CN105217049B - Aircraft capable of mounting and levitating interferometer for direction finding - Google Patents
Aircraft capable of mounting and levitating interferometer for direction finding Download PDFInfo
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- CN105217049B CN105217049B CN201510698960.4A CN201510698960A CN105217049B CN 105217049 B CN105217049 B CN 105217049B CN 201510698960 A CN201510698960 A CN 201510698960A CN 105217049 B CN105217049 B CN 105217049B
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Abstract
The invention discloses an aircraft capable of mounting and levitating interferometer for direction finding. The aircraft comprises an interferometer antenna array, an airborne direction finding device (22) and a rotor craft. The interferometer antenna array comprises an antenna array part (1) and a stand rod part (2). The antenna array part (1) comprises three active perpendicular polarizing antennas (3), an antenna middle fixing base (4) and three supporting devices (5). The antenna middle fixing base (4) comprises a supporting arm fixing base (6), a supporting arm rotating base (7), a supporting arm rotating base symmetrical part (8) and a stand rod base (9). The supporting arm rotating base (7) and the supporting arm rotating base symmetrical part (8) drive the supporting devices (5) and the active perpendicular polarizing antennas (3) to horizontally rotate through rotating shafts (10), and fixation is conducted through a locking device. The aircraft is convenient to install and detach, antennas of different specifications are selected according to actual situations, and the aircraft is convenient to store.
Description
Technical field
The aircraft of interferometer direction finding the present invention relates to a kind of carry goes up to the air.
Background technology
Direction-finding station is, according to propagation properties, to determine the mistake of radio wave arrival bearing using instrument and equipment
Journey.Determine " arrival bearing ", refer to the direction that electric wave reaches in the tangible electromagnetic environment in direction-finder set location, direction-finding station,
Common final purpose is to determine " direction of radiation source " and " particular location of radiation source ".
For interferometer direction finding system, its direction finding principle is：According to electric wave in traveling, the electric wave for coming from different directions is arrived
During up to direction estimation antenna array, the phase place that spatially each direction-finder antenna unit is received is different, thus mutual phase contrast is also different,
By determining come wave phase and phase contrast, you can determine arrival bearing.In interferometer direction finding mode, it is direct measurement direction finding day
The phase place of line induced voltage, then solves phase contrast, and its mathematical formulae is quite similar with the formula of amplitude comparison expression direction finding.Interfere
Instrument direction finding have high precision, fireballing feature and be used widely in electronic warfare.
The content of the invention
It is an object of the invention to overcome the deficiencies in the prior art, there is provided a kind of flight of carry lift-off interferometer direction finding
Device, solves prior art and cannot facilitate carry external monitoring direction-finding equipment, can only be by aircraft and direction-finding equipment integration production
Problem；And solve the problems, such as that the airborne direction finding equipment internal temperature of prior art is raised so that communication distance is greatly shortened.
The purpose of the present invention is achieved through the following technical solutions：A kind of flight of carry lift-off interferometer direction finding
Device, it includes interferometer antenna battle array, airborne direction finding equipment and rotor craft；
Described interferometer antenna battle array includes antenna array part and upright part；Described antenna array part includes that three have
Fixed seat and active vertical poliarizing antenna in the middle of fixed seat, three connection antennas in the middle of source vertical polarized antenna, an antenna
Support meanss；In the middle of described antenna, fixed seat includes a support arm fixed seat, support arm rotation seat, a support arm rotation seat
Symmetrical member and a vertical rod base；Described support arm rotation seat and support arm rotation seat symmetrical member by rotating shaft drive support meanss and
Active vertical poliarizing antenna is horizontally rotated, and is fixed by locking device；It is separately mounted to support arm rotation seat and support arm
The support meanss length of two active vertical poliarizing antennas of rotation seat symmetrical member is identical, and active installed in support arm fixed seat is hung down
Straight poliarizing antenna is less than λ/2 with the horizontal linear distance of the active vertical poliarizing antenna for being arranged on support arm rotation seat, and wherein λ/2 are
The half-wavelength of maximum operating frequency；Described upright part includes vertical rod, the vector synthesizer for being arranged at vertical rod stage casing, is arranged at
Radio-frequency cable inside vertical rod, one end of described vertical rod connect aerial plug and vertical rod base by the tight lock tube of first antenna,
The other end of vertical rod connects data-interface by the tight lock tube of the second antenna, and described vector synthesizer is for by three active verticals
The radiofrequency signal that poliarizing antenna is received carries out Vector modulation, and the radiofrequency signal after synthesis is connect by radio-frequency cable and data
Mouth is sent to airborne direction finding equipment；
Described airborne direction finding equipment includes external shell and internal circuit；Described internal circuit include GPS module,
Gps antenna, electronic compass, X86 boards, receiver, WIFI module and WIFI omnidirectional antennas；GPS module is received from gps antenna
Radiofrequency signal, the outfan of GPS module is connected with X86 boards, and electronic compass is connected with X86 boards, receiver receive from
The radiofrequency signal of interferometer antenna battle array, receiver are connected with X86 process plates, the detection antenna control output end of X86 boards with it is dry
Interferometer antenna array connects, and X86 boards are also connected with WIFI module, and WIFI module is connected with WIFI omnidirectional antennas, WIFI omnidirectional antennas
Line is received from the signal of external monitoring terminal or to outside monitoring terminal sending signal；The side of described external shell sets
It is equipped with the screw on rotor craft for carry；
Described rotor craft includes fuselage and arranges the aircraft circuit with fuselage interior, and described fuselage includes machine
Body, multiple rotor arms being connected with body and multiple rotor modules being connected with rotor arm, described rotor module include control
The rotor of the arrangements for speed regulation of rotor shaft rotation, rotor shaft and rotor shaft connection, described organism bottom is provided with multiple for hanging
Carry the hook of airborne direction finding equipment；Described aircraft circuit includes wireless communication module, control module, energy module；It is described
Energy module be that wireless communication module, control module, arrangements for speed regulation are powered；Described wireless communication module is connected with control module
Connect, multiple control output ends of control module are connected with arrangements for speed regulation.
