CN108899654A - High rail spacecraft GNSS receiver antenna based on the wave beam that is close to - Google Patents
High rail spacecraft GNSS receiver antenna based on the wave beam that is close to Download PDFInfo
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- CN108899654A CN108899654A CN201810603526.7A CN201810603526A CN108899654A CN 108899654 A CN108899654 A CN 108899654A CN 201810603526 A CN201810603526 A CN 201810603526A CN 108899654 A CN108899654 A CN 108899654A
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- Prior art keywords
- antenna
- high rail
- earth
- gnss receiver
- spacecraft
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Classifications
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q7/00—Loop antennas with a substantially uniform current distribution around the loop and having a directional radiation pattern in a plane perpendicular to the plane of the loop
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/22—Supports; Mounting means by structural association with other equipment or articles
- H01Q1/24—Supports; Mounting means by structural association with other equipment or articles with receiving set
-
- 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
- H01Q1/362—Structural form of radiating elements, e.g. cone, spiral, umbrella; Particular materials used therewith for broadside radiating helical antennas
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
- H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
- H01Q19/18—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces
Landscapes
- Variable-Direction Aerials And Aerial Arrays (AREA)
Abstract
The invention belongs to communication engineering technical fields, provide a kind of high rail spacecraft GNSS receiver antenna based on the wave beam that is close to.The high rail spacecraft GNSS receiver antenna is ring structure, the antenna that traditional receivers hemisphere face covers is improved to only to cover the antenna of annular region, make the main lobe of high rail spacecraft GNSS receiver in bipyramid planar, the female cone of main lobe and earth surface are tangent, and the earth is in the null of antenna.The present invention can make high rail receiver exclude the direction that can not have signal, improve the gain that high rail spacecraft GNSS receiver gets over the earth opposite side signal of shoulder leakage, enable high rail receiver more accurately to complete to position, reduces the sensitivity requirement of receiver baseband portion.
Description
Technical field
The invention belongs to communication engineering technical fields, are related to satellite navigation and positioning field, provide a kind of based on the wave beam that is close to
High rail spacecraft GNSS receiver antenna.
Background technique
Due to its orbit altitude height, a satellite can almost cover entire hemisphere high rail satellite, thus communication,
Particularly important effect is played in the fields such as meteorology.Orbit determination problems about spacecraft are the emphasis of high rail area research.And
Traditional Satellite Orbit Determination technology mostly uses the form of earth station, when high rail number of satellite is excessive, will inevitably enlarge earth station
Processing difficulty, and China not yet completes the construction of the earth station of Global coverage at present.Global Navigation Satellite System (Global
Navigation Satellite System, GNSS) it is fairly perfect navigation positioning system, it can be provided entirely for user
The positioning and time service service of weather.With being constantly progressive for scientific and technological level, the application range of GNSS is also more and more extensive, will be existing
GNSS system apply in high rail spacecraft autonomous positioning have very important practical significance.
Compared to increasingly mature Orbit determination for LEOs technology, there is also many urgently to solve for the GNSS positioning of high rail spacecraft
Certainly the problem of.GNSS navigation satellite is mainly directed towards terrestrial user service, therefore the radiation side of navigation satellite signal at the beginning of design
To being directed to the earth's core.And the running track of high rail spacecraft is higher than GNSS satellite track, this allows for high rail spacecraft GNSS and connects
Receipts machine can only receive the signal from earth opposite, as shown in Figure 1.Due to distance mistake between navigation satellite and high rail spacecraft
Far, path loss can increase many than ground receiver, cause the signal-to-noise ratio for receiving signal too low.Simultaneously because receiving signal strips
Part is harsh, and the visible star number amount of receiver is also greatly decreased.
Antenna used in traditional receivers at least covers half of spherical surface, can largely in addition to receiving useful signal
It receives and is interfered from other of the earth and universe, to influence detection of the receiver to GNSS signal.
Summary of the invention
In view of the problems of the existing technology, the present invention provides a kind of high rail spacecraft GNSS reception based on the wave beam that is close to
Machine antenna improves the gain that rail receiver gets over the earth opposite side signal of shoulder leakage.
In order to achieve the above object, the technical scheme is that：
A kind of high rail spacecraft GNSS receiver antenna based on the wave beam that is close to, the high rail spacecraft GNSS receiver
Antenna is ring structure, and the antenna that traditional receivers hemisphere face covers is improved to only to cover the antenna of annular region, makes high rail
The main lobe of spacecraft GNSS receiver is in bipyramid planar, and the female cone and earth surface of main lobe are tangent, and the earth is in the zero of antenna
In falling into, the gain that high rail spacecraft GNSS receiver gets over the earth opposite side signal of shoulder leakage is improved.
