CN108521835A - The circular polarized antenna component of unmanned plane and unmanned plane - Google Patents
The circular polarized antenna component of unmanned plane and unmanned plane Download PDFInfo
- Publication number
- CN108521835A CN108521835A CN201780005016.3A CN201780005016A CN108521835A CN 108521835 A CN108521835 A CN 108521835A CN 201780005016 A CN201780005016 A CN 201780005016A CN 108521835 A CN108521835 A CN 108521835A
- Authority
- CN
- China
- Prior art keywords
- signal
- unmanned plane
- circular polarized
- satellite
- polarized antenna
- 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
Links
- 238000000034 method Methods 0.000 claims abstract description 18
- 238000012545 processing Methods 0.000 claims description 57
- 238000007781 pre-processing Methods 0.000 claims description 34
- 230000008569 process Effects 0.000 claims description 9
- 230000015572 biosynthetic process Effects 0.000 claims description 4
- 238000000926 separation method Methods 0.000 claims description 4
- 238000003786 synthesis reaction Methods 0.000 claims description 4
- 230000005611 electricity Effects 0.000 claims description 2
- 230000008054 signal transmission Effects 0.000 claims description 2
- 230000006978 adaptation Effects 0.000 claims 1
- 238000005516 engineering process Methods 0.000 abstract description 11
- 238000010586 diagram Methods 0.000 description 21
- 230000017525 heat dissipation Effects 0.000 description 7
- 238000001914 filtration Methods 0.000 description 6
- 230000003321 amplification Effects 0.000 description 5
- 238000003199 nucleic acid amplification method Methods 0.000 description 5
- 238000013507 mapping Methods 0.000 description 4
- 230000010287 polarization Effects 0.000 description 4
- 241001061260 Emmelichthys struhsakeri Species 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- 239000004411 aluminium Substances 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 229910052802 copper Inorganic materials 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000005183 dynamical system Methods 0.000 description 2
- 230000005684 electric field Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000010897 surface acoustic wave method Methods 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- PEZNEXFPRSOYPL-UHFFFAOYSA-N (bis(trifluoroacetoxy)iodo)benzene Chemical group FC(F)(F)C(=O)OI(OC(=O)C(F)(F)F)C1=CC=CC=C1 PEZNEXFPRSOYPL-UHFFFAOYSA-N 0.000 description 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 239000011203 carbon fibre reinforced carbon Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 229910021389 graphene Inorganic materials 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000004807 localization Effects 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002203 pretreatment Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- H01Q1/22—Supports; Mounting means by structural association with other equipment or articles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/285—Aircraft wire antennas
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q21/00—Antenna arrays or systems
- H01Q21/24—Combinations of antenna units polarised in different directions for transmitting or receiving circularly and elliptically polarised waves or waves linearly polarised in any direction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
- Waveguide Aerials (AREA)
Abstract
The embodiment of the invention discloses a kind of unmanned plane and the circular polarized antenna components of unmanned plane, the unmanned plane includes fuselage body, real time dynamic differential method RTK components and the circular polarized antenna component being arranged at the top of the fuselage body, wherein, the circular polarized antenna component, for receiving satellite-signal；The RTK components, satellite-signal for being received according to the circular polarized antenna component and the RTK data obtained from the base stations RTK determine the location information of unmanned plane.The unmanned plane is positioned using RTK technologies, improves the accuracy of positioning.Meanwhile the unmanned plane of the present embodiment receives satellite-signal using circular polarized antenna, and the size of the circular polarized antenna is smaller, light-weight, and then the smaller size of unmanned plane, and increases the cruise duration of unmanned plane.
Description
Technical field
The present invention relates to air vehicle technique field, more particularly to the circular polarized antenna component of a kind of unmanned plane and unmanned plane.
Background technology
In recent years, with the rapid development of unmanned plane (Unmanned Aerial Vehicle, UAV) technology, unmanned plane is answered
With more and more extensive.For example, transporting cargo using unmanned plane in carrier, farmland is measured using unmanned plane in agriculture field,
It is surveyed and drawn using unmanned plane in survey field.In actual use, in order to ensure logistics unmanned plane freight supply, mapping nothing
Man-machine mapping accuracy etc., unmanned plane need pinpoint landing and are fixed to required accurate location.However, it is existing nobody
The positioning accuracy of machine is low, cannot be satisfied high accuracy positioning requirement, cannot meet the needs of meticulous process.
Invention content
The present invention provides the circular polarized antenna component of a kind of unmanned plane and unmanned plane, for solving unmanned plane in the prior art
The problem of high accuracy positioning information can not be obtained.
First aspect present invention provides a kind of unmanned plane, including：It fuselage body, real time dynamic differential method RTK components and sets
Set the circular polarized antenna component at the top of the fuselage body, wherein
The circular polarized antenna component, for receiving satellite-signal；
The RTK components, satellite-signal for being received according to the circular polarized antenna component and obtain from the base stations RTK
RTK data determine the location information of unmanned plane.
Second aspect of the present invention provides a kind of circular polarized antenna component of unmanned plane, which is characterized in that including：Circular polarisation day
Line and the aerial signal pre-processing assembly being connect with the circular polarized antenna, wherein
The circular polarized antenna, for receiving satellite-signal；
The pre-processing assembly includes：Signal separator device, the first processing component, second processing component and signal synthesizer
Part, wherein
The Signal separator device, the first frequency range and second in the satellite-signal for receiving the circular polarized antenna
Band separation；
First processing component, the first band satellite signal for being exported to the Signal separator device carry out first
Default processing；
The second processing component, the second band satellite signal for being exported to the Signal separator device carry out second
Default processing；
The signal synthesizer part, the satellite for being exported to first processing component and the second processing component are believed
It number is synthesized.
The circular polarized antenna component of unmanned plane and unmanned plane provided by the present invention, wherein unmanned plane include fuselage body,
RTK components and the circular polarized antenna component being arranged at the top of fuselage body, circular polarized antenna component are used to receive satellite-signal,
The RTK data that RTK components are used for the satellite-signal that is received according to circular polarized antenna component and are obtained from the base stations RTK determine nobody
The location information of machine.That is the unmanned plane of the present embodiment can preferably receive satellite-signal, simultaneously using circular polarized antenna component
It is positioned using RTK technologies, improves the accuracy of positioning.Meanwhile the unmanned plane of the present embodiment is connect using circular polarized antenna
Satellite-signal is received, and the size of the circular polarized antenna is smaller, light-weight, and then the smaller size of unmanned plane, and increases
The cruise duration of unmanned plane.
Description of the drawings
It is required in being described below to embodiment in order to illustrate more clearly of the technical solution of the method for the present invention embodiment
The attached drawing used is briefly described, it should be apparent that, the accompanying drawings in the following description is some embodiments of the method for the present invention,
For those skilled in the art, without creative efforts, other be can also be obtained according to these attached drawings
Attached drawing.