Keeper of the multiple and support arm fixed seat in fixed angle is provided with described rotating shaft, in support arm rotation seat
Angle Selection is carried out when rotating with support arm rotation seat symmetrical member.
Described external shell is provided with multiple air vents, is provided with cold drawing on described X86 boards.
Described internal circuit also includes power management plate and battery；Battery is connected with power management plate, power management plate
Respectively to GPS module, electronic compass, X86 boards, receiver, WIFI module and dry after the voltage to battery is changed
Interferometer antenna array is powered.
Described rotor craft also includes two supports, and the fixing end of described support is connected with organism bottom.
Described interferometer antenna battle array also includes main fixed seat, and described main fixed seat is by the tight lock tube protection of the second antenna
Data-interface.
Described locking device includes rotating nut and rotation nut sleeve.
Described vector synthesizer include two SP3T switch, three six throw switches of hilted broadsword, 0 degree of power combiner,
90 degree of power combiners, 180 degree power combiner and 270 degree of power combiners；The input of the first SP3T switch is received
From the radiofrequency signal of the active vertical poliarizing antenna installed in support arm fixed seat, the outfan of the first SP3T switch and the
One hilted broadsword, six throw switch connects, and five outfans of six throw switch of the first hilted broadsword are input into the first of 0 degree of power combiner respectively
End, the of the first input end of 90 degree of power combiners, the first input end of 180 degree power combiner, 270 degree of power combiners
The first input end connection of six throw switch of one input and the 3rd hilted broadsword；The first input end of the second SP3T switch and second
Input is received from the active vertical poliarizing antenna installed in support arm rotation seat respectively and is arranged on support arm rotation seat symmetrical member
Active vertical poliarizing antenna, the outfan of the second SP3T switch is connected with the input of six throw switch of the second hilted broadsword,
Wherein four outfans of two hilted broadswords, six throw switch the second input respectively with 0 degree of power combiner, 90 degree of power combiners
The second input, the second input of 180 degree power combiner and 270 degree of power combiners the connection of the second input, the
5th outfan of two hilted broadswords, six throw switch passes through resistance eutral grounding；0 degree of power combiner, 90 degree of power combiners, 180 degree power
The outfan of synthesizer and 270 degree of power combiners the second input respectively with six throw switch of the 3rd hilted broadsword, the 3rd input,
4th input and the connection of the 5th input, the radiofrequency signal after the outfan output vector synthesis of six throw switch of the 3rd hilted broadsword is extremely
Data-interface.
Described 0 degree of power combiner, 90 degree of power combiners, 180 degree power combiner and 270 degree of power combiners are equal
Including a phase shifter and a synthesizer, the input of phase shifter receives single from six throw switch of the first hilted broadsword and second respectively
The signal of six throw switch of knife, two outfans of phase shifter are connected with synthesizer, and the outfan of synthesizer is thrown with the 3rd hilted broadsword six
Switch connection.
Described vector synthesizer also includes a control input port, and described control input port receiver carries direction finding
The Transistor-Transistor Logic level signal of the X86 boards of equipment, for control is installed in the active vertical poliarizing antenna of support arm rotation seat and is arranged on
The switching of the active vertical poliarizing antenna of support arm rotation seat symmetrical member, and for controlling the phase place of phase shifter.
The invention has the beneficial effects as follows：
(1) the invention provides a kind of interferometer antenna battle array being easily installed with dismounting, can select according to practical situation
The antenna array part of different size need to only be installed by the different active vertical poliarizing antenna of specification；And in antenna
Battle array rotates three active vertical poliarizing antennas to together using after completing, convenient to deposit.
(2) using rotation and locking device so that aerial angle can be selected according to practical situation, practicality
By force.
(3) it is further, as antenna during installing with dismounting can be opened and be closed up by the present invention,
The problem that angle is recalculated can be produced.And when the mode of the setting fixed angle keeper in rotating shaft is employed, can be to normal
With angle carry out quick alignment, it is easy to use and reliable.
