CN109425875A - Satellite-signal separating and treating apparatus and method - Google Patents
Satellite-signal separating and treating apparatus and method Download PDFInfo
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- CN109425875A CN109425875A CN201710792191.3A CN201710792191A CN109425875A CN 109425875 A CN109425875 A CN 109425875A CN 201710792191 A CN201710792191 A CN 201710792191A CN 109425875 A CN109425875 A CN 109425875A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/28—Satellite selection
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/35—Constructional details or hardware or software details of the signal processing chain
- G01S19/37—Hardware or software details of the signal processing chain
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Abstract
This application provides a kind of satellite-signal separating and treating apparatus and methods.The satellite-signal separating and treating apparatus includes: aerial array；And processor, wherein, the aerial array includes multiple array elements, and the processor adjusts the shape of the compound direction figure of the multiple array element, to decay to being formed in other satellite-signals simultaneously to forming directive gain in satellite-signal to be separated, so that satellite-signal to be separated be separated.Required bay high number is reduced, and the size and cost of aerial array substantially reduce.
Description
Technical field
This application involves satellite-signal separating and treating apparatus and methods.
Background technique
As Global Satellite Navigation System (GNSS) is widely applied in Military and civil fields, around the navigation pair of GNSS system
Anti- research is also paid attention to increasingly.
Under complicated deceiving jamming scene, need to separate the satellite-signal received, thus to every
Satellite-signal introduces delay and the Doppler of setting respectively all the way.In this way, target can be disturbed on specified position, phase
Than in the direct forwarding without Signal separator, there is higher concealment and controllability.
Disclosed civil signal can carry out Signal separator based on pseudo-code.But for unknown pseudo noise code authorization signal, mesh
It is preceding that there are mainly two types of spatial processing methods to be used for Signal separator.First method utilizes multiple parabola antennas, by adjusting it
Azimuth and pitch angle enable each antenna be directed toward and track a satellite to be separated.Second method is then to utilize aerial array
It forms gain wave beam and is directed at satellite to be separated.Both satellite-signal separation methods all only only account for be separated in the prior art
Satellite-signal comes to information, in this way, in order to realize enough spatial resolutions, the main lobe width of antenna and the main beam of array
The sufficiently narrow requirement to meet spatial resolution need to be reached, this means that biggish antenna aperture and more element number of array.
It is generally necessary to which the parabola antenna of one group of diameter 3m is used to separate multiple navigation satellite signals.In order to reach identical spatial discrimination
Rate, a half-wavelength planar antenna array then at least need a array elements up to a hundred.Both of which has very high hardware cost and reality
Existing complexity.
Summary of the invention
The purpose of the application is to provide a kind of satellite-signal separating and treating apparatus and method, and hardware cost is low, realizes letter
It is single.
According to the one aspect of the application, a kind of satellite-signal separating and treating apparatus is provided, comprising: aerial array；With
And processor, wherein the aerial array includes multiple array elements, and the processor adjusts the compound direction figure of the multiple array element
Shape, to decay to being formed in other satellite-signals simultaneously to forming directive gain in satellite-signal to be separated.
According to the one aspect of the application, a kind of satellite-signal method for separating and processing is provided, comprising: by including multiple
Satellite-signal of the antenna array receiver of array element from multi-satellite adjusts the shape of the compound direction figure of the multiple array element,
To decay to being formed in other satellite-signals simultaneously to forming directive gain in satellite-signal to be separated.
According to presently filed embodiment, when carrying out satellite-signal separation, it is contemplated that all satellite-signals come to letter
Breath is utilized aerial array for the steering vector of all satellites, calculates weighting of the aerial array for satellite-signal to be separated
Vector decays to being formed to forming directive gain, thus will in other satellite-signals simultaneously in satellite-signal to be separated
Satellite-signal to be separated is separated, and required bay high number is reduced, and the size and cost of aerial array substantially reduce.
Detailed description of the invention
Fig. 1 shows a kind of satellite-signal separating and treating apparatus of embodiment according to the application.
Fig. 2 shows the satellite-signal separating and treating apparatus according to the another embodiment of the application.
Fig. 3 show array element arrangement mode and the satellite-signal of a kind of aerial array of embodiment according to the application come
To schematic diagram.