Fig. 1 is the application scenario diagram of unmanned plane provided in an embodiment of the present invention positioning；
Fig. 2 is the structural schematic diagram of unmanned aerial vehicle example one provided in an embodiment of the present invention；
Fig. 3 is the graphics for the unmanned plane that the embodiment of the present invention one provides；
Fig. 4 is the front view for the unmanned plane that the embodiment of the present invention one provides；
Fig. 5 is the vertical view for the unmanned plane that the embodiment of the present invention one provides；
Fig. 6 is the structural schematic diagram of unmanned aerial vehicle example two provided in an embodiment of the present invention；
Fig. 7 is the structural schematic diagram of thermal component in the embodiment of the present invention two；
Fig. 8 is the structural schematic diagram of circular polarized antenna component in the unmanned plane that the embodiment of the present invention three provides；
Fig. 9 is another structural schematic diagram of circular polarized antenna component in the unmanned plane that the embodiment of the present invention three provides；
Figure 10 is feed network structures schematic diagram in circular polarized antenna component；
Figure 11 is the structural schematic diagram of the circular polarized antenna assembly embodiment one of unmanned plane provided in an embodiment of the present invention；
Figure 12 is the structural schematic diagram of the circular polarized antenna assembly embodiment two of unmanned plane provided in an embodiment of the present invention；
Figure 13 is another structural representation of the circular polarized antenna assembly embodiment two of unmanned plane provided in an embodiment of the present invention
Figure；
Figure 14 is the structural schematic diagram of the circular polarized antenna assembly embodiment three of unmanned plane provided in an embodiment of the present invention.
Reference sign：
1：Unmanned plane；
2：The base stations RTK；
3：Satellite；
10：Fuselage body；
11：Propeller；
12：Undercarriage；
20：RTK components；
30：Circular polarized antenna component；
31：Circular polarized antenna；
32：Pre-processing assembly；
33：Head cover；
310：Feeding network；
311：Feed pin；
322：Grounding pin；
320：Oscillator unit；
321：First oscillator；
322：Second oscillator；
324：Feed end；
323：Ground terminal；
330：Cylindrical base；
40：Thermal component；
41：First through hole；
110：Second through-hole；
50：Signal separator device；
60：First processing component；
61：First bandpass filter；
62：First attenuator；
70：Second processing component；
71：Second bandpass filter；
72：Second attenuator；
80：Signal synthesizer part；
301：First electric bridge；
302：Second electric bridge；
303：Balun；
304：First oscillator unit；
305：Second oscillator unit；
306：Third oscillator unit；
307：4th oscillator unit；
81：First amplifier unit；
82：Second amplifier unit.
Specific implementation mode
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.Based on the embodiments of the present invention, those skilled in the art are not having
There is the every other embodiment obtained under the premise of making creative work, shall fall within the protection scope of the present invention.
With the development of unmanned plane, unmanned plane has obtained widely answering in fields such as mapping, planning farmland, electric inspection process
With, and these fields are required to unmanned plane and are accurately positioned.Currently, unmanned plane generally use GPS positioning, and GPS location precision is low,
It cannot be satisfied the demand of high position precision.
In order to solve the above-mentioned technical problem, unmanned plane provided in an embodiment of the present invention, by the way that RTK (Real- are arranged
Timekinematic, real time dynamic differential method) component, it is positioned using RTK technologies, positioning accuracy can reach centimetre
Rank, and then the positioning accuracy of unmanned plane is substantially increased, expand the use scope of unmanned plane.
Wherein, RTK location technologies are the carrier phases that global navigation satellite location technology is combined with data communication technology
Real time dynamic differential location technology, it can provide three-dimensional localization result of the survey station point in specified coordinate system in real time.In RTK
Under measurement pattern, base station sends its observation and survey station coordinate information to rover station together by data-link, and rover station is not
Satellite Observations are only acquired, the data from base station are also received by data-link, and form difference observation in system
It is handled in real time.
Fig. 1 is the application scenario diagram of unmanned plane provided in an embodiment of the present invention positioning, as shown in Figure 1, the nothing of the present embodiment
Man-machine 1 is equivalent to above-mentioned rover station, and the base stations RTK 2 of the present embodiment are equivalent to above-mentioned base station.Unmanned plane 1 and the base stations RTK
2 receive the satellite-signal that satellite 3 emits, meanwhile, unmanned plane 1 receives the RTK data that the base stations RTK 2 are sent, and according to satellite-signal
It is positioned with RTK data.
Technical scheme of the present invention is described in detail with specifically embodiment below.These specific implementations below
Example can be combined with each other, and same or analogous concept or process may be repeated no more in some embodiments.
Fig. 2 is the structural schematic diagram of unmanned aerial vehicle example one provided in an embodiment of the present invention, and Fig. 3 is the embodiment of the present invention one
The graphics of the unmanned plane of offer, Fig. 4 are the front view for the unmanned plane that the embodiment of the present invention one provides, and Fig. 5 is that the present invention is implemented
The vertical view for the unmanned plane that example one provides.As shown in Figures 1 to 5, the unmanned plane of the present embodiment includes：Fuselage body 10, RTK groups
Part 20 and the circular polarized antenna component 30 being arranged at the top of fuselage body 10, wherein circular polarized antenna component 30 is defended for receiving
Star signal；RTK components 20, the satellite-signal for being received according to circular polarized antenna component 30 and the RTK from the acquisition of the base stations RTK
Data determine the location information of unmanned plane, and specifically, RTK components can be believed according to the satellite that circular polarized antenna component 30 receives
Number and the RTK data that are obtained from the base stations RTK carry out Differential positioning and determine the location information of unmanned plane.
The unmanned plane of the present embodiment can be plant protection drone, unmanned plane of taking photo by plane, mapping unmanned plane etc., and the present embodiment is to nothing
Man-machine concrete type is not limited.
As shown in Figures 3 to 5, the unmanned plane of the present embodiment further includes the dynamical system being arranged on fuselage body 10, rises
Frame 12 etc. is fallen, wherein dynamical system may include motor (not shown), propeller 11 etc..
Specifically, as shown in Figures 2 to 5, the unmanned plane of the present embodiment is other than including fuselage body 10 (for the ease of explaining
State, Fig. 2 merely illustrates the top enclosure of fuselage body), further include RTK components 20 and circular polarized antenna component 30.Wherein, entelechy
Changing antenna module 30 can be arranged in any position of fuselage body 10, such as be arranged at the top of fuselage body 10, in this way, just
In the reception of satellite-signal, also allow for being fixedly mounted.RTK components 20 can also be arranged in any position of fuselage body 10,
Such as be arranged in 10 the inside of fuselage body, such fuselage body 10 can play the role of protection to RTK components 20, avoid damaging
RTK components 20, and then ensure that the functional reliability of RTK components 20, it provides safeguard for the accurate positionin of unmanned plane.
Since satellite-signal is circularly polarised wave, in order to improve the reception to satellite-signal, the present embodiment is in unmanned plane
Using circular polarized antenna component 30, which can effectively receive the satellite-signal of circularly polarised wave, reduce letter
Number loss, provide high-precision reference data to be accurately positioned.
The circular polarized antenna component 30 of the present embodiment includes at least circular polarized antenna 31, and circular polarized antenna 31 is defended for receiving
Star signal.The track of the aerial radiation instantaneous electric field vector of circular polarized antenna 31 is a circle, along the direction of propagation, if electric field is sweared
Amount is rotated by right-handed helix direction, referred to as right-handed circular polarization, if being rotated by left hand helix direction, referred to as left-hand circular polarization.
It should be noted that the rotation direction of circular polarized antenna 31 is identical as the rotation direction of the circularly polarised wave of satellite-signal, for example, working as
When satellite-signal is right-handed circular polarization wave, then circular polarized antenna 31 is dextrorotation, when satellite-signal is left-hand circular polarization wave, is then justified
Poliarizing antenna 31 is dextrorotation, this is because circular polarized antenna 31 can only receive circularly polarised wave identical with its rotation direction.
The circular polarized antenna 31 of the present embodiment can be：Right-angled intersection doublet, microstrip antenna, helical antenna and micro-strip
Reflective array etc..
Preferably, the circular polarized antenna 31 of the present embodiment can be four arm helix microstrip antennas.