(4) present invention is also arranged at vector synthesizer in interferometer antenna battle array, and three active vertical poliarizing antennas are connect
Three radiofrequency signals for receiving are synthesized, and the radiofrequency signal after synthesis is sent, and facilitate subsequent conditioning circuit to be processed.
The present invention adopts various radiator structures, it is ensured that the communication distance of airborne direction finding equipment will not be because of the reason for temperature
Reduce.
(1) increase air vent on the shell of equipment, natural wind is incorporated into into device interior, so as to by the heat of device interior
Amount is taken away, and reduces the temperature of equipment.
(2) increase cold drawing on the core board of X86, increase the temperature that cold drawing reduces X86 boards, improve X86 boards
Stability and reliability.
Present invention also offers a kind of rotor craft with hook, specifically, can be with monitoring and direction-finding equipment by hanging
Hook is loaded on rotor craft；Also, the present invention is also to notifying flight position to ground based terminal in real time.
Description of the drawings
Fig. 1 is 1 decomposition chart of interferometer antenna battle array embodiment；
Fig. 2 is the structure chart after the completion of the assembling of interferometer antenna battle array embodiment 1；
Fig. 3 is fixed seat partial structural diagram in the middle of antenna；
Fig. 4 is data-interface structural representation；
Fig. 5 is 2 decomposition chart of interferometer antenna battle array embodiment；
Fig. 6 is vector synthesizer module frame chart；
Fig. 7 is interferometer antenna battle array schematic diagram；
Fig. 8 is the airborne direction finding equipment structural representation after perforate；
Fig. 9 is airborne direction finding equipment internal circuit blocks figure；
Figure 10 is power management plate distribution condition schematic diagram；
Figure 11 is rotor craft structure chart；
Figure 12 is rotor craft partial schematic diagram；
Circuit module figures of the Figure 13 for rotor craft；
In figure, 1- antenna arrays part, 2- upright parts, 3- active vertical poliarizing antennas, fixed seat in the middle of 4- antennas, 5-
Support arrangement, 6- support arm fixed seats, 7- support arm rotation seats, 8- support arm rotation seat symmetrical members, 9- vertical rod bases, 10- rotating shafts, 11- stand
Bar, 12- aerial plugs, 13- data-interfaces, the tight lock tube of 14- first antennas, the tight lock tube of the second antennas of 15-, the main fixed seats of 16-,
17- rotates nut, 18- rotation nut sleeves, 19- antenna fixing seats, 20- rotation backing pins, 21- vector synthesizers, the airborne direction findings of 22-
Equipment, 23- air vents, 24- rotor arms, 25- arrangements for speed regulation, 26- rotors, 27- bases, 28- columns, 29- hooks, 30-
Frame, 31- screws.
Specific embodiment
Technical scheme is described in further detail below in conjunction with the accompanying drawings：
A kind of aircraft of carry lift-off interferometer direction finding, it includes interferometer antenna battle array, airborne direction finding equipment and rotation
Rotor aircraft.
As shown in Figure 1 and Figure 5, interferometer antenna battle array includes antenna array part 1 and upright part 2.
As shown in Fig. 2 described antenna array part 1 includes fixing in the middle of three active vertical poliarizing antennas, 3, antenna
The support meanss 5 of fixed seat 4 and active vertical poliarizing antenna 3 in the middle of 4, three connection antennas of seat.
As shown in figure 3, fixed seat 4 includes 6, support arm rotation seat 7, of a support arm fixed seat in the middle of described antenna
Individual support arm rotation seat symmetrical member 8 and a vertical rod base 9；Described support arm rotation seat 7 and support arm rotation seat symmetrical member 8 are by turning
Axle 10 drives support meanss 5 and active vertical poliarizing antenna 3 to be horizontally rotated, and is fixed by locking device.
It is separately mounted to the support of two active vertical poliarizing antennas of support arm rotation seat 7 and support arm rotation seat symmetrical member 8
5 length of device is identical.
In order to avoid phase ambiguity, rotate installed in the active vertical poliarizing antenna 3 of support arm fixed seat 6 and installed in support arm
The horizontal linear distance of the active vertical poliarizing antenna 3 of seat 7 is less than λ/2, wherein half-wavelength of λ/2 for maximum operating frequency.
The distance between antenna in support arm fixed seat 6 and the antenna on support arm rotation seat 7, with installation
Distance between antenna in support arm fixed seat 6 and the antenna on support arm rotation seat symmetrical member 8 is equal, and is less than
The half-wavelength of λ/2, i.e. maximum operating frequency, phase place are less than 180 degree.Here we select 150 degree of maximum operating frequency.
Now, have two kinds of situations to produce, support meanss 5 are shorter and support meanss 5 are longer：As shown in figure 1, embodiment 1
When being longer for support meanss 5, antenna distance is 600mm, and operating frequency now is 70～200MHz；Such as Fig. 5 institutes
Show, when embodiment 2 is shorter for support meanss 5, antenna distance is 220mm, operating frequency now is 200～500.
