CN104269610A - Satellite data transmission antenna with wide beam and even gain advantages - Google Patents
Satellite data transmission antenna with wide beam and even gain advantages Download PDFInfo
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- CN104269610A CN104269610A CN201410498129.XA CN201410498129A CN104269610A CN 104269610 A CN104269610 A CN 104269610A CN 201410498129 A CN201410498129 A CN 201410498129A CN 104269610 A CN104269610 A CN 104269610A
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- data transmission
- satellite data
- transmission antenna
- antenna
- conical reflector
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 34
- 230000008901 benefit Effects 0.000 title abstract description 4
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- 238000009826 distribution Methods 0.000 abstract description 2
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- 230000000149 penetrating effect Effects 0.000 abstract 1
- 238000013461 design Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 4
- 230000005855 radiation Effects 0.000 description 4
- 230000006872 improvement Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000906 Bronze Inorganic materials 0.000 description 1
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000037396 body weight Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 239000010974 bronze Substances 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000011017 operating method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
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Abstract
The invention provides a satellite data transmission antenna with the wide beam and even gain advantages. The satellite data transmission antenna is of a double-helical-antenna structure and carries out feed through a coaxial line (1). The satellite data transmission antenna is characterized in that a conical reflector cup (3) is arranged at the bottom end of the coaxial line (1) in a penetrating mode, and a concave hole (4) is formed in the bottom of the conical reflector cup (3). The satellite data transmission antenna is provided with the conical reflector cup, so that influence on the antenna from reflection of a satellite deck is reduced; for a small ground proximity detector, the antenna has the even gain distribution within the required beam range by designing parameters of helical antennas, and meanwhile gains not within the beam range can be rapidly decreased; the small antenna has the wide beam and even gain advantages.
Description
Technical field
The present invention relates to space technology field, be specifically related to a kind of satellite data transmission antenna with broad beam uniform gain.
Background technology
Usual ground proximity feeler carries out digital transmission communication in order to realize with ground station, and its astronomical cycle is in absolute orientation face, and satellite requires the expenditure of energy and keeps the antenna subtend earth all the time, and antenna beam is saddle-shaped shaped-beam, and beam gain is depression at center.Particularly for small-sized satellite, due to its limited energy, and while transmitting data over the ground, what its attitude of requirement maintenance was constant carries out detected event (such as observe fixed star, measure magnetic field etc.), now, the attitude of part satellite is exactly generally keep inertial orientation, and antenna direction remains unchanged in space, so the shaped-beam antenna of central concave in the past can not use, require that the miniaturized number of a kind of broad beam uniform gain of design passes antenna and satisfies the demands.
Summary of the invention
The object of the invention is to, passing for solving existing number the wave beam requirement that antenna cannot realize broad beam uniform gain, the invention provides a kind of satellite data transmission antenna with broad beam uniform gain.
For achieving the above object, satellite data transmission antenna of the present invention adopts dual spiral antenna structure, and carries out feed by the coaxial line be provided with; The bottom of described coaxial line wears a conical reflector, and the bottom of this conical reflector is provided with shrinkage pool, by changing diameter and the degree of depth of shrinkage pool, makes the axial direct radio magnetic wave of satellite data transmission antenna and reflection electromagnetic wave be superposed to maximum gain point.
As the further improvement of technique scheme, the top of described coaxial inner conductor is welded on the inwall of its outer conductor, the top of this outer conductor offers the barron structure of two symmetrical grooves as satellite data transmission antenna, the top being welded in outer conductor of two the helix symmetries be provided with in described satellite data transmission antenna, to form the constant amplitude to two helix two-arm, anti-phase feed.
As the further improvement of technique scheme, the half of wavelength centered by the depth of groove that described coaxial line top is offered.
As the further improvement of technique scheme, the diameter of described conical reflector is two to four times of beam center wavelength, and the inclination angle between its glass of face and horizontal plane is 10 °-20 °.