The circular polarized antenna 31 of the present embodiment, antenna height is low, and lateral dimension is small, and then the smaller whole ruler of unmanned plane
It is very little, realize the miniaturization of unmanned plane.Meanwhile the circular polarized antenna 31 of the present embodiment is light-weight, and then improve the continuous of unmanned plane
ETS estimated time of sailing.
In actual use, the base stations RTK on ground receive the satellite-signal that satellite is sent, and obtain carrier phase observation
The RTK data such as value, Pseudo-range Observations, RTK base station coordinates, and the RTK data are sent to RTK components 20.Meanwhile on unmanned plane
Circular polarized antenna component 30 receive satellite-signal, and by the satellite signal transit to RTK components 20, at this point, RTK components 20 obtain
Obtained RTK data and satellite-signal.Then, RTK data and satellite-signal are carried out real time differential processing by RTK components 20, are obtained
Basic lineal vector (Δ X, Δ Y, Δ Z) between unmanned plane and the base stations RTK.Then, the base stations RTK are added on the basis of basic lineal vector
Coordinate obtains the WGS84 coordinates of unmanned plane, the i.e. geocentric coordinate system of unmanned plane.Finally, carry out coordinate conversion (for example, according to
Beijing coordinate system in 1954, Xi'an Geodetic Coordinate System 1980 or Local Independent Coordinate System etc.), obtain unmanned plane plane coordinates x, y and
Normal high h, and then realize the precise positioning of unmanned plane.
Optionally, as shown in Fig. 2, the circular polarized antenna component 30 of the present embodiment can also include being located at circular polarized antenna
Head cover 33 on 31, the head cover 33 can play a protective role to circular polarized antenna 31.
Optionally, the base stations RTK of the present embodiment can be a list base station RTK, can also be the base stations network RTK, this reality
It is without limitation to apply example, is set with specific reference to actual needs.
Unmanned plane provided in an embodiment of the present invention, including fuselage body, RTK components and the circle being arranged at the top of fuselage body
Poliarizing antenna component, wherein circular polarized antenna component is used for for receiving satellite-signal, RTK components according to circular polarized antenna group
Satellite-signal that part receives and the RTK data obtained from the base stations RTK determine the location information of unmanned plane.That is the nothing of the present embodiment
It is man-machine, it is positioned using RTK technologies, improves the accuracy of positioning.Meanwhile the unmanned plane of the present embodiment uses circular polarisation day
Line receives satellite-signal, and the size of the circular polarized antenna is smaller, light-weight, and then the smaller size of unmanned plane, and increases
The cruise duration of unmanned plane is added.
Fig. 6 is the structural schematic diagram of unmanned aerial vehicle example two provided in an embodiment of the present invention, on the basis of above-described embodiment
On, as shown in fig. 6, the unmanned plane of the present embodiment can also include thermal component 40, which is arranged in fuselage body
On 10, for radiating to RTK components 20.
The present embodiment is not limited the shape and size of thermal component 40, is set with specific reference to actual needs.Example
Such as, the shape and size of thermal component 40 can be matched with the shape and size of RTK components 20, that is, when RTK components 20 are rectangular
When shape plate body, thermal component 40 can also be rectangular plate body.Optionally, the size of thermal component 40 is more than RTK components 20
Size, and then increase the heat dissipation area of thermal component 40, improve the radiating efficiency to RTK components 20.
The thermal component 40 of the present embodiment can be made using any heat sink material, it is, for example, possible to use gold, silver, copper, aluminium
Etc. the metal materials of good heat conductivities be made, the thermal conductivity such as graphene, graphite, carbon fiber and C/C composite materials can also be used
The good nonmetallic materials of energy are made.
Optionally, the thermal component 40 of the present embodiment can be radiator, for example, by multiple groups of fins at copper aluminium dissipate
Hot device.Optionally, the thermal component 40 of the present embodiment can also be metallic heat radiating plate.
Optionally, the thermal component 40 of the present embodiment is contacted with the arbitrary face of RTK components 20, for generate RTK plates
Heat transfer is gone out.For example, thermal component 40 can be arranged in the lower surface of RTK components 20, and with the lower surface of RTK components 20
Contact heat dissipation, optionally, thermal component 40 can also be arranged in the upper surface of RTK components 20, be connect with the upper surface of RTK components 20
Touch heat dissipation etc..
Shown in Fig. 6, the circular polarized antenna component 30 of the present embodiment may be mounted on thermal component 40, and dissipate
Thermal part 40 is arranged between circular polarized antenna component 30 and RTK components 20.
Specifically, as shown in fig. 6, the setting of thermal component 40 connects on RTK components 20, and with the upper surface of RTK components 20
It touches.Since the device on RTK components 20 is arranged at the upper surface of RTK components 20 substantially so that the heat of 20 upper surface of RTK components
In quantity set, in this way, being arranged thermal component 40 on RTK components 20, heat dissipation is given convenient for the heat transfer of 20 upper surface of RTK components
Component 40, and then improve the radiating efficiency of RTK components 20.
Meanwhile circular polarized antenna component 30 being mounted on thermal component 40, it may be implemented to circular polarized antenna component 30
Fixed installation, avoid using antenna mounting seat etc., and then reduce the number of parts of unmanned plane.
Optionally, the connection between the circular polarized antenna component 30 and thermal component 40 of the present embodiment can be welding, glue
The non-dismountable mode such as connect to connect, can also be set by card, removablies connection, the present embodiment such as screw thread do not limit this
System is set with specific reference to actual needs.
Optionally, as shown in fig. 6, being connected by bolt between the present embodiment circular polarized antenna component 30 and thermal component 40
Connect, specifically, at least one threaded hole be set on circular polarized antenna component 30, it is corresponding, be arranged on thermal component 40 to
The female boss of a few tool, for example, as shown in fig. 6, four vertex in circular polarized antenna component 30 are respectively arranged 1
Threaded hole, it is corresponding, four boss with internal thread hole are set on the corresponding position of thermal component 40.Then, using spiral shell
Bolt connects one to one each boss and each threaded hole, and then circular polarized antenna component 30 is fixed on thermal component 40
On.When needing replacing or repairing circular polarized antenna component 30, directly circular polarized antenna component 30 is torn open from thermal component 40
It is lower, and then improve circular polarized antenna component 30 removes and installs convenience.
Fig. 7 is the structural schematic diagram of thermal component in the embodiment of the present invention two.As shown in Figure 6 and Figure 7, the present embodiment is dissipating
First through hole 41 is provided on hot plate, the circular polarized antenna component 30 and the RTK components 20 are by being threaded through described first
Connecting line connection in through-hole 41.
Wherein, it is connected by connecting line between the circular polarized antenna component 30 and RTK components 20 of the present embodiment, carries out data
Interaction, specifically, the satellite signal transit received circular polarized antenna component 30 by the connecting line to RTK components 20.
Specifically, as shown in Figure 6 and Figure 7, when the setting of thermal component 40 circular polarized antenna component 30 and RTK components 20 it
Between when, for the ease of the connection of circular polarized antenna component 30 and RTK components 20, the present embodiment is then provided with first on heat sink
Through-hole 41, such connecting line can pass through first through hole 41, circular polarized antenna component 30 and RTK components 20 linked together.
That is the present embodiment, connecting line are threaded through in first through hole 41, can be arranged to avoid connecting line in the outside of thermal component 40, be caused
The mixed and disorderly problem of cabling.Meanwhile first through hole 41 plays the role of fixed and protects to connecting line so that circular polarized antenna component
The connection of 30 and RTK components 20 is relatively reliable.