Described upright part 2 includes vertical rod 11 and the radio-frequency cable being arranged inside vertical rod 11, described vertical rod 11
One end connects aerial plug 12 and vertical rod base 9 by the tight lock tube 14 of first antenna, as shown in figure 4, the other end of vertical rod 11 leads to
Cross the tight connection of lock tube 15 data-interface 13 of the second antenna and record direction-finding equipment 22.
A kind of interferometer antenna battle array for being provided with vector synthesizer also includes main fixed seat 16, and described main fixed seat 16 passes through
The tight lock tube 15 of second antenna protects data-interface 13.
After antenna is using completing, after the process dismantled, the data-interface 13 of upright part 2 can be exposed to sky
In gas, and data-interface 13 is protected using main fixed seat 16, improve the life-span of whole antenna array.
Described locking device includes rotating nut 17 and rotation nut sleeve 18.Be provided with described rotating shaft 10 it is multiple with
Keeper of the support arm fixed seat 6 in fixed angle, for carrying out when rotating in support arm rotation seat 7 and support arm rotation seat symmetrical member 8
Angle Selection.Described fixed angle includes 30 degree, 45 degree, 60 degree, 90 degree, 120 degree, 135 degree and 150 degree.
As antenna during installing with dismounting can be opened and be closed up by the present invention.Angle weight can be produced
The new problem for calculating.And when the mode of the setting fixed angle keeper in rotating shaft is employed, the angle commonly used can be carried out
Quick alignment, it is easy to use and reliable.
Described support meanss 5 connect one end of active vertical polarized antenna 3 and are provided with antenna fixing seat 19.
Rotation backing pin 20 is provided with described support arm rotation seat 7 and support arm rotation seat symmetrical member 8.
As shown in fig. 6, described vector synthesizer 21 include two SP3T switch, three six throw switches of hilted broadsword, 0 degree
Power combiner, 90 degree of power combiners, 180 degree power combiner and 270 degree of power combiners；First SP3T switch
Input receives the radiofrequency signal from the active vertical poliarizing antenna 3 installed in support arm fixed seat 6, the first SP3T switch
Outfan be connected with six throw switch of the first hilted broadsword, five outfans of six throw switch of the first hilted broadsword respectively with 0 degree of power combing
The first input end of device, the first input end of 90 degree of power combiners, the first input end of 180 degree power combiner, 270 degree of work(
The first input end connection of six throw switch of first input end and the 3rd hilted broadsword of rate synthesizer；The first of second SP3T switch
Input and the second input receive respectively from installed in support arm rotation seat 7 active vertical poliarizing antenna 3 and be arranged on
The active vertical poliarizing antenna 3 of arm rotation seat symmetrical member 8, six throw switch of the outfan of the second SP3T switch and the second hilted broadsword
Input connection, wherein four outfans of six throw switch of the second hilted broadsword the second input respectively with 0 degree of power combiner,
The second of second input of 90 degree of power combiners, the second input of 180 degree power combiner and 270 degree of power combiners
Input connects, and the 5th outfan of six throw switch of the second hilted broadsword passes through resistance eutral grounding；0 degree of power combiner, 90 degree of power are closed
Grow up to be a useful person, the outfan of 180 degree power combiner and 270 degree of power combiners is input into the second of six throw switch of the 3rd hilted broadsword respectively
End, the 3rd input, the 4th input and the connection of the 5th input, the outfan output vector synthesis of six throw switch of the 3rd hilted broadsword
Radiofrequency signal afterwards is to data-interface 13.
Described 0 degree of power combiner, 90 degree of power combiners, 180 degree power combiner and 270 degree of power combiners are equal
Including a phase shifter and a synthesizer, the input of phase shifter receives single from six throw switch of the first hilted broadsword and second respectively
The signal of six throw switch of knife, two outfans of phase shifter are connected with synthesizer, and the outfan of synthesizer is thrown with the 3rd hilted broadsword six
Switch connection.
Described vector synthesizer 21 also includes a control input port, outside described control input port acceptance
Transistor-Transistor Logic level signal, controls digit for 4, and wherein 1 is used for active vertical poliarizing antenna 3 of the control installed in support arm rotation seat 7
With the switching of the active vertical poliarizing antenna 3 installed in support arm rotation seat symmetrical member 8,3 are used for controlling the phase of phase shifter in addition
Position.
Schematic diagrams of the Fig. 7 for interferometer antenna battle array, in figure, " 1 " number antenna represents the antenna in support arm fixed seat 6,
In figure, " 2 " number antenna represents the antenna on support arm rotation seat 7, and in figure, " 3 " number antenna is represented installed in support arm rotation seat
Antenna on symmetrical member 8.
When arrival bearing is θ, signal reaches 3 antenna times differences, therefore can obtain two wave path-differences, is respectively
Φ 12 and Φ 13.
When the elevation angle of incoming wave signal is 0 °, wave path-difference is as follows
Can be obtained by formula (1) and formula (2)
12/ Φ 13 of tan θ=Φ；(3)
Arrival bearing can be obtained by formula (3)
θ=arctan (12/ Φ 13 of Φ).
