CN102647223B - 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
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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 (Global Position System), maintain higher satellite orbit determination precision and clock correction and determine that precision is that the receiving terminal of guaranteeing to navigate obtains the location of large system requirements or the key of time service precision.Obtaining accurate track and clock correction parameter conventionally need to lay in the world large number of ground station and carry out Continuous Observation, China does not possess such global strategy geographical resource at present, therefore China will adopt inter-satellite link technology in the GPS (Global Position System) of grinding, one of them critical function is in the situation that only configuring minority monitoring station, to obtain the metrical information of other segmental arc on track by the accurate measurement of inter-satellite link, thereby reaches the ability that obtains Precise Orbit parameter.
Navigation satellite passes through inter-satellite link, broadcast and receive spread spectrum distance measuring signal and carry out the precise distance measurement between satellite, accurate interstellar distance value obtain the time delay that need to deduct Inter-satellite Links transmission circuit itself, just can obtain the actual distance between satellite, the certainty of measurement of the time delay of Inter-satellite Links transmission circuit own is by the range accuracy directly affecting between 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 is by range accuracy between the star affecting between satellite.
At present, the method for testing of the absolute time delay of antenna delay mainly contains: (1) calibration tower method.Specifically can be referring to GJB GJB3153-1998 " precision instrumentation radar is demarcated and proofreaied and correct ", Yao Shikang, Sun Zhenqi, Zhang Dingcai etc.; (2) without tower Calibration 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 technology the 1st phase in 2009.Calibration tower method and all use zero apart from transponder and school zero antenna without tower Calibration Method, zero is also a test difficult problem apart from the precision calibration of transponder and the absolute time delay of school zero antenna itself, their stated accuracy will have a strong impact on the stated accuracy of tested antenna delay, zero use apart from transponder is different from the real work situation of inter-satellite link antenna, time delay value under calibration result and inter-satellite link antenna real work state status there are differences, and without in tower Calibration Method, school zero antenna installation site difference can cause demarcating numerical value change, 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, be difficult to obtain one for testing the standard antenna of time delay, secondly, dual-mode antenna meets under far field condition, and while test by vector net analysis instrument, test stube cable or waveguide are long, under Ka frequency range working condition, the time delay calibration 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 instrument test is the group delay of a frequency range, can not correctly reflect that inter-satellite link transmits the time delay situation of the spread spectrum distance measuring signal of certain signal specific system.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, provide a kind of navigation satellite inter-satellite link antenna absolute time delay scaling method, can correctly reflect the time of day of the absolute time delay of inter-satellite link antenna in inter-satellite link circuit transmission distance measuring signal situation, obtain 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 as follows:
(1) by inter-satellite link transmitter by test cable and attenuator and inter-satellite link receiver wired connection, inter-satellite link transmitter produces inter-satellite link distance measuring signal output, inter-satellite link receiver receives inter-satellite link distance measuring signal and carries out spread spectrum range finding;
(2) second signal that second signal inter-satellite link transmitter being produced and inter-satellite link receiver produce is as two inputs of time-interval counter, be respectively used to start or stop time-interval counter counting, measure inter-satellite link transmitter and the inter-satellite link receiver time difference between second signal separately by time-interval counter;
(3) according to the measurement result of the pseudorange measurement of inter-satellite link receiver and time-interval counter, obtain the combination time delay of inter-satellite link transmitter, cable, attenuator, inter-satellite link receiver, when deduction attenuator, delay the null value that obtains measuring passage;
(4) choose at least 3 inter-satellite link antennas as antenna to be measured, antenna to be measured forms a test combination between two, in any one test combination, one of them antenna to be measured is connected with inter-satellite link transmitter, another antenna to be measured is connected with inter-satellite link receiver, distance R in any one test combination between two antennas to be measured keeps wave beam identical and two antennas to be measured mutually to aim at, wherein
λ is wavelength corresponding to frequency signal centre frequency to be measured, the diameter that D is antenna to be measured;
(5), according to the pseudorange measurement of inter-satellite link receiver, time-interval counter count value, obtain adding the combination time delay between the measurement transmitting-receiving after antenna to be measured;
(6) be free-space propagation time delay by the distance R conversion between two antennas to be measured in any one test combination, when the null value that adds the measurement passage that the combination time delay deduction step (3) between measurement after antenna to be measured transmitting-receiving obtains that step (5) is obtained and free-space propagation, delay, obtain in any one test combination two antennas to be measured separately definitely time delay and;
(7) utilize the result of step (6), obtain the absolute time delay of each antenna to be measured by the form of solving equations.