Optionally, the connecting line of the present embodiment can be the connecting line that any one can transmit signal, it is preferred that can be with
It is IPEX connecting lines.
Shown in Fig. 6, in the alternatively possible realization method of the present embodiment, for the ease of fixed radiating part
There is the second through-hole 110 being adapted to thermal component 40, thermal component 40 to fix for part 40, the top of the present embodiment fuselage body 10
In stating the second through-hole 110.
Optionally, the thermal component 40 of the present embodiment can be welded in the second through-hole 110, i.e., by the week of thermal component 40
Side and the periphery of the second through-hole 110 are welded.
Optionally, thermal component 40 is arranged to T-shaped boss, the wherein size of 40 bottom of thermal component is less than heat dissipation
The size at 40 top of component, meanwhile, the size fit of the size of 40 bottom of thermal component and the second through-hole 110, and thermal component
The size at 40 tops is more than the size of the second through-hole 110.In this way, when thermal component 40 is arranged in the second through-hole 110, heat dissipation
40 bottom of component is located at the second through-hole 110, and can be interference fit, transition cooperation or clearance fit, radiating part between the two
40 top of part is connected to the edge of the second through-hole 110, and thermal component 40 can be hung on to the top of fuselage body 10 in this way, and
Other connections can be no longer carried out between the two, and then simplify the mounting process of thermal component 40.
Optionally, the periphery of the second through-hole 110 can also be made heavy platform, the i.e. periphery of the second through-hole 110 by the present embodiment
It is recessed, a heavy platform is formed, the shape and size of the heavy platform are adapted to the shape and size of thermal component 40, and thermal component 40 can
To be arranged in the heavy platform, and then convenient for the fixed installation of thermal component 40.
Optionally, radiating surface and fuselage body 10 of the thermal component 40 close to circular polarized antenna component 30 in the present embodiment
Outer surface of cupular part seamlessly transits so that thermal component 40 constitutes a part for fuselage body 10, improves the aesthetics of unmanned plane.
Unmanned plane provided in an embodiment of the present invention, by the way that thermal component is arranged on fuselage body, so that the thermal component
It radiates to RTK components, and then improves the radiating efficiency of RTK components, improve the functional reliability of RTK components.Into one
Step, RTK components are arranged between circular polarized antenna component and RTK components, and circular polarized antenna component is mounted on heat dissipation
On component, the fixation to circular polarized antenna component is realized.
Fig. 8 is the structural schematic diagram of circular polarized antenna component in the unmanned plane that the embodiment of the present invention three provides, and Fig. 9 is this hair
Another structural schematic diagram of circular polarized antenna component in the unmanned plane that bright embodiment three provides, Figure 10 are in circular polarized antenna component
Feed network structures schematic diagram.On the basis of the above embodiments, as shown in Fig. 8 to Fig. 9, the circular polarized antenna group of the present embodiment
Part 30 includes circular polarized antenna 31 and the aerial signal pre-processing assembly 32 being connect with circular polarized antenna 31.Wherein, pretreated group
Part 32, the satellite-signal for being received to circular polarized antenna 31 pre-process, wherein the effect of the pretreatment component is
The gain for increasing circular polarized antenna component 30, filters out the noise in the satellite-signal received, RTK components 20 and pre-processing assembly
32 connections, the RTK data for being specifically used for the satellite-signal after being pre-processed according to pre-processing assembly 32 and being obtained from the base stations RTK are true
Determine the location information of unmanned plane.
Specifically, in actual use, circular polarized antenna 31 receives the satellite-signal of satellite launch, and satellite-signal is passed
Pass pre-processing assembly 32, the pretreatments such as pre-processing assembly 32 is amplified satellite-signal, filters then will be pretreated
Satellite-signal be sent to RTK components 20.RTK components 20 receive the RTK data of the base stations RTK transmission simultaneously, and according to pretreatment
The satellite-signal and RTK data crossed carry out real time differential processing, determine the location information of unmanned plane.
Shown in Fig. 8 to Figure 10, the circular polarized antenna 31 of the present embodiment includes feeding network 310, multiple oscillators
Unit 320 and cylindrical base 330, wherein each oscillator unit 320 includes the first oscillator 321 and the second oscillator 322,
In, first oscillator 321 and second oscillator 322 are spirally arranged in the cylindrical base 330 and to described
The upper end of cylindrical base 330 extends, each oscillator unit 320 can also include feed end 324 and ground terminal 323, institute
Each oscillator unit 320 is stated to connect with the feeding network 310 by feed end 324 and ground terminal 323.
The cylindrical base 330 of the present embodiment can be cylinder, such as can be hollow cylinder, can reduce in this way
The weight of circular polarized antenna 31 improves the cruise duration of unmanned plane.Optionally, which can also be filled circles
Cylinder, structure are relatively stablized.
Optionally, the cylindrical base 330 of the present embodiment is flexible base board, and first oscillator unit can be arranged in flexible base
On plate, then, then by flexibility be coiled into cylinder substantially, be convenient for antenna processing and fabricating.
Optionally, the circular polarized antenna 31 of the present embodiment is FPC (Flexible Printed Circuit, soft circuit
Plate) microstrip antenna, wherein each oscillator unit 320 can be L antenna elements or IFA (Inverted-F) antenna element, preferably
Can be PIFA units.
As shown in Figure 8 and Figure 9, the length of the first oscillator 321 is more than the length of the second oscillator 322, wherein the first oscillator 321
For receive high frequency satellite-signal (such as the L1 frequency ranges of GPS positioning system, BEI-DOU position system B1, F1 frequency range, Galileo positioning
The corresponding satellite-signal of at least one of system E1 frequency ranges, GLONASS positioning system G1 frequency ranges), the second oscillator 322 is used for
Reception low frequency satellite-signal (such as L2, L5 frequency range of GPS positioning system, BEI-DOU position system B2, B3, F2 frequency range, Galileo are fixed
The corresponding satellite-signal of at least one of position system E5, E6 frequency range, GLONASS positioning system G2, G3 frequency range).
Optionally, the feeding network 310 of the present embodiment and pre-processing assembly 32 can be arranged on the same circuit board, this
Just feeding network 310 and pre-processing assembly 32 connect sample prescription, reduce and occupy volume.
Optionally, the feeding network 310 of the present embodiment includes the feed pin 311 being connect with feed end 324, and with connect
The grounding pin 322 that ground terminal 323 connects.Wherein, feed pin 311 is identical as the quantity of feed end 324 of oscillator unit 320,
Grounding pin 322 is identical as the quantity of ground terminal 323 of oscillator unit 320 so that feed pin 311 and oscillator unit 320 1
One is correspondingly connected with, and grounding pin 322 connects one to one with ground terminal 323.
Specifically, as shown in Figure 9 and Figure 10, it is assumed that the circular polarized antenna 31 of the present embodiment is four arm circular polarized antennas 31,
Including four oscillator units 320.The bottom end of each oscillator unit 320 is arranged there are one feed end 324 and a ground terminal 323,
Corresponding feeding network 310 includes the 4th feed pin 311 and the 4th grounding pin 322, each feed end of oscillator unit 320
324 connect one to one with each feed pin 311 on feeding network 310, each ground terminal 323 of oscillator unit 320 with
Each grounding pin 322 on feeding network 310 connects one to one.Then, the output port of feeding network 310 and pretreatment
The input port of component 32 connects, can be by the satellite signal transit received to pre-processing assembly 32, so that pre-processing assembly
32 pairs of satellite-signals pre-process.
