CN108872721A - A kind of in-orbit method for self-calibrating of space array antenna - Google Patents

A kind of in-orbit method for self-calibrating of space array antenna Download PDF

Info

Publication number
CN108872721A
CN108872721A CN201810256741.4A CN201810256741A CN108872721A CN 108872721 A CN108872721 A CN 108872721A CN 201810256741 A CN201810256741 A CN 201810256741A CN 108872721 A CN108872721 A CN 108872721A
Authority
CN
China
Prior art keywords
array element
array
signal
phase
ground
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
Application number
CN201810256741.4A
Other languages
Chinese (zh)
Inventor
杨博
刘宁
胡楚峰
陈卫军
张朋
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Northwestern Polytechnical University
Xian Aisheng Technology Group Co Ltd
Original Assignee
Northwestern Polytechnical University
Xian Aisheng Technology Group Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Northwestern Polytechnical University, Xian Aisheng Technology Group Co Ltd filed Critical Northwestern Polytechnical University
Priority to CN201810256741.4A priority Critical patent/CN108872721A/en
Publication of CN108872721A publication Critical patent/CN108872721A/en
Pending legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
    • G01R29/00—Arrangements for measuring or indicating electric quantities not covered by groups G01R19/00 - G01R27/00
    • G01R29/08—Measuring electromagnetic field characteristics
    • G01R29/10—Radiation diagrams of antennas
    • 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
    • G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
    • G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
    • G01S7/40—Means for monitoring or calibrating
    • G01S7/4004—Means for monitoring or calibrating of parts of a radar system
    • G01S7/4026—Antenna boresight

Landscapes

  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Electromagnetism (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)
  • Radar Systems Or Details Thereof (AREA)

Abstract

The present invention provides a kind of in-orbit method for self-calibrating of space array antenna, and aerial array to be calibrated emits signal to the ground, and receives ground echo；It is related that all adjacent two array element i to the signal that j is received are subjected to conjugation, change the transmitting signal phase delay of each array element at random, the conjugation correlation of the echo-signal of n times pulse is overlapped after the times N of repeatedly setting, and it is average to calculate the time, obtains the phase difference of adjacent two array element i and j；Choosing first array element in aerial array is reference array element, calculates the phase difference of other array elements and reference array element and compensates to each array element.The present invention can carry out in-orbit estimation and calibration to array element phase error in the case where not increasing any optional equipment.