Fig. 4 shows a kind of satellite-signal method for separating and processing of embodiment according to the application, obtained multiple
The schematic diagram of the shape of the compound direction figure of array element.
Specific embodiment
With reference to the accompanying drawings the satellite-signal separating and treating apparatus to disclosed in the present application based on aerial array and method into
Row is described in detail.For simplicity, in the explanation of each embodiment of the application, same or similar device uses same or similar
Appended drawing reference.
First below by taking GPS satellite navigation system as an example, defended from the angle analysis of visible satellite quantity and inter-satellite angle
The spatial distribution characteristic of star.
According to the baseline configuration of GPS, GPS constellation is made of 24 operational satellites, these satellites are located at 6 the earth's core rails
Road plane has 4 satellites in each orbital plane.The GPS relative positioning dispersed enough ensure that Global Subscriber all and have good
Observability.Any position at the earth's surface, it is seen that the quantity of satellite is differed from minimum value 4 to maximum value 11.In addition, usually
Minimum angles between satellite are not less than 10, and in most cases the angle between satellite is all larger than 20 degree.
According to the analysis above to satellite spatial distribution, it can be seen that effective signal separating method should can be with
From at most 11 received, and minimum angle be 10 ° satellite-signal in extract any specified satellite-signal.It considers
The range of sensitivity of general GPS receiver, should be not less than 20dB to 30dB to the decaying of other satellite-signals.Currently available technology
In satellite-signal separation method only only account for the coming to information of satellite-signal to be separated, in this way, day needed for Signal separator
Linear array array number amount depends on the spatial resolution of aerial array, it is necessary to very narrow wave beam is formed by a large amount of bays,
The signal of other satellites of ability effective attenuation.It can according to the relationship of uniform line-array beam major lobe of directional diagram width and element number of array
, to reach 10 ° of main lobe width, it usually needs at least 12 bays.If to satellite-signal come to azimuth
Two-dimensional beam scanning is carried out with pitch angle, then is needed using planar array, the pattern function of general rectangle battle array is two linear battle arrays
The product of pattern function, that is, to reach 10 ° of spatial resolution, at least need 12 × 12 bays.
According to a kind of embodiment of the application, a kind of satellite-signal separating and treating apparatus and method are proposed, packet is passed through
Satellite-signal of the antenna array receiver from multi-satellite for including multiple array elements adjusts the shape of the compound direction figure of multiple array elements
Shape decays to being formed to forming directive gain in other satellite-signals simultaneously in satellite-signal to be separated.In this way, all
Satellite-signal is utilized to information, and the array number amount of required aerial array depends on number of satellites to be separated, and
It is not spatial resolution.
Fig. 1 shows a kind of satellite-signal separating and treating apparatus of embodiment according to the application.As described in Figure 1, it defends
Star signal separation process device 10 includes aerial array 100 and processor 200.Aerial array 100 can be received from M (M > 1)
The satellite-signal of satellite, aerial array 100 further comprises a array element 110 of N (N > 1).Processor 200 can adjust antenna array
The compound direction diagram shape of multiple array elements 110 of column 100, in coming to formation directive gain simultaneously at it for satellite-signal to be separated
His satellite-signal comes to decaying is formed, so that satellite-signal to be separated be separated.
Any one satellite-signal be can choose as satellite-signal to be separated, in this way, only by with M antenna array
The aerial array of member, it will be able to through the above way separate M satellite-signal one by one.Certainly, in order to realize that engineering is answered
The more suitable aerial array arrangement in, the quantity of bay can also be greater than M, for example, M+1, M+2 or M+ can be used
3 bays.In this way, the size and cost of aerial array will substantially reduce.
Fig. 2 shows the satellite-signal separating and treating apparatus according to the another embodiment of the application.As shown in Fig. 2,
Processor 200 includes determining module 210 and computing module 220.Determining module 210 determines that the aerial array defends each
The steering vector of star.Computing module 220 according to steering vector of the aerial array for each satellite calculate aerial array for
The weight vectors of the satellite to be separated, to adjust the shape of the compound direction figure of multiple array elements of aerial array.