Unmanned plane provided in an embodiment of the present invention, by circular polarized antenna component be arranged to circular polarized antenna and with circular polarisation day
Aerial signal pre-processing assembly two parts of line connection, wherein the satellite that pre-processing assembly is used to receive circular polarized antenna
Signal is pre-processed；RTK components are connect with pre-processing assembly, specifically for the satellite after being pre-processed according to pre-processing assembly
Signal and the RTK data obtained from the base stations RTK determine the location information of unmanned plane, and then improve the processing energy to satellite-signal
Power so that the position of the unmanned plane determined based on treated satellite-signal is more accurate.
Figure 11 is the structural schematic diagram of the circular polarized antenna assembly embodiment one of unmanned plane provided in an embodiment of the present invention.Such as
Shown in Figure 11, the circular polarized antenna component 30 of the present embodiment includes：Circular polarized antenna 31 and the day being connect with circular polarized antenna 31
Line Signal Pretreatment component 32, wherein circular polarized antenna 31 includes multiple oscillator units 320 and feeding network 310, pretreated group
Part 32 includes：Signal separator device 50, the first processing component 60, second processing component 70 and signal synthesizer part 80, wherein
Circular polarized antenna 31, for receiving satellite-signal.
Signal separator device 50, the first frequency range and the second frequency range in the satellite-signal for receiving circular polarized antenna 31
Separation.
First processing component 60, it is default that the first band satellite signal for being exported to Signal separator device 50 carries out first
Processing.
Second processing component 70, it is default that the second band satellite signal for being exported to Signal separator device 50 carries out second
Processing.
Signal synthesizer part 80, the satellite-signal for being exported to the first processing component 60 and second processing component 70 carry out
Synthesis.
Specifically, as shown in figure 11, in actual use, circular polarized antenna 31 receives the satellite-signal of satellite launch, and
The satellite-signal is sent to Signal separator device 50.And since satellite-signal includes the signal of different frequency range, the present embodiment
Satellite-signal is divided into the first band satellite signal and the second band satellite signal.In this way, when Signal separator device 50 receives
After satellite-signal, Signal separator device 50 detaches satellite-signal, is separated into the first band satellite signal and the second frequency range
Satellite-signal.
Optionally, first frequency range of the present embodiment include at least the L1 frequency ranges of GPS positioning system, BEI-DOU position system B1,
At least one of F1 frequency ranges, GALILEO positioning system E1 frequency ranges, GLONASS positioning system G1 frequency ranges.
Optionally, second frequency range of the present embodiment includes at least L2, L5 frequency range of GPS positioning system, BEI-DOU position system
At least one of B2, B3, F2 frequency range, GALILEO positioning system E5, E6 frequency range, GLONASS positioning system G2, G3 frequency range.
Then, the first band satellite signal is sent to the first processing component 60 by Signal separator device 50, so that at first
Reason component 60 is amplified, filter etc. first to the first band satellite signal and pre-processes.Meanwhile by Signal separator device 50 by
Two band satellite signals are sent to second processing component 70, so that second processing component 70 puts the second band satellite signal
Greatly, second pretreatment such as filtering.
After signal processing is complete, by treated, the first band satellite signal is sent to signal synthesis to the first processing component 60
Device 80, by treated, the second band satellite signal is sent to signal synthesizer part 80 to second processing component 70.Finally, signal
Synthesizer 80 is to treated the first band satellite signal and treated that the second band satellite signal synthesizes, and will close
At satellite-signal be sent to RTK components 20.Wherein, Signal separator device and signal synthesizer part can be power splitter.
That is the antenna module of the present embodiment, first detaches satellite-signal, is used to the satellite-signal of different frequency range
Different preprocess methods, and then realize the accurate processing to satellite-signal, it avoids using same process flow to different frequencies
The satellite-signal of section is handled and satellite-signal is caused to be distorted, amplification factor is undesirable, the halfway problem of noise filtering, this
Sample makes the positioning based on the accurate pretreated satellite-signal more accurate, further improves the accurate positioning of unmanned plane
Property.
The circular polarized antenna component of unmanned plane provided in an embodiment of the present invention, by the way that circular polarized antenna and and circular polarisation is arranged
The aerial signal pre-processing assembly of antenna connection, wherein pre-processing assembly includes Signal separator device, the first processing component, second
Processing component and signal synthesizer part, circular polarized antenna is for receiving satellite-signal；Signal separator device is used for circular polarisation day
First frequency range and the second band separation in the satellite-signal that line receives；First processing component, for defeated to Signal separator device
The the first band satellite signal gone out carries out the first default processing；Second processing component, for being exported to Signal separator device
Two band satellite signals carry out the second default processing；Signal synthesizer part, for the first processing component and second processing component
The satellite-signal of output is synthesized, and then improves the processing accuracy of satellite-signal, improves the nothing based on the satellite-signal
Man-machine positioning accuracy.
Figure 12 is the structural schematic diagram of the circular polarized antenna assembly embodiment two of unmanned plane provided in an embodiment of the present invention, figure
13 be another structural schematic diagram of the circular polarized antenna assembly embodiment two of unmanned plane provided in an embodiment of the present invention.In above-mentioned reality
On the basis of applying example, as shown in figure 12, first processing component 60 of the present embodiment includes at least one first bandpass filter 61,
For being filtered to the first band satellite signal that Signal separator device 50 exports.
Optionally, first bandpass filter 61 of the present embodiment is, i.e. first bandpass filtering selected according to the first frequency range
Device 61 allows the signal of the first frequency range to pass through, and by the signal and ratio first frequency range upper limiting frequency lower than the first frequency range lower frequency limit
High signal is decayed or is inhibited.
The quantity of the first bandpass filter 61 is set according to actual needs in the present embodiment, and the present embodiment does not do this
Limitation.
Optionally, first bandpass filter 61 of the present embodiment can be (Surface Acoustic Wave, sound surface
Wave filter) SAW filter
Shown in Figure 12, the second processing component 70 of the present embodiment includes at least one second bandpass filter
71, for being filtered to the second band satellite signal that Signal separator device 50 exports.
Optionally, second bandpass filter 71 of the present embodiment is, i.e. second bandpass filtering selected according to the second frequency range
Device 71 allows the signal of the second frequency range to pass through, and by the signal and ratio second frequency range upper limiting frequency lower than the second frequency range lower frequency limit
High signal is decayed or is inhibited.
The quantity of the second bandpass filter 71 is set according to actual needs in the present embodiment, and the present embodiment does not do this
Limitation.
Optionally, second bandpass filter 71 of the present embodiment can be (Surface Acoustic Wave, sound surface
Wave filter) SAW filter.
Shown in Fig. 8 to Figure 10, the circular polarized antenna 31 of the present embodiment include multiple oscillator units 320, with it is every
The feeding network 310 and cylindrical base 330 of one oscillator unit 320 connection, wherein each oscillator unit 320 includes
First oscillator 321 and the second oscillator 322, wherein first oscillator, 321 and second oscillator 322 is spirally arranged described
Extend in cylindrical base 330 and to the upper end of the cylindrical base 330.The structure of the circular polarized antenna 31 describes reference
Described in above-described embodiment, details are not described herein.
Optionally, the circular polarized antenna 31 of the present embodiment can be four arm circular polarized antennas 31, that is, include 4 oscillator units
320。
At this point, as shown in figure 13, the feeding network 310 of the present embodiment includes the first electric bridge 301, the second electric bridge 302 and divides
The balun 303 not connect with the first electric bridge 301 and the second electric bridge 302, wherein first electric bridge 301 respectively with the first oscillator
Unit 304 and second oscillator unit 305 adjacent with the first oscillator unit 304 are connect；Second electric bridge 302 respectively with third
Oscillator unit 306 and fourth oscillator unit 307 adjacent with third oscillator unit 306 are connect；The balun 303 will be for that will handle
Signal transmission afterwards is to the pre-processing assembly 32.