Description

A kind of in-orbit method for self-calibrating of space array antenna
Technical field
The invention belongs to antenna distortion measurements and calibration field, are related to the subjects such as radar, signal processing.
Background technique
Deformation occurs for meeting compared with original design after the in-orbit expansion of space array antenna.Deformation can be by folding and unfolding process It generates；It is also possible to generate due to the influence by factors such as transmitting vibrations；Either in orbit during by long term thermal The influence of effect and generate.Space array antenna increasingly enlargement, the development of lightness keep the influence of space antenna deformation more next Seriously.
The deformation of array antenna will affect the flatness of front, change relative position between array element, so as to cause each array element The unknown variations of signal phase, influence antenna performance, so that antenna gain reduces, minor level deteriorates, and beam position changes Become.Therefore in-orbit calibration must be carried out to array antenna deformation, to eliminate phase change in the control of array element phase delay It influences, realizes the compensation to bay phase.
At present for this problem, used and technology that is studying has：
Ground point target alignment known to 1.
Satellite antenna is surveyed by installing the point targets such as transmitter, receiver or corner reflector in ground known point Amount and calibration.When the scanned ground of satellite antenna, it is measured by transmitting, reception, reflection signal.This method needs Ground system is installed, and waits satellite by can just measure, needs a large amount of artificial and time cost.
2. near field measurement antenna
Near field measurement antenna is an independently installed measurement antenna in satellite platform.Array antenna respectively radiates the phase of array element Position delay can be measured by near field measurement antenna.The shortcomings that this technology is to need independent mechanical support structure, increases volume Outer structure and equipment, improves satellite launch cost.
3. unknown ground target calibration
Measurement and calibration to array antenna can also be realized by reflecting point target naturally using the ground of multiple Location-Unknowns.This The advantages of kind method is not need to install detection calibration equipment on ground, cost of labor is reduced, the disadvantage is that being sometimes difficult to find Suitable nature point target.
4. reflection clutter calibration naturally
Natural reflection point target alignment is found typical reflectance point as benchmark on ground and is measured.Naturally clutter school is reflected The quasi- reflection signal using a large amount of irrelevant scatterers is calibrated.This method utilizes the statistical property pair for reflecting noise signal Array element phase change is estimated.Its principle is, when receiving uniform ground return clutter, adjacent array element receives the correlation of signal The average phase of Data-Statistics is equal to 0.Therefore, any 0 value of being not equal to can mean that the opposite variation of phase between array element.Based on this Kind principle can estimate array element phase.The shortcomings that this method is to need individual transmitting antenna transmitting signal for calibration It uses.
5. wireless beacon method
Different near field measurement antenna method, wireless beacon method installs beacon at the antenna back side, is measured and is believed by additional antenna Cursor position, to obtain the deformation situation of entire antenna.It is identical as near field measurement antenna method, the shortcomings that this technology be need it is only Vertical measurement antenna increases additional structure and equipment, improves satellite launch cost.
6. optical deformation measurement method
The Space-Based Radar project of United States Air Force laboratory (AFRL) and JPL joint study uses optical method for measuring deformation, By installing camera on the absolute construction for being similar near field measurement antenna, deformation is measured.
Also there is the survey that may be implemented by installation complicated laser emitter, receiver and mirror surface to surface deformation Amount.
All there is the disadvantages of structure is complicated, higher cost in existing all distortion measurements and calibration method, additional in order to install Calibrator (-ter) unit and the deformation of structure itself and vibration problem introduced also brings along many problems.
Summary of the invention
For overcome the deficiencies in the prior art, the present invention provides a kind of in-orbit method for self-calibrating of array antenna, by allowing not Calibrated antenna itself emits signal, and receives ground echo signal to calibrate oneself, can be further simplified satellite structure, Reduce cost.
The technical solution adopted by the present invention to solve the technical problems includes the following steps：
1) aerial array to be calibrated includes M array element, and aerial array emits signal to the ground, and receives ground echo； The signal that k-th of array element receives on arrayWherein, ekBattle array when for no phase error The signal that first k is received at every sampling moment, φkPostpone for the electronic circuit in different channels, dkFor array element caused by deformation with The distance change on ground, ηkTo measure noise, λ is signal wavelength, δkThe phase introduced for electronic circuit delay and change in location is prolonged The sum of late；
2) that all adjacent two array element i and the signal that j is received are carried out conjugation is related, obtains Wherein ε is noise, Δ δij=δi-δjFor the phase difference of adjacent array element；
3) the transmitting signal phase delay for changing each array element at random, enables phase delay obey uniformly dividing between [0,2 π] Cloth repeats step 1) with 2), enters step 4) after the times N of repeatedly setting；
4) the conjugation correlation of the echo-signal of n times pulse is overlapped, and it is average to calculate the time, obtains