The present invention's advantage is compared with prior art:
(1) in the inventive method, test signal adopts inter-satellite link transmitter to generate, signal transmission system is consistent in-orbit with inter-satellite link for the working frequency range of test signal, signal system, utilize inter-satellite link receiver to carry out spread spectrum distance measuring method, carry out pseudo range measurement, the time delay can truly reflect inter-satellite link antenna receiving-sending inter-satellite link signal time;
(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 the measure error problem that standard antenna design parameter is not up to standard brought;
(3) calibration process of time delay of the present invention and the null value of test channel are demarcated and all between inter-satellite link transmitter and receiver, are carried out, do not need to use the long cable of ka frequency range or long wave to lead, avoided the long cable of ka frequency range or long waveguide delay to demarcate the large error condition occurring;
(4) in the inventive method, do not need to use null value transponder, 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 affects inter-satellite link antenna delay stated accuracy.
Accompanying drawing explanation
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.Second poor between the pps pulse per second signal that wherein time-interval counter generates for the pps pulse per second signal He Xingjian road receiver of measuring inter-satellite link transmitter and generating.
The key step of the inventive method is as follows:
(1) the multiple identical inter-satellite link antennas of navigation satellite configuration, the working frequency range of each antenna is consistent, the signal system of antenna transmission is consistent, in the case of not having reference antenna that transmit after receive time delay demarcated, number of antennas to be measured is no less than 3, antenna to be measured is inactive component, and the absolute time delay of same antenna reception to be measured and transmitting is consistent.
(2) null value of measuring passage is calibrated.By inter-satellite link transmitter by test cable and attenuator and inter-satellite link receiver wired connection.Inter-satellite link transmitter output inter-satellite link distance measuring signal, 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, inter-satellite link receiver receives distance measuring signal and carries out spread spectrum range finding, attenuator is decayed to inter-satellite link transmitter output signal, guarantees that the signal level that is input to inter-satellite link receiver is at normal range of receiving.
Inter-satellite link receiver receives the spread spectrum distance measuring signal of inter-satellite link transmitter output, signal is carried out to acquisition and tracking and the data processing of filtering, down-conversion, spread-spectrum signal, obtain pseudo-range measurements, time-interval counter is measured the time difference between the pps pulse per second signal of inter-satellite link transmitter generation and the pps pulse per second signal of inter-satellite link receiver generation, the pseudo-range measurements obtaining at certain second moment inter-satellite link receiver deducts the second poor of pulse per second (PPS) between this moment transmitter and receiver, the combination latency measurement value T between being received and dispatched
z1.
Measure the time delay T of attenuator in the center frequency point of inter-satellite link signal with vector net analysis instrument
z2.Measure the null value T of passage
zcan be calculated as follows:
T
Z＝T
Z1-T
Z2 (1)
(3) be connected with inter-satellite link transmitter as transmitting antenna with antenna 1, antenna 2 is connected with inter-satellite link receiver as reception antenna, the distance R between two antennas to be measured, wherein
λ is wavelength corresponding to frequency signal centre frequency to be measured, the diameter that D is antenna to be measured, and the wave beam of two antennas to be measured aims at mutually.According to the measurement result of the pseudorange measurement of inter-satellite link receiver and time-interval counter, the combination latency measurement value T between being received and dispatched
c1.Air line distance R between accurate measurement antenna 1 and antenna 2, converts as radio wave is at free-space propagation time delay T
d, that is:
T
D＝c/R (2)
In formula, c is the light velocity;
Measure passage null value, deduct free-space propagation delay volume again combining time delay deduction between the transmitting-receiving measuring, obtain the absolute time delay T of antenna 1
1with the absolute time delay T of antenna 2
2combination time delay value.That is:
T
1+T
2＝T
C1-T
Z-T
D (3)
(4) use antenna 3 as transmitting antenna, antenna 2 is as reception antenna, and repeating step (3), obtains the absolute time delay T of antenna 3
3with the absolute time delay T of antenna 2
2combination time delay value.