Specifically, as shown in figure 13, the circular polarized antenna 31 of the present embodiment includes 4 oscillator units 320, respectively first
Oscillator unit 304, the second oscillator unit 305, third oscillator unit 306 and the 4th oscillator unit 307.It is wherein each adjacent to shake
The phase of subelement 320 differs 90 degree, for example, the phase of the first oscillator unit 304 is 0 degree, the phase of the second oscillator unit 305
It it is 90 degree, the phase of third oscillator unit 306 is 180 degree, and the phase of the 4th oscillator unit 307 is 270 degree.
First oscillator unit 304 and the second oscillator unit 305 are connect with the first electric bridge 301, the second oscillator unit 305 and
Two oscillator units 305 are connect with the second electric bridge 302.Wherein, the first electric bridge 301 is used to receive the first oscillator unit 304
The satellite-signal that satellite-signal and the second oscillator unit 305 receive is synthesized, and the second electric bridge 302 is used for third oscillator unit
The satellite-signal that 306 satellite-signals received and the 4th oscillator unit 307 receive is synthesized.
It can be seen from the above, due to the first oscillator unit 304, the second oscillator unit 305, third oscillator unit 306 and the 4th
The phase of oscillator unit 307 differs 90 degree, and therefore, first electric bridge 301 and the second electric bridge 302 of the present embodiment are 90 degree of electricity
Bridge.
Phase difference between first electric bridge 301 treated satellite-signal and the second electric bridge 302 treated satellite-signal
180 degree.Then, the two-way satellite-signal of treated phase difference 180 degree is sent to by the first electric bridge 301 and the second electric bridge 302
Balun 303.Balun 303 synthesizes the two-way satellite-signal of phase difference 180 degree, and the satellite signal transit after synthesis is given
Pre-processing assembly 32, and then realize the efficient reception to satellite-signal.
It can be seen from the above, the circular polarized antenna 31 of the present embodiment includes 4 oscillator units 320, each oscillator unit 320 is equal
Satellite-signal can be received, feeding network 310 synthesizes the satellite-signal that each oscillator unit 320 receives, in turn
Improve the receiving efficiency of satellite-signal.
Optionally, the feeding network 310 of the present embodiment and the pre-processing assembly 32 are arranged on the same circuit board, just
In management, and reduce the number of components of antenna module.
The circular polarized antenna component of unmanned plane provided in an embodiment of the present invention, by being arranged at least in the first processing component
One the first bandpass filter, for being filtered to the first band satellite signal that Signal separator device exports, at second
At least one second bandpass filter is set in reason component, the second band satellite signal for exporting to Signal separator device into
Row filtering, and then realize and the satellite-signal of different frequency range is filtered respectively, improve the accuracy of filtering.Meanwhile by presenting
First electric bridge, the second electric bridge and balun are set in electric network, to realize the efficient reception to satellite-signal.
Figure 14 is the structural schematic diagram of the circular polarized antenna assembly embodiment three of unmanned plane provided in an embodiment of the present invention.
On the basis of above-described embodiment, as shown in figure 14, the present embodiment is provided between feeding network 310 and Signal separator device 50
First amplifier unit 81, the satellite-signal which is used to export feeding network 310 are amplified.
Specifically, since the satellite-signal received is weaker, the present embodiment is in feeding network 310 and Signal separator device 50
Between the first amplifier unit 81 is set, the satellite-signal that such feeding network 310 exports after the amplification of the first amplifier unit 81,
It is then forwarded to Signal separator device 50, so that Signal separator device 50 accurately detaches satellite-signal, and then is realized to defending
Star signal is effectively treated.
Optionally, first amplifier unit 81 of the present embodiment can be follow-up amplifier.
Shown in Figure 14, first processing component 60 of the present embodiment further includes the first attenuator 62, this first declines
Subtract device 62 for decaying to the first band satellite signal that Signal separator device 50 exports.
Optionally, the second processing component 70 of the present embodiment include the second attenuator 72, second attenuator 72 for pair
The second band satellite signal that Signal separator device 50 exports is decayed.
Specifically, as shown in figure 14, when satellite-signal by the first amplifier unit 81 amplification after, the intensity meeting of satellite-signal
Increase, corresponding amplitude increases.Then, Signal separator device 50 detaches the satellite-signal of high signal intensity, is separated into
First band satellite signal and the second frequency satellite-signal.At this point, the first band satellite signal and the second frequency satellite-signal
Signal strength it is also relatively strong.At this point, in order to which amplified satellite-signal is saturated, then need to the first band satellite signal and second
Band satellite signal is decayed.
Optionally, first attenuator 62 of the present embodiment and the second attenuator 72 can be π type attenuators.
Optionally, first attenuator 62 of the present embodiment can be arranged in Signal separator device 50 and the first bandpass filter
Between 61, the second attenuator 72 can be arranged between Signal separator device 50 and the second bandpass filter 71.
Optionally, first attenuator 62 of the present embodiment can be arranged in the first bandpass filter 61 and signal synthesizer part
Between 80, the second attenuator 72 can be arranged between the second bandpass filter 71 and signal synthesizer part 80.
Optionally, as Figure 14 shows, when the first processing component 60 includes two the first bandpass filters 61, the first attenuator
62 can be arranged between two the first bandpass filters 61.Similarly, when second processing component 70 includes that two the second band logicals are filtered
When wave device 71, the second attenuator 72 can be arranged between two the second bandpass filters 71.
Shown in Figure 14, the pre-processing assembly 32 of the present embodiment further includes connect with signal synthesizer part 80
Two amplifier units 82, the satellite-signal which is used to export signal synthesizer part 80 are amplified.
Specifically, as shown in figure 14, due to satellite-signal very little, it is therefore desirable to gain it is larger, single-stage amplification often without
Method is met the requirements, and therefore, in order to obtain sufficiently large gain, the pre-processing assembly 32 of the present embodiment includes not only the first enlarging section
Part 81 further includes the second amplifier unit 82, realizes the amplification step by step to satellite-signal so that the satellite that pre-processing assembly 32 exports
Signal meets preset requirement, can be received and processed by RTK components 20, and then improves the reliability of unmanned plane positioning.
The circular polarized antenna component of unmanned plane provided in an embodiment of the present invention, by feeding network and Signal separator device
Between be provided with the first amplifier unit, which is used for the satellite-signal that is exported to feeding network and is amplified, with
Ensure that subsequent Signal separator device efficiently separates satellite-signal and effective filter of the bandpass filter to satellite-signal
Wave.
Finally it should be noted that：The above embodiments are only used to illustrate the technical solution of the present invention., rather than its limitations；To the greatest extent
Present invention has been described in detail with reference to the aforementioned embodiments for pipe, it will be understood by those of ordinary skill in the art that：Its according to
So can with technical scheme described in the above embodiments is modified, either to which part or all technical features into
Row equivalent replacement；And these modifications or replacements, various embodiments of the present invention technology that it does not separate the essence of the corresponding technical solution
The range of scheme.
Claims (27)
1. a kind of unmanned plane, which is characterized in that including：Fuselage body, RTK components and the circle being arranged at the top of the fuselage body
Poliarizing antenna component, wherein
The circular polarized antenna component, for receiving satellite-signal；
The RTK components, satellite-signal for being received according to the circular polarized antenna component and obtain from the base stations RTK
RTK data determine the location information of unmanned plane.
