CN102638318B - Method applicable to correcting equiamplitude vibration error of aerofoil conformal array - Google Patents
Method applicable to correcting equiamplitude vibration error of aerofoil conformal array Download PDFInfo
- Publication number
- CN102638318B CN102638318B CN201210072711.0A CN201210072711A CN102638318B CN 102638318 B CN102638318 B CN 102638318B CN 201210072711 A CN201210072711 A CN 201210072711A CN 102638318 B CN102638318 B CN 102638318B
- Authority
- CN
- China
- Prior art keywords
- matrix
- represent
- vector
- phase center
- array
- 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.)
- Expired - Fee Related
Links
Images
Abstract
The invention discloses a method applicable to correcting equiamplitude vibration error of an aerofoil conformal array, which mainly solves the problems of time varying and 2pi fuzziness in the process of correcting equiamplitude vibration error of the aerofoil conformal array. The method includes: firstly, estimating a signal subspace of each moment by supposing the fact that phase center errors of adjacent snapshots are equal; secondly, building estimated cost function of array element position vector according to estimated signal subspaces; thirdly, calculating the cost function by means of Newton iteration method to obtain array position vector of each moment; fourthly, fitting the array position vectors by curve fitting method, and assuming the difference between the fitting value of the array position vectors and the ideal value as phase center errors; and finally, correcting the phase center errors of received data according to the obtained phase center error value. The method applicable to correcting equiamplitude vibration error of the aerofoil conformal array overcomes the problems of time varying and 2pi fuzziness of the phase center errors of the aerofoil conformal array and can be applied to correcting equiamplitude vibration error of the aerofoil conformal array.
Description
Technical field
The invention belongs to signal process field, relate to the phase center error calibration method of even linear array, can be used for the correction of the phase center error that the conformal array antenna of wing causes due to continuous vibration in aircraft flight process.
Background technology
Aircraft is in the middle of flight course, and wing and air-flow interact and can produce chatter phenomenon, and in the time that speed reaches a certain specific threshold, the amplitude of the flutter of aerofoil being caused by disturbance just remains unchanged, and claims that this speed is flutter speed.Generally, think that now the zitterbewegung of wing is simple harmonic oscillation.Change because the continuous vibration of wing causes with it conformal array antenna phase center, thereby produced phase center error.
The phase center error that wing continuous vibration causes has following characteristics:
1) airfoil variable is larger.Bay is far away apart from wing root, and phase center error is larger, easily causes that 2 π are fuzzy;
2) data dependence variation.Due to flutter of aerofoil, phase center error can slowly change along with the time, thereby caused the correlation variation between sample data.
At present, conventional phase center error calibration method, as add auxiliary array element, add the accurate known information source of direction etc., mainly for the constant situation of error, do not consider that flutter of aerofoil causes the time dependent situation of phase center error, and because airfoil variable is larger, easily cause that 2 π are fuzzy, adopt conventional method phase calibration errors of centration cannot obtain correct result.
Summary of the invention
The object of the invention is to the deficiency for conventional phase center error calibration method, the bearing calibration of the conformal array continuous vibration of a kind of wing phase center error has been proposed, with eliminate 2 π that cause due to flutter of aerofoil fuzzy and time change effect, effectively improve the correction accuracy of phase center error.
The technical scheme that realizes the object of the invention is that the phase center error change feature comparatively slowly first causing for flutter of aerofoil, supposes that the phase center error of adjacent snap is identical, estimates respectively the signal subspace in each moment; Then,, according to the signal subspace of estimating to obtain, adopt the method for subspace fitting to carry out the rough estimate of error; Finally, adopt the method fit error curve of curve, carry out the accurate estimation of error.Specific implementation step is as follows:
(1) suppose that the phase center error of adjacent n snap is identical, n is odd number, utilizes following formula to obtain the k time snap to receive the covariance matrix of data
Wherein, L is fast umber of beats, and x (l) represents the l time sample data, ()
hrepresenting matrix conjugate transpose; According to
estimate the signal subspace in this moment;
(2), according to the signal subspace of estimating to obtain, adopt the method based on subspace fitting to set up the cost function that element position vector is estimated:
Wherein,
represent the estimated value of element position vector, U
srepresent signal subspace,
represent array manifold matrix,
+representing matrix
generalized inverse; Arg () represents to get plural argument,
represent to get the transition formula evaluation minimum that makes in bracket
value, || ||
2represent to get 2 norms;
(3) utilize Newton iteration method to calculate above-mentioned cost function, obtain the element position vector in each moment, realize the rough estimate to phase center error;
(4) adopt curve-fitting method to carry out matching to the element position vector obtaining in step (3), the match value of this element position vector and the difference of ideal value are phase center error, realize the accurate estimation of phase center error;
(5) according to the phase center error of estimating to obtain, carry out the correction of phase center error.
