CN109412744A - A kind of comprehensive interference system of unmanned plane - Google Patents
A kind of comprehensive interference system of unmanned plane Download PDFInfo
- Publication number
- CN109412744A CN109412744A CN201811493958.3A CN201811493958A CN109412744A CN 109412744 A CN109412744 A CN 109412744A CN 201811493958 A CN201811493958 A CN 201811493958A CN 109412744 A CN109412744 A CN 109412744A
- Authority
- CN
- China
- Prior art keywords
- signal
- satellite
- antenna
- transmitting
- digital power
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04K—SECRET COMMUNICATION; JAMMING OF COMMUNICATION
- H04K3/00—Jamming of communication; Counter-measures
- H04K3/40—Jamming having variable characteristics
- H04K3/42—Jamming having variable characteristics characterized by the control of the jamming frequency or wavelength
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04K—SECRET COMMUNICATION; JAMMING OF COMMUNICATION
- H04K3/00—Jamming of communication; Counter-measures
- H04K3/60—Jamming involving special techniques
- H04K3/65—Jamming involving special techniques using deceptive jamming or spoofing, e.g. transmission of false signals for premature triggering of RCIED, for forced connection or disconnection to/from a network or for generation of dummy target signal
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04K—SECRET COMMUNICATION; JAMMING OF COMMUNICATION
- H04K3/00—Jamming of communication; Counter-measures
- H04K3/80—Jamming or countermeasure characterized by its function
- H04K3/84—Jamming or countermeasure characterized by its function related to preventing electromagnetic interference in petrol station, hospital, plane or cinema
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04K—SECRET COMMUNICATION; JAMMING OF COMMUNICATION
- H04K3/00—Jamming of communication; Counter-measures
- H04K3/80—Jamming or countermeasure characterized by its function
- H04K3/90—Jamming or countermeasure characterized by its function related to allowing or preventing navigation or positioning, e.g. GPS
Abstract
The invention discloses a kind of comprehensive interference systems of unmanned plane, are related to wireless navigation field of communication technology.Including Anneta module, navigation satellite curve generation module, 2.4G and 5.8G frequency band digital power throttle signal generation module；Firstly, carrying out navigation Deceiving interference to the unmanned plane that will be invaded in this shield by navigation satellite curve generation module, cooperation omnidirectional interference Anneta module is used.It is interfered secondly, passing wireless signal to no-manned machine distant control and figure by 2.4G and 5.8G frequency band digital power throttle signal generation module using digital power compacting, cooperation omnidirectional interference Anneta module uses.Comprehensive, real-time, unattended interference function is completed, it is the same which is similar to shield, in 360 ° of target installation point horizontal direction, horizontal force distance radius 1:10 and 30 ° of vertical direction pitching, the disposition system of perpendicular acting distance 1:5.
Description
Technical field
The present invention relates to wireless navigation field of communication technology more particularly to a kind of comprehensive interference systems of unmanned plane.
Background technique
Unmanned plane, no matter in appearance or aspect of performance fast development, was increasingly navigated in recent years as consumer level commodity
Mould fan's pursues, and is also end of appearing in the newspapers repeatly by the accident that unmanned plane causes still, more has external related report about terror point
Son is occurred using the news that unmanned plane carry bomb besieges government bodies and related military fortress.In face of the unmanned plane of " stirring up trouble "
Event, its cruelty development could effectively be inhibited by having only rationally to take counterattacking measure and improve relevant laws and regulations.
It is formed currently, unmanned plane jamming equipment mainly suppresses cooperation directional aerial with power, and most equipment need
First discovery unmanned plane reuses jamming equipment and expels or capture after, and efficiency is extremely low, and collects in face of extensive unmanned plane bee colony
When body besieges, just seem helpless.
Summary of the invention
The purpose of the present invention is to provide a kind of comprehensive interference systems of unmanned plane, to solve existing in the prior art
Foregoing problems.
To achieve the goals above, The technical solution adopted by the invention is as follows:
A kind of comprehensive interference system of unmanned plane, including Anneta module, navigation satellite curve generation module, 2.4G with
5.8G frequency band digital power throttle signal generation module；
The navigation satellite signal curve generation module generates navigation satellite deception letter using satellite signal simulator
Number；
The 2.4G and 5.8G frequency band digital power throttle signal generation module are for generating 2.4G and 5.8G frequency band digital
Power throttle signal；
The Anneta module uses the form of antenna array, is sequentially divided into four layers from top to bottom, first layer is fixed for satellite-signal
To receiving antenna, the ephemeris for the satellite signal simulator updates；The second layer is navigation satellite curve theaomni-directional transmission
Antenna, the transmitting for navigation satellite curve；Third layer is 5.8G frequency band digital power throttle signal transmitting antenna, by 6
A identical orientation antenna is circumferentially symmetrical, and each antenna mounting surface tilts 12.5 ° of angles, forms omnidirectional antenna array, is used for
The transmitting of 5.8G frequency band digital power throttle signal；4th layer is 2.4G frequency band digital power throttle signal transmitting antenna, by 6
Identical orientation antenna is circumferentially symmetrical, and each antenna mounting surface tilts 12.5 ° of angles, forms omnidirectional antenna array, is used for 2.4G
The transmitting of frequency band digital power throttle signal.