2. unmanned plane according to claim 1, which is characterized in that the unmanned plane further includes being arranged in the fuselage body
On thermal component, for radiating to the RTK components.
3. unmanned plane according to claim 2, which is characterized in that the circular polarized antenna component is mounted on the radiating part
On part, and the thermal component is arranged between the circular polarized antenna component and the RTK components.
4. unmanned plane according to claim 3, which is characterized in that be provided with first through hole, the circle on the heat sink
Poliarizing antenna component is connected with the RTK components by the connecting line being threaded through in the first through hole.
5. according to claim 2-4 any one of them unmanned planes, which is characterized in that the top of the fuselage body has and institute
The second through-hole of thermal component adaptation is stated, the thermal component is fixed in second through-hole.
6. unmanned plane according to claim 5, which is characterized in that the thermal component is close to the circular polarized antenna component
The outer surface of cupular part of radiating surface and the fuselage body seamlessly transit.
7. unmanned plane according to claim 1, which is characterized in that the circular polarized antenna component include circular polarized antenna and
The aerial signal pre-processing assembly being connect with the circular polarized antenna, wherein
The pre-processing assembly, the satellite-signal for being received to the circular polarized antenna pre-process；
The RTK components, connect with the pre-processing assembly, specifically for defending after being pre-processed according to the pre-processing assembly
Star signal and the RTK data obtained from the base stations RTK determine the location information of the unmanned plane.
8. unmanned plane according to claim 7, which is characterized in that the circular polarized antenna includes feeding network, Duo Gezhen
Subelement and cylindrical base, wherein each oscillator unit includes the first oscillator and the second oscillator, wherein described first shakes
Sub and described second oscillator is spirally arranged in the cylindrical base and extends to the upper end of the cylindrical base,
Each oscillator unit includes feed end and ground terminal, each described oscillator unit passes through feed end and ground terminal and the feedback
Electric network connects.
9. unmanned plane according to claim 8, the feeding network and the pre-processing assembly are arranged in the same circuit
On plate.
10. unmanned plane according to claim 8, which is characterized in that the length of first oscillator is shaken more than described second
The length of son.
11. according to claim 8-10 any one of them unmanned planes, which is characterized in that the feeding network includes and the feedback
The feed pin of electric end connection, and the grounding pin that is connect with the ground terminal.
12. unmanned plane according to claim 8, which is characterized in that the cylindrical base is flexible base board.
13. unmanned plane according to claim 2, which is characterized in that the thermal component is metallic heat radiating plate.
14. a kind of circular polarized antenna component of unmanned plane, which is characterized in that including：Circular polarized antenna and with the circular polarisation day
The aerial signal pre-processing assembly of line connection, wherein
The circular polarized antenna, for receiving satellite-signal；
The pre-processing assembly includes：Signal separator device, the first processing component, second processing component and signal synthesizer part,
Wherein
The Signal separator device, the first frequency range and the second frequency range in the satellite-signal for receiving the circular polarized antenna
Separation；
First processing component, it is default that the first band satellite signal for being exported to the Signal separator device carries out first
Processing；
The second processing component, it is default that the second band satellite signal for being exported to the Signal separator device carries out second
Processing；
The signal synthesizer part, satellite-signal for being exported to first processing component and the second processing component into
Row synthesis.
15. antenna module according to claim 14, which is characterized in that
First frequency range includes at least the L1 frequency ranges, BEI-DOU position system B1 frequency ranges, GALILEO positioning system of GPS positioning system
At least one of E1 frequency ranges, GLONASS positioning system G1 frequency ranges.
16. the antenna module according to claims 14 or 15, which is characterized in that
L2, L5 frequency range, BEI-DOU position system B2, B3 frequency range, the Galileo that second frequency range includes at least GPS positioning system are fixed
At least one of position system E5, E6 frequency range, GLONASS positioning system G2, G3 frequency range.
17. antenna module according to claim 14, which is characterized in that
First processing component includes at least one first bandpass filter, and for being exported to the Signal separator device
One band satellite signal is filtered.
18. antenna module according to claim 17, first bandpass filter is selected according to the first frequency range.
19. antenna module according to claim 14, which is characterized in that the second processing component includes at least one
Two band-pass filter, the second band satellite signal for being exported to the Signal separator device are filtered.
20. antenna module according to claim 19, which is characterized in that second bandpass filter is according to the second frequency
Duan Xuanding's.
21. according to claim 14-20 any one of them antenna modules, which is characterized in that
First processing component includes the first attenuator, and the first band satellite for being exported to the Signal separator device is believed
Number decay.
22. according to claim 14-21 any one of them antenna modules, which is characterized in that
The second processing component includes the second attenuator, and the second band satellite for being exported to the Signal separator device is believed
Number decay.
23. according to claim 14-22 any one of them antenna modules, which is characterized in that the circular polarized antenna includes more
A oscillator unit, the feeding network being connect with each oscillator unit and cylindrical base, wherein each oscillator unit
Including the first oscillator and the second oscillator, wherein first oscillator and the second oscillator are spirally arranged in the cylindrical base
Extend on plate and to the upper end of the cylindrical base.
24. antenna module according to claim 23, which is characterized in that the multiple oscillator unit is 4 oscillator units,
The feeding network includes the first electric bridge, the second electric bridge and the balun with the first electric bridge and the second electric bridge connection respectively, wherein institute
The first electric bridge is stated to connect with the first oscillator unit and second oscillator unit adjacent with the first oscillator unit respectively；Second electricity
Bridge is connect with third oscillator unit and fourth oscillator unit adjacent with third oscillator unit respectively；The balun will be for that will handle
Signal transmission afterwards is to the pre-processing assembly.
25. antenna module according to claim 23, which is characterized in that the feeding network and the pre-processing assembly are set
It sets on the same circuit board.
26. antenna module according to claim 23, which is characterized in that the feeding network and the Signal separator device
Between be provided with the first amplifier unit, the satellite-signal that first amplifier unit is used to export the feeding network is put
Greatly.
