CN105811068A - Portable satellite antenna structure - Google Patents
Portable satellite antenna structure Download PDFInfo
- Publication number
- CN105811068A CN105811068A CN201610159623.2A CN201610159623A CN105811068A CN 105811068 A CN105811068 A CN 105811068A CN 201610159623 A CN201610159623 A CN 201610159623A CN 105811068 A CN105811068 A CN 105811068A
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- CN
- China
- Prior art keywords
- fixed disk
- end fixed
- bulb
- connecting rod
- support arm
- 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.)
- Granted
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Classifications
-
- 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
-
- 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
- H01Q15/14—Reflecting surfaces; Equivalent structures
- H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
- H01Q15/165—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal composed of a plurality of rigid panels
- H01Q15/166—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal composed of a plurality of rigid panels sector shaped
-
- 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
- H01Q19/12—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 wherein the surfaces are concave
- H01Q19/13—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 wherein the surfaces are concave the primary radiating source being a single radiating element, e.g. a dipole, a slot, a waveguide termination
Landscapes
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Support Of Aerials (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
The invention provides a portable satellite antenna structure, which comprises a reflecting cover, a front-end fixed disk, a rear-end fixed disk, a tuner adjusting bracket and a support seat, wherein the reflecting cover comprises combined blades; the front-end fixed disk comprises a connecting rod, a bulb and a press plate; the press plate is provided with the connecting rod; the bulb is arranged at one end of the connecting rod; the press plate and the connecting rod are coaxially arranged; a connection hole is formed in the center position of the rear-end fixed disk; and the tuner adjusting bracket comprises a sleeve, an elevation adjusting shaft, a support arm, a support rotating shaft, a support arm locking bolt, a small swing arm, a small swing arm locking bolt, a turning direction adjusting ring and an adjusting ring arm locking bolt. The portable satellite antenna structure has the advantages of being reliable in structure, convenient to carry and fast to disassemble and assemble, and meanwhile, adjustment on the satellite angle by the satellite antenna is facilitated.
Description
Technical field
The present invention relates to the satellite electron communications field, specifically a kind of Portable satellite aerial structure.
Background technology
Satellite communication equipment has become as the indispensable electronic equipment of modernization sciemtifec and technical sphere, satellite-signal has wide coverage and signal transmits the advantage not affected by physical features, it is widely used during communication in the wild, diameter dimension very much not Portable belt due to satellite antenna mounting structure complexity and reflector, it thus provides a Portable satellite aerial structure is easy to field carries use.
The technical problem to be solved in the present invention is: can be split by each parts of satellite antenna, makes satellite antenna dismounting efficient and convenient simultaneously.
The technical solution adopted for the present invention to solve the technical problems is:
Providing a kind of Portable satellite aerial structure, including reflector, front end fixed disk, rear end fixed disk, tuner adjusting bracket and bearing, reflector is formed by combining leaf；Front end fixed disk includes connecting rod, bulb and platen, and platen is provided with connecting rod, and one end of connecting rod is provided with bulb, and described platen and connecting rod are coaxially disposed mutually；Fixed disk center, rear end is provided with connecting hole；Tuner adjusting bracket includes sleeve pipe, the elevation angle regulates axle, support arm, support rotating shaft, support arm clamping screw, little swing arm, little swing arm clamping screw, rotation direction regulates ring and regulates ring arm clamping screw, described rotation direction regulates and is provided with adjustment ring arm clamping screw on ring circumference, rotation direction is regulated ring and is connected with one end of little swing arm by little swing arm clamping screw, the other end of little swing arm is provided with support rotating shaft, support rotating shaft and be provided with support arm installing hole, one end of support arm is arranged in brace installing hole by support arm clamping screw, described support arm can around supporting shaft swing, the other end of support arm is provided with the elevation angle and regulates axle, the elevation angle regulates and is provided with sleeve pipe on axle；Bearing includes mounting flange, bulb bearing shell and flange hole, and mounting flange is provided with flange hole, and mounting flange is arranged on the bottom of bearing, and bulb bearing shell is arranged on the top of bearing；Connecting rod cooperates with connecting hole and is connected, reflector is arranged between front end fixed disk and rear end fixed disk, reflector is clamped and fixes by described front end fixed disk and rear end fixed disk, tuner adjusting bracket regulates ring by rotation direction and is arranged on the fixed disk of rear end, described rotation direction regulates the diameter of bore diameter more than rear end fixed disk of ring, sleeve pipe is arranged on the front end of reflector, and bulb is arranged in bulb bearing shell, and described bulb can rotate in bulb bearing shell.
