CN102647223A - Absolute time delay calibration method for inter-satellite link of navigational satellite - Google Patents
Absolute time delay calibration method for inter-satellite link of navigational satellite Download PDFInfo
- Publication number
- CN102647223A CN102647223A CN2012100869018A CN201210086901A CN102647223A CN 102647223 A CN102647223 A CN 102647223A CN 2012100869018 A CN2012100869018 A CN 2012100869018A CN 201210086901 A CN201210086901 A CN 201210086901A CN 102647223 A CN102647223 A CN 102647223A
- Authority
- CN
- China
- Prior art keywords
- inter
- satellite link
- antenna
- time delay
- measured
- 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.)
- Granted
Links
Abstract
The invention provides an absolute time delay calibration method for an inter-satellite link of a navigational satellite. The inter-satellite link of the navigational satellite is provided with a plurality of antennas and uses transmission signals as spread spectrum ranging signals, so that an inter-satellite link transmitter transmits spread spectrum signals with the same structure with the inter-satellite link transmission signal through an antenna to be detected, and an inter-satellite link receiver is used for receiving the spread spectrum signals through one another antenna to be detected. Receiving-transmitting link combined time delays which are formed by matching three or more than three antennas in pair can be measured. An absolute time delay when each testing antenna receives and transmits inter-satellite link signals is obtained through data processing according to a combined time delay value, a zero calibration result of a testing channel, and a space transmission time delay of a receiving-transmitting antenna. The method provided by the invention is simple and convenient to operate without a special calibration antenna. By using a test signal with the same structure with the inter-satellite link transmission signals, the transmission time delay of the inter-satellite link signals can be actually reflected by a calibration result.
Description
Technical field
The present invention relates to the scaling method of the absolute time delay of a kind of navigation satellite inter-satellite link antenna, the absolute time delay that can be used for navigational satellite system inter-satellite link antenna is demarcated.
Background technology
In GPS, keep higher satellite orbit and confirm that precision and clock correction confirms that precision is that the receiving terminal of guaranteeing to navigate obtains the location of big system requirements or the key of time service precision.Obtaining accurate track and clock correction parameter need lay the large number of ground station usually in the world and carry out Continuous Observation; China does not possess such global strategy geographical resource at present; Therefore China will adopt the inter-satellite link technology in the GPS of grinding; One of them critical function is to obtain the metrical information of other segmental arc on the track in the accurate measurement of passing through inter-satellite link under the situation that only disposes the minority monitoring station, thereby reaches the ability that obtains the Precise Orbit parameter.
Navigation satellite passes through inter-satellite link; Broadcast and receive the spread spectrum distance measuring signal and carry out the precise distance measurement between the satellite; The time delay of obtaining needs deduction satellite inter-satellite link transmission circuit itself of accurate interstellar distance value; Just can obtain the actual distance between the satellite, the certainty of measurement of the time delay of satellite inter-satellite link transmission circuit own will directly influence the range accuracy between the satellite.The inter-satellite link antenna of navigation satellite is the important component part of inter-satellite link transmission circuit; Therefore; The absolute time delay value of navigation satellite inter-satellite link dual-mode antenna is a key index parameter of navigational satellite system, and the precision that the absolute time delay of dual-mode antenna is demarcated will influence the precision of finding range between the star between the satellite.