According to a kind of embodiment of the application, M satellite-signal is separated by the aerial array with N number of array element,
Array received to signal model can indicate are as follows:
Wherein,
X (t) is the dimension observation data vector of N × 1, the signal that the corresponding array element of every row receives；
sj(t) j-th of satellite-signal is indicated；
aj(j=1 ... M) indicates geometry of the aerial array for the steering vector of j-th of satellite-signal, with aerial array
Configuration is related with the arrival bearing of satellite-signal；
N (t) is that N × 1 ties up noise signal vector, and every row corresponds to the additive white Gaussian noise at its corresponding array element.
By constructing weight vectors to aerial array, to receive signal weighting summation to each array element, antenna array can control
Arrange the gain come to difference to signal, that is, the compound direction diagram shape of multiple array elements.The output signal of array can indicate are as follows:
In order to realize that satellite-signal separates, using all satellite-signals come to information, for satellite to be separated building plus
Weight vector is to sum to array received signal weighting, so that coming to formation directive gain in satellite-signal to be separated simultaneously at it
His satellite-signal comes to decaying is formed, so that satellite-signal to be separated be separated.
Without loss of generality, it is assumed that as satellite-signal to be separated, receiving signal can indicate the satellite of j=1 are as follows:
For satellite j=1 to be separated, the output signal of array when weight vectors are w are as follows:
According to the present embodiment, processor 200 determines aerial array for the steering vector a of each satellitej, according to day
Steering vector a of the linear array for each satellitej, the weight vectors w of multiple array elements of aerial array is calculated, thus exporting
In signal, in satellite-signal s to be separated1(t) come to formed directive gain simultaneously in other satellite-signals sj(t) come to shape
At decaying.In this way, will only include satellite-signal to be separated in output signal, and other satellite-signals have been attenuated to noise component(s)
In.
According to a kind of embodiment of the application, the determining module 210 of processor 200 can be true based on matrix synthetic methods
Aerial array is determined for the steering vector a of each satellitej。
For a specified satellite, the arrival direction of steering vector and satellite-signal, the posture and geometric configuration of array,
The factors such as bay and the imperfection of radio-frequency channel are related.In aerial array after calibration, bay and radio frequency are logical
The non-ideal factor in road can be ignored, and steering vector can be calculated by the relative position of satellite and array at this time.
Fig. 3 shows a kind of battle array of the aerial array of the satellite-signal separating and treating apparatus of embodiment according to the application
First arrangement mode and satellite-signal come to schematic diagram.Assuming that the incident direction vector of a satellite-signal are as follows:
Wherein, θ indicate direction vector array the elevation angle on an x-y plane,Indicate the azimuth between X-axis.To one
As receiver for, it is seen that the direction of satellite is to fasten definition in ENU local coordinate system, the feelings known to aerial array posture
Under condition, the coordinate in incident direction antenna coordinate system can be calculated by the coordinate in ENU coordinate system multiplied by a spin matrix
It arrives.
The geometric configuration of array namely the arrangement mode of bay, can be indicated by matrix:
P=[p1,p2,…pN]T,
Wherein, N is element number of array, pk=[xk,yk,zk]TIndicate position of k-th of the array element in antenna coordinate system.
Then steering vector a of the aerial array for each satellitejIt can indicate are as follows:
WhereinλIndicate the wavelength of the carrier signal of satellite-signal,
Indicate the incident direction vector of jth satellite-signal.
According to a kind of embodiment of the application, the determining module 210 of processor 200 is also based on signal trace method
Determine aerial array for the steering vector a of each satellitej.For example, satellite navigation system usually broadcasts civilian and army simultaneously
With signal, the steering vector of Service Signal can be determined by tracking civil signal based on the method for signal trace.
Compared with based on array synthetic method, the method based on signal trace is without a large amount of prior information and complicated school
Quasi- process, by directly extracting the amplitude and phase of the satellite-signal received, aerial array pair from different array element channels
In the steering vector a of each satellitejIt can indicate are as follows:
Wherein, vjk,φjkRespectively indicate j-th of the satellite-signal S amplitude and carrier wave phase extracted from k-th of array element channel
Position.
It, can be by determining module 210 to received by each of N number of array element array element for each visible satellite
Satellite-signal extracts its amplitude and phase, constitutes steering vector.The determination method of this steering vector do not need satellite direction and
The priori knowledge of array geometry configuration, and all non-ideal factors of array and radio-frequency front-end be included in extraction amplitude and
In phase, be in this way it is self-alignment, it is more convenient effectively.