As preferably, described combination leaf is sector structure, and reflector is arranged between front end fixed disk and rear end fixed disk after being combined by multiple combination leaves.
As preferably, described combination leaf adopts galvanized steel plain sheet material to make.
As preferably, described support arm is circular tube structure.
As preferably, described platen is curved surface arcuate structure.
As preferably, described platen adopts magnetic material to make.
As preferably, the end face of described rear end fixed disk and reflector link is spill globoidal structure.
As preferably, described connecting rod circumference is provided with external thread structure.
As preferably, described connecting hole is provided with female thread structure.
The invention has the beneficial effects as follows, the present invention has that structure is reliable, is easy to carry and dismounts advantage efficiently, simultaneously facilitates the satellite antenna adjustment to star angle.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, the accompanying drawing used required in embodiment or description of the prior art will be briefly described below, apparently, accompanying drawing in the following describes is only some embodiments of the present invention, for those of ordinary skill in the art, under the premise not paying creative work, it is also possible to obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is the overall combinative structure schematic diagram that the embodiment of the present invention provides；
Fig. 2 is the overall decomposition texture schematic diagram that the embodiment of the present invention provides；
Fig. 3 is the bowl portion decomposition texture schematic diagram that the embodiment of the present invention provides；
In figure: 1. reflector, 1.1. combines leaf；
2. front end fixed disk, 2.1. connecting rod, 2.2. bulb, 2.3 platens；
3. rear end fixed disk, 3.1. connecting hole；
4. tuner adjusting bracket, 4.1. sleeve pipe, the 4.2. elevation angle regulates axle, 4.3. support arm, 4.4. rotating shaft, 4.41. support arm installing hole, 4.5. support arm clamping screw, the little swing arm of 4.6. are supported, 4.7. little swing arm clamping screw, 4.8. rotation direction regulates ring, and 4.9. regulates ring arm clamping screw；
5. bearing, 5.1. mounting flange, 5.2. bulb bearing shell, 5.3. flange hole.
Detailed description of the invention
Below in conjunction with specific embodiment, such scheme is described further.It should be understood that these embodiments are an illustration for the present invention rather than restriction the scope of the present invention.The implementation condition adopted in embodiment can do further adjustment according to the condition of concrete producer, and not marked implementation condition is generally the condition in normal experiment.
As shown in Figure 1-Figure 3, Fig. 1 is the overall combinative structure schematic diagram that the embodiment of the present invention provides, and Fig. 2 is the overall decomposition texture schematic diagram that the embodiment of the present invention provides, and Fig. 3 is the bowl portion decomposition texture schematic diagram that the embodiment of the present invention provides.