The main lobe width c of the antenna, i.e., the difference of the semiapex angle of male cone (strobilus masculinus) in Double-conical-surface are calculated according to formula (1)：
In formula：RGNSSFor GNSS satellite orbit radius；RearthFor earth radius；RGEOFor high rail satellite orbit radius；HIon
For layer height；A is the half of GNSS satellite signal beam width；
The null width b of the antenna, the i.e. semiapex angle of Double-conical-surface inner conical surface are calculated according to formula (2)：
The antenna can be helical antenna, spot beam anternma, aerial array or reflector antenna.
The invention has the advantages that high rail receiver can be made to exclude the direction that can not have signal, such as earth side
To raising rf gain enables high rail receiver more accurately to complete to position, and the sensitivity for reducing receiver baseband portion needs
It asks.
Detailed description of the invention
Fig. 1 is that high rail spacecraft receives earth opposite side GNSS satellite signal schematic representation；
Fig. 2 is to realize annular covering by changing antenna directivity；
Fig. 3 is the calculating schematic diagram of antenna direction graph parameter；
Fig. 4 is helical antenna operating mode schematic diagram, and it (c) is circular cone mould that (a), which is normal direction mould, (b) is axial mode,；
Fig. 5 is the reflector antenna diagrammatic cross-section of Double-conical-surface wave cover.
Specific embodiment
Below in conjunction with specific embodiment, the present invention will be further described.
A kind of high rail spacecraft GNSS receiver antenna based on the wave beam that is close to, the day that traditional receivers hemisphere face is covered
Line is improved to only cover an antenna for annular region, makes the main lobe of high rail spacecraft GNSS receiver in bipyramid planar, main lobe it is interior
Circular cone is tangent with earth surface, as shown in Fig. 2, the earth is in the null of antenna, improves rail receiver and earth opposite side is got over
The gain of the signal of shoulder leakage.The main lobe width c of the antenna, i.e., the difference of the semiapex angle of male cone (strobilus masculinus) in Double-conical-surface, such as Fig. 3 institute
Show, is calculated according to formula (1).The null width b of the antenna, the i.e. semiapex angle of Double-conical-surface inner conical surface, as shown in figure 3, root
It is calculated according to formula (2).Angle a indicates navigation satellite signal radiation scope in Fig. 3, determines the receivable range of signal of high rail satellite,
The value is fixed as 42 degree；The angle of angle b expression inner conical surface, it is assumed that earth radius 6371km, high rail receiver height are h km,
The then size of available angle b is：The coverage area of antenna is inside and outside two circular conical surfaces
The annular section of composition, using angle c as the circular conical surface of apex angle.
Structural grain icon closes the antenna for stating application scenarios, which can be helical antenna, spot beam anternma, antenna
Array or reflector antenna.The specific mature problem of antenna design method data tradition is not described in detail herein.
Embodiment 1：Spot beam anternma
High rail spacecraft is in GEO track, and orbit altitude 35786km receives GPS constellation satellite-signal, then main lobe width c
It is 3.1814 °, b=8.6907 ° of the angle of inner conical surface.
It is realized and is covered using spot beam anternma, need to consider that spot beam anternma belongs to offset-fed source antenna, efficiency takes 0.65, because
This G=34.9218dB, antenna aperture 4m.
Embodiment 2：Helical antenna
High rail spacecraft is in GEO track, and orbit altitude 35786km receives GPS constellation satellite-signal, then main lobe width c
It is 3.1814 °, b=8.6907 ° of the angle of inner conical surface.
It is realized and is covered using helical antenna, the radiation characteristic of helical antenna determines that wherein D is by its diameter wavelength ratio D/ λ
Screw diameter, λ are wavelength.Under different-diameter wavelength ratio, helical antenna can show different radiation characteristics, operating mode
As shown in Figure 4.
As D/ λ>When 0.46, antenna greatest irradiation direction can split into both direction, be in coniform, and occur among main lobe
Null, this helical antenna are known as circular cone mould spiral antenna.The radiation characteristic of circular cone mould spiral antenna can be well by high rail
Receiver is utilized, as shown in Fig. 4 (c).
Embodiment 3：Reflector antenna
High rail spacecraft is in GEO track, and orbit altitude 35786km receives GPS constellation satellite-signal, then main lobe width c
It is 3.1814 °, b=8.6907 ° of the angle of inner conical surface.
Using reflector antenna realize Double-conical-surface cover, antenna structure as shown in figure 5, the antenna include two reflectings surface,
Double-conical-surface covering is realized whereby.
Embodiments of the present invention above described embodiment only expresses, but it cannot be understood as special to the present invention
The limitation of the range of benefit, it is noted that for those skilled in the art, without departing from the inventive concept of the premise,
Various modifications and improvements can be made, these are all belonged to the scope of protection of the present invention.