Preferably, the navigation satellite curve generates in accordance with the following steps:
When A1, position that satellite signal simulator determines receiver and receiver are to the reception of navigation satellite curve
Between；
A2 extrapolates the transmitting satellite of navigation satellite curve according to almanac data；
A3 calculates its accurate location according to the almanac data of transmitting satellite, and then calculates each transmitting satellite and connect
The distance of receipts machine obtains the propagation delay that navigation satellite curve reaches receiver；
A4 subtracts propagation delay using the receiving time of navigation satellite curve, obtains navigation satellite curve
Emission time；
A5 obtains the navigation message at the moment and the initial phase of satellite signal carrier, pseudo-code according to signal emission time
Position；
A6, satellite signal simulator calculates primary transmitting satellite at a distance from receiver at regular intervals, with front and back two
Secondary obtained range difference obtains the speed of related movement of transmitting satellite and receiver divided by the time interval, and then obtains satellite
The Doppler frequency shift of signal carrier and pseudo-code；
A7, foundation emit initial phase, carrier wave and the puppet of the asterisk of satellite, navigation message, satellite signal carrier and pseudo-code
The Doppler frequency shift of code generates navigation satellite curve according to the following formula:
Wherein,
In formula,Indicate the radiofrequency signal for the jth satellite that receiver receives, t is the signal time of reception, with GPS system
The system time indicates；Aj(t) amplitude of the jth satellite-signal received for receiver； Respectively represent the Pseudo-Random Noise Code and numeric data code of signal；Cause for ionosphere
Satellite-signal time delay, due to the effect of dispersion in ionosphere, its influence to carrier phase and code phase is equal in magnitude, symbol phase
Instead；For signal overall delay caused by the other factors in addition to ionosphere；Δfj(t) carrier frequency that Doppler effect generates is indicated
Offset；Represent carrier phase error；And φj0Respectively indicate phase noise and the clock drift of satellite atomic clock；n
(t) thermal noise received for receiver；RjFor GPS satellite antenna phase center to the geometric distance of GPS receiver antenna；C is
The light velocity,For the space time delay of signal；For Satellite clock errors；The error introduced for troposphere.
Preferably, the 2.4G and 5.8G frequency band digital power throttle signal generates in accordance with the following steps:
B1, FPGA generate M sequence: y=x21+x13+x5+x2；And M sequence is generated into pseudo-random sequence as output signal
Data；
B2, by the time stepping of carrier wave in the bandwidth of ARM setting signal, signal；
The data of generation are obtained the baseband interference signal of required bandwidth by low-pass filter by B3；B4 chooses M sequence
Several bits of middle shift register are multiplied the carrier frequency jumped with modulated carrier frequencies stepping；
Baseband interference signal after low-pass filtering is multiplied with jump carrier frequency and is modulated, obtains broadband interference by B5
Signal.
Preferably, it after 2.4G the or 5.8G frequency band digital power throttle signal generates, is exported, is passed through in the form of broadband
After centimetre device, in the power amplifier in parallel into two, the signal exported from each power amplifier passes through a radio frequency one
After dividing three centimeters of devices, it is respectively transmitted in three different directional aerials.
Preferably, the navigation satellite curve omnidirectional transmitter antenna uses common omnidirectional microstrip antenna, work frequency
Section is GPS L1/BD2 B1/GLONASS L1 frequency point；Antenna gain >=-4.7dbi (pitch angle≤30 °), antenna standing wave ratio≤
2.0；Output impedance is 50 Ω.
Preferably, the working frequency range of the 2.4G frequency band digital power throttle signal transmitting antenna is 2400MHz-
2500MHz frequency point, antenna gain >=9.8dbi (pitch angle=0 °), antenna standing wave ratio≤2.0, output impedance are 50 Ω.
Preferably, the working frequency range of the 5.8G frequency band digital power throttle signal transmitting antenna is 5725MHz-
5800MHz frequency point, antenna gain >=10.5dbi (pitch angle=0 °), antenna standing wave ratio≤2.0, output impedance are 50 Ω.
Preferably, the Anneta module is shield shape, including main body and column, and the column is located at the main body
In inner cavity, 6 directional aerials of the 5.8G frequency band digital power throttle signal transmitting antenna are evenly arranged on the body outer wall
On six faces, 6 directional aerials of the 2.4G frequency band digital power throttle signal transmitting antenna are evenly arranged on the body outer wall
Six faces on, the navigation satellite curve omnidirectional transmitter antenna is located at the top of the column, and the satellite-signal is fixed
It is located at the top of the column to receiving antenna.