The present invention compared with prior art, has the following advantages:
1) the present invention adopts Newton iteration method direct estimation element position vector, solves the element position vector that obtains and the difference of desirable element position vector and is phase center error, and 2 π that avoided conventional method phase calibration errors of centration to produce are fuzzy;
2) the present invention adopts the method for curve to carry out matching to array element position vector, and the time realization that has reduced phase center error resembles the impact on error correction precision.
Accompanying drawing explanation
Fig. 1 is flow chart of the present invention;
Fig. 2 is the analogous diagram of element position correcting action of the present invention with signal to noise ratio situation of change;
Fig. 3 is the analogous diagram of element position correcting action of the present invention with snap situation of change.
Embodiment
With reference to Fig. 1, performing step of the present invention is as follows:
Step 1 is estimated the signal subspace of each moment data.
(1a) suppose that the phase center error of adjacent n snap is identical, n is odd number, utilizes following formula to obtain the k time snap to receive the covariance matrix of data
Wherein, L is fast umber of beats, and x (l) represents the l time sample data, ()
hrepresenting matrix conjugate transpose;
(1b) covariance matrix to the k time snap reception data
carry out feature decomposition, be decomposed into the multiply accumulating form of characteristic value and characteristic vector, and characteristic value is arranged by order from big to small:
Wherein, M is array number, λ
ifor covariance matrix
characteristic value, v
ibe and eigenvalue λ
icorresponding characteristic vector, i=1,2 ... M; P is information source number,
for white noise power;
(1c) defined feature value λ
1, λ
2..., λ
pthe subspace that characteristic of correspondence vector is opened is signal subspace U
s:
U
s=[v
1,v
2,…,v
P]。<5>
Step 2 adopts subspace fitting method to set up the cost function that element position vector is estimated.
Wherein, x
n, y
nbe respectively n abscissa and the ordinate after array element deformation, n=1,2 ..., M, ()
trepresenting matrix transposition;
(2b), by the following formula of coordinate figure substitution of element position vector, obtain the spatial domain steering vector a (θ of i information source
i):
Wherein, θ
irepresent the arrival bearing of i information source, i=1,2 ..., P, P is information source number τ
n(θ
i)=[sin θ
i, cos θ
i] [x
n, y
n]
t, n=1,2 ..., M, e
()represent the exponential function take natural logrithm e the end of as, ()
trepresenting matrix transposition, λ is carrier wavelength, j represents imaginary unit;
Wherein, ()
trepresenting matrix transposition, θ=[θ
1, θ
2..., θ
p]
trepresent arrival bearing's vector;
(2d) according to array manifold matrix
the cost function that obtains the estimation of element position vector is:
Wherein,
represent the estimated value of element position vector, arg () represents to get plural argument,
represent to get the transition formula evaluation minimum that makes in bracket
value, || ||
2represent to get 2 norms, ()
+represent to ask Generalized Inverse Matrix; I
mrepresent M rank unit matrix, matrix P
awith C be intermediate variable,
w is weight matrix, and Tr () represents to ask matrix trace,
for cost matrix:
Weight matrix W obtains by following formula:
Wherein, ()
2represent squared operation, ()
-1the representing matrix operation of inverting, Λ
sfor intermediate variable, Λ
s=diag (λ
1, λ
2..., λ
p), diag () represents vector to form diagonal matrix,
represent noise power estimation value:
Step 3 utilizes Newton iteration method to calculate element position vector estimate cost function, obtains the element position vector in each moment, realizes the rough estimate to phase center error.