In a kind of specific embodiment, it is provided that a kind of Portable satellite aerial structure, including reflector 1, front end fixed disk 2, rear end fixed disk 3, tuner adjusting bracket 4 and bearing 5, reflector 1 is made up of combination leaf 1.1；Front end fixed disk 2 includes connecting rod 2.1, bulb 2.2 and platen 2.3, and platen 2.3 is provided with connecting rod 2.1, and one end of connecting rod 2.1 is provided with bulb 2.2, and described platen 2.3 is coaxially disposed mutually with connecting rod 2.1；Rear end fixed disk 3 center is provided with connecting hole 3.1；nullTuner adjusting bracket 4 includes sleeve pipe 4.1、The elevation angle regulates axle 4.2、Support arm 4.3、Support rotating shaft 4.4、Support arm clamping screw 4.5、Little swing arm 4.6、Little swing arm clamping screw 4.7、Rotation direction regulates ring 4.8 and regulates ring arm clamping screw 4.9，Described rotation direction regulates and is provided with adjustment ring arm clamping screw 4.9 on ring 4.8 circumference，Rotation direction is regulated ring 4.8 and is connected by one end of little swing arm clamping screw 4.7 with little swing arm 4.6，The other end of little swing arm 4.6 is provided with support rotating shaft 4.4，Support rotating shaft 4.4 and be provided with support arm installing hole 4.41，One end of support arm 4.3 is arranged in brace installing hole 4.41 by support arm clamping screw 4.5，Described support arm 4.3 can swing around supporting rotating shaft 4.4，The other end of support arm 4.3 is provided with the elevation angle and regulates axle 4.2，The elevation angle regulates and is provided with sleeve pipe 4.1 on axle 4.2；Bearing 5 includes mounting flange 5.1, bulb bearing shell 5.2 and flange hole 5.3, and mounting flange 5.1 is provided with flange hole 5.3, and mounting flange 5.1 is arranged on the bottom of bearing 5, and bulb bearing shell 5.2 is arranged on the top of bearing 5；Connecting rod 2.1 cooperates with connecting hole 3.1 and is connected, reflector 1 is arranged between front end fixed disk 2 and rear end fixed disk 3, reflector 1 is clamped and fixes with rear end fixed disk 3 by described front end fixed disk 2, tuner adjusting bracket 4 regulates ring 4.8 by rotation direction and is arranged on rear end fixed disk 3, described rotation direction regulates the diameter of bore diameter more than rear end fixed disk 3 of ring 4.8, sleeve pipe 4.1 is arranged on the front end of reflector 1, bulb 2.2 is arranged in bulb bearing shell 5.2, and described bulb 2.2 can rotate in bulb bearing shell 5.2.
As preferably, described combination leaf 1.1 is sector structure, and reflector 1 is arranged between front end fixed disk 2 and rear end fixed disk 3 after being combined by multiple combination leaves 1.1, therefore, can reduce the space that reflector 1 takies when satellite antenna carries.
As preferably, described combination leaf 1.1 adopts galvanized steel plain sheet material to make, and galvanized steel plain sheet has good pressworkability and good weatherability properties, can be adsorbed on magnetic material, therefore simultaneously, it is simple to combination leaf 1.1 is arranged on platen 2.3.
As preferably, described support arm 4.3 is circular tube structure, therefore, it is simple to the angular adjustment of tuner and can reduce the weight of support arm 4.3.
As preferably, described platen 2.3 is curved surface arcuate structure, therefore, it is possible to make platen 2.3 coordinate tightr with reflector 1, it is to avoid the combination leaf 1.1 of reflector 1 deforms when fixing.
As preferably, described platen 2.3 adopts magnetic material to make, it is possible to be easy to the fixed and positioned of combination leaf 1.1, avoids combination leaf 1.1 clamping process to rotate, therefore, it is simple to the installation of satellite antenna and adjustment simultaneously.
As preferably, described rear end fixed disk 3 and the end face of reflector 1 link are spill globoidal structure, therefore, it is possible to make rear end fixed disk 3 coordinate tightr with reflector 1, it is to avoid the combination leaf 1.1 of reflector 1 deforms when fixing.
As preferably, described connecting rod 2.1 circumference is provided with external thread structure, therefore, it is simple to the installation of rear end fixed disk 3 and front end fixed disk 2, it is simple to the dismounting of combination leaf 1.1, simultaneously facilitates production and processing.
As preferably, described connecting hole 3.1 is provided with female thread structure.