The beneficial effects of the present invention are: the comprehensive interference system of unmanned plane provided by the invention, including Anneta module, navigation
Satellite curve generation module, 2.4G and 5.8G frequency band digital power throttle signal generation module；Firstly, passing through navigation satellite
Curve generation module carries out navigation Deceiving interference to the unmanned plane that will be invaded in this shield, and cooperation omnidirectional interferes day
Wire module uses.Secondly, being passed by 2.4G and 5.8G frequency band digital power throttle signal generation module to no-manned machine distant control and figure
Wireless signal is used using digital power compacting interference, cooperation omnidirectional interference Anneta module.It, can be complete by the above two o'clock measure
At comprehensive, real-time, unattended interference function, the system is the same similar to shield, in target installation point horizontal direction
360 °, horizontal force distance radius 1:10 (remote controler is apart from aircraft and interference source apart from the ratio between plane distance) and vertical direction
30 ° of pitching, the disposition system of perpendicular acting distance 1:5 can be widely applied to important place defense and its related fields, packet
Include government bodies' unit, military fortress and more sensitive similar to oil plant, gas station etc. and easily invaded by slow small micro- unmanned plane
The relevant range disturbed.
Detailed description of the invention
Fig. 1 is that baseband interference signal generates flow chart；
Fig. 2 is M sequence spectrogram；
Fig. 3 is that M sequence data pass through low-pass filter spectrogram；
Fig. 4 is 2.4G band interference signal hardware design schematic diagram；
Fig. 5 is 5.8G band interference signal hardware design schematic diagram；
Fig. 6 is that interference signal is exported to the schematic diagram of antenna surface；
Fig. 7 is composed structure schematic diagram inside Anneta module；
Fig. 8 is Anneta module material object display figure one；
Fig. 9 is Anneta module material object display figure two.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, below in conjunction with attached drawing, to the present invention into
Row is further described.It should be appreciated that the specific embodiments described herein are only used to explain the present invention, it is not used to
Limit the present invention.
The embodiment of the invention provides a kind of comprehensive interference systems of unmanned plane, including Anneta module, navigation satellite to cheat
Signal generator module, 2.4G and 5.8G frequency band digital power throttle signal generation module；
The navigation satellite signal curve generation module generates navigation satellite deception letter using satellite signal simulator
Number；
The 2.4G and 5.8G frequency band digital power throttle signal generation module are for generating 2.4G and 5.8G frequency band digital
Power throttle signal；
The Anneta module uses the form of antenna array, is sequentially divided into four layers from top to bottom, first layer is fixed for satellite-signal
To receiving antenna, the ephemeris for the satellite signal simulator updates；The second layer is navigation satellite curve theaomni-directional transmission
Antenna, the transmitting for navigation satellite curve；Third layer is 5.8G frequency band digital power throttle signal transmitting antenna, by 6
A identical orientation antenna is circumferentially symmetrical, and each antenna mounting surface tilts 12.5 ° of angles, forms omnidirectional antenna array, is used for
The transmitting of 5.8G frequency band digital power throttle signal；4th layer is 2.4G frequency band digital power throttle signal transmitting antenna, by 6
Identical orientation antenna is circumferentially symmetrical, and each antenna mounting surface tilts 12.5 ° of angles, forms omnidirectional antenna array, is used for 2.4G
The transmitting of frequency band digital power throttle signal.
In use, navigation satellite curve generation module block generates navigation satellite using satellite signal simulator
Curve carries out navigation Deceiving interference to the unmanned plane that will be invaded in this shield, and cooperation omnidirectional interferes Anneta module
It uses.
In addition, 2.4G and 5.8G frequency band digital power throttle signal generation module generate 2.4G and 5.8G frequency band digital power
Throttle signal passes wireless signal using digital power compacting interference to no-manned machine distant control and figure, and cooperation omnidirectional interferes antenna mould
Block uses.
By the above two o'clock measure, achievable comprehensive, real-time, unattended interference function.