At present, the method for testing of the absolute time delay of antenna time delay mainly contains: (1) calibration tower method.Specifically can be referring to GJB GJB3153-1998 " the accurate measurement radar is demarcated and proofreaied and correct ", Yao Shikang, Sun Zhenqi, Zhang Dingcai etc.; (2) no tower beacon school method.Specifically can be referring to Huang Xufeng, Qin Shunyou " garden bore telemetry antenna time-delay measuring method " radio-communication engineering Vol.33No.4 in 2007; (3) vector net analysis method.Specifically can be referring to Wu Chunbang, Yang Wenli, Liu Bo " navigation satellite antenna phase center and delay testing " space electronic 2009 the 1st phases of technology.Calibration tower method all uses zero apart from transponder and school zero antenna with no tower beacon school method; Zero precision calibration apart from transponder and the absolute time delay of school zero antenna itself also is a test difficult problem; Their stated accuracy will have a strong impact on the stated accuracy of tested antenna time delay; Zero is different with the real work situation of inter-satellite link antenna apart from the use of transponder, and the time delay value under calibration result and the inter-satellite link antenna real work state status there are differences, and does not have in the method for tower beacon school; School zero antenna installation site difference can cause demarcating numerical value change, and definite error of zero antenna installation site, school also can be brought calibrated error.Vector net analysis method has adopted standard antenna as test reference, for navigation satellite inter-satellite link ka band antenna, is difficult to obtain a standard antenna that is used to test time delay; Secondly; Dual-mode antenna satisfies under the far field condition, and when testing through vector net analysis appearance, test stube cable or waveguide are long; Under Ka frequency range working condition, the calibration of the time delay of long test cable or waveguide will guarantee to stablize, high accuracy is very difficult.The most important thing is: adopting the time delay value of vector net analysis appearance test is the group delay of a frequency range, can not correctly reflect the time delay situation of the spread spectrum distance measuring signal of certain signal specific system of inter-satellite link transmission.
Summary of the invention
Technology of the present invention is dealt with problems and is: the deficiency that overcomes prior art; Provide a kind of navigation satellite inter-satellite link antenna absolute time delay scaling method; The time of day that can correctly reflect the absolute time delay of inter-satellite link antenna under the inter-satellite link circuit transmission distance measuring signal situation obtains the high-precision time-delay calibration value of inter-satellite link antenna.
Technical solution of the present invention is: the absolute time delay scaling method of a kind of navigation satellite inter-satellite link antenna, and step is following:
(1) the inter-satellite link transmitter is passed through test cable and attenuator and inter-satellite link receiver wired connection, the inter-satellite link transmitter produces inter-satellite link distance measuring signal and output, and inter-satellite link receiver reception inter-satellite link distance measuring signal carries out spread spectrum and finds range;
(2) second signal that the second that the inter-satellite link transmitter is produced, signal produced with the inter-satellite link receiver is as two inputs of time-interval counter; Be respectively applied for and start or stop time-interval counter counting, measure inter-satellite link transmitter and inter-satellite link receiver time difference between second signal separately through time-interval counter;
(3) according to the pseudorange measurement of inter-satellite link receiver and the measurement result of time-interval counter, obtain the combination time delay of inter-satellite link transmitter, cable, attenuator, inter-satellite link receiver, delay the null value that obtains measuring passage during the deduction attenuator;
(4) choose at least 3 inter-satellite link antennas as antenna to be measured; Antenna to be measured constitutes a test combination in twos; In any test combination; One of them antenna to be measured is connected with the inter-satellite link transmitter; Another antenna to be measured is connected with the inter-satellite link receiver; Distance R in any test combination between two antennas to be measured keeps identical and wave beams two antennas to be measured aim at each other, and wherein
λ is the corresponding wavelength of frequency signal centre frequency to be measured, and D is the diameter of antenna to be measured;
(5), obtain adding the combination time delay between the measurement transmitting-receiving behind the antenna to be measured according to pseudorange measurement, the time-interval counter count value of inter-satellite link receiver;
(6) the distance R conversion between two antennas to be measured in any test combination is the free space propagation delay; After the null value and free space propagation delay of the measurement passage that the combination time delay deduction step (3) between the measurement transmitting-receiving behind the adding antenna to be measured that step (5) is obtained obtains, obtain in any test combination two antennas to be measured separately absolute time delay with;
(7) utilize the result of step (6), obtain the absolute time delay of each antenna to be measured through the form of the group of solving an equation.