In the steering vector a for obtaining aerial arrayjAfterwards, the computing module 220 of processor 200 calculates adding for aerial array
Weight vector w adjusts the shape of the compound direction figure of multiple array elements of aerial array, satellite-signal to be separated is separated.
Assuming that statistical iteration between each satellite-signal, and irrelevant with noise, then the output signal y (t) of aerial array
Power can indicate are as follows:
Wherein, PjFor the power of jth road satellite-signal, PnFor the power of noise signal.
Weight vectors w is calculated, so that the gain of satellite-signal to be separated increases, for example, coming for signal to be separated can be enabled
There is directive gain upwards, that is,
wHa1=α1=1.
Meanwhile when calculating weight vectors, other satellite-signals are considered as interference, the pact of decaying is set up at it
Beam,
wHaj=αj(j=2 ..., M).
So that other satellite-signals decay to predetermined threshold αj(j=2 ..., M).Predetermined threshold can be according to receiver
Sensitivity setting, for example, the residual signal level after being weighted synthesis can be enabled at least below receiver sensitivity.
In addition, as can be seen that noise power may be weighted vector from the calculation formula of output signal power
Modulus value amplification, in order to guarantee desired signal specifically enough signal-to-noise ratio, so as to the synthesis of subsequent curve, the structure of weight vectors
Build noise should be made as small as possible namely the modulus value of weight vectors answer it is as small as possible.
Therefore, it according to a kind of embodiment of the application, converts Signal separator problem to following based on Multiple linear constraint
Optimization problem:
Wherein, w indicates weight vectors of the aerial array for the satellite-signal to be separated, aj(j=1 ..., M) it indicates
Steering vector of the aerial array for each satellite, M expression visible satellite sum, i indicate satellite to be separated, αjIndicate decaying
Predetermined threshold, min indicate minimize, s.t. indicate constraint condition.
In this way, according to presently filed embodiment, when carrying out satellite-signal separation, it is contemplated that all satellite-signals come
To information, aerial array is utilized for the steering vector of all satellites, calculates aerial array for satellite-signal to be separated
Weight vectors decay to being formed to forming directive gain in other satellite-signals simultaneously in satellite-signal to be separated, from
And separate satellite-signal to be separated, required bay high number is reduced, and the size and cost of aerial array are significantly
It reduces.
Without loss of generality, satellite i=1 to be separated can be enabled, to solve optimal weighting vector, Ying Caiyong Lagrange multiplier
Method constructs Lagrangian:
Then optimal weighting vector w should meet:
By first equation it can be found that optimal weighting vector can be expressed as aerial array leading for each satellite
Draw the linear combination of vector:
It is updated in latter two constraint equation, λ, μ can be solvedj(j=2 ..., M).Channel syndrome, optimal weighting vector
Following form can be denoted as:
wopt=A (AHA)-1B,
Wherein,
A=[a1,a2,…aM], for the array manifold matrix being made of steering vector of the aerial array for all satellites；
B=[1, α2,…αM]T, for the dimensional vector of M × 1 being made of directive gain and attenuation coefficient.
In this way, the output signal of receiver can indicate are as follows:
Aerial array adding for satellite to be separated is obtained by optimizing to calculate based on above-mentioned satellite gain Multiple linear constraint
Weight vector, it will be able to so that guaranteeing the gain of satellite-signal to be separated, while other satellites in the output signal of aerial array
Signal is weighted the residual signal level after synthesis lower than receiver sensitivity, and noise is also as small as possible, thus receiver
It can be properly received satellite-signal to be separated, and other satellite-signals are considered as interference, and then realize the separation of signal to be separated.
Here, schematically using the satellite of j=1 as satellite to be separated.It is appreciated that satellite to be separated can be
Any one in visible satellite.Usually in practical application, needing to separate all visible satellite signals, based on known
Every satellite steering vector information, above-mentioned optimization problem is solved to each satellite-signal, and swear using the weighting of result
Amount is weighted synthesis to array received signal vector respectively, it can isolates all visible satellite signals one by one.