Wherein, the navigation satellite curve generates in accordance with the following steps:
When A1, position that satellite signal simulator determines receiver and receiver are to the reception of navigation satellite curve
Between；
A2 extrapolates the transmitting satellite of navigation satellite curve according to almanac data；
A3 calculates its accurate location according to the almanac data of transmitting satellite, and then calculates each transmitting satellite and connect
The distance of receipts machine obtains the propagation delay that navigation satellite curve reaches receiver；
A4 subtracts propagation delay using the receiving time of navigation satellite curve, obtains navigation satellite curve
Emission time；
A5 obtains the navigation message at the moment and the initial phase of satellite signal carrier, pseudo-code according to signal emission time
Position；
A6, satellite signal simulator calculates primary transmitting satellite at a distance from receiver at regular intervals, with front and back two
Secondary obtained range difference obtains the speed of related movement of transmitting satellite and receiver divided by the time interval, and then obtains satellite
The Doppler frequency shift of signal carrier and pseudo-code；
A7, foundation emit initial phase, carrier wave and the puppet of the asterisk of satellite, navigation message, satellite signal carrier and pseudo-code
The Doppler frequency shift of code generates navigation satellite curve according to the following formula:
Wherein,
In formula,Indicate the radiofrequency signal for the jth satellite that receiver receives, t is the signal time of reception, with GPS system
The system time indicates；Aj(t) amplitude of the jth satellite-signal received for receiver； Respectively represent the Pseudo-Random Noise Code and numeric data code of signal；For electricity
Satellite-signal time delay caused by absciss layer, due to the effect of dispersion in ionosphere, its influence size phase to carrier phase and code phase
Deng symbol is opposite；For signal overall delay caused by the other factors in addition to ionosphere；Δfj(t) indicate that Doppler effect generates
Carrier frequency shift；Represent carrier phase error；And φj0Respectively indicate the phase noise of satellite atomic clock
It is floated with clock；N (t) is the thermal noise that receiver receives；RjFor GPS satellite antenna phase center to the geometry of GPS receiver antenna
Distance；C is the light velocity,For the space time delay of signal；For Satellite clock errors；The error introduced for troposphere.
Specifically, with the generation of the generation summary navigation curve of GPS-L1 satellite-signal.
If jth GPS satellite is in tiThe signal of moment (GPS system time) transmitting are as follows:
In formula, AjIndicate the amplitude of transmitting signal；Cj(ti) indicate satellite launch Pseudo-Random Noise Code C/A code；Dj(ti)
Indicate the navigation message modulated on signal, i.e. numeric data code；For spreading code, fL1Indicate L1 carrier frequency
Rate (1575.42MHz)；Indicate the first phase of L1 carrier signal.
Jth satellite emission signal passes through spatial, finally reaches GPS receiving antenna.Signal has space propagation delay,
And signal is changed.These variations mainly include: satellite clock correction, signal pass through delay (ionosphere caused by atmosphere
Delay and troposphere delay), the frequency shift (FS) that there is Doppler effect to generate, the shadow generated by relativistic effect and earth rotation
Ring, thermal noise equal error influences, furthermore receiver antenna will receive when receiving signal different degrees of multipath interference and
Electromagnetic interference.The signal can indicate are as follows:
Wherein,
In formula,Indicate the radiofrequency signal for the jth satellite that receiver receives, t is the signal time of reception, with GPS system
The system time indicates；Aj(t) amplitude of the jth satellite-signal received for receiver； Respectively represent the Pseudo-Random Noise Code and numeric data code of signal；To be defended caused by ionosphere
Star signal time delay, due to the effect of dispersion in ionosphere, its influence to carrier phase and code phase is equal in magnitude, and symbol is opposite；For signal overall delay caused by the other factors in addition to ionosphere；Δfj(t) carrier frequency for indicating that Doppler effect generates is inclined
It moves；Represent carrier phase error；WithIndicate phase noise and the clock drift of satellite atomic clock；N (t) is to receive
The thermal noise that machine receives.RjFor GPS satellite antenna phase center to the geometric distance of GPS receiver antenna；C is the light velocity,I.e.
The space time delay of signal；For Satellite clock errors；The error introduced for troposphere.
In satellite signal simulator, since the parallel generation of signal is based on clock source, therefore signalWithIt is completely the same.Doppler frequency shift can indicate are as follows:
WhereinIt is receiver and the relative velocity vector of user,Indicate that receiver is directed toward the Unit Vector of the straight line of satellite
Amount, soSatellite receiver user has been obtained in radial relative velocity size.
Simulator generates intermediate-freuqncy signal first, then obtains radiofrequency signal by up-conversion, the letter of the process and receiver
Number processing is opposite.The intermediate-freuqncy signal that simulator generates is made of I, Q two-way, signal expression are as follows:
In formulaωLOFor the local frequency of up-converter circuit,Indicate the road intermediate frequency I letter
Number；Indicate the road intermediate frequency I signal；AjIndicate the amplitude of transmitting signal；Indicate the puppet of satellite launch
Pseudonoise code C/A code；Indicate the navigation message modulated on signal, i.e. numeric data code；cos(ωIFIt t) is expansion
Frequency code；sin(ωIFIt t) is spreading code.
Up-converter circuit use quadrature up-conversion form, intermediate frequency I, Q two paths of signals respectively with orthogonal carrier multiplication, then
Subtract each other, obtains radiofrequency signal.