The present invention's advantage compared with prior art is:
(1) test signal adopts the inter-satellite link transmitter to generate in the inventive method; The working frequency range of test signal, signal system are consistent in rail transmission signals system with inter-satellite link; Utilize the inter-satellite link receiver to carry out the spread spectrum distance measuring method; Carry out pseudo range measurement, the time delay in the time of truly reflecting inter-satellite link antenna receiving-sending inter-satellite link signal;
(2) the inventive method utilizes inter-satellite link to dispose many antennas condition, carries out the mutual pairing of antenna and measures, and does not need special standard antenna, has avoided standard antenna design parameter institute not up to standard errors caused problem;
(3) null value of the calibration process of time delay of the present invention and TCH test channel is demarcated and all between the inter-satellite link transmitter and receiver, is carried out; Need not use long cable of ka frequency range or long wave to lead, avoid long cable of ka frequency range or long wave to lead time delay and demarcated the mistake situation that occurs;
(4) need not use the null value transponder in the inventive method, the technology of having avoided the accurate time delay of null value transponder to demarcate realizes a difficult problem, and also having eliminated the time delay calibrated error of null value transponder own influences inter-satellite link antenna time delay stated accuracy.
Description of drawings
Fig. 1 is the theory diagram of the inventive method.
Embodiment
As shown in Figure 1, be the schematic diagram of the inventive method.The capital equipment that the inventive method relates to comprises inter-satellite link transmitter, inter-satellite link receiver and time-interval counter.Wherein time-interval counter is used to measure second poor between the pps pulse per second signal that the road receiver generates between pps pulse per second signal that the inter-satellite link transmitter generates and star.
The key step of the inventive method is following:
(1) navigation satellite disposes a plurality of identical inter-satellite link antennas; The working frequency range of each antenna is consistent; The signal system of antenna transmission is consistent, and under the situation of the reference antenna that does not have transmit after receive time delay to demarcate, number of antennas to be measured is no less than 3; Antenna to be measured is an inactive component, and same antenna to be measured receives consistent with the absolute time delay of emission.
(2) null value of measuring passage is calibrated.The inter-satellite link transmitter is passed through test cable and attenuator and inter-satellite link receiver wired connection.Inter-satellite link transmitter output inter-satellite link distance measuring signal; The link distance measuring signal has identical centre frequency, modulation system, spread spectrum code check and spread spectrum mode with the distance measuring signal of inter-satellite link actual transmission; The inter-satellite link receiver receives distance measuring signal and carries out the spread spectrum range finding; Attenuator is decayed to the inter-satellite link transmitter output signal, and the signal level that guarantees to be input to the inter-satellite link receiver is at normal range of receiving.
The inter-satellite link receiver receives the spread spectrum distance measuring signal of inter-satellite link transmitter output; Signal is carried out the acquisition and tracking and the data processing of filtering, down-conversion, spread-spectrum signal; Obtain pseudo-range measurements; Time difference between the pps pulse per second signal that pps pulse per second signal that time-interval counter measurement inter-satellite link transmitter generates and inter-satellite link receiver generate; Certain second constantly the pseudo-range measurements that obtains of inter-satellite link receiver to deduct between this moment transmitter and the receiver second of pulse per second (PPS) poor, the combination latency measurement value T between obtaining receiving and dispatching
Z1
Measure the time delay T of attenuator in the center frequency point of inter-satellite link signal with vector net analysis appearance
Z2Measure the null value T of passage
ZCan calculate by following formula:
T
Z＝T
Z1-T
Z2 (1)
(3) be connected with the inter-satellite link transmitter as transmitting antenna with antenna 1; Antenna 2 is connected with the inter-satellite link receiver as reception antenna; Distance R between two antennas to be measured; Wherein
λ is the corresponding wavelength of frequency signal centre frequency to be measured; D is the diameter of antenna to be measured, and the wave beam of two antennas to be measured aims at each other.According to the pseudorange measurement of inter-satellite link receiver and the measurement result of time-interval counter, the combination latency measurement value T between obtaining receiving and dispatching
C1Air line distance R between accurate measurement antenna 1 and the antenna 2, convert into radio wave at free space propagation delay T
D, that is:
T
D＝c/R (2)
C is the light velocity in the formula;
Combination time delay deduction between the transmitting-receiving that measures is measured the passage null value, deducted free space propagation delay amount again, obtain antenna 1 absolute time delay T
1With antenna 2 absolute time delay T
2The combination time delay value.That is:
T
1+T
2＝T
C1-T
Z-T
D (3)
(4) with antenna 3 as transmitting antenna, antenna 2 is as reception antenna, repeating step (3) obtains antenna 3 absolute time delay T
3With antenna 2 absolute time delay T
2The combination time delay value.