According to further aspect of the application, it is also proposed that a kind of satellite-signal method for separating and processing, comprising: by including
Satellite-signal of the antenna array receiver of multiple array elements from multi-satellite adjusts the shape of the compound direction figure of multiple array elements,
To decay to being formed in other satellite-signals simultaneously to forming directive gain in satellite-signal to be separated.The satellite-signal point
From processing method further include: determine aerial array for the steering vector of each satellite；According to aerial array for each
The steering vector of satellite calculates aerial array for the weight vectors of the satellite to be separated, adjusts day by the weight vectors
The shape of the compound direction figure of multiple array elements of linear array, in coming to formation directive gain simultaneously at it for satellite-signal to be separated
His satellite-signal decays to formation.
According to a kind of embodiment, the array element quantity of aerial array can be determined according to maximum visible satellite quantity.Wherein,
The aerial array can be according to the satellite-signal to be separated and other satellites for the steering vector of each satellite-signal
The arrangement mode of multiple array elements of the arrival bearing and aerial array of signal determines.Optionally, aerial array is for each
The steering vector of satellite can be by tracking the known signal from satellite to be separated He other satellites, and according to being tracked
Know that the amplitude and phase of signal determine.
According to a kind of embodiment, according to the steering vector for each satellite-signal of aerial array obtained,
Optimized based on satellite-signal gain Multiple linear constraint and calculates aerial array for the weight vectors of satellite to be separated.Wherein, it is based on
Satellite-signal gain Multiple linear constraint optimal conditions include, and calculate weight vectors and make to have to direction and referring to for signal to be separated
To gain, other satellite-signals are decayed to direction signal lower than predetermined threshold, and the modulus value of weight vectors is minimum.
Such as weight vectors can be calculated based on the optimization of following satellite-signal gain Multiple linear constraint:
Wherein, w indicates weight vectors of the aerial array for the satellite-signal to be separated, aj(j=1 ..., M) it indicates
Steering vector of the aerial array for each satellite, M expression visible satellite sum, i indicate satellite to be separated, αjIndicate decaying
Predetermined threshold, min indicate minimize, s.t. indicate constraint condition.
Fig. 4 shows a kind of satellite-signal method for separating and processing of embodiment according to the application, obtained multiple
The schematic diagram of the shape of the compound direction figure of array element.For ease of illustration, it is assumed here that all visible satellite signals are bowed in
The elevation angle is fixed, and azimuth changes on [0 °, 360 °].After carrying out signal separation process, the conjunction of multiple array elements of aerial array
At the shape of directional diagram as shown in figure 4, the solid line on azimuth indicates the arrival bearing of satellite-signal to be separated, on azimuth
Dotted line indicate other satellite-signals come to.As it can be seen that coming in satellite-signal to be separated to formation directive gain, while at other
Satellite-signal comes to decaying is formed, so that satellite-signal to be separated be separated.
Known satellite spatial distribution is utilized present applicant proposes a kind of, satellite-signal separating treatment is carried out based on aerial array
Device and method, the authorization signal unknown for pseudo-code generating mode separate.Furthermore, it is to be understood that according to the application
The satellite-signal separating and treating apparatus and method proposed is also applied for unauthorized signal known to pseudo-code generating mode.
It is described above by reference to illustrative embodiment of the attached drawing to the application.Those skilled in the art should manage
Solution, the purpose that the embodiment above is merely to illustrate that and the example lifted, rather than be used to be limited, it is all in the application
Introduction and claims under made any modification, equivalent replacement etc., should be included in this application claims
In the range of.
Claims (16)
1. a kind of satellite-signal separating and treating apparatus, comprising:
Aerial array；And
Processor,
Wherein, the aerial array includes multiple array elements, and the processor adjusts the shape of the compound direction figure of the multiple array element
Shape decays to being formed to forming directive gain, to separate in other satellite-signals simultaneously in satellite-signal to be separated
State satellite-signal to be separated.
2. device as described in claim 1, wherein the processor includes determining module and computing module,
The determining module determines the aerial array for the steering vector of each satellite；
The computing module calculates aerial array for described according to steering vector of the aerial array for each satellite
The weight vectors of satellite to be separated adjust the shape of the compound direction figure of multiple array elements of aerial array by the weight vectors
Shape decays to being formed to forming directive gain in other satellite-signals simultaneously in satellite-signal to be separated.
3. device as described in claim 1, wherein the array element quantity of the aerial array is true by maximum visible satellite quantity
It is fixed.