Assuming that signal simulator generates N GPS satellite signal simultaneously, then have
Satellite signal simulator simulation is the satellite-signal for reaching receiver antenna end, so Satellite Simulation signal is root
It is generated according to the time for reaching receiver antenna end.It has been determined that the position of receiving time and receiver can be according to satellite
Almanac data, which extrapolates receiver, can receive the signal of which satellite, and simulator only generates the signal of this several satellites.So
The accurate location of visible star is calculated according to almanac data afterwards, and then calculates each visible star at a distance from receiver, is obtained
The propagation delay of satellite-signal arrival receiver.It is exactly signal emission time that signal reception time, which subtracts propagation delay,.Obviously not
It is different with the signal propagation delay of satellite, so reaching each satellite-signal of receiver in synchronization must be when different
Carve sending.According to the telegraph text content at the signal emission time available moment and satellite signal carrier, pseudo-code it is initial
Phase.Simulator calculates a satellite at a distance from receiver at regular intervals (20ms), the distance obtained twice with front and back
Difference has just obtained the speed of related movement of satellite and receiver divided by the time interval, and then obtains Doppler's frequency of satellite-signal
It moves.There are the initial phase of the asterisk of visible satellite, navigation message, carrier wave and pseudo-code, the Doppler frequency shift of carrier wave and pseudo-code, root
Institute's satellite-signal to be simulated can be generated according to formula (2).
As shown in Figs. 1-5, the 2.4G and 5.8G frequency band digital power throttle signal generates in accordance with the following steps:
B1, FPGA generate M sequence: y=x21+x13+x5+x2；And M sequence is generated into pseudo-random sequence as output signal
Data；
B2, by the time stepping of carrier wave in the bandwidth of ARM setting signal, signal；
The data of generation are obtained the baseband interference signal of required bandwidth by low-pass filter by B3；
B4 chooses several bits of loads jumped that are multiplied with modulated carrier frequencies stepping of shift register in M sequence
Wave frequency rate；
Baseband interference signal after low-pass filtering is multiplied with jump carrier frequency and is modulated, obtains broadband interference by B5
Signal.
As shown in fig. 6, exported in the form of broadband after 2.4G the or 5.8G frequency band digital power throttle signal generates,
After centimetre device, in the power amplifier in parallel into two, the signal exported from each power amplifier is penetrated by one
Frequently it after one point of three centimeters of device, is respectively transmitted in three different directional aerials.
The navigation satellite curve omnidirectional transmitter antenna uses common omnidirectional microstrip antenna, working frequency range GPS
L1/BD2 B1/GLONASS L1 frequency point；Antenna gain >=-4.7dbi (pitch angle≤30 °), antenna standing wave ratio≤2.0；Output
Impedance is 50 Ω.
Antenna measurement result is as shown in the table:
| Frequency (MHz) | Efficiency (%) | Gain (dBi) |
| 1560 | 69.8711 | 4.79212 |
| 1564 | 72.0226 | 4.80492 |
| 1568 | 76.0084 | 5.35076 |
| 1572 | 79.6673 | 5.49657 |
| 1576 | 84.137 | 5.7443 |
| 1580 | 86.5137 | 5.58233 |
| 1584 | 88.5913 | 5.59423 |
| 1588 | 92.4459 | 561984 |
| 1592 | 94.477 | 5.30713 |
| 1596 | 97.4624 | 5.7078 |
| 1600 | 95.007 | 5.64358 |
| 1604 | 95.1785 | 6.00554 |
| 1608 | 93.9942 | 5.82187 |
| 1612 | 94.2201 | 5.83832 |
The working frequency range of the 2.4G frequency band digital power throttle signal transmitting antenna is 2400MHz-2500MHz frequency point,
Antenna gain >=9.8dbi (pitch angle=0 °), antenna standing wave ratio≤2.0, output impedance are 50 Ω.
It is tested by standard microwave darkroom, 6 interference antenna surfaces of 2.4G frequency range fully meet design requirement, with one of them
For face, test result is as follows shown in table:
According to Principle of Communication electromagnetic wave in free space loss formula are as follows:
Los (dB)=32.45+20LgF (MHz)+20LgD (km)
In formula
D --- operating distance；
F --- working frequency；
Interference signal reaches the signal strength P of disturbed equipment after being issued by interference source are as follows:
P=p1+w+g-los
In formula
P1 --- analog signal output intensity；
W --- power amplifier gain；
G --- antenna gain；
In the case that circuit board simulates signal output intensity and power amplifier gain is constant, increasing antenna gain be can be improved
Interference signal reaches the signal strength of disturbed equipment, further enhances the interference effect to disturbed equipment.
The working frequency range of the 5.8G frequency band digital power throttle signal transmitting antenna is 5725MHz-5800MHz frequency point,
Antenna gain >=10.5dbi (pitch angle=0 °), antenna standing wave ratio≤2.0, output impedance are 50 Ω.