When the elevation angle of arrival bearing is β, wave path-difference is as follows
Can be obtained by formula (4) and formula (5)
12/ Φ 13 of tan θ=Φ；(6)
Arrival bearing can be obtained by formula (6) tangent of negating
θ=arctan (12/ Φ 13 of Φ)；
Can also be obtained by formula (4) and formula (5)
The incoming wave elevation angle can be obtained by formula (7) cosine of negating
Described airborne direction finding equipment 22 includes external shell and internal circuit.As shown in figure 9, described internal circuit bag
Include GPS module, gps antenna, electronic compass, X86 boards, receiver, WIFI module and WIFI omnidirectional antennas；GPS module is received
From the radiofrequency signal of gps antenna, the outfan of GPS module is connected with X86 boards, and electronic compass is connected with X86 boards, is received
Machine receives the radiofrequency signal from monitoring and direction-finding antenna, and receiver is connected with X86 process plates, the detection day line traffic control of X86 boards
Outfan is connected with monitoring and direction-finding antenna, and X86 boards are also connected with WIFI module, and WIFI module is connected with WIFI omnidirectional antennas,
WIFI omnidirectional antennas are received from the signal of external monitoring terminal or to outside monitoring terminal sending signal.
Lift-off interferometer direction finding, the liter null device for using is rotor craft.Rotor craft can not fly in the rainy day, because
This airborne direction finding equipment 22 also avoids the need for rain-proof, increases air vent 23, natural wind is incorporated into equipment on the shell of equipment
Inside, so as to the heat of device interior is taken away, reduces the temperature of equipment.Airborne direction finding equipment 22 after perforate is as shown in Figure 8.
Described air vent 23 is arranged at the both sides of airborne direction finding equipment 22, and is symmetric.
In order to improve the stability of X86 boards, increase cold drawing on the core board of X86, increase cold drawing and reduce X86 boards
Temperature, improve reliability.
After antenna receives spacing wave, it is sent to digital receiver and is processed；Lower change is simulated by digital receiver
Frequency and AD samplings, output i/q signal to X86 process plates, X86 process plates carry out FFT process, export the frequency for needing to i/q signal
Spectrum information and amplitude information, X86 process plates process the azimuth information of electronic compass simultaneously.Spectrum information, amplitude information and orientation
Information is transferred to external monitoring terminal by exporting transmission unit.
USRP B210 of the digital receiver using Ettus, the board realize the frequency conversion of broadband rf signal, intermediate-freuqncy signal
ADC, the DDC process to i/q signal.
The core processing such as the main completion system signal processing of X86 system boards and network management, is provided simultaneously with WIFI and leads to
Letter and transfer function, X86 mainboards possess standard interface using what Guangzhou Zhiyuan Electronics Co., Ltd. developed
COME1054-02 core boards.
Aircraft in flight course, by aerial airflow influence, and the change of flight path, sending out at any time by flight attitude
Changing, it is therefore desirable to select three axle electronic compass.The present invention feels microelectronic ECS-V1.0 electronic compass, the electricity using Nanjing
The features such as sub- compass has small volume, low in energy consumption, high sensitivity, fast response time.
From small volume, WIFI module that is lightweight, having network interface and USB port.The present invention selects BL-3070-RZ1B types
WIFI module.
Aircraft carries WIFI antennas and selects small volume, lightweight omnidirectional WIFI antennas, selection card king KW-5106 of the present invention
Type antenna.
Described internal circuit also includes power management plate and battery；Battery is connected with power management plate, power management plate
Respectively to GPS module, electronic compass, X86 boards, receiver, WIFI module and prison after the voltage to battery is changed
Survey direction-finder antenna to power.Figure 10 and following table represent that power management does distribution condition.
| Equipment | Antenna array | Receiver | Electronic compass | X86 process plates | WIFI module |
| Voltage (V) | 5 | 6 | 5 | 12 | 5 |
| Electric current (mA) | 420 | 2000 | 10 | 1000 | 200 |
| Power consumption (W) | 2.1 | 12 | 0.05 | 12 | 1 |
1 loading equipemtn power consumption of table
As seen from the above table, loading equipemtn voltage has three kinds, i.e. 5V, 6V and 12V, and power consumption has 27W.By the conversion efficiency of power supply
For 85%, total power consumption is 31.7W.
Selection of Battery cobalt acid lithium battery, the voltage range of single battery is 2.75～4.2V, this practical required voltage for+
5V ,+6V and+12V, it is therefore desirable to which two battery series connection, voltage range reach 5.5～8.4V, can meet the direct voltage stabilizing of+5V ,+6V
Demand.The capacity of single cobalt acid lithium battery is 3.4Ah (18650 type battery of Panasonic), and the capacity of two batteries is 7.2Ah, electric
Pond use time is calculated as follows：
7.2 (Ah) × 1 (only) × 6 (V) × 0.85 (efficiency 85%)/24 (W)=1.53h；
In order to perform the monitoring and direction-finding task of longer time, in the range of weight is allowed, battery is increased to into 4.