A kind of satellite data transmission antenna advantage with broad beam uniform gain of the present invention is:
Satellite data transmission antenna of the present invention, by being provided with conical reflector, reduces the impact of satellite capsule plate reflection on antenna; For small-sized ground proximity feeler, by design helical antenna parameter, antenna can be made in the beam area required (± 70 °) to have uniform gain profiles (gain >=0dBi), and the gain simultaneously outside beam area can decline fast; Achieve miniature antenna total body weight when being no more than 120g, still there is the feature of broad beam uniform gain.
Accompanying drawing explanation
Fig. 1 is a kind of satellite data transmission antenna structure view with broad beam uniform gain in the embodiment of the present invention.
Fig. 2 is the structural representation of the conical reflector in the embodiment of the present invention.
Fig. 3 is that the broad beam number not being provided with conical reflector passes antenna pattern.
Fig. 4 is that the broad beam number being provided with conical reflector passes antenna pattern.
Reference numeral
1, coaxial line 2, helix 3, conical reflector
4, shrinkage pool
Embodiment
Below in conjunction with drawings and Examples, a kind of satellite data transmission antenna with broad beam uniform gain of the present invention is described in detail.
As shown in Figure 1, this satellite data transmission antenna adopts dual spiral antenna structure to the satellite data transmission antenna body structure with broad beam uniform gain in the present invention, and carries out feed by the coaxial line 1 be provided with, and feed is on antenna top.
In the present embodiment, the top of described coaxial inner conductor is welded on the inwall of its outer conductor, the top of this outer conductor can offer the barron structure of two symmetrical grooves as satellite data transmission antenna, the top being welded in outer conductor of two the helix symmetries be provided with in described satellite data transmission antenna, for the formation of the constant amplitude to two helix two-arm, anti-phase feed.
Based on the structure of above-mentioned satellite data transmission antenna; this satellite data transmission antenna and common helical antenna operation principle different; existing helical antenna adopts normal direction mould or axial mode radiation; and satellite data transmission antenna of the present invention is the leaky wave radiation characteristic work utilizing helix relevant to complex propagation constant; when operating frequency changes, its radiation main lobe can penetrate direction change from back reflection to side.
The complex propagation constant β of spiral can be write as β=β
r-j β
i, bringing above formula into propagation factor has e
-j β Z=e
-β iZe
-j β rZ, wherein, β
rfor complex propagation constant real part, β
icomplex propagation constant imaginary part, Z are coordinate Z axis; When wave beam is by very soaking, back reflection is departed from its greatest irradiation direction, and its maximum sensing angle is approximate following formula:
θ
m≈cos
-1(β
i/k)
In above formula, k=2 π/λ is free space wave number, and λ is wavelength, if suitably control complex propagation constant real part β
r, the maximum sensing of wave beam that namely programmable single-chip system is predetermined, controls its imaginary part simultaneously and can reach predetermined lobe shape and gain requirement.And just need to increase maximum sensing drift angle for obtaining broad beam, but when maximum sensing angle is departed from too large, wave beam zero angle (axis) near zone gain as shown in Figure 3 can be caved in, and causes beam gain uneven.
In order to solve the problem, as shown in Figure 1, the bottom of coaxial line 1 of the present invention wears a conical reflector 3, and as shown in Figure 2, the bottom of this conical reflector is provided with shrinkage pool 4.By changing diameter and the degree of depth of shrinkage pool 4, make the axial direct radio magnetic wave of satellite data transmission antenna and reflection electromagnetic wave be superposed to maximum gain point, and pass through the diameter and the inclination angle that change conical reflector, the electromagnetic wave distribution situation in other direction can be changed again.Because the electromagnetic wave of the direct radiation of helix and the electromagnetic wave of reflector 3 reflection are at space overlapping, antenna gain can be made when parameter is suitable to keep evenly, therefore, utilize this conical reflector that the gain of wave beam zero angle near zone not only can be made no longer to cave in, and the front and back ratio of antenna can be increased.As shown in Figure 4, utilizing the above-mentioned antenna being provided with conical reflector to carry out measurement result and Fig. 3, to carry out contrast known, not only, the beam gain of angular domain (0-20 °) improves, from θ=0, a ° gain 7.6Bi changes to θ=20 ° gain 3.6dBi, and the front and back ratio of gain also improves, before and after its gain, ratio is-16.2dBc, improves 6.6dB than the antenna gain not being provided with conical reflector.