(3a) hypothesis array element initial position vector
for desirable element position vector;
(3b) establishing k is iterations, makes k=0, by array element initial position vector
substitution formula <3>, adopts Newton iterative to calculate the element position vector of the 1st iteration
wherein,
represent the element position vector that the k+1 time iteration obtains,
represent the element position vector that the k time iteration obtains, the step factor that β is iteration,
represent cost matrix
the k time iterative value of second dervative,
represent cost matrix
the k time iterative value of first derivative, ()
-1the representing matrix operation of inverting;
Wherein, Re () represents to get real part operation, ()
trepresenting matrix matrix transpose operation,
for intermediate variable, provided by following formula:
M is array number, ' 0 ' expression null matrix, I
m-1for M-1 rank unit matrix;
B is intermediate variable, obtains by following formula:
Wherein,
i
mrepresent M rank unit matrix, the operation of ' ⊙ ' representing matrix dot product, H
xX, H
xY, H
yX, H
yYfor intermediate variable, obtain by following formula:
()
hrepresenting matrix conjugate transpose,
w is weight matrix;
with
for intermediate variable, provided by following formula respectively:
,<19>
Wherein, f
0represent carrier frequency, c represents the light velocity, and j is imaginary unit, Λ
sinand Λ
cosjust be respectively, cosine diagonal matrix:
Λ
sin=diag([sinθ
1,sinθ
2,…,sinθ
P]
T)
Λ
cos=diag([cosθ
1,cosθ
2,…,cosθ
P]
T)
θ
ibe the arrival bearing of i information source, i=1,2 ..., P, P is number of source, diag () represents vector to form diagonal matrix;
Wherein, vecd () represents that the diagonal element of getting matrix forms column vector;
(3c) make k=k+1, by the k time iterative value of element position vector
substitution formula <3>, the k+1 time iterative value of calculating element position vector
If (3d)
λ
0for carrier wavelength, iteration stopping,
be the element position vector that estimation obtains; Otherwise continue to carry out (3c).
Step 4 adopts curve-fitting method to carry out matching to array element position vector, and the match value of this element position vector and the difference of ideal value are phase center error, realizes the accurate estimation of phase center error.
(4a) establish
represent the element position vector being obtained by the n time snap data estimation:
(4b) make matching vector d be:
d=[1,2,…,L]
T,<23>
If d
irepresent i the element of vector d, i=1,2 ..., L, with three rank fitting of a polynomial error curves, H represents observation matrix, H is:
(4c) establish I
xm, I
ymrepresent abscissa and the ordinate value of m array element error vector,
abscissa and the ordinate value of m the array element error vector that expression matching obtains, m=1,2 ..., M,
Order
Obtain according to curve-fitting method:
Respectively with
with
represent vector
with
n element, m=1,2 ..., M, n=1,2 ..., L; Order
represent to estimate the element position vector of the n time snap of m array element obtaining,
for:
(4d) establish Q
mnbe the element position vector ideal value of the n time snap of m array element, m=1,2 ..., M, n=1,2 ..., L, the n time snap of m array element phase center error estimate be:
(5a) by estimate the n time snap of m array element of obtaining phase center error estimate φ
mnsubstitution formula <19>, obtain the n time snap phase center error vector estimated value Φ
n:
Wherein, m=1,2 ..., M, n=1,2 ..., L, M is array number, L is fast umber of beats;
(5b) according to phase center error vector estimated value Φ
n, the n time fast beat of data x (n) carried out to phase center error correction:
Wherein,
represent the correction result to the n time fast beat of data x (n), diag () represents vector to be formed to diagonal matrix, ()
-1representing matrix is inverted.
Effect of the present invention can be by illustrating the processing of emulated data below:
1 experimental situation and condition
Experimental situation: experiment adopts the half-wavelength uniform line-array that an array number is 8, and linear array is installed along aerofoil surface.
Simulated conditions: wing length is 4.2m, tip largest deformation amount is 0.21m, flutter of aerofoil frequency is 11.14Hz, flutter angle is [0.05rad, 0.05rad], and first phase is 0, radar operation wavelength is 1.2m, pulse repetition frequency is 1400Hz, and far field exists two mutual incoherent echo signals, and its arrival bearing is respectively-20 °, 10 °.