As shown in figure 11, rotor craft, including fuselage and the circuit of setting and fuselage interior, described fuselage includes machine
Body, multiple rotor arms 24 being connected with body and multiple rotor modules being connected with rotor arm 24, described rotor module are included
The arrangements for speed regulation 25, rotor shaft of control rotor shaft rotation and the rotor 26 of rotor shaft connection；
As shown in figure 12, described organism bottom is provided with multiple hooks 29 for carry airborne direction finding equipment 22, machine
The housing side of load direction-finding equipment 22 is provided with and is matched the screw 31 for using with hook 29；
As shown in figure 13, described circuit includes wireless communication module, control module, energy module and locating module；Institute
The energy module stated is powered for wireless communication module, control module, arrangements for speed regulation 25 and locating module；Described radio communication mold
Block is connected with control module, and multiple control output ends of control module are connected with arrangements for speed regulation 25, the outfan of locating module with
Control module connects.
Wireless communication module is received after the control command on ground, is sent to control module, and control module is to control
Order be analyzed after control arrangements for speed regulation 25, to reach, control direction (including it is mobile somewhither and hovering) purpose.
In real time flying quality is sent by wireless communication module by locating module to the control end on ground.
Angle between two rotor arms 24 of arbitrary neighborhood is identical.
Described rotor arm 24 has 8, and body is provided with a rotor arm 24 every 45 degree.
Described body includes base 27 and the column 28 being arranged on base 27, the described connection rotor arm of base 27
24,27 bottom of base is provided with multiple hooks 29, and described column 28 is internally provided with the circuit.
A kind of rotor craft with hook also includes two supports 30, fixing end and the body bottom of described support 30
Portion connects.
Described energy module includes at least one lithium battery.
Described wireless communication module is the one of which in 3G module/4G modules/WIFI module/bluetooth module.
In the air, and final process and being displayed on the notebook on ground is carried out for the reception of signal and process part.Will
By aerial signal transmission to ground, it is necessary to use radio communication, currently available radio communication has bluetooth, WIFI and public logical
3G/4G communications in letter system.This develop concern it is important that the transmission range of radio communication, following table list four kinds it is wireless
The representative communication distance of transmission.
| Communication mode | Bluetooth | WIFI | 3G | 4G |
| Transmission range (rice) | 10 | 300 | ∝ (during the network coverage) | ∝ (during the network coverage) |
The transmission range of 2 four kinds of radio communications of table
The lift-off of rotor craft is highly 600 meters to the maximum, when flying radius reaches 500 meters, rotor craft distance
The air line distance of operator is 800 meters.From table 1 it follows that the transmission range of bluetooth and WIFI is not all reached so far,
Preferably with 3G or 4G public communication network transmission datas.
One of which of the described locating module for GPS module/big dipper module.
Described control module includes microcontroller, model MSP430 of described microcontroller.MSP430 is lightweight
Small volume.
Claims (10)
1. a kind of carry goes up to the air the aircraft of interferometer direction finding, it is characterised in that：It includes interferometer antenna battle array, airborne direction finding
Equipment（22）And rotor craft；
Described interferometer antenna battle array includes antenna array part（1）And upright part（2）；Described antenna array part（1）Including
Three active vertical poliarizing antennas（3）, fixed seat in the middle of an antenna（4）, fixed seat in the middle of three connection antennas（4）With it is active
Vertical polarized antenna（3）Support meanss（5）；Fixed seat in the middle of described antenna（4）Including a support arm fixed seat（6）, one
Individual support arm rotation seat（7）, a support arm rotation seat symmetrical member（8）With a vertical rod base（9）；Described support arm rotation seat（7）
With support arm rotation seat symmetrical member（8）By rotating shaft（10）Drive support meanss（5）With active vertical poliarizing antenna（3）The level of carrying out
Rotation, is fixed by locking device；It is separately mounted to support arm rotation seat（7）With support arm rotation seat symmetrical member（8）Two
The support meanss of active vertical poliarizing antenna（5）Length is identical, installed in support arm fixed seat（6）Active vertical poliarizing antenna
（3）With installed in support arm rotation seat（7）Active vertical poliarizing antenna（3）Horizontal linear distance be less than λ/2, wherein λ/2 are
The half-wavelength of maximum operating frequency；Described upright part（2）Including vertical rod（11）, be arranged at vertical rod（11）The vector in stage casing is closed
Grow up to be a useful person（21）, be arranged at vertical rod（11）Internal radio-frequency cable, described vertical rod（11）One end pass through the tight lock tube of first antenna
（14）Connection aerial plug（12）With vertical rod base（9）, vertical rod（11）The other end pass through the tight lock tube of the second antenna（15）Connection
Data-interface（13）, described vector synthesizer（21）For by three active vertical poliarizing antennas（3）The radio frequency letter for receiving
Vector modulation number is carried out, and the radiofrequency signal after synthesis is passed through into radio-frequency cable and data-interface（13）Send to airborne direction finding and set
It is standby（22）；