T
3+T
2＝T
C2-T
Z-T
D (4)
T in the formula
C2Be the combination latency measurement value between the transmitting-receiving.
(5) with antenna 3 as transmitting antenna, antenna 1 is as reception antenna, repeating step (3) obtains antenna 3 absolute time delay T
3With antenna 1 absolute time delay T
1The combination time delay value.
T
3+T
1＝T
C3-T
Z-T
D (5)
T in the formula
C3Be the combination latency measurement value between the transmitting-receiving.
The mutual pairing of (6) three antennas, transmitting-receiving each other, the system of linear equations of three of measuring combination time delay value equation:
The solving equation group obtains the absolute time delay of transmitting-receiving of each antenna:
Can resolve the absolute time delay of each antenna thus.
(5) when antenna number during more than three, any antenna antenna pairing as a reference in newly-increased antenna and above-mentioned three antennas, transmitting-receiving each other; Measure the combination time delay value, deduct absolute time delay, the free space propagation delay of reference antenna and measure the passage null value, obtain the absolute time delay of newly-increased antenna; Suppose with antenna 1 antenna as a reference; Be used to demarcate the emission of analog signal, repeating step (3) obtains the newly-increased absolute time delay T of antenna
nWith antenna 1 absolute time delay T
1The combination time delay value.
T
n+T
1＝T
Cn-T
Z-T
D (10)
T in the formula
CnBe the combination latency measurement value between antenna 1 and the newly-increased antenna receiving-sending.
Therefore, the absolute time delay of newly-increased antenna is:
T
n＝T
Cn-T
1-T
Z-T
D (11)
The content of not doing to describe in detail in the specification of the present invention belongs to those skilled in the art's known technology.
Claims (1)
1. absolute time delay scaling method of navigation satellite inter-satellite link antenna is characterized in that step is following:
(1) the inter-satellite link transmitter is passed through test cable and attenuator and inter-satellite link receiver wired connection, the inter-satellite link transmitter produces inter-satellite link distance measuring signal and output, and inter-satellite link receiver reception inter-satellite link distance measuring signal carries out spread spectrum and finds range;
(2) second signal that the second that the inter-satellite link transmitter is produced, signal produced with the inter-satellite link receiver is as two inputs of time-interval counter; Be respectively applied for and start or stop time-interval counter counting, measure inter-satellite link transmitter and inter-satellite link receiver time difference between second signal separately through time-interval counter;
(3) according to the pseudorange measurement of inter-satellite link receiver and the measurement result of time-interval counter, obtain the combination time delay of inter-satellite link transmitter, cable, attenuator, inter-satellite link receiver, delay the null value that obtains measuring passage during the deduction attenuator;
(4) choose at least 3 inter-satellite link antennas as antenna to be measured; Antenna to be measured constitutes a test combination in twos; In any test combination; One of them antenna to be measured is connected with the inter-satellite link transmitter; Another antenna to be measured is connected with the inter-satellite link receiver; Distance R in any test combination between two antennas to be measured keeps identical and wave beams two antennas to be measured aim at each other, and wherein
λ is the corresponding wavelength of frequency signal centre frequency to be measured, and D is the diameter of antenna to be measured;