2 experiment contents and result
If I
mnbe the element position vector actual value of the n time snap of m array element, m=1,2 ..., M, n=1,2 ..., L, definition element position correcting action is:
Experiment 1, makes the signal to noise ratio of echo signal change, observes under different signal to noise ratio conditions, and when accurately estimating and accurately estimating, the situation that element position estimated bias changes, simulation result is as shown in Figure 2.Wherein, fast umber of beats is 500.
Experiment 2, the fast umber of beats that order receives data changes, observes under different snap conditions, when accurately estimating and accurately estimating, the situation that element position estimated bias changes, simulation result is as shown in Figure 3.Wherein, signal-to-noise ratio settings is 20dB.
As can be seen from Figure 2, under the lower condition of signal to noise ratio, the effect that adopts the inventive method to carry out phase center estimation error is better than does not carry out the accurately effect of estimation, and along with the raising of signal to noise ratio, the element position estimated bias curve of two kinds of methods overlaps gradually.
As can be seen from Figure 3, under the signal to noise ratio 20dB condition of setting, adopt the inventive method to carry out phase center estimation error and be greater than at 350 o'clock at fast umber of beats in this experiment, element position estimated bias tends towards stability; And the method phase estimation deviation of not carrying out accurately estimation is always larger, cannot reach the object of estimating phase center error, can find out from testing 1 result, while accurately estimation, need to be in the time that signal to noise ratio be greater than 30dB, performance could approach by the inventive method, and this condition is very inaccessible in actual applications.
Claims (4)
1. the conformal array continuous vibration of a wing error calibration method, comprises the steps:
(1) suppose that the phase center error of adjacent n snap is identical, n is odd number, utilizes following formula to obtain the k time snap to receive the covariance matrix of data
Wherein, L is fast umber of beats, and x (l) represents the l time sample data, ()
hrepresenting matrix conjugate transpose;
(2a) covariance matrix to the k time snap reception data
carry out feature decomposition, be decomposed into the multiply accumulating form of characteristic value and characteristic vector, and characteristic value is arranged by order from big to small:
Wherein, M is array number, λ
ifor covariance matrix
characteristic value, v
ibe and eigenvalue λ
icorresponding characteristic vector, i=1,2 ... M; P is information source number,
for white noise power;
(2b) defined feature value λ
1, λ
2..., λ
pthe subspace that characteristic of correspondence vector is opened is signal subspace U
s:
U
S=[v
1,v
2,…,v
P];
(3), according to the signal subspace of estimating to obtain, the method for employing based on subspace fitting set up the cost function of estimation error:
Wherein,
represent the estimated value of element position vector, U
srepresent signal subspace,
represent array manifold matrix,
representing matrix
generalized inverse; Arg () represents to get plural argument,
represent to get the transition formula evaluation minimum that makes in bracket
value, || ||
2represent to get 2 norms;
(4) utilize Newton iteration method to calculate above-mentioned cost function, obtain the element position vector in each moment, realize the rough estimate to phase center error;
(5) adopt curve-fitting method to carry out matching to the element position vector obtaining in step (3), the match value of this element position vector and the difference of ideal value are phase center error, realize the accurate estimation of phase center error;
(6) according to the phase center error of estimating to obtain, carry out the correction of phase center error.