Described airborne direction finding equipment（22）Including external shell and internal circuit；Described internal circuit include GPS module,
Gps antenna, electronic compass, X86 boards, receiver, WIFI module and WIFI omnidirectional antennas；GPS module is received from gps antenna
Radiofrequency signal, the outfan of GPS module is connected with X86 boards, and electronic compass is connected with X86 boards, receiver receive from
The radiofrequency signal of interferometer antenna battle array, receiver are connected with X86 boards, the detection antenna control output end of X86 boards and interference
Instrument antenna array connects, and X86 boards are also connected with WIFI module, and WIFI module is connected with WIFI omnidirectional antennas, WIFI omnidirectional antennas
Receive from the signal of external monitoring terminal or to outside monitoring terminal sending signal；The side of described external shell is arranged
There is the screw on rotor craft for carry（31）；
Described rotor craft includes fuselage and arranges and the aircraft circuit of fuselage interior, described fuselage include body,
Multiple rotor arms being connected with body（24）With multiple and rotor arm（24）The rotor module of connection, described rotor module include
The arrangements for speed regulation of control rotor shaft rotation（25）, rotor shaft and rotor shaft connection rotor（26）, described organism bottom arranges
Have multiple for carry airborne direction finding equipment（22）Hook（29）；Described aircraft circuit includes wireless communication module, control
Molding block, energy module；Described energy module is wireless communication module, control module, arrangements for speed regulation（25）Power supply；Described
Wireless communication module is connected with control module, multiple control output ends of control module and arrangements for speed regulation（25）Connection.
2. a kind of carry according to claim 1 goes up to the air the aircraft of interferometer direction finding, it is characterised in that：Described turns
Axle（10）On be provided with it is multiple with support arm fixed seat（6）Keeper in fixed angle, in support arm rotation seat（7）And support arm
Rotation seat symmetrical member（8）Angle Selection is carried out during rotation.
3. a kind of carry according to claim 1 goes up to the air the aircraft of interferometer direction finding, it is characterised in that：Described is outer
Portion's housing is provided with multiple air vents（23）, on described X86 boards, it is provided with cold drawing.
4. a kind of carry according to claim 1 goes up to the air the aircraft of interferometer direction finding, it is characterised in that：Described is interior
Portion's circuit also includes power management plate and battery；Battery is connected with power management plate, and power management plate enters in the voltage to battery
Powered to GPS module, electronic compass, X86 boards, receiver, WIFI module and interferometer antenna battle array after row conversion respectively.
5. a kind of carry according to claim 1 goes up to the air the aircraft of interferometer direction finding, it is characterised in that：Described rotation
Rotor aircraft also includes two supports（30）, described support（30）Fixing end be connected with organism bottom.
6. a kind of carry according to claim 1 goes up to the air the aircraft of interferometer direction finding, it is characterised in that：Described is dry
Interferometer antenna array also includes main fixed seat（16）, described main fixed seat（16）By the tight lock tube of the second antenna（15）Protection data
Interface（13）.
7. a kind of carry according to claim 1 goes up to the air the aircraft of interferometer direction finding, it is characterised in that：Described lock
Tight device includes rotating nut（17）With rotation nut sleeve（18）.
8. a kind of carry according to claim 1 goes up to the air the aircraft of interferometer direction finding, it is characterised in that：Described arrow
Amount synthesizer（21）Including two SP3T switch, three six throw switches of hilted broadsword, 0 degree of power combiner, 90 degree of power combings
Device, 180 degree power combiner and 270 degree of power combiners；The input of the first SP3T switch receive from installed in
Arm fixed seat（6）Active vertical poliarizing antenna（3）Radiofrequency signal, the outfan of the first SP3T switch and the first hilted broadsword
Six throw switches connect, five outfans of six throw switch of the first hilted broadsword first input end respectively with 0 degree of power combiner, 90 degree
The first input end of power combiner, the first input end of 180 degree power combiner, the first input of 270 degree of power combiners
The first input end of end and six throw switch of the 3rd hilted broadsword connects；The first input end of the second SP3T switch and the second input
Received from installed in support arm rotation seat respectively（7）Active vertical poliarizing antenna（3）With installed in support arm rotation seat symmetrical member
（8）Active vertical poliarizing antenna（3）, the input company of six throw switch of the outfan of the second SP3T switch and the second hilted broadsword
Connect, wherein four outfans of six throw switch of the second hilted broadsword the second input respectively with 0 degree of power combiner, 90 degree of power are closed
Second input of the second input, the second input of 180 degree power combiner and the 270 degree of power combiners grown up to be a useful person connects
Connect, the 5th outfan of six throw switch of the second hilted broadsword passes through resistance eutral grounding；0 degree of power combiner, 90 degree of power combiners, 180
Outfan second input respectively with six throw switch of the 3rd hilted broadsword of degree power combiner and 270 degree of power combiners, the 3rd
The connection of input, the 4th input and the 5th input, penetrating after the outfan output vector synthesis of six throw switch of the 3rd hilted broadsword
Frequency signal is to data-interface（13）.