Based on the structure of above-mentioned satellite data transmission antenna, the operating procedure of carrying out Antenna Design is: first, broad beam size as requested, back reflection angle is departed near wave beam maximum angular in the greatest irradiation direction of antenna, such as when beamwidth requires at 140 degree, so greatest irradiation direction is departed from back reflection angle and is selected between 65 ~ 75 degree.After simulation optimization, it is high that antenna pattern presents an edge gain, the state of intermediate gain depression.The adjustment operation in the greatest irradiation direction of above-mentioned antenna is the requirement in order to meet antenna beam scope, to be obtained the area size of gain depression and the position of antenna phase center by emulation, provides information for next step adds conical reflector.
Secondly, the conical reflector of design centre band shrinkage pool, according to the area size of gain obtained above depression and the positional information of antenna phase center, the degree of depth of adjusted design shrinkage pool is carried out by the parameter of antenna phase center, antenna phase center is made to be n/2 times (n is positive integer) of center of antenna wavelength to shrinkage pool bottom surface distance, during initial setting up, assuming that phase center is on antenna top, the diameter of shrinkage pool can be designed to be about 1/2 of centre wavelength, the area size caved according to gain in the diameter of conical reflector and inclination angle designs, the diameter of conical reflector generally gets 2 ~ 4 times of centre wavelengths, inclination angle between its glass of face and horizontal plane gets 10 ~ 20 degree.
Then, through simulation analysis, the directional diagram according to emulation is optimized front step parameter, obtains last antenna electric performance design parameter.
Finally, consider mechanical characteristic, the machining model of designing antenna, model imports mechanical analysis software and carries out mechanics property analysis, if do not met the demands, amendment mechanical structure, until till meeting performance requirement.Generate processing drawing to process, now helix and feed pipe can adopt beryllium-bronze to make, and weld by high temperature silver brazing, and described conical reflector can adopt aluminium alloy to make.
It should be noted last that, above embodiment is only in order to illustrate technical scheme of the present invention and unrestricted.Although with reference to embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that, modify to technical scheme of the present invention or equivalent replacement, do not depart from the spirit and scope of technical solution of the present invention, it all should be encompassed in the middle of right of the present invention.
Claims (4)
1. have a satellite data transmission antenna for broad beam uniform gain, this satellite data transmission antenna adopts dual spiral antenna structure, and carries out feed by the coaxial line (1) be provided with; It is characterized in that, the bottom of described coaxial line (1) wears a conical reflector (3), the bottom of this conical reflector (3) is provided with shrinkage pool (4), by changing diameter and the degree of depth of shrinkage pool (4), the axial direct radio magnetic wave of satellite data transmission antenna and reflection electromagnetic wave is made to be superposed to maximum gain point.
2. the satellite data transmission antenna with broad beam uniform gain according to claim 1, it is characterized in that, the top of described coaxial line (1) inner wire is welded on the inwall of its outer conductor, the top of this outer conductor offers the barron structure of two symmetrical grooves as satellite data transmission antenna, the top being welded in outer conductor that two helixes (2) be provided with in described satellite data transmission antenna are symmetrical, to form constant amplitude, the anti-phase feed to two helix (2) two-arm.
3. the satellite data transmission antenna with broad beam uniform gain according to claim 2, is characterized in that, the half of wavelength centered by the depth of groove that described coaxial line (1) top is offered.