It is tested by standard microwave darkroom, 6 interference antenna surfaces of 5.8G frequency range fully meet design requirement, in wherein one
For a face, it is shown that test result is as follows:
As Figure 7-9, the Anneta module is shield shape, including main body and column, the column are located at the master
In the inner cavity of body, 6 directional aerials of the 5.8G frequency band digital power throttle signal transmitting antenna are evenly arranged on outside the main body
On six faces of wall, 6 directional aerials of the 2.4G frequency band digital power throttle signal transmitting antenna are evenly arranged on the main body
On six faces of outer wall, the navigation satellite curve omnidirectional transmitter antenna is located at the top of the column, the satellite letter
Number directional receiving antenna is located at the top of the column.
By using above-mentioned technical proposal disclosed by the invention, following beneficial effect has been obtained: nothing provided by the invention
Man-machine comprehensive interference system, including Anneta module, navigation satellite curve generation module, 2.4G and 5.8G frequency band digital function
Rate throttle signal generation module；Firstly, by navigation satellite curve generation module to the nothing that will be invaded in this shield
Man-machine to carry out navigation Deceiving interference, cooperation omnidirectional interference Anneta module uses.Secondly, passing through 2.4G and 5.8G frequency band digital function
Rate throttle signal generation module passes wireless signal using digital power compacting interference to no-manned machine distant control and figure, and cooperation omnidirectional is dry
Disturb Anneta module use.By the above two o'clock measure, achievable comprehensive, real-time, unattended interference function, the system class
It is the same to be similar to shield, in 360 ° of target installation point horizontal direction, horizontal force distance radius 1:10 (remote controler apart from aircraft with
Interference source is apart from the ratio between plane distance) and 30 ° of vertical direction pitching, the disposition system of perpendicular acting distance 1:5 can
To be widely used in important place defense and its related fields, including government bodies' unit, military fortress and be similar to oil plant plus
Petrol station etc. is more sensitive and easily by the relevant range of slow small micro- unmanned plane invasion.
The above is only a preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
Depending on protection scope of the present invention.
Claims (8)
1. a kind of comprehensive interference system of unmanned plane, which is characterized in that generate mould including Anneta module, navigation satellite curve
Block, 2.4G and 5.8G frequency band digital power throttle signal generation module；
The navigation satellite signal curve generation module generates navigation satellite curve using satellite signal simulator；
The 2.4G and 5.8G frequency band digital power throttle signal generation module are for generating 2.4G and 5.8G frequency band digital power
Throttle signal；
The Anneta module uses the form of antenna array, is sequentially divided into four layers from top to bottom, first layer is that satellite-signal orientation connects
Antenna is received, the ephemeris for the satellite signal simulator updates；The second layer is navigation satellite curve omnidirectional transmitter antenna,
Transmitting for navigation satellite curve；Third layer is 5.8G frequency band digital power throttle signal transmitting antenna, identical by 6
Directional aerial is circumferentially symmetrical, and each antenna mounting surface tilts 12.5 ° of angles, forms omnidirectional antenna array, is used for 5.8G frequency range
The transmitting of digital power throttle signal；4th layer is 2.4G frequency band digital power throttle signal transmitting antenna, by 6 identical orientations
Antenna is circumferentially symmetrical, and each antenna mounting surface tilts 12.5 ° of angles, forms omnidirectional antenna array, is used for 2.4G frequency band digital
The transmitting of power throttle signal.
2. the comprehensive interference system of unmanned plane as described in claim 1, which is characterized in that the navigation satellite curve is pressed
It is generated according to following steps:
A1, position that satellite signal simulator determines receiver and receiver are to the receiving time of navigation satellite curve；
A2 extrapolates the transmitting satellite of navigation satellite curve according to almanac data；
A3 calculates its accurate location according to the almanac data of transmitting satellite, and then calculates each transmitting satellite and receiver
Distance, obtain navigation satellite curve reach receiver propagation delay；
A4 subtracts propagation delay using the receiving time of navigation satellite curve, obtains the transmitting of navigation satellite curve
Moment；
A5 obtains the navigation message at the moment and the initial phase of satellite signal carrier, pseudo-code according to signal emission time；
A6, satellite signal simulator calculate primary transmitting satellite at a distance from receiver at regular intervals, are obtained twice with front and back
The range difference arrived obtains the speed of related movement of transmitting satellite and receiver divided by the time interval, and then obtains satellite-signal
The Doppler frequency shift of carrier wave and pseudo-code；
A7, according to the initial phase of the asterisk of transmitting satellite, navigation message, satellite signal carrier and pseudo-code, carrier wave and pseudo-code
Doppler frequency shift generates navigation satellite curve according to the following formula:
Wherein,
In formula,Indicate the radiofrequency signal for the jth satellite that receiver receives, t is the signal time of reception, when with GPS system
Between indicate；Aj(t) amplitude of the jth satellite-signal received for receiver； Respectively represent the Pseudo-Random Noise Code and numeric data code of signal；Cause for ionosphere
Satellite-signal time delay, due to the effect of dispersion in ionosphere, its influence to carrier phase and code phase is equal in magnitude, symbol phase
Instead；For signal overall delay caused by the other factors in addition to ionosphere；Δfj(t) carrier frequency that Doppler effect generates is indicated
Offset；Represent carrier phase error；And φj0Respectively indicate phase noise and the clock drift of satellite atomic clock；n
(t) thermal noise received for receiver；RjFor GPS satellite antenna phase center to the geometric distance of GPS receiver antenna；C is
The light velocity,For the space time delay of signal；For Satellite clock errors；The error introduced for troposphere.