9. a kind of carry according to claim 8 goes up to the air the aircraft of interferometer direction finding, it is characterised in that：Described 0
Degree power combiner, 90 degree of power combiners, 180 degree power combiner and 270 degree of power combiners include a phase shifter
With a synthesizer, the input of phase shifter receives the letter from six throw switch of six throw switch of the first hilted broadsword and the second hilted broadsword respectively
Number, two outfans of phase shifter are connected with synthesizer, and the outfan of synthesizer is connected with six throw switch of the 3rd hilted broadsword.
10. a kind of carry according to claim 9 goes up to the air the aircraft of interferometer direction finding, it is characterised in that：Described
Vector synthesizer（21）Also include a control input port, described control input port receiver carries direction-finding equipment（22）'s
The Transistor-Transistor Logic level signal of X86 boards, for control installed in support arm rotation seat（7）Active vertical poliarizing antenna（3）Be arranged on
Support arm rotation seat symmetrical member（8）Active vertical poliarizing antenna（3）Switching, and for controlling the phase place of phase shifter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510698960.4A CN105217049B (en) | 2015-10-23 | 2015-10-23 | Aircraft capable of mounting and levitating interferometer for direction finding |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510698960.4A CN105217049B (en) | 2015-10-23 | 2015-10-23 | Aircraft capable of mounting and levitating interferometer for direction finding |
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| Publication Number | Publication Date |
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| CN105217049A CN105217049A (en) | 2016-01-06 |
| CN105217049B true CN105217049B (en) | 2017-03-22 |
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| CN201510698960.4A Active CN105217049B (en) | 2015-10-23 | 2015-10-23 | Aircraft capable of mounting and levitating interferometer for direction finding |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107672803A (en) * | 2017-09-14 | 2018-02-09 | 青岛四合信息科技有限公司 | A kind of technology and device of the automatic detection calibration radio guard of unmanned plane |
| CN109660881B (en) * | 2017-10-10 | 2021-10-19 | 华为技术有限公司 | Customer premises equipment CPE, CPE installing support and CPE system |
| CN115411522A (en) * | 2022-09-26 | 2022-11-29 | 成都零点科技有限公司 | Antenna support device suitable for monitoring aircraft frequency spectrum |
Citations (3)
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|---|---|---|---|---|
| CN101895352A (en) * | 2010-06-24 | 2010-11-24 | 南京天之谱科技有限公司 | Single-soldier backpack type radio monitoring direction-finding system |
| US8952843B1 (en) * | 2012-03-23 | 2015-02-10 | Rockwell Collins, Inc. | Directional AESA with interferometer direction finding mode |
| CN205044992U (en) * | 2015-10-23 | 2016-02-24 | 成都九华圆通科技发展有限公司 | Carry aircraft that interferometer direction -finding was used that goes up to air |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004093245A2 (en) * | 2003-04-15 | 2004-10-28 | Tecom Industries, Inc. | Electronically scanning direction finding antenna system |
| US8559011B2 (en) * | 2011-11-15 | 2013-10-15 | The United States Of America, As Represented By The Secretary Of The Navy | Micro-spectral sensor |
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2015
- 2015-10-23 CN CN201510698960.4A patent/CN105217049B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101895352A (en) * | 2010-06-24 | 2010-11-24 | 南京天之谱科技有限公司 | Single-soldier backpack type radio monitoring direction-finding system |
| US8952843B1 (en) * | 2012-03-23 | 2015-02-10 | Rockwell Collins, Inc. | Directional AESA with interferometer direction finding mode |
| CN205044992U (en) * | 2015-10-23 | 2016-02-24 | 成都九华圆通科技发展有限公司 | Carry aircraft that interferometer direction -finding was used that goes up to air |
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| 机载二维干涉仪测向误差分析;毛虎等;《火力与指挥控制》;20111231;第36卷(第12期);第67-71页 * |
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| CN105217049A (en) | 2016-01-06 |
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Inventor after: Ning Tao Inventor after: Wang Qingsong Inventor after: Ma Xiaolin Inventor after: Yin Qi Inventor after: Li Guiping Inventor after: Wu Weidong Inventor before: Ning Tao Inventor before: Ma Xiaolin Inventor before: Yin Qi Inventor before: Li Guiping Inventor before: Wu Weidong |
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Denomination of invention: Aircraft capable of mounting and levitating interferometer for direction finding Effective date of registration: 20170727 Granted publication date: 20170322 Pledgee: Chengdu SME financing Company Limited by Guarantee Pledgor: Jiuhua Yuantong Science and Technology Development Co., Ltd., Chengdu Registration number: 2017510000045 |
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Date of cancellation: 20210105 Granted publication date: 20170322 Pledgee: Chengdu SME financing Company Limited by Guarantee Pledgor: CHENGDU JIUHUA YUANTONG TECHNOLOGY DEVELOPMENT Co.,Ltd. Registration number: 2017510000045 |