5) it calculatesPhaseThe then phase difference δ of adjacent two array element i and jij=ψij；
6) choosing first array element in aerial array is reference array element, according to Δ δijCalculate other array elements and reference array element Phase difference
7) phase of array element each in addition to reference array element is compensated, by the phase of each array element fromIt is adjusted toComplete the self calibration of aerial array.
Number of repetition N >=100.
The beneficial effects of the invention are as follows：Array element phase error can be carried out in the case where not increasing any optional equipment In-orbit estimation and calibration.This method emits signal by not calibrated antenna to the ground, the echo-signal received to each array element It is handled, phase error can be estimated and is compensated, realize in-orbit self calibration.The phase error that this method estimates is same When include element position variation and electronic circuit delay influence.
Detailed description of the invention
Fig. 1 is the array pattern (2D) before calibration
Fig. 2 is the array pattern (2D) after calibration
Fig. 3 is the array pattern (3D) before calibration
Fig. 4 is the array pattern (3D) after calibration
Fig. 5 is flow chart of the method for the present invention.
Specific embodiment
Present invention will be further explained below with reference to the attached drawings and examples, and the present invention includes but are not limited to following implementations Example.
The present invention includes the following steps：
1) (M array element, phase are aerial array to be calibratedEmit signal to the ground, and receives ground Face echo.The signal that k-th of array element receives on array is：
Here ek(n) for no phase error when, signal that array element k is received at every sampling moment.φkFor different channels Electronic circuit delay, dkFor the distance change of array element caused by deformation and ground, ηkTo measure noise.λ is wavelength, δkFor electricity The sum of the phase delay that sub- line delay and change in location introduce.
2) that all adjacent two array element i and the signal that j is received are carried out conjugation is related, obtains：
Wherein ε is noise, Δ δij=δi-δjFor the phase difference of adjacent array element.
3) the transmitting signal phase delay for changing each array element at random, enables phase delay obey uniformly dividing between [0,2 π] Cloth.Step 1 and 2 is repeated, after repetition N (N >=100) is secondary, enters step 4.
4) the conjugation correlation of the echo-signal of n times pulse is overlapped, and it is average to calculate the time, obtains：
5) it calculatesPhaseThe then phase difference δ of adjacent two array element i and jij=ψij。
6) choosing first array element is reference array element, according to Δ δijCalculate the phase difference of other array elements and reference array element
7) phase of each array element is compensated, by phase fromIt is adjusted to This completes self calibrations.
In order to illustrate the effect of the method for invention, the present invention is emulated.Initially set up receipt signal model.Assuming that thunder Up to transmitting signal pulse sT(t) it is：
sT(t)=g (t) exp (j2 π f0t) (4)
Wherein g (t) is complex envelope, f0For carrier frequency.Reception signal from scatterer i is：
Wherein c indicates that the light velocity, r are the distance of radar and scatterer, then two-way approach delay isReceive signal multiplied by Factor f (θ, β), this factor is by reflectivity, elevation angle θ and deflection β decision, wTFor beam gain.After removing carrier frequency, dissipate The echo-signal of beam i is：
Wherein λ is wavelength.The echo-signal of all scatterers is superimposed, is obtained：
Wherein N is scatterer number.
The signal that i-th of array element receives is ei'(n).In order to it is expectedAveragely replace collection flat using the time , it obtains
Fig. 1-Fig. 4 gives simulation result.In simulations, aerial array is made of 8 × 8 array elements.Fig. 1 is before calibrating Array pattern, abscissa are angle, and ordinate is normalized gain.Fig. 2 is the directional diagram after calibration.Fig. 3 is 3D form Array pattern before calibration shows the arrangement mode of aerial array in figure, and x-axis, y-axis are angle, and z-axis is that normalization increases Benefit.Fig. 4 is the array pattern after the calibration of 3D form.
Simulation results show the validity of algorithm.It can be seen that the phase between different array elements from the directional diagram of synthesis to miss The available high-precision estimation of difference and calibration.Even if array antenna initial phase error causes antenna that cannot focus completely, calculate Method still can work normally, and accurately estimates array element phase error and is compensated by, realizes in-orbit self calibration.
When using array antenna unit as micro-strip squaerial the case where one dimensional linear array, as embodiment.In this example, Antenna is 8 yuan of linear arrays.
1) signal that the array element i (i=1 ..., 8) of aerial array to be calibrated is received is：
2) signal that all adjacent two array elements receive is subjected to conjugation correlation：
3) the transmitting signal phase delay for changing each array element at random enables transmitting signal phase delayObey [0,2 π] it Between be uniformly distributed.130 step 1) are repeated to step 2), subsequently into step 4).
4) the conjugation related computational time of the echo-signal of 130 subpulses is averaged：
5) it calculatesPhase?：
ψ12=62 °, ψ23=-113 °, ψ34=-79 °, ψ45=137 °, ψ56=107 °, ψ67=-149 °, ψ78=38 ° becauseIt is 0, therefore above-mentioned ψijValue is the phase difference δ of adjacent array elementij=δi-δj, i.e.,：
Δδ12=62 °, Δ δ23=-113 °, Δ δ34=-79 °, Δ δ45=137, Δ δ56=107, Δ δ67=-149, Δ δ78=38 °
6) phase for choosing first array element of linear array is fixed phaseArray element 1 is calculated to array element 8 and fixed phase Phase difference?：
7) phase difference is compensated, adjusts the transmitting signal delay of each array element, enable the signal delay knots modification of array element i ForThe signal phase error that each array element can be eliminated realizes the self calibration of array antenna.