3. the comprehensive interference system of unmanned plane as described in claim 1, which is characterized in that the 2.4G and 5.8G frequency band digital
Power throttle signal generates in accordance with the following steps:
B1, FPGA generate M sequence: y=x21+x13+x5+x2；And M sequence is generated into pseudo-random sequence as the number of output signal
According to；
B2, by the time stepping of carrier wave in the bandwidth of ARM setting signal, signal；
The data of generation are obtained the baseband interference signal of required bandwidth by low-pass filter by B3；B4 chooses in M sequence and moves
Several bits of bit register are multiplied the carrier frequency jumped with modulated carrier frequencies stepping；
Baseband interference signal after low-pass filtering is multiplied with jump carrier frequency and is modulated, obtains wideband interferer signal by B5.
4. the comprehensive interference system of unmanned plane as described in claim 3, which is characterized in that 2.4G the or 5.8G band number
After word power throttle signal generates, exported in the form of broadband, after centimetre device, the power amplifier in parallel into two
In, the signal exported from each power amplifier after a radio frequency one divides three centimeters of devices, be respectively transmitted to three it is different
In directional aerial.
5. the comprehensive interference system of unmanned plane as described in claim 1, which is characterized in that the navigation satellite curve is complete
Common omnidirectional microstrip antenna is used to transmitting antenna, working frequency range is GPS L1/BD2 B1/GLONASS L1 frequency point；Antenna
Gain >=-4.7dbi (pitch angle≤30 °), antenna standing wave ratio≤2.0；Output impedance is 50 Ω.
6. the comprehensive interference system of unmanned plane as described in claim 1, which is characterized in that the 2.4G frequency band digital power pressure
The working frequency range of signal transmitting antenna processed is 2400MHz-2500MHz frequency point, antenna gain >=9.8dbi (pitch angle=0 °), day
Line standing-wave ratio≤2.0, output impedance are 50 Ω.
7. the comprehensive interference system of unmanned plane as described in claim 1, which is characterized in that the 5.8G frequency band digital power pressure
The working frequency range of signal transmitting antenna processed be 5725MHz-5800MHz frequency point, antenna gain >=10.5dbi (pitch angle=0 °),
Antenna standing wave ratio≤2.0, output impedance are 50 Ω.
8. the comprehensive interference system of unmanned plane as described in claim 1, which is characterized in that the Anneta module is shield
Shape, including main body and column, the column are located in the inner cavity of the main body, the 5.8G frequency band digital power throttle signal hair
6 directional aerials for penetrating antenna are evenly arranged on six faces of the body outer wall, the 2.4G frequency band digital power throttle signal
6 directional aerials of transmitting antenna are evenly arranged on six faces of the body outer wall, navigation satellite curve omnidirectional hair
The top that antenna is located at the column is penetrated, the satellite-signal directional receiving antenna is located at the top of the column.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811493958.3A CN109412744A (en) | 2018-12-07 | 2018-12-07 | A kind of comprehensive interference system of unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811493958.3A CN109412744A (en) | 2018-12-07 | 2018-12-07 | A kind of comprehensive interference system of unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109412744A true CN109412744A (en) | 2019-03-01 |
Family
ID=65457832
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811493958.3A Pending CN109412744A (en) | 2018-12-07 | 2018-12-07 | A kind of comprehensive interference system of unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109412744A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110113130A (en) * | 2019-05-10 | 2019-08-09 | 神御科技(深圳)有限公司 | A method of composite interference is flexibly defined by external command |
| CN111641472A (en) * | 2020-05-07 | 2020-09-08 | 中国电子科技集团公司第十四研究所 | Anti-unmanned aerial vehicle interference equipment based on phased array |
| CN112887051A (en) * | 2021-01-11 | 2021-06-01 | 北京无线电计量测试研究所 | Unmanned aerial vehicle remote control signal interference unit and use method thereof |
| CN113238265A (en) * | 2021-05-10 | 2021-08-10 | 杭州星辰大海科技有限公司 | Unmanned aerial vehicle capturing system and method |
| CN113296137A (en) * | 2020-02-24 | 2021-08-24 | 香港理工大学深圳研究院 | Interferometric deformation monitoring method and device and receiver |
| CN115951374A (en) * | 2023-03-13 | 2023-04-11 | 钛玛科（北京）工业科技有限公司 | Signal interference suppression method |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107607965A (en) * | 2017-08-30 | 2018-01-19 | 桂林电子科技大学 | A kind of black winged Navigation of Pilotless Aircraft deception system and method |
