CN112670705A - Satellite-borne circularly polarized antenna - Google Patents
Satellite-borne circularly polarized antenna Download PDFInfo
- Publication number
- CN112670705A CN112670705A CN202011336685.9A CN202011336685A CN112670705A CN 112670705 A CN112670705 A CN 112670705A CN 202011336685 A CN202011336685 A CN 202011336685A CN 112670705 A CN112670705 A CN 112670705A
- Authority
- CN
- China
- Prior art keywords
- spiral line
- satellite
- circularly polarized
- borne
- helix
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000004020 conductor Substances 0.000 claims abstract description 3
- 229910000906 Bronze Inorganic materials 0.000 claims description 4
- 229910052790 beryllium Inorganic materials 0.000 claims description 4
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 claims description 4
- 239000010974 bronze Substances 0.000 claims description 4
- KUNSUQLRTQLHQQ-UHFFFAOYSA-N copper tin Chemical compound [Cu].[Sn] KUNSUQLRTQLHQQ-UHFFFAOYSA-N 0.000 claims description 4
- 238000010586 diagram Methods 0.000 description 6
- 230000010287 polarization Effects 0.000 description 5
- 238000004891 communication Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000003321 amplification Effects 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000003199 nucleic acid amplification method Methods 0.000 description 2
- 241000122106 Diatraea saccharalis Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000006260 foam Substances 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 230000000699 topical effect Effects 0.000 description 1
Images
Abstract
The invention relates to the technical field of antennas, and discloses a satellite-borne circularly polarized antenna which comprises a first spiral line, a second spiral line, a feed network, a tensioning mechanism and a radio frequency interface, wherein the tail ends of the first spiral line and the second spiral line are respectively connected to the feed network, the top ends of the first spiral line and the second spiral line are respectively connected with the tensioning mechanism, the first spiral line and the second spiral line are mutually crossed and coiled, the first spiral line and the second spiral line are made of elastic conductive materials, and the radio frequency interface is arranged on the feed network. The satellite-borne circularly polarized antenna provided by the invention adopts the double-arm conical spiral line, the working bandwidth of the antenna is improved, the whole antenna can be simply folded and unfolded through the elastic matching tensioning mechanism of the spiral line, and the structure is simple.
Description
Technical Field
The invention relates to the technical field of antennas, in particular to a satellite-borne circularly polarized broadband antenna.
Background
In a modern radio frequency system, the broadband antenna can meet the requirement that a plurality of radio frequency electronic systems receive and transmit electromagnetic waves through the same antenna aperture, and the number of the antennas can be reduced, so that the complexity of the system is greatly reduced, and the miniaturization of equipment is realized.
Thirdly, any incoming wave with linear polarization can be received by the circularly polarized antenna, or the circularly polarized wave radiated by the circularly polarized antenna can be received by any linearly polarized antenna. Therefore, the strength of the signal received by the circularly polarized antenna is not affected by the relative orientation of the transmitting antenna and the receiving antenna. In addition, circular polarization can effectively suppress rain and fog interference and multipath effects, and is widely used in satellite communication, radar and other systems.
The small satellite has high application value in communication, radar and navigation due to the fast development period and low cost. Meanwhile, small satellites are required to have small volume and light weight.
The conical helical antenna has wide bandwidth, can receive and transmit circularly polarized waves, but has high height, and cannot be directly applied to small satellites.
The currently reported deployable circularly polarized helical antenna includes:
a. single-arm cylindrical helical Antennas (see documents: j.costationine, y.tawk, s.moth, c.g. christodouou, s.e.barbin.a modified textual shared available antenna for documents, 2012IEEE-APS Topical Conference on antenna and Propagation in Wireless Communications and j.costationine, k.y.kabalan, a.el Hajj, y.tawk, c.g. christodouou.a configurable/scalable available antenna for documents, 2013IEEE Antennas and Propagation in interactive Society system) can achieve single-feed-point folding and unfolding, but with narrower bandwidth.
b. Four-arm helical Antennas (see documents: S.Gao, K.Clark, M.Unwin, J.Zackrisson, W.A.Shiroma et al.antennas for modular small satellites, IEEE Antennas and amplification major, 51(4), pp.40-56,2009 and J.Costatine, Y.Tawk, C.G.Christodou, et al.UHF amplified magnetic Antennas for CubeSat, IEEE Transactions on Antennas and amplification, 64(9), pp.3752-3759,2016) with constant helical diameter and complex deployment mechanism.
c. Conical helical Antennas (see documents s.gao, k.clark, m.uwin, j.zakrisson, w.a.shiroma et al.antennas for modular small satellites, IEEE Antennas and Propagation Antennas, 51(4), pp.40-56,2009), which require radomes and are therefore not easily collapsible.