(5), obtain adding the combination time delay between the measurement transmitting-receiving behind the antenna to be measured according to pseudorange measurement, the time-interval counter count value of inter-satellite link receiver;
(6) the distance R conversion between two antennas to be measured in any test combination is the free space propagation delay; After the null value and free space propagation delay of the measurement passage that the combination time delay deduction step (3) between the measurement transmitting-receiving behind the adding antenna to be measured that step (5) is obtained obtains, obtain in any test combination two antennas to be measured separately absolute time delay with;
(7) utilize the result of step (6), obtain the absolute time delay of each antenna to be measured through the form of the group of solving an equation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210086901.8A CN102647223B (en) | 2012-03-26 | 2012-03-26 | Absolute time delay calibration method for inter-satellite link of navigational satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210086901.8A CN102647223B (en) | 2012-03-26 | 2012-03-26 | Absolute time delay calibration method for inter-satellite link of navigational satellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102647223A true CN102647223A (en) | 2012-08-22 |
| CN102647223B CN102647223B (en) | 2014-07-02 |
Family
ID=46659821
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210086901.8A Active CN102647223B (en) | 2012-03-26 | 2012-03-26 | Absolute time delay calibration method for inter-satellite link of navigational satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102647223B (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103001709A (en) * | 2012-09-29 | 2013-03-27 | 西安空间无线电技术研究所 | Antenna delay test method |
| CN103117822A (en) * | 2013-01-25 | 2013-05-22 | 华中科技大学 | Device for receiver channel group delay measurement |
| CN104917573A (en) * | 2015-05-13 | 2015-09-16 | 北京理工大学 | Antenna beam synthesizing phase absolute delay calibration device and method |
| CN106226760A (en) * | 2016-07-15 | 2016-12-14 | 中国电子科技集团公司第五十四研究所 | A kind of have measurement apparatus and the method that wireless device time delay is demarcated |
| CN107070567A (en) * | 2017-04-06 | 2017-08-18 | 中国科学院国家授时中心 | Time delay calibrating method between a kind of ground satellite station station based on pseudo satellite, pseudolite |
| CN109581447A (en) * | 2018-12-06 | 2019-04-05 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | More Radio Link Combined Calculation Spread Spectrum TT&C equipment zero methods |
| CN109725369A (en) * | 2019-02-26 | 2019-05-07 | 北京空间飞行器总体设计部 | A kind of whole star environment down space x-ray telescope ground calibration system and method |
| CN110823019A (en) * | 2019-10-30 | 2020-02-21 | 中国空空导弹研究院 | Testing device and testing method for airborne transmitting Beidou satellite signals |
| CN111273239A (en) * | 2020-02-21 | 2020-06-12 | 中国西安卫星测控中心 | External field calibration compensation method for pointing accuracy of inter-satellite link phased array antenna |
| CN112751605A (en) * | 2020-12-29 | 2021-05-04 | 上海卫星工程研究所 | Method, system and medium for testing capturing and tracking characteristics of double-star dynamic inter-satellite link |
| CN112865894A (en) * | 2021-01-19 | 2021-05-28 | 中国科学院国家授时中心 | Time delay calibration method for navigation ground station equipment based on satellite transponder |
| CN113382466A (en) * | 2021-04-29 | 2021-09-10 | 西安空间无线电技术研究所 | Novel time delay monitoring and calibrating method based on time division duplex system |
| CN113447956A (en) * | 2021-06-15 | 2021-09-28 | 中国人民解放军63921部队 | Satellite navigation satellite-ground integrated automatic time delay calibration method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11109016A (en) * | 1997-10-01 | 1999-04-23 | Japan Radio Co Ltd | Glonass receiver |