Claims (2)

1. a kind of in-orbit method for self-calibrating of space array antenna, it is characterised in that include the following steps：
1) aerial array to be calibrated includes M array element, and aerial array emits signal to the ground, and receives ground echo；Array The signal that upper k-th of array element receivesWherein, ekArray element k when for no phase error The signal received at every sampling moment, φkPostpone for the electronic circuit in different channels, dkFor array element caused by deformation and ground The distance change in face, ηkTo measure noise, λ is signal wavelength, δkThe phase delay introduced for electronic circuit delay and change in location The sum of；
2) that all adjacent two array element i and the signal that j is received are carried out conjugation is related, obtainsWherein ε For noise, Δ δij=δi-δjFor the phase difference of adjacent array element；
3) the transmitting signal phase delay for changing each array element at random, enables phase delay obey being uniformly distributed between [0,2 π], Step 1) is repeated with 2), is entered step 4) after the times N of repeatedly setting；
4) the conjugation correlation of the echo-signal of n times pulse is overlapped, and it is average to calculate the time, obtains
5) it calculatesPhaseThe then phase difference δ of adjacent two array element i and jij=ψij；
6) choosing first array element in aerial array is reference array element, according to Δ δijCalculate the phase of other array elements with reference array element Potential differenceI=2 ..., M；
7) phase of array element each in addition to reference array element is compensated, by the phase of each array element fromIt is adjusted to Complete the self calibration of aerial array.
2. the in-orbit method for self-calibrating of space array antenna according to claim 1, it is characterised in that：The number of repetition N≥100。
CN201810256741.4A 2018-03-27 2018-03-27 A kind of in-orbit method for self-calibrating of space array antenna Pending CN108872721A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201810256741.4A CN108872721A (en) 2018-03-27 2018-03-27 A kind of in-orbit method for self-calibrating of space array antenna

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201810256741.4A CN108872721A (en) 2018-03-27 2018-03-27 A kind of in-orbit method for self-calibrating of space array antenna

Publications (1)

Publication Number Publication Date
CN108872721A true CN108872721A (en) 2018-11-23

Family

ID=64326479

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201810256741.4A Pending CN108872721A (en) 2018-03-27 2018-03-27 A kind of in-orbit method for self-calibrating of space array antenna

Country Status (1)

Country Link
CN (1) CN108872721A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112305526A (en) * 2020-10-22 2021-02-02 电子科技大学 Distributed array system synchronization method based on external calibration source
WO2021043068A1 (en) * 2019-09-03 2021-03-11 中兴通讯股份有限公司 Digital-analog hybrid beamforming multi-channel correction method and device
CN112505630A (en) * 2020-11-18 2021-03-16 安洁无线科技（苏州）有限公司 Analysis compensation method of millimeter wave radar
CN113726453A (en) * 2021-08-31 2021-11-30 南通大学 Method for calibrating broadband antenna array in time domain
CN115586502A (en) * 2022-12-13 2023-01-10 西安电子科技大学 Method and device for receiving and correcting external field time-frequency near-field broadband signals

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1802771A (en) * 2003-06-26 2006-07-12 日本电气株式会社 Adaptive antenna reception method and device
CN101436890A (en) * 2008-12-10 2009-05-20 中国移动通信集团广东有限公司 Method and equipment for estimating antenna array error parameter
CN101799542A (en) * 2010-01-08 2010-08-11 西安电子科技大学 Passive coherent location radar direction finding system based on Adcock antenna and direction finding method thereof
CN102520408A (en) * 2011-12-30 2012-06-27 北京华航无线电测量研究所 Three-dimensional imaging method for three-dimensional imaging system with cylindrical array surface
CN103135083A (en) * 2011-11-24 2013-06-05 西安电子科技大学 Electromagnetic vector sensor array amplitude and phase error self-correcting method based on array rotation
CN104181513A (en) * 2014-07-30 2014-12-03 西安电子科技大学 Array element position correcting method of radar antenna
CN105353229A (en) * 2015-10-20 2016-02-24 上海无线电设备研究所 Phased array amplitude-phase error near-field calibration method based on one-dimensional rotation
CN107783087A (en) * 2017-10-27 2018-03-09 西南电子技术研究所（中国电子科技集团公司第十研究所） The automatic correcting method of sphere phase array antenna near-field passage calibration link