d. Conical helical Antennas (see documents: A.J. Erest, Y.Tawk, J.Costantine, C.G. Christodou.A bottom fed planar antenna design for CubeSat, IEEE Transactions on Antennas and Propagation,63(1), pp.41-47,2015), using logarithmic conical helical circuits, requiring foam as a support, not easily collapsible, or using soft substrates for printing (see documents: J.Costantine, Y.Tawk, C.G.Christodou, et al UHF.depolyyaural Antennas for CubeSat, IEEE Transactions on Antennas and Propagation,64 (9)), 3752-3759,2016, not easily expandable.
In summary, the existing deployable satellite-borne circularly polarized broadband antenna has the technical problems of narrow bandwidth, complicated deployment mechanism, difficulty in folding or unfolding, and the like.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the existing problems, the satellite-borne circularly polarized broadband antenna is provided, and the conical helical antenna is adopted, so that the working bandwidth of the antenna is improved; the structure is simple, the reliability is high, and the folding and the unfolding can be realized; and the device is folded in the launching stage to reduce the height, so that a small satellite can be conveniently placed in the device, and the device can be unfolded and operated after the satellite is in orbit.
The technical scheme adopted by the invention is as follows: a satellite-borne circularly polarized antenna comprises a first spiral line, a second spiral line, a feed network, a radio frequency interface and a tensioning mechanism; radio frequency interface installs on the feed network, the end of first helix and second helix is connected respectively on the feed network, the top of first helix and second helix respectively with straining mechanism links to each other, first helix with the second helix intercrossing spirals, first helix with the second helix adopts to make with elastic conducting material, and when the antenna needs work, release straining mechanism, through the elasticity of first helix and second helix self, realize the expansion of antenna, when work is accomplished, need fold up when working, through fixing straining mechanism on the feed network, draw in first helix and second helix folding in.
Further, the first spiral line and the second spiral line are made of beryllium bronze wires with round sections and elasticity.
Further, the equation of the first spiral line is:
where, referring to fig. 3, ρ is the radius of the polar coordinate, i.e. the distance of the projection of the point on the xoy plane from the origin O of the coordinate,
is a polar coordinate angle, i.e. the included angle between the projection of a point on the xoy plane and the x-axis, rho0Is the initial radius, a is the growth rate, theta is the included angle between the outer envelope of the first spiral line and the z-axis,
the value is in the range of 0 to 2N pi, N being the number of turns of the first spiral. And the first spiral line and the second spiral line are arranged in central symmetry, namely the second spiral line is obtained by rotating the first spiral line for 180 degrees around the z axisAnd (4) obtaining.
Furthermore, a first feeding point and a second feeding point are arranged on the feeding network, the tail end of the first spiral line is connected to the first feeding point, and the tail end of the second spiral line is connected to the second feeding point.
Further, the tensioning mechanism has a resistance value, and the range of the resistance value is 0-200 ohms.
Compared with the prior art, the beneficial effects of adopting the technical scheme are as follows:
a. the antenna adopts the elastic conductive metal material, on one hand, the antenna is used as a radiator of the antenna, on the other hand, the antenna can be unfolded by itself due to the elasticity, no additional unfolding or supporting mechanism is needed, and the structure is simple.
b. And a double-arm conical spiral line is adopted, and the circularly polarized bandwidth is wide.
c. The spiral line feeds power at the bottom and is in hard connection with the feed network, so that the reliability is high.
Drawings
FIG. 1 is a schematic diagram of a spread state of a satellite-borne circularly polarized broadband antenna according to the present invention.
Fig. 2 is a schematic view of a folded state of the satellite-borne circularly polarized broadband antenna according to the present invention.
Fig. 3 is a schematic view of helix a.
FIG. 4 is a plot of circularly polarized axial ratio results.
Fig. 5 is a graph of gain results.
FIG. 6 is a schematic diagram of a 5GHz direction of the satellite-borne circularly polarized antenna in an unfolded state.
Reference numerals: 1-tensioning mechanism, 2-radio frequency interface, 3-feed network, 4-helix A, 5-helix B, 6-feed point A, 7-feed point B.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1 and fig. 2, an embodiment of the present invention provides a satellite-borne circularly polarized antenna, including: helix A, helix B, radio frequency interface, feed network and straining device.
Specifically, in this embodiment, helix A and helix B are connected with resistant irradiation's straining device on the helix top, and helix A and helix B's end is installed on the feed network, and helix A and helix B all adopt the preparation of having elastic metal material to form. The satellite-borne circularly polarized antenna is prepared in its unfolded state by fixing the tensioning mechanism to the feed network before satellite transmission, as shown in fig. 2.