| GB2438504A (en) * | 2006-05-25 | 2007-11-28 | Boeing Co | Navigation signal group delay calibration |
| CN101488802A (en) * | 2009-02-25 | 2009-07-22 | 清华大学 | Receiving and sending synchronization method used for wireless channel absolute time delay test |
| CN101494495A (en) * | 2009-02-27 | 2009-07-29 | 航天东方红卫星有限公司 | Method for implementing split-second precision synchronism using spread-spectrum answering machine |
-
2012
- 2012-03-26 CN CN201210086901.8A patent/CN102647223B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11109016A (en) * | 1997-10-01 | 1999-04-23 | Japan Radio Co Ltd | Glonass receiver |
| GB2438504A (en) * | 2006-05-25 | 2007-11-28 | Boeing Co | Navigation signal group delay calibration |
| CN101488802A (en) * | 2009-02-25 | 2009-07-22 | 清华大学 | Receiving and sending synchronization method used for wireless channel absolute time delay test |
| CN101494495A (en) * | 2009-02-27 | 2009-07-29 | 航天东方红卫星有限公司 | Method for implementing split-second precision synchronism using spread-spectrum answering machine |
Non-Patent Citations (4)
| Title |
|---|
| PLUMB, J.ET AL.: ""absolute calibration of a geodetic time transfer system"", 《IEEE TRANSACTIONS ON ULTRASONICS, FERROELECTRICS AND FREQUENCY CONTROL》, vol. 52, no. 11, 30 November 2005 (2005-11-30) * |
| 原亮，王宏兵，刘昌洁，: ""天线时延标定在卫星导航技术中的应用"", 《无线电工程》, no. 10, 31 October 2010 (2010-10-31) * |
| 吴春邦，杨文丽，刘波，: ""导航卫星天线相位中心及时延测试"", 《空间电子技术》, no. 1, 31 March 2009 (2009-03-31) * |
| 魏海涛，蔚保国，李刚，原亮，: ""卫星导航设备时延精密标定方法与测试"", 《中国科学：物理学 力学 天文学》, vol. 40, no. 5, 31 May 2010 (2010-05-31) * |
Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103001709A (en) * | 2012-09-29 | 2013-03-27 | 西安空间无线电技术研究所 | Antenna delay test method |
| CN103001709B (en) * | 2012-09-29 | 2015-07-08 | 西安空间无线电技术研究所 | Antenna delay test method |
| CN103117822A (en) * | 2013-01-25 | 2013-05-22 | 华中科技大学 | Device for receiver channel group delay measurement |
| CN103117822B (en) * | 2013-01-25 | 2014-12-31 | 华中科技大学 | Device for receiver channel group delay measurement |
| CN104917573A (en) * | 2015-05-13 | 2015-09-16 | 北京理工大学 | Antenna beam synthesizing phase absolute delay calibration device and method |
| CN106226760A (en) * | 2016-07-15 | 2016-12-14 | 中国电子科技集团公司第五十四研究所 | A kind of have measurement apparatus and the method that wireless device time delay is demarcated |
| CN107070567B (en) * | 2017-04-06 | 2020-04-10 | 中国科学院国家授时中心 | Satellite ground station inter-station time delay calibration method based on pseudo satellite |
| CN107070567A (en) * | 2017-04-06 | 2017-08-18 | 中国科学院国家授时中心 | Time delay calibrating method between a kind of ground satellite station station based on pseudo satellite, pseudolite |
| CN109581447A (en) * | 2018-12-06 | 2019-04-05 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | More Radio Link Combined Calculation Spread Spectrum TT&C equipment zero methods |
| CN109725369A (en) * | 2019-02-26 | 2019-05-07 | 北京空间飞行器总体设计部 | A kind of whole star environment down space x-ray telescope ground calibration system and method |
| CN109725369B (en) * | 2019-02-26 | 2021-06-11 | 北京空间飞行器总体设计部 | Space X-ray telescope ground calibration system and method under whole-satellite environment |
| CN110823019B (en) * | 2019-10-30 | 2022-03-15 | 中国空空导弹研究院 | Testing device and testing method for airborne transmitting Beidou satellite signals |
| CN110823019A (en) * | 2019-10-30 | 2020-02-21 | 中国空空导弹研究院 | Testing device and testing method for airborne transmitting Beidou satellite signals |
| CN111273239A (en) * | 2020-02-21 | 2020-06-12 | 中国西安卫星测控中心 | External field calibration compensation method for pointing accuracy of inter-satellite link phased array antenna |