4. the satellite data transmission antenna with broad beam uniform gain according to claim 1, is characterized in that, the diameter of described conical reflector (3) is two to four times of beam center wavelength, and the inclination angle between its glass of face and horizontal plane is 10 °-20 °.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410498129.XA CN104269610B (en) | 2014-09-25 | 2014-09-25 | A kind of satellite data transmission antenna with broad beam uniform gain |
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| CN201410498129.XA CN104269610B (en) | 2014-09-25 | 2014-09-25 | A kind of satellite data transmission antenna with broad beam uniform gain |
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| CN104269610B CN104269610B (en) | 2017-09-26 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2608016C1 (en) * | 2015-08-03 | 2017-01-11 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Дальневосточный Федеральный Университет" (Двфу) | Device for generating spatial spiral field |
| RU2608059C1 (en) * | 2015-08-03 | 2017-01-12 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Дальневосточный Федеральный Университет" (Двфу) | Device for generating spatial spiral field |
| RU2609821C1 (en) * | 2015-08-03 | 2017-02-06 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Дальневосточный Федеральный Университет" (Двфу) | Device for generating spatial spiral field |
| RU2610289C2 (en) * | 2015-08-03 | 2017-02-08 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Дальневосточный Федеральный Университет" (Двфу) | Device for generating spatial spiral field |
| CN107039751A (en) * | 2017-01-12 | 2017-08-11 | 成都天锐通科技有限公司 | A kind of helical antenna of uhf band |
| CN109462008A (en) * | 2018-10-08 | 2019-03-12 | 江苏三和欣创通信科技有限公司 | A kind of more star helical antennas of single-frequency that multisystem is compatible |
| CN111129739A (en) * | 2020-01-10 | 2020-05-08 | 西安聪睿电子科技有限公司 | Miniaturized anti-high-overload circularly polarized omnidirectional antenna |
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| CN1287393A (en) * | 1999-08-31 | 2001-03-14 | 三星电子株式会社 | Spiral antenna |
| TW200627708A (en) * | 2005-01-27 | 2006-08-01 | Univ Nat Taiwan | Bifilar helical antenna |
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2014
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| CN1287393A (en) * | 1999-08-31 | 2001-03-14 | 三星电子株式会社 | Spiral antenna |
| US7151509B2 (en) * | 2003-12-24 | 2006-12-19 | The Boeing Company | Apparatus for use in providing wireless communication and method for use and deployment of such apparatus |
| TW200627708A (en) * | 2005-01-27 | 2006-08-01 | Univ Nat Taiwan | Bifilar helical antenna |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2608016C1 (en) * | 2015-08-03 | 2017-01-11 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Дальневосточный Федеральный Университет" (Двфу) | Device for generating spatial spiral field |
| RU2608059C1 (en) * | 2015-08-03 | 2017-01-12 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Дальневосточный Федеральный Университет" (Двфу) | Device for generating spatial spiral field |
| RU2609821C1 (en) * | 2015-08-03 | 2017-02-06 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Дальневосточный Федеральный Университет" (Двфу) | Device for generating spatial spiral field |
| RU2610289C2 (en) * | 2015-08-03 | 2017-02-08 | Федеральное Государственное Автономное Образовательное Учреждение Высшего Профессионального Образования "Дальневосточный Федеральный Университет" (Двфу) | Device for generating spatial spiral field |
| CN107039751A (en) * | 2017-01-12 | 2017-08-11 | 成都天锐通科技有限公司 | A kind of helical antenna of uhf band |
| CN107039751B (en) * | 2017-01-12 | 2023-05-16 | 成都天锐通科技有限公司 | Spiral antenna of UHF frequency band |
| CN109462008A (en) * | 2018-10-08 | 2019-03-12 | 江苏三和欣创通信科技有限公司 | A kind of more star helical antennas of single-frequency that multisystem is compatible |
| CN111129739A (en) * | 2020-01-10 | 2020-05-08 | 西安聪睿电子科技有限公司 | Miniaturized anti-high-overload circularly polarized omnidirectional antenna |
| CN111129739B (en) * | 2020-01-10 | 2024-05-03 | 西安聪睿电子科技有限公司 | Miniaturized high overload resistant circularly polarized omnidirectional antenna |
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Address after: 100190 No. two south of Zhongguancun, Haidian District, Beijing 1 Patentee after: NATIONAL SPACE SCIENCE CENTER, CAS Address before: 100190 No. two south of Zhongguancun, Haidian District, Beijing 1 Patentee before: NATIONAL SPACE SCIENCE CENTER, CHINESE ACADEMY OF SCIENCES |
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Granted publication date: 20170926 |