Claims (2)
1. a kind of high rail spacecraft GNSS receiver antenna based on the wave beam that is close to, which is characterized in that the high rail spacecraft
GNSS receiver antenna is ring structure, and the antenna that traditional receivers hemisphere face covers is improved to only to cover the day of annular region
Line makes the main lobe of high rail spacecraft GNSS receiver in bipyramid planar, and the female cone of main lobe is tangent with earth surface, and the earth is in
In the null of antenna, the gain that high rail spacecraft GNSS receiver gets over the earth opposite side signal of shoulder leakage is improved；
The main lobe width c of the antenna, i.e., the difference of the semiapex angle of male cone (strobilus masculinus) in Double-conical-surface are calculated according to formula (1)：
In formula：RGNSSFor GNSS satellite orbit radius；RearthFor earth radius；RGEOFor high rail satellite orbit radius；HIonFor electricity
Absciss layer height；A is the half of GNSS satellite signal beam width；
The null width b of the antenna, the i.e. semiapex angle of Double-conical-surface inner conical surface are calculated according to formula (2)：
2. a kind of high rail spacecraft GNSS receiver antenna based on the wave beam that is close to according to claim 1, feature exist
In the antenna can be helical antenna, spot beam anternma, aerial array or reflector antenna.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810603526.7A CN108899654A (en) | 2018-06-05 | 2018-06-05 | High rail spacecraft GNSS receiver antenna based on the wave beam that is close to |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810603526.7A CN108899654A (en) | 2018-06-05 | 2018-06-05 | High rail spacecraft GNSS receiver antenna based on the wave beam that is close to |
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| CN108899654A true CN108899654A (en) | 2018-11-27 |
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| CN201810603526.7A Pending CN108899654A (en) | 2018-06-05 | 2018-06-05 | High rail spacecraft GNSS receiver antenna based on the wave beam that is close to |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113745848A (en) * | 2020-05-29 | 2021-12-03 | 华为技术有限公司 | Antenna, use method and communication base station |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU3791597A (en) * | 1996-05-07 | 1997-11-26 | Leo One Ip, L.L.C. | Multi-band concentric helical antenna |
| RU2516822C2 (en) * | 2012-01-23 | 2014-05-20 | Открытое Акционерное Общество "Государственный Научно-Исследовательский Навигационно-Гидрографический Институт" | Apparatus for subglacial reception of satellite navigation system signals |
| CN104577319A (en) * | 2015-01-14 | 2015-04-29 | 西安电子科技大学 | Conical die single-arm spiral antenna with periodically-changing arm width |
| CN105006659A (en) * | 2014-04-25 | 2015-10-28 | 泰勒斯公司 | Assembly of two dual-reflector antennas and satellite comprising the same |
| CN205790398U (en) * | 2016-05-11 | 2016-12-07 | 广东通宇通讯股份有限公司 | Double frequency-band dual reflector antenna |
| CN107069225A (en) * | 2017-04-27 | 2017-08-18 | 成都雷电微力科技有限公司 | A kind of Cassegrain antenna feed structure and Cassegrain antenna |
| CN206893804U (en) * | 2017-06-23 | 2018-01-16 | 广州市易恒信息技术有限公司 | Improve the satellite antenna of positive feedback formula bireflectance parabola antenna reception and emission effciency |
-
2018
- 2018-06-05 CN CN201810603526.7A patent/CN108899654A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU3791597A (en) * | 1996-05-07 | 1997-11-26 | Leo One Ip, L.L.C. | Multi-band concentric helical antenna |
| RU2516822C2 (en) * | 2012-01-23 | 2014-05-20 | Открытое Акционерное Общество "Государственный Научно-Исследовательский Навигационно-Гидрографический Институт" | Apparatus for subglacial reception of satellite navigation system signals |
| CN105006659A (en) * | 2014-04-25 | 2015-10-28 | 泰勒斯公司 | Assembly of two dual-reflector antennas and satellite comprising the same |
| CN104577319A (en) * | 2015-01-14 | 2015-04-29 | 西安电子科技大学 | Conical die single-arm spiral antenna with periodically-changing arm width |
| CN205790398U (en) * | 2016-05-11 | 2016-12-07 | 广东通宇通讯股份有限公司 | Double frequency-band dual reflector antenna |
| CN107069225A (en) * | 2017-04-27 | 2017-08-18 | 成都雷电微力科技有限公司 | A kind of Cassegrain antenna feed structure and Cassegrain antenna |
| CN206893804U (en) * | 2017-06-23 | 2018-01-16 | 广州市易恒信息技术有限公司 | Improve the satellite antenna of positive feedback formula bireflectance parabola antenna reception and emission effciency |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113745848A (en) * | 2020-05-29 | 2021-12-03 | 华为技术有限公司 | Antenna, use method and communication base station |
| CN113745848B (en) * | 2020-05-29 | 2024-03-01 | 华为技术有限公司 | Antenna, using method and communication base station |
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Application publication date: 20181127 |