4. device as claimed in claim 2, wherein the determining module is according to the satellite-signal to be separated and other satellites
The arrangement mode of multiple array elements of the arrival bearing and aerial array of signal determines the aerial array for each satellite
Steering vector.
5. device as claimed in claim 2, wherein the determining module tracking is from the satellite to be separated and other satellites
Known signal determine the aerial array for each satellite according to the amplitude and phase of the known signal tracked
Steering vector.
6. device as claimed in claim 2, wherein the computing module is according to determining module aerial array obtained
The steering vector for each satellite-signal, the aerial array is calculated based on the optimization of satellite-signal gain Multiple linear constraint
For the weight vectors of the satellite to be separated.
7. device as claimed in claim 6, wherein calculate weight vectors packet based on the optimization of satellite-signal gain Multiple linear constraint
Include: calculate weight vectors make signal to be separated come to direction have directive gain, other satellite-signals come to direction believe
It number decays to lower than predetermined threshold, and the modulus value of weight vectors is minimum.
8. device as claimed in claim 7, wherein it is excellent that the computing module is based on following satellite-signal gain Multiple linear constraint
Change and calculate weight vectors:
minwHw
Wherein, w indicates weight vectors of the aerial array for the satellite-signal to be separated, aj(j=1 ..., M) indicate antenna
Steering vector of the array for each satellite, M expression visible satellite sum, i indicate satellite to be separated, αjIndicate the pre- of decaying
Determine thresholding, min indicates to minimize, and s.t. indicates constraint condition.
9. a kind of satellite-signal method for separating and processing, comprising: defended by the antenna array receiver for including multiple array elements from more
The satellite-signal of star adjusts the shape of the compound direction figure of the multiple array element, refers in satellite-signal to be separated to formation
Come simultaneously in other satellite-signals to decaying is formed, to separate the satellite-signal to be separated to gain.
10. method as claimed in claim 9, comprising: determine the aerial array for the steering vector of each satellite；Root
Aerial array is calculated for the weight vectors of the satellite to be separated according to steering vector of the aerial array for each satellite, is led to
The shape for crossing the compound direction figure of multiple array elements of weight vectors adjustment aerial array, satellite-signal to be separated come to
Directive gain is formed to decay to formation in other satellite-signals simultaneously.
11. method as claimed in claim 9, wherein determine the array element of the aerial array according to maximum visible satellite quantity
Quantity.
12. method as claimed in claim 10, wherein according to the incoming wave of the satellite-signal to be separated and other satellite-signals
The arrangement mode of multiple array elements of direction and aerial array determines the aerial array leading for each satellite-signal
Draw vector.
13. method as claimed in claim 10, wherein known letter of the tracking from the satellite to be separated He other satellites
Number, according to the amplitude and phase of the known signal tracked, determine the aerial array for the steering vector of each satellite.
14. method as claimed in claim 10, wherein according to aerial array obtained for each satellite-signal
Steering vector calculates the aerial array adding for the satellite to be separated based on the optimization of satellite-signal gain Multiple linear constraint
Weight vector.
15. method as claimed in claim 14, wherein calculate weight vectors based on the optimization of satellite-signal gain Multiple linear constraint
Include: calculate weight vectors make signal to be separated come there is directive gain to direction, other satellite-signals carry out Xiang Fangxiang
Signal is decayed to lower than predetermined threshold, and the modulus value of weight vectors is minimum.
16. device as claimed in claim 15, wherein calculate weighting based on the optimization of following satellite-signal gain Multiple linear constraint
Vector:
minwHw
Wherein, w indicates weight vectors of the aerial array for the satellite-signal to be separated, aj(j=1 ..., M) indicate antenna
Steering vector of the array for each satellite, M expression visible satellite sum, i indicate satellite to be separated, αjIndicate the pre- of decaying
Determine thresholding, min indicates to minimize, and s.t. indicates constraint condition.
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| CN112327330A (en) * | 2020-11-02 | 2021-02-05 | 上海瀚讯信息技术股份有限公司 | Immittance platform equipment, satellite navigation countermeasure system and method |
| EP3754380A3 (en) * | 2019-03-07 | 2021-04-07 | John Piper | Method for complete spatial separation of wireless signals |
| WO2022134762A1 (en) * | 2020-12-24 | 2022-06-30 | 深圳大学 | Signal angle and signal frequency estimation method, apparatus and device, and storage medium |
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