2. the conformal array continuous vibration of wing according to claim 1 error calibration method, wherein the described Newton iteration method of utilizing of step (4) is calculated above-mentioned cost function, carries out as follows:
(4b) establishing k is iterations, makes k=0, by array element initial position vector
substitution formula <3>, adopts Newton iterative to calculate the element position vector of the 1st iteration
Wherein,
represent the element position vector that the k+1 time iteration obtains,
represent the element position vector that the k time iteration obtains, the step factor that β is iteration,
represent cost matrix
the k time iterative value of second dervative,
represent cost matrix
the k time iterative value of first derivative, ()
-1the representing matrix operation of inverting;
Wherein, Re () represents to get real part operation, ()
trepresenting matrix matrix transpose operation,
for intermediate variable, provided by following formula:
M is array number, ' 0' represents null matrix, I
m-1for M-1 rank unit matrix;
B is intermediate variable, obtains by following formula:
Wherein,
i
mrepresent M rank unit matrix, ' the operation of ⊙ ' representing matrix dot product, H
xX, H
xY, H
yX, H
yYfor intermediate variable, obtain by following formula:
()
hrepresenting matrix conjugate transpose,
w is weight matrix;
with
for intermediate variable, provided by following formula respectively:
Wherein, f
0represent carrier frequency, c represents the light velocity, and j is imaginary unit, Λ
sinand Λ
cosjust be respectively, cosine diagonal matrix:
Λ
sin=diag([sinθ
1,sinθ
2,…,sinθ
P]
T)<10>
Λ
cos=diag([cosθ
1,cosθ
2,…,cosθ
P]
T),
θ
ibe the arrival bearing of i information source, i=1,2 ..., P, P is number of source, diag () represents vector to form diagonal matrix;
Wherein, vecd () represents that the diagonal element of getting matrix forms column vector;
(4c) make k=k+1, by the k time iterative value of element position vector
substitution formula <3>, the k+1 time iterative value of calculating element position vector
3. the conformal array continuous vibration of wing according to claim 1 error calibration method, wherein the described employing curve-fitting method of step (5) carries out matching to the element position vector obtaining in step (3), carries out as follows:
(5a) establish
represent the element position vector being obtained by the n time snap data estimation:
(5b) make matching vector d be:
d=[1,2, …,L]
T, <13>
If d
irepresent i the element of vector d, i=1,2 ..., L, with three rank fitting of a polynomial error curves, H represents observation matrix, H is:
(5c) establish I
xm, I
ymrepresent abscissa and the ordinate value of m array element error vector,
abscissa and the ordinate value of m the array element error vector that expression matching obtains, m=1,2 ..., M,
Order
Obtain according to curve-fitting method:
Respectively with
with
represent vector
with
n element, m=1,2, ..., M, n=1,2 ..., L; Order
represent to estimate the element position vector of the n time snap of m array element obtaining,
for:
(5d) establish Q
mnbe the element position vector ideal value of the n time snap of m array element, m=1,2 ..., M, n=1,2 ..., L, the n time snap of m array element phase center error estimate be:
4. the conformal array continuous vibration of wing according to claim 1 error calibration method, wherein the described phase center error obtaining according to estimation of step (5), carries out the correction of phase center error, carries out as follows:
(5a) by estimate the n time snap of m array element of obtaining phase center error estimate φ
mnsubstitution formula <19>, obtain the n time snap phase center error vector estimated value Φ
n:
Wherein, m=1,2 ..., M, n=1,2 ..., L, M is array number, and L is fast umber of beats, and λ is carrier wavelength;
(5b) according to phase center error vector estimated value Φ
n, the n time fast beat of data x (n) carried out to phase center error correction:
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201210072711.0A CN102638318B (en) | 2012-03-19 | 2012-03-19 | Method applicable to correcting equiamplitude vibration error of aerofoil conformal array |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201210072711.0A CN102638318B (en) | 2012-03-19 | 2012-03-19 | Method applicable to correcting equiamplitude vibration error of aerofoil conformal array |
Publications (2)
Publication Number | Publication Date |
---|---|
CN102638318A CN102638318A (en) | 2012-08-15 |
CN102638318B true CN102638318B (en) | 2014-05-14 |
Family
ID=46622575
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201210072711.0A Expired - Fee Related CN102638318B (en) | 2012-03-19 | 2012-03-19 | Method applicable to correcting equiamplitude vibration error of aerofoil conformal array |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN102638318B (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN106772221B (en) * | 2016-12-26 | 2019-04-23 | 西安电子科技大学 | Conformal array amplitude and phase error correction method based on wing deformation fitting |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101349741A (en) * | 2008-08-29 | 2009-01-21 | 西安电子科技大学 | Phased array digital multi-beam forming machine for electron reconnaissance |