Specific works process, when satellite antenna carries, open bulb bearing shell 5.2, bulb 2.2 is taken out in bulb bearing shell 5.2, bearing 5 is made to separate with connecting rod 2.1, by screwing support arm clamping screw 4.5 counterclockwise, support arm 4.3 is separated with little swing arm 4.6, by screwing adjustment ring arm clamping screw 4.9 counterclockwise, rotation direction regulates ring 4.8 separate with rear end fixed disk 3, by screwing rear end fixed disk 3 counterclockwise, front end fixed disk 2 and rear end fixed disk 3 is made no longer to clamp each combination leaf 1.1 of reflector 1, combination leaf 1.1 is taken off respectively from front end fixed disk 2, therefore, it is easy to carrying of satellite antenna.
nullWhen satellite antenna uses，Each combination leaf 1.1 of reflector 1 is arranged on front end fixed disk 2 by platen 2.3 absorption successively，Rear end fixed disk 3 is connected with the connecting rod 2.1 on front end fixed disk 2，Screw rear end fixed disk 3 clockwise simultaneously，The each combination leaf 1.1 making reflector 1 is clamped between rear end fixed disk 3 and front end fixed disk 2，Rotation direction regulates ring 4.8 be enclosed within the circumference of rear end fixed disk 3，Regulate rotation direction simultaneously and regulate the position of ring 4.8，By screwing adjustment ring arm clamping screw 4.9 clockwise，Make rotation direction regulate ring 4.8 to be fixed on rear end fixed disk 3，Bulb 2.2 is arranged in bulb bearing shell 5.2，The adjusting ball head 2.2 position in bulb bearing shell 5.2 simultaneously，Support arm 4.3 is installed by supporting rotating shaft 4.4 one end of little swing arm 4.6，Regulate setting angle and the position of support arm 4.3 simultaneously，By screwing support arm clamping screw 4.5 clockwise，Support arm 4.3 is made to be fixed in little swing arm 4.6；Tuner is arranged in sleeve pipe 4.1, regulates axle 4.2 by the elevation angle and regulate the angle of tuner, when carrying out satellite antenna to star, it is possible to regulate the relative position between each parts further, it is achieved normally receiving of satellite-signal.
With the above-mentioned desirable embodiment according to the present invention for enlightenment, by above-mentioned description, relevant staff in the scope not necessarily departing from this invention technological thought, can carry out various change and amendment completely.The technical scope of this invention is not limited to the content in description, it is necessary to determine its technical scope according to right.
Claims (9)
1. a Portable satellite aerial structure, including reflector, front end fixed disk, rear end fixed disk, tuner adjusting bracket and bearing, it is characterised in that: reflector is formed by combining leaf；Front end fixed disk includes connecting rod, bulb and platen, and platen is provided with connecting rod, and one end of connecting rod is provided with bulb, and described platen and connecting rod are coaxially disposed mutually；Fixed disk center, rear end is provided with connecting hole；Tuner adjusting bracket includes sleeve pipe, the elevation angle regulates axle, support arm, support rotating shaft, support arm clamping screw, little swing arm, little swing arm clamping screw, rotation direction regulates ring and regulates ring arm clamping screw, described rotation direction regulates and is provided with adjustment ring arm clamping screw on ring circumference, rotation direction is regulated ring and is connected with one end of little swing arm by little swing arm clamping screw, the other end of little swing arm is provided with support rotating shaft, support rotating shaft and be provided with support arm installing hole, one end of support arm is arranged in brace installing hole by support arm clamping screw, described support arm can around supporting shaft swing, the other end of support arm is provided with the elevation angle and regulates axle, the elevation angle regulates and is provided with sleeve pipe on axle；Bearing includes mounting flange, bulb bearing shell and flange hole, and mounting flange is provided with flange hole, and mounting flange is arranged on the bottom of bearing, and bulb bearing shell is arranged on the top of bearing；Connecting rod cooperates with connecting hole and is connected, reflector is arranged between front end fixed disk and rear end fixed disk, reflector is clamped and fixes by described front end fixed disk and rear end fixed disk, tuner adjusting bracket regulates ring by rotation direction and is arranged on the fixed disk of rear end, described rotation direction regulates the diameter of bore diameter more than rear end fixed disk of ring, sleeve pipe is arranged on the front end of reflector, and bulb is arranged in bulb bearing shell, and described bulb can rotate in bulb bearing shell.
