structures from the at least one group of short-circuit structures as a test group short-circuit structure according to the initial distance, the debugging distance and the target distance, and returning to the step of controlling the test group short-circuit structures to be in a connected state; until the debugging distance corresponding to the test group short circuit structure accords with the target distance. If the distance between the second group of short circuit structures and the center point of the antenna body is smaller than the distance between the first group of short circuit structures and the center point of the antenna body, the first group of short circuit structures can be reset to be in an off state.
In a specific implementation process, the debugging sequence can be determined according to the distance from each group of short circuit structures to the central point of the antenna from large to small. For example, taking fig. 7 as an example, the distance between the first group of short-circuit structures 401 and the center point of the antenna is smaller than the distance between the second group of short-circuit structures 402 and the center point of the antenna, so that in actual debugging, the second group of short-circuit structures 402 may be debugged first, and then the first group of short-circuit structures 401 may be debugged. In other words, taking the short-circuit structure as the metalized via as an example, an electric nicking tool may be used to scrape off the metal layer on the inner wall of each metalized via in the second group of short-circuit structures 402, and then a smith chart may be obtained; if the obtained smith chart does not meet the preset impedance test requirement, the metal layer on the inner wall of each metalized via hole in the first short-circuit structure 401 can be scraped by using the graver. In this way, debugging can be performed in order.
Further, the preset target distance required by the impedance test may be determined by those skilled in the art based on experience and practical conditions, for example, the target distance may be 0, that is, a cusp where the two modes intersect coincides with a center of a smith chart, so that the impedance matching effect of the satellite navigation antenna corresponding to the target distance may be optimal.
In order to more clearly describe the tuning method of the circularly polarized satellite navigation antenna, the flow involved in the embodiment of the present invention is generally described below with reference to fig. 11. As shown in fig. 11, the following steps may be included:
In step 1102, an initial distance between a cusp where two modes intersect in the first smith chart and a center of the first smith chart is determined from the first smith chart.
Therefore, the positions of the potential zero points can be adjusted by debugging at least one group of short circuit structures, and the impedance matching effect of the satellite navigation antenna can be optimal by comparing the debugging distances obtained by debugging for many times.
An embodiment of the present invention further provides an apparatus, where the apparatus includes:
a memory for storing a software program;
and the processor is used for reading the software program in the memory and executing the debugging method of the circularly polarized satellite navigation antenna described in the various possible implementation modes.
An embodiment of the present invention further provides a computer storage medium, where a software program is stored, and when the software program is read and executed by one or more processors, the method for debugging a circularly polarized satellite navigation antenna described in the foregoing various possible implementation manners is implemented.
Embodiments of the present invention further provide a computer program product containing instructions, which when run on a computer, enable the computer to perform the method for debugging a circularly polarized satellite navigation antenna described in the above various possible implementation manners.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present invention is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (8)
1. The circularly polarized satellite navigation antenna is characterized by comprising an antenna body and at least one group of short-circuit structures arranged on the antenna body, wherein the short-circuit structures are used for adjusting the position of a zero potential point of the antenna body; the antenna body includes: the dielectric substrate, a first metal patch arranged on the upper surface of the dielectric substrate and a second metal patch arranged on the lower surface of the dielectric substrate are used for grounding; each short circuit structure sequentially and vertically penetrates through the first metal patch, the dielectric substrate and the second metal patch;
each group of short circuit structures comprises N short circuit structures, and the distance between any two adjacent short circuit structures in the N short circuit structures is greater than or equal to a preset threshold value; the distance between any one of the N short-circuit structures and the central point of the antenna body is the same and is smaller than the distance between the feed point of the antenna body and the central point of the antenna body; the preset threshold is determined according to N, wherein N is an integer greater than or equal to 4; the distance between any short circuit structure in the N short circuit structures and the central point of the antenna body is calculated in the following mode:
the antenna comprises M groups of short-circuit structures, wherein M is an integer greater than or equal to 1; d is the distance between any short circuit structure in the N short circuit structures and the center point of the antenna body; l is the distance between the feed point and the central point of the antenna body;
and the distances between any two groups of short circuit structures in the at least one group of short circuit structures and the central point of the antenna body are different.
2. The satellite navigation antenna of claim 1, wherein a distance between any two adjacent shorting structures of the N shorting structures is the same.
3. The satellite navigation antenna of claim 1, wherein the antenna body is provided with two or more feed points.
4. The satellite navigation antenna of claim 1, wherein N is a multiple of 4.
5. The satellite navigation antenna of claim 1, wherein the dielectric substrate is made of ceramic.
6. The satellite navigation antenna of any one of claims 1 to 5, wherein the shorting structure is a metalized via or a shorting pin.
7. A method for debugging a circularly polarized satellite navigation antenna, wherein the method is applied to the satellite navigation antenna of any one of claims 1 to 6, the satellite navigation antenna comprises at least one set of short-circuit structures, and the method comprises:
controlling the at least one group of short-circuit structures to be in a disconnected state, and carrying out impedance test on the satellite navigation antenna to obtain a first Smith chart;
determining an initial distance between a cusp where two modes intersect in the first Smith chart and the center of the first Smith chart according to the first Smith chart;
controlling a short-circuit structure of a test group to be in a connected state, carrying out impedance test on the satellite navigation antenna to obtain a second Smith chart, and determining a debugging distance between a cusp where two modes intersect in the second Smith chart and the circle center of the second Smith chart according to the second Smith chart; the test set of short-circuit structures is a first set of short-circuit structures in the at least one set of short-circuit structures;
and determining the respective on-off states of the at least one group of short circuit structures according to the initial distance, the debugging distance and a preset impedance test requirement.
8. The method of claim 7, wherein determining the respective on-off states of the at least one set of shorting structures according to the initial distance, the debugging distance, and a preset impedance test requirement comprises:
determining whether the debugging distance meets the target distance required by the preset impedance test;
if not, according to the initial distance, the debugging distance and the target distance, re-determining a second group of short-circuit structures from the at least one group of short-circuit structures as the test group short-circuit structures, and returning to the step of controlling the test group short-circuit structures to be in a connected state; until the debugging distance corresponding to the test group short circuit structure accords with the target distance; if the distance between the second group of short-circuit structures and the center point of the antenna body is smaller than the distance between the first group of short-circuit structures and the center point of the antenna body, the first group of short-circuit structures are reset to be in an off state.
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| WO2009052234A1 (en) * | 2007-10-19 | 2009-04-23 | Board Of Trustees Of Michigan State University | Variable frequency patch antenna |
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| US10205240B2 (en) * | 2015-09-30 | 2019-02-12 | The Mitre Corporation | Shorted annular patch antenna with shunted stubs |
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