When the satellite-borne circularly polarized antenna needs to work, the tensioning mechanism is released, the antenna is unfolded through the elasticity of the spiral line A and the spiral line B, and after the work is finished and the antenna needs to be folded, the tensioning mechanism is fixed on the feed network to fold the spiral line A and the spiral line B.
In this embodiment, the equation for helix A is
Where, referring to fig. 3, ρ is the radius of the polar coordinate, i.e. the distance of the projection of the point on the xoy plane from the origin O of the coordinate,
is a polar coordinate angle, i.e. the included angle between the projection of a point on the xoy plane and the x-axis, rho0At the initial radius, a is the growth rate and θ is the included angle between the outer envelope of the helix A and the z-axis.
The value is in the range of 0 to 2N pi, N being the number of turns of the helix a.
The spiral line A and the spiral line B are arranged in a centrosymmetric mode, namely the spiral line B is obtained after the spiral line A rotates 180 degrees around a z axis.
Preferably, a feeding point a and a feeding point B are further provided on the feeding network, and the spiral line a and the spiral line B are fixed to the feeding network at the feeding point a and the feeding point B by hard connection at the tail end of the spiral line.
Preferably, the spiral line A and the spiral line B adopt circular beryllium bronze wires.
Preferably, the tension mechanism has a resistance value in the range of 0 to 200 ohms.
In the following, a specific implementation example is given.
The satellite-borne circularly polarized antenna designed by the method has the working frequency (Freq) from 2.5GHz to 7 GHz. The materials of the spiral line A and the spiral line B are beryllium bronze, the diameter is 1mm, and the initial radius rho03mm, the growth rate a is 0.1, the included angle theta between the outer envelope of the spiral line A and the z axis is 10 degrees, and the number of turns N of the spiral line A is 28. When the feeding network is folded, the tensioning mechanism is tensioned and fixed on the feeding network through a stay cable; when the spiral line is unfolded, the inhaul cable is released, and the spiral line is unfolded.
The circular polarization Axial Ratio (AR) result of the satellite-borne circular polarization antenna in the unfolded state is shown in fig. 4, and circular polarization is realized within the working frequency band.
The Gain (Gain) result of the satellite-borne circularly polarized antenna in the unfolded state is shown in fig. 5, and the Gain of more than 7dB is realized in the working frequency band.
The 5GHz directional diagram of the satellite-borne circularly polarized antenna in the unfolded state is shown in fig. 6, wherein the dotted line in the diagram is a xoy plane circularly polarized gain directional diagram, and the solid line is a yoz plane circularly polarized gain directional diagram.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed. Those skilled in the art to which the invention pertains will appreciate that insubstantial changes or modifications can be made without departing from the spirit of the invention as defined by the appended claims.
Claims (8)
1. A satellite-borne circularly polarized antenna is characterized by comprising a first spiral line, a second spiral line, a feed network and a tensioning mechanism; the end of first helix and second helix is connected respectively on the feed network, the top of first helix and second helix respectively with straining device links to each other, first helix with the second helix intercrossing spirals, first helix with the second helix adopts elastic conducting material to make.
2. The satellite-borne circularly polarized antenna as claimed in claim 1, wherein the first spiral line and the second spiral line are made of circular beryllium bronze wires.
3. The satellite-borne circularly polarized antenna according to claim 1, wherein the equation of the first spiral is:
wherein rho is the radius of a polar coordinate, namely the distance from the projection of a point on the xoy plane to the origin O of the coordinate,
is a polar coordinate angle, i.e. the included angle between the projection of a point on the xoy plane and the x-axis, rho0Is the initial radius, a is the growth rate, theta is the included angle between the outer envelope of the first spiral line and the z-axis,
the value is in the range of 0 to 2N pi, N being the number of turns of the first spiral.
4. The satellite-borne circularly polarized antenna according to claim 4, wherein the first spiral line and the second spiral line are arranged in a central symmetry manner.
5. The satellite-borne circularly polarized antenna according to claim 1, wherein a first feeding point and a second feeding point are provided on the feeding network, a terminal end of the first spiral line is connected to the first feeding point, and a terminal end of the second spiral line is connected to the second feeding point.
6. The satellite-borne circularly polarized antenna according to claim 1, wherein said tension mechanism has a resistance value.
7. The satellite-borne circularly polarized antenna according to claim 6, wherein the resistance value is in a range of 0 to 200 ohms.