CN102262692A (en) * | 2011-06-24 | 2011-11-30 | 中国航空工业集团公司科学技术委员会 | Method for optimizing skins of airplane airfoil by subsonic flutter |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7650253B2 (en) * | 2008-05-08 | 2010-01-19 | L-3 Communications Corporation | Accelerometer and method for error compensation |
CN101950851A (en) * | 2010-06-23 | 2011-01-19 | 电子科技大学 | Staggered MIMO radar array antenna construction method |
CN102142853B (en) * | 2010-12-31 | 2013-09-11 | 中国电子科技集团公司第五十四研究所 | Error matrix compensation method of monopulse tracking receiver system |
CN102269813B (en) * | 2011-06-23 | 2012-11-28 | 中国电子科技集团公司第三十八研究所 | Interference processing technology of airborne non-vertical dual-antenna InSAR system |
-
2012
- 2012-03-19 CN CN201210072711.0A patent/CN102638318B/en not_active Expired - Fee Related
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101349741A (en) * | 2008-08-29 | 2009-01-21 | 西安电子科技大学 | Phased array digital multi-beam forming machine for electron reconnaissance |
CN102262692A (en) * | 2011-06-24 | 2011-11-30 | 中国航空工业集团公司科学技术委员会 | Method for optimizing skins of airplane airfoil by subsonic flutter |
Non-Patent Citations (4)
Title |
---|
吕斌等.机翼低速风洞试验颤振模型优化设计方法.《北京航空航天大学学报》.2006,(第02期),全文. |
张伟伟等.超音速、高超音速机翼的气动弹性计算方法.《西北工业大学学报》.2003,(第06期),全文. |
机翼低速风洞试验颤振模型优化设计方法;吕斌等;《北京航空航天大学学报》;20060330(第02期);全文 * |
超音速、高超音速机翼的气动弹性计算方法;张伟伟等;《西北工业大学学报》;20031230(第06期);全文 * |
Also Published As
Publication number | Publication date |
---|---|
CN102638318A (en) | 2012-08-15 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN101251597B (en) | Method for self-correction of array error of multi-input multi-output radar system | |
CN107179535A (en) | A kind of fidelity based on distortion towed array strengthens the method for Wave beam forming | |
CN104166136A (en) | Interference subspace tracking-based high-efficiency self-adaptive monopulse angle measurement method | |
CN103364772B (en) | Target low elevation estimation method based on real number field generalized multiple-signal sorting algorithm | |
CN103885048A (en) | Bistatic MIMO radar transceiver array amplitude phase error correction method | |
CN109782238B (en) | Combined calibration method for amplitude-phase response and array element position of sensor array element | |
CN103353588B (en) | Two-dimensional DOA (direction of arrival) angle estimation method based on antenna uniform planar array | |
CN104181513B (en) | A kind of bearing calibration of radar antenna element position | |
CN106772221B (en) | Conformal array amplitude and phase error correction method based on wing deformation fitting | |
CN104678372A (en) | Joint estimation method for super-resolution distance value and angle value by using orthogonal frequency division multiplexing radar | |
CN103926555B (en) | A kind of method that utilization not rounded signal measuring antenna array receiver machine width is mutually responded | |
CN104297740A (en) | Method for estimating Doppler spectrum of radar target on basis of phase analysis | |
CN103323815A (en) | Underwater acoustic locating method based on equivalent sound velocity | |
CN106646417A (en) | Iterative maximum likelihood estimation method for generalized Pareto distribution parameter | |
CN104076332A (en) | Estimation method for magnitudes and phases of radar uniform linear array | |
Ding et al. | Super‐resolution 3D imaging in MIMO radar using spectrum estimation theory | |
US20230160991A1 (en) | Method for jointly estimating gain-phase error and direction of arrival (doa) based on unmanned aerial vehicle (uav) array | |
CN103364762A (en) | Estimation method for arriving direction of monostatic MIMO radar based on random array manifolds | |
CN107064893B (en) | Pareto distribution with wide scope method for parameter estimation based on logarithmic moment | |
CN105223554A (en) | Based on the space-time adaptive Monopulse estimation method of Doppler's triple channel Combined Treatment | |
CN102638318B (en) | Method applicable to correcting equiamplitude vibration error of aerofoil conformal array | |
CN104698448B (en) | Conformal array robust angle estimation method based on manifold separation under movement platform | |
CN106054122A (en) | Time domain broadband signal frequency domain closed loop direction-finding method based on digital signal processor | |
CN105242236A (en) | Array element position error correction method in broadband signal super-resolution direction measurement | |
CN108020811A (en) | The 1 dimension uniform linear array direction-finding method based on target source phase shift differential technique |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
C14 | Grant of patent or utility model | ||
GR01 | Patent grant | ||
CF01 | Termination of patent right due to non-payment of annual fee | ||
CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140514 Termination date: 20200319 |