| CN112751605A (en) * | 2020-12-29 | 2021-05-04 | 上海卫星工程研究所 | Method, system and medium for testing capturing and tracking characteristics of double-star dynamic inter-satellite link |
| CN112865894A (en) * | 2021-01-19 | 2021-05-28 | 中国科学院国家授时中心 | Time delay calibration method for navigation ground station equipment based on satellite transponder |
| CN112865894B (en) * | 2021-01-19 | 2022-06-14 | 中国科学院国家授时中心 | Time delay calibration method for navigation ground station equipment based on satellite transponder |
| CN113382466A (en) * | 2021-04-29 | 2021-09-10 | 西安空间无线电技术研究所 | Novel time delay monitoring and calibrating method based on time division duplex system |
| CN113382466B (en) * | 2021-04-29 | 2023-02-28 | 西安空间无线电技术研究所 | Novel time delay monitoring and calibrating method based on time division duplex system |
| CN113447956A (en) * | 2021-06-15 | 2021-09-28 | 中国人民解放军63921部队 | Satellite navigation satellite-ground integrated automatic time delay calibration method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102647223B (en) | 2014-07-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102647223B (en) | Absolute time delay calibration method for inter-satellite link of navigational satellite | |
| CN102636790B (en) | Absolute time delay calibration system of inter-satellite link antennas of navigational satellites | |
| CN102545935B (en) | Calibration receiving device and calibration receiving method of radio frequency simulation system | |
| FI78566C (en) | FOERFARANDE OCH ANORDNING VID ANTENN- OCH MOTTAGNINGSSYSTEM AV EN RADIOTEODOLIT. | |
| CN103064089B (en) | Method for calibrating satellite navigation digital multi-beam launching array antenna phase center | |
| CN101738598B (en) | Method for performing real-time measurement on track and position of satellite or aircraft | |
| CN101776753B (en) | Symmetrical double-journey incoherent speed measurement method of air fleet link | |
| CN104459683A (en) | Multi-target displacement high-accuracy measurement method and system based on microwave radar | |
| CN101349753B (en) | Deformation telemetry technology of large-scale buildings | |
| CN104062648A (en) | Distributed-network high-frequency ground wave radar system and control method thereof | |
| CN107070567A (en) | Time delay calibrating method between a kind of ground satellite station station based on pseudo satellite, pseudolite | |
| CN109581447A (en) | More Radio Link Combined Calculation Spread Spectrum TT&C equipment zero methods | |
| CN103257340B (en) | Method for calibrating amplitude consistency of a plurality of ground receivers with radar satellite | |
| CN201191184Y (en) | Digital wireless electric height meter | |
| Thoelert et al. | GNSS signal verification with a high gain antenna-calibration strategies and high quality signal assessment | |
| CN109974573A (en) | A kind of three-dimensional deformation measurement method that microwave radar is merged with Beidou | |
| CN103792519A (en) | Spaceborne radar clock drifting on-orbit correction method based on active calibrator | |
| CN107765239A (en) | A kind of design and implementation method of economical short distance range radar | |
| CN102055536A (en) | Reflector antenna delay measurement method | |
| US8952848B2 (en) | System and method for determining the location of the phase center of an antenna | |
| RU2530233C1 (en) | Radio-technical system | |
| CN104678078A (en) | Soil humidity calibrating and measuring method based on global positioning system (GPS) reflected signal | |
| CN1332214C (en) | Method for determining full round number funiness of radio guidance system | |
| RU2608748C1 (en) | Method for measuring flight speed of an aerial object and the radar station for its implementation | |
| CN103001709B (en) | Antenna delay test method |
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 |