2. a kind of Portable satellite aerial structure as claimed in claim 1, it is characterised in that described combination leaf is sector structure, and reflector is arranged between front end fixed disk and rear end fixed disk after being combined by multiple combination leaves.
3. a kind of Portable satellite aerial structure as claimed in claim 1, it is characterised in that described combination leaf adopts galvanized steel plain sheet material to make.
4. a kind of Portable satellite aerial structure as claimed in claim 1, it is characterised in that described support arm is circular tube structure.
5. a kind of Portable satellite aerial structure as claimed in claim 1, it is characterised in that described platen is curved surface arcuate structure.
6. a kind of Portable satellite aerial structure as claimed in claim 1, it is characterised in that described platen adopts magnetic material to make.
7. a kind of Portable satellite aerial structure as claimed in claim 1, it is characterised in that the end face of described rear end fixed disk and reflector link is spill globoidal structure.
8. a kind of Portable satellite aerial structure as claimed in claim 1, it is characterised in that described connecting rod circumference is provided with external thread structure.
9. a kind of Portable satellite aerial structure as claimed in claim 1, it is characterised in that described connecting hole is provided with female thread structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610159623.2A CN105811068B (en) | 2016-03-21 | 2016-03-21 | A kind of Portable satellite aerial structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610159623.2A CN105811068B (en) | 2016-03-21 | 2016-03-21 | A kind of Portable satellite aerial structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105811068A true CN105811068A (en) | 2016-07-27 |
| CN105811068B CN105811068B (en) | 2018-05-08 |
Family
ID=56454094
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610159623.2A Expired - Fee Related CN105811068B (en) | 2016-03-21 | 2016-03-21 | A kind of Portable satellite aerial structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105811068B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107834197A (en) * | 2017-10-25 | 2018-03-23 | 成都远东高科科技有限公司 | Antenna tuning system with anti-electromagnetic interference function |
| CN107834196A (en) * | 2017-10-25 | 2018-03-23 | 成都远东高科科技有限公司 | Antenna tuning unit with function of seismic resistance |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101950844A (en) * | 2010-08-30 | 2011-01-19 | 北京爱科迪信息通讯技术有限公司 | Portable satellite antenna system with auxiliary star aiming device and star aiming method thereof |
| US20140152492A1 (en) * | 2012-03-10 | 2014-06-05 | Harris Corporation | Portable satellite communication system |
| CN204333206U (en) * | 2014-12-04 | 2015-05-13 | 北京华胜天成信息技术发展有限公司 | A kind of collapsible Automatic-expanding mounting of Portable satellite communication antenna |
| CN105305012A (en) * | 2015-12-02 | 2016-02-03 | 湖南创智数码科技股份有限公司 | Satellite portable station |
-
2016
- 2016-03-21 CN CN201610159623.2A patent/CN105811068B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101950844A (en) * | 2010-08-30 | 2011-01-19 | 北京爱科迪信息通讯技术有限公司 | Portable satellite antenna system with auxiliary star aiming device and star aiming method thereof |
| US20140152492A1 (en) * | 2012-03-10 | 2014-06-05 | Harris Corporation | Portable satellite communication system |
| CN204333206U (en) * | 2014-12-04 | 2015-05-13 | 北京华胜天成信息技术发展有限公司 | A kind of collapsible Automatic-expanding mounting of Portable satellite communication antenna |
| CN105305012A (en) * | 2015-12-02 | 2016-02-03 | 湖南创智数码科技股份有限公司 | Satellite portable station |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107834197A (en) * | 2017-10-25 | 2018-03-23 | 成都远东高科科技有限公司 | Antenna tuning system with anti-electromagnetic interference function |
| CN107834196A (en) * | 2017-10-25 | 2018-03-23 | 成都远东高科科技有限公司 | Antenna tuning unit with function of seismic resistance |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105811068B (en) | 2018-05-08 |
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Granted publication date: 20180508 Termination date: 20210321 |