| US20180231667A1 (en) * | 2015-10-19 | 2018-08-16 | Pacific Telecom & Navigation (Shenzhen) Limited | Gnss-r earth surface survey device and method |
-
2018
- 2018-12-07 CN CN201811493958.3A patent/CN109412744A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20180231667A1 (en) * | 2015-10-19 | 2018-08-16 | Pacific Telecom & Navigation (Shenzhen) Limited | Gnss-r earth surface survey device and method |
| CN107607965A (en) * | 2017-08-30 | 2018-01-19 | 桂林电子科技大学 | A kind of black winged Navigation of Pilotless Aircraft deception system and method |
Non-Patent Citations (1)
| Title |
|---|
| 杨勇等: "小型无人机通信干扰器设计", 《河北工业大学学报》 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110113130A (en) * | 2019-05-10 | 2019-08-09 | 神御科技(深圳)有限公司 | A method of composite interference is flexibly defined by external command |
| CN110113130B (en) * | 2019-05-10 | 2021-08-03 | 神御科技(深圳)有限公司 | Method for flexibly defining composite interference through external instruction |
| CN113296137A (en) * | 2020-02-24 | 2021-08-24 | 香港理工大学深圳研究院 | Interferometric deformation monitoring method and device and receiver |
| CN113296137B (en) * | 2020-02-24 | 2023-11-17 | 香港理工大学深圳研究院 | Interference type deformation monitoring method, device and receiver |
| CN111641472A (en) * | 2020-05-07 | 2020-09-08 | 中国电子科技集团公司第十四研究所 | Anti-unmanned aerial vehicle interference equipment based on phased array |
| CN112887051A (en) * | 2021-01-11 | 2021-06-01 | 北京无线电计量测试研究所 | Unmanned aerial vehicle remote control signal interference unit and use method thereof |
| CN113238265A (en) * | 2021-05-10 | 2021-08-10 | 杭州星辰大海科技有限公司 | Unmanned aerial vehicle capturing system and method |
| CN113238265B (en) * | 2021-05-10 | 2024-04-09 | 杭州星辰大海科技有限公司 | Unmanned aerial vehicle capturing system and method |
| CN115951374A (en) * | 2023-03-13 | 2023-04-11 | 钛玛科（北京）工业科技有限公司 | Signal interference suppression method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109412744A (en) | A kind of comprehensive interference system of unmanned plane | |
| Reinisch et al. | Ionospheric sounding in support of over-the-horizon radar | |
| CN101799542B (en) | Passive coherent location radar direction finding system based on Adcock antenna and direction finding method thereof | |
| CN101980048B (en) | Antenna array forming technology-based ground-based radar system for space debris | |
| CN101173985A (en) | Passive radar detection method for detecting low-altitude objective by satellite signal | |
| CN105891815B (en) | A kind of Combined estimator algorithm based on broadcast singal passive location | |
| CN109557518A (en) | ADS-B earth station interference free performance detection method based on gaussian filtering | |
| CN108872971A (en) | A kind of object localization method and device based on the single array of movement | |
| CN111487609A (en) | Multi-frequency continuous wave MIMO array radar system and target parameter estimation method thereof | |
| CN109541564B (en) | ADS-B ground station anti-interference performance detection method based on mean value filtering | |
| Zhang et al. | Efficient signal separation method based on antenna arrays for GNSS meaconing | |
| Gao et al. | Development of distributed aperture coherence-synthetic radar technology | |
| Loke | Sensor synchronization, geolocation and wireless communication in a shipboard opportunistic array | |
| CN104020465A (en) | Outer radiation source radar angle measurement method based on eight-unit small-bore circular array antenna | |
| CN207587954U (en) | A kind of dual-linear polarization antenna feed array component | |
| Schantz | On the origins of rf-based location | |
| CN114167505B (en) | Low ionosphere D layer detection system and method based on Loran very low frequency signal | |
| CN107978840A (en) | A kind of dual-linear polarization antenna feed array component | |
| CN103091685A (en) | Space-time cascade anti-interference device based on inertial navigation processing method thereof | |
| CN111273223A (en) | Passive positioning countermeasure method based on double-antenna time delay | |
| CN107678047A (en) | A kind of position safety protecting method based on pseudo satellite, pseudolite | |
| Arribas et al. | Advances in the theory and implementation of GNSS antenna array receivers | |
| Wang et al. | Measurement and Analysis of Antenna Pattern for MIMO HF Surface Wave Radar | |
| Ghosh et al. | Selective suppression of IRNSS S-band signals for specific applications | |
| Jiang et al. | Distributed Sensitivity and Critical Interference Power Analysis of Multi-Degree-of-Freedom Navigation Interference for Global Navigation Satellite System Array Antennas |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190301 |