8. The satellite-borne circularly polarized antenna according to claim 1, wherein a radio frequency interface is further disposed on the feeding network.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011336685.9A CN112670705A (en) | 2020-11-25 | 2020-11-25 | Satellite-borne circularly polarized antenna |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011336685.9A CN112670705A (en) | 2020-11-25 | 2020-11-25 | Satellite-borne circularly polarized antenna |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112670705A true CN112670705A (en) | 2021-04-16 |
Family
ID=75402951
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011336685.9A Pending CN112670705A (en) | 2020-11-25 | 2020-11-25 | Satellite-borne circularly polarized antenna |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112670705A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5216436A (en) * | 1991-05-31 | 1993-06-01 | Harris Corporation | Collapsible, low visibility, broadband tapered helix monopole antenna |
| CN1220772A (en) * | 1997-03-17 | 1999-06-23 | 松下电器产业株式会社 | Method and device for plasma treatment |
| CN1261210A (en) * | 1999-01-19 | 2000-07-26 | 皇家菲利浦电子有限公司 | Antenna system for satellite mobile telephone and mobile telephone therewith |
| US20110248894A1 (en) * | 2010-04-13 | 2011-10-13 | Crowley Robert J | Adjustable spiral antenna for portable use |
| CN106887689A (en) * | 2017-03-31 | 2017-06-23 | 中国电子科技集团公司第二十九研究所 | Broadband and wideangle circular polarisation conical spiral antenna |
-
2020
- 2020-11-25 CN CN202011336685.9A patent/CN112670705A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5216436A (en) * | 1991-05-31 | 1993-06-01 | Harris Corporation | Collapsible, low visibility, broadband tapered helix monopole antenna |
| CN1220772A (en) * | 1997-03-17 | 1999-06-23 | 松下电器产业株式会社 | Method and device for plasma treatment |
| CN1261210A (en) * | 1999-01-19 | 2000-07-26 | 皇家菲利浦电子有限公司 | Antenna system for satellite mobile telephone and mobile telephone therewith |
| US20110248894A1 (en) * | 2010-04-13 | 2011-10-13 | Crowley Robert J | Adjustable spiral antenna for portable use |
| CN106887689A (en) * | 2017-03-31 | 2017-06-23 | 中国电子科技集团公司第二十九研究所 | Broadband and wideangle circular polarisation conical spiral antenna |
Non-Patent Citations (1)
| Title |
|---|
| 刘颖 等: "圆锥对数螺旋天线的设计和验证", 《电子信息对抗技术》 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6791508B2 (en) | Wideband conical spiral antenna | |
| US6653987B1 (en) | Dual-band quadrifilar helix antenna | |
| US5255005A (en) | Dual layer resonant quadrifilar helix antenna | |
| US6320549B1 (en) | Compact dual mode integrated antenna system for terrestrial cellular and satellite telecommunications | |
| US6147647A (en) | Circularly polarized dielectric resonator antenna | |
| US6133891A (en) | Quadrifilar helix antenna | |
| US9246224B2 (en) | Broadband antenna system allowing multiple stacked collinear devices and having an integrated, co-planar balun | |
| US6229499B1 (en) | Folded helix antenna design | |
| USRE42533E1 (en) | Capacitatively shunted quadrifilar helix antenna | |
| US10038235B2 (en) | Multi-mode, multi-band antenna | |
| US20170237174A1 (en) | Broad Band Diversity Antenna System | |
| CN108155460B (en) | Double-frequency omni-directional coupling support-section loaded spiral antenna and manufacturing method thereof | |
| US6535179B1 (en) | Drooping helix antenna | |
| H Patel et al. | A comprehensive review on multi-band microstrip patch antenna comprising 5G wireless communication | |
| US7515113B2 (en) | Antenna with parasitic rings | |
| King et al. | Helical antennas | |
| CN106961006B (en) | Dual-band dual-mode miniaturized handheld antenna | |
| CN112670705A (en) | Satellite-borne circularly polarized antenna | |
| Gschwendtner et al. | Spiral antenna with frequency-independent coplanar feed for mobile communication systems | |
| US7420521B2 (en) | Wideband segmented dipole antenna | |
| US20190391223A1 (en) | Eloran receiver with ferromagnetic body and related antennas and methods | |
| Narimani et al. | Design of a Self-Phased Quadrifilar Helix Antenna for Satellite Communication | |
| KR100581442B1 (en) | An antenna arrangement for a portable radio communication device | |
| Wang et al. | A high-power wide beamwidth circularly polarized antenna with lightning protection | |
| Renwarin et al. | Conformal Triangular Slotted Antenna for Rocket Sounding Application |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210416 |
|
| RJ01 | Rejection of invention patent application after publication |