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1802771A (en) * 2003-06-26 2006-07-12 日本电气株式会社 Adaptive antenna reception method and device
CN101436890A (en) * 2008-12-10 2009-05-20 中国移动通信集团广东有限公司 Method and equipment for estimating antenna array error parameter
CN101799542A (en) * 2010-01-08 2010-08-11 西安电子科技大学 Passive coherent location radar direction finding system based on Adcock antenna and direction finding method thereof
CN103135083A (en) * 2011-11-24 2013-06-05 西安电子科技大学 Electromagnetic vector sensor array amplitude and phase error self-correcting method based on array rotation
CN102520408A (en) * 2011-12-30 2012-06-27 北京华航无线电测量研究所 Three-dimensional imaging method for three-dimensional imaging system with cylindrical array surface
CN104181513A (en) * 2014-07-30 2014-12-03 西安电子科技大学 Array element position correcting method of radar antenna
CN105353229A (en) * 2015-10-20 2016-02-24 上海无线电设备研究所 Phased array amplitude-phase error near-field calibration method based on one-dimensional rotation
CN107783087A (en) * 2017-10-27 2018-03-09 西南电子技术研究所（中国电子科技集团公司第十研究所） The automatic correcting method of sphere phase array antenna near-field passage calibration link

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
中国航空学会 主编: "无人机共形阵列天线的自校准算法", 《014（第五届）中国无人机大会论文集 第1版》 *

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021043068A1 (en) * 2019-09-03 2021-03-11 中兴通讯股份有限公司 Digital-analog hybrid beamforming multi-channel correction method and device
CN112305526A (en) * 2020-10-22 2021-02-02 电子科技大学 Distributed array system synchronization method based on external calibration source
CN112305526B (en) * 2020-10-22 2023-05-26 电子科技大学 Distributed array system synchronization method based on external calibration source
CN112505630A (en) * 2020-11-18 2021-03-16 安洁无线科技（苏州）有限公司 Analysis compensation method of millimeter wave radar
CN112505630B (en) * 2020-11-18 2024-05-14 安洁无线科技（苏州）有限公司 Analysis compensation method of millimeter wave radar
CN113726453A (en) * 2021-08-31 2021-11-30 南通大学 Method for calibrating broadband antenna array in time domain
CN113726453B (en) * 2021-08-31 2023-11-03 南通大学 Method for calibrating broadband antenna array in time domain
CN115586502A (en) * 2022-12-13 2023-01-10 西安电子科技大学 Method and device for receiving and correcting external field time-frequency near-field broadband signals
CN115586502B (en) * 2022-12-13 2023-03-07 西安电子科技大学 Method and device for receiving and correcting external field time-frequency near-field broadband signals

Similar Documents

Publication Publication Date Title
CN108872721A (en) A kind of in-orbit method for self-calibrating of space array antenna
US8184042B2 (en) Self calibrating conformal phased array
KR101220952B1 (en) System and technique for calibrating radar arrays
US10663563B2 (en) On-site calibration of array antenna systems
US6731236B1 (en) Methods and apparatus for optimizing interferometric radar altimeter cross track accuracy
US7199753B2 (en) Calibration method for receive only phased array radar antenna
US9979084B2 (en) Satellite-based phased array calibration
EP1977266B1 (en) Automatic delay calibration and tracking for ultra-wideband antenna array
CN110058204A (en) One kind being based on the matched satellite antenna beam center calibrating method of directional diagram
Ryzhikov et al. Measurement of angular coordinates of point targets in the onboard weather navigation radar based on a multi-channel phased antenna array with an assimetic pattern
JP2006284385A (en) Reference station system for gps satellite
US20110205121A1 (en) Method of determining real time location of reflecting objects and system thereof
Shimizu et al. Flash LiDAR development for space rendezvous
CN111141312B (en) Method for overcoming radio altimeter height measurement failure or height measurement precision drop
JP2001153906A (en) Instrument and method for measuring antenna
RU2682239C1 (en) Low-flying target accurate tracking method by elevation angle under interference conditions
US6768455B1 (en) Calibration probe motion detector
Zeng et al. Error analysis of angle inverse RCS for millimeter wave SAR radiometric calibration
Nohmi Development of vibration-imaging radar (VirA)
Haibo et al. The study of mono-pulse angle measurement based on digital array radar
JP2003188641A (en) Mirror surface precision measuring apparatus for reflector antenna and mirror surface control system
Mi et al. SAR Antenna Pattern Measurement by Internal Calibration Method for GF‐3 Satellite
Viikari et al. A frequency shift technique for pattern correction in hologram-based CATRs
Hees et al. Verification of the GMES sentinel-1 antenna model
Hartmann et al. Analysis and Measurement of Reflector Antennas in the MM-Wave Frequency Range

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
WD01 Invention patent application deemed withdrawn after publication

Application publication date: 20181123

WD01 Invention patent application deemed withdrawn after publication