27. according to claim 14-26 any one of them antenna modules, which is characterized in that the pre-processing assembly further includes
The second amplifier unit being connect with the signal synthesizer part, second amplifier unit is for defeated to the signal synthesizer part
The satellite-signal gone out is amplified.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| PCT/CN2017/117033 WO2019119237A1 (en) | 2017-12-18 | 2017-12-18 | Unmanned aerial vehicle and circularly polarized antenna assembly thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108521835A true CN108521835A (en) | 2018-09-11 |
| CN108521835B CN108521835B (en) | 2020-10-23 |
Family
ID=63434482
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201780005016.3A Expired - Fee Related CN108521835B (en) | 2017-12-18 | 2017-12-18 | Unmanned aerial vehicle and unmanned aerial vehicle's circular polarization antenna module |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN108521835B (en) |
| WO (1) | WO2019119237A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109659710A (en) * | 2018-12-14 | 2019-04-19 | 深圳市易讯物联科技有限公司 | It is a kind of improve radio frequency environment knob antenna and its application |
| CN109839650A (en) * | 2019-01-04 | 2019-06-04 | 哈瓦国际航空技术（深圳）有限公司 | A kind of compatible RTK localization method of unmanned plane, system, equipment and storage medium |
| WO2020134029A1 (en) * | 2018-12-27 | 2020-07-02 | 深圳市道通智能航空技术有限公司 | Antenna and unmanned aerial vehicle |
| WO2020150960A1 (en) * | 2019-01-24 | 2020-07-30 | 深圳市大疆创新科技有限公司 | Positioning information fusion method and apparatus, and intelligent terminal |
| WO2023123503A1 (en) * | 2021-12-31 | 2023-07-06 | 深圳市大疆创新科技有限公司 | Polarization direction control method, remote control device and storage medium |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2622145A1 (en) * | 2005-09-14 | 2007-03-22 | Novatel Inc. | Helicopter shipboard landing system |
| CN101296019A (en) * | 2008-05-27 | 2008-10-29 | 北京航空航天大学 | Relay repeater system for unmanned helicopter |
| WO2013040701A1 (en) * | 2011-09-20 | 2013-03-28 | Novatel Inc. | Gnss positioning system including an anti-jamming antenna and utilizing phase center corrected carrier |
| CN104092007A (en) * | 2014-06-27 | 2014-10-08 | 华南理工大学 | Broadband circular polarization omni antenna based on tilting oscillators |
| US9105961B2 (en) * | 2013-03-14 | 2015-08-11 | Hemisphere Gnss Inc. | Low profile, wideband GNSS dual frequency antenna structure |
| CN104931978A (en) * | 2014-03-18 | 2015-09-23 | 广东冠能电力科技发展有限公司 | Power line patrol unmanned aerial vehicle navigation system based on GPS RTK technology |
| CN105467415A (en) * | 2016-01-18 | 2016-04-06 | 中国民航大学 | Miniature unmanned plane RTK relative positioning method based on difference air pressure height constraints |
| CN106680854A (en) * | 2017-01-17 | 2017-05-17 | 桂林电子科技大学 | Low cost and high precision positioning system and method |
| US20170146990A1 (en) * | 2015-11-19 | 2017-05-25 | Caterpillar Inc. | Augmented communication and positioning using unmanned aerial vehicles |
| CN206378597U (en) * | 2017-01-17 | 2017-08-04 | 桂林电子科技大学 | A kind of low-cost and high-precision alignment system |
| CN207233932U (en) * | 2017-10-09 | 2018-04-13 | 北京沃氏航空科技有限公司 | Gps antenna holder assembly and unmanned plane |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205509001U (en) * | 2016-02-05 | 2016-08-24 | 广州市赛奥自动化技术有限公司 | Be applied to antenna device of satellite receiver |
-
2017
- 2017-12-18 WO PCT/CN2017/117033 patent/WO2019119237A1/en active Application Filing
- 2017-12-18 CN CN201780005016.3A patent/CN108521835B/en not_active Expired - Fee Related
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2622145A1 (en) * | 2005-09-14 | 2007-03-22 | Novatel Inc. | Helicopter shipboard landing system |
| CN101296019A (en) * | 2008-05-27 | 2008-10-29 | 北京航空航天大学 | Relay repeater system for unmanned helicopter |
| WO2013040701A1 (en) * | 2011-09-20 | 2013-03-28 | Novatel Inc. | Gnss positioning system including an anti-jamming antenna and utilizing phase center corrected carrier |
| US9105961B2 (en) * | 2013-03-14 | 2015-08-11 | Hemisphere Gnss Inc. | Low profile, wideband GNSS dual frequency antenna structure |
| CN104931978A (en) * | 2014-03-18 | 2015-09-23 | 广东冠能电力科技发展有限公司 | Power line patrol unmanned aerial vehicle navigation system based on GPS RTK technology |
| CN104092007A (en) * | 2014-06-27 | 2014-10-08 | 华南理工大学 | Broadband circular polarization omni antenna based on tilting oscillators |
| US20170146990A1 (en) * | 2015-11-19 | 2017-05-25 | Caterpillar Inc. | Augmented communication and positioning using unmanned aerial vehicles |
| CN105467415A (en) * | 2016-01-18 | 2016-04-06 | 中国民航大学 | Miniature unmanned plane RTK relative positioning method based on difference air pressure height constraints |
| CN106680854A (en) * | 2017-01-17 | 2017-05-17 | 桂林电子科技大学 | Low cost and high precision positioning system and method |
| CN206378597U (en) * | 2017-01-17 | 2017-08-04 | 桂林电子科技大学 | A kind of low-cost and high-precision alignment system |
| CN207233932U (en) * | 2017-10-09 | 2018-04-13 | 北京沃氏航空科技有限公司 | Gps antenna holder assembly and unmanned plane |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109659710A (en) * | 2018-12-14 | 2019-04-19 | 深圳市易讯物联科技有限公司 | It is a kind of improve radio frequency environment knob antenna and its application |
| WO2020134029A1 (en) * | 2018-12-27 | 2020-07-02 | 深圳市道通智能航空技术有限公司 | Antenna and unmanned aerial vehicle |
| CN109839650A (en) * | 2019-01-04 | 2019-06-04 | 哈瓦国际航空技术（深圳）有限公司 | A kind of compatible RTK localization method of unmanned plane, system, equipment and storage medium |
| WO2020150960A1 (en) * | 2019-01-24 | 2020-07-30 | 深圳市大疆创新科技有限公司 | Positioning information fusion method and apparatus, and intelligent terminal |
| WO2023123503A1 (en) * | 2021-12-31 | 2023-07-06 | 深圳市大疆创新科技有限公司 | Polarization direction control method, remote control device and storage medium |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2019119237A1 (en) | 2019-06-27 |
| CN108521835B (en) | 2020-10-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108521835A (en) | The circular polarized antenna component of unmanned plane and unmanned plane | |
| CN102646860A (en) | Triangular phased array antenna subarray | |
| US8941540B2 (en) | Antenna array | |
| CN104597467B (en) | A kind of GNSS-R detection devices and method based on phased array | |
| CN207149691U (en) | A kind of ultralow section high integration phased array antenna based on SIP encapsulation | |
| CN107611588A (en) | A kind of ultralow section high integration phased array antenna based on SIP encapsulation | |
| CN101859924B (en) | Dual-band array antenna of frequency-selection-based surface resonance unit | |
| CN111316499A (en) | Millimeter wave antenna structure, microwave rotary radar and movable platform | |
| EP3625591B1 (en) | Apparatus and method for receiving satellite positioning signals | |
| CN105990681A (en) | Antenna and airborne communication device | |
| EP3353854B1 (en) | Compact broadband antenna system with enhanced multipath rejection | |
| CN109546331A (en) | A kind of miniaturized planar two-band high-accuracy satellite navigation antenna | |
| CN106716710A (en) | Rack of unmanned aerial vehicle, unmanned aerial vehicle and antenna switching method | |
| JP7064428B2 (en) | Antenna elements, array antennas, communication units, mobiles and base stations | |
| US20180011202A1 (en) | Method for calculating attitude angle and apparatus therefor | |
| Obelleiro et al. | Synthesis of onboard array antennas including interaction with the mounting platform and mutual coupling effects | |
| CN111596272A (en) | Airborne multi-polarization SAR system external calibration method based on corner reflector | |
| CN205790365U (en) | A kind of multifrequency Big Dipper high-precision antenna | |
| CN205828657U (en) | Circular polarized antenna | |
| Rodenbeck et al. | AUTOMATED PATTERN MEASUREMENT FOR CIRCULARLY-POLARIZED ANTENNAS USING THE PHASE-AMPLITUDE METHOD. | |
| CN207183526U (en) | Anti-interference array is antenna integrated | |
| CN106025515A (en) | Double-layer coupling double-frequency circular polarization microstrip antenna | |
| CN207977453U (en) | The three of four cellular types stack antenna structure | |
| Chang et al. | Broadband wide-beam circular polarization antenna for global navigation satellite systems application | |
| CN112368590A (en) | Microwave antenna structure, microwave rotary radar and movable platform |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201023 |