T
3+T
2＝T
C2-T
Z-T
D (4)
T in formula
c2for the combination latency measurement value between transmitting-receiving.
(5) use antenna 3 as transmitting antenna, antenna 1 is as reception antenna, and repeating step (3), obtains the absolute time delay T of antenna 3
3with the absolute time delay T of antenna 1
1combination time delay value.
T
3+T
1＝T
C3-T
Z-T
D (5)
T in formula
c3for the combination latency measurement value between 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:
Solving equation group, obtains the absolute time delay of transmitting-receiving of each antenna:
Can resolve thus the absolute time delay of each antenna.
(5) when number of antennas is during more than three, in newly-increased antenna and above-mentioned three antennas, any one antenna is as matching with reference to antenna, transmitting-receiving each other, measure combination time delay value, deduct absolute time delay, the free-space propagation time delay of reference antenna and measure passage null value, obtain the absolute time delay of newly-increased antenna, suppose with antenna 1 conduct with reference to antenna, for the transmitting of calibration mold analog signal, repeating step (3), obtains the newly-increased absolute time delay T of antenna
nwith the absolute time delay T of antenna 1
1combination time delay value.
T
n+T
1＝T
Cn-T
Z-T
D (10)
T in formula
cnfor the combination latency measurement value between antenna 1 and 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 not being described in detail in specification of the present invention belongs to those skilled in the art's known technology.
Claims (1)
1. the absolute time delay scaling method of navigation satellite inter-satellite link antenna, is characterized in that step is as follows:
(1) by inter-satellite link transmitter by test cable and attenuator and inter-satellite link receiver wired connection, inter-satellite link transmitter produces inter-satellite link distance measuring signal output, inter-satellite link receiver receives inter-satellite link distance measuring signal and carries out spread spectrum range finding;
(2) second signal that second signal inter-satellite link transmitter being produced and inter-satellite link receiver produce is as two inputs of time-interval counter, be respectively used to start or stop time-interval counter counting, measure inter-satellite link transmitter and the inter-satellite link receiver time difference between second signal separately by time-interval counter;
(3) utilize the pseudo-range measurements of certain second moment inter-satellite link receiver to deduct the measured value of this moment time-interval counter, obtain the combination time delay of inter-satellite link transmitter, cable, attenuator, inter-satellite link receiver, when deduction attenuator, delay the null value that obtains measuring passage;
(4) choose at least 3 inter-satellite link antennas as antenna to be measured, antenna to be measured forms a test combination between two, in any one test combination, one of them antenna to be measured is connected with inter-satellite link transmitter, another antenna to be measured is connected with inter-satellite link receiver, distance R in any one test combination between two antennas to be measured keeps wave beam identical and two antennas to be measured mutually to aim at, wherein
λ is wavelength corresponding to frequency signal centre frequency to be measured, the diameter that D is antenna to be measured; Described inter-satellite link antenna is identical, and the working frequency range of each inter-satellite link antenna is consistent, and the signal system of each inter-satellite link antenna transmission is consistent, and the absolute time delay of same inter-satellite link antenna reception and transmitting is consistent;
(5), according to the pseudorange measurement of inter-satellite link receiver, time-interval counter count value, obtain adding the combination time delay between the measurement transmitting-receiving after antenna to be measured;
(6) be free-space propagation time delay by the distance R conversion between two antennas to be measured in any one test combination, when the null value that adds the measurement passage that the combination time delay deduction step (3) between measurement after antenna to be measured transmitting-receiving obtains that step (5) is obtained and free-space propagation, delay, obtain in any one test combination two antennas to be measured separately definitely time delay and;
(7) utilize the result of step (6), obtain the absolute time delay of each antenna to be measured by the form of solving equations.
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| CN103001709B (en) * | 2012-09-29 | 2015-07-08 | 西安空间无线电技术研究所 | Antenna delay test method |
| CN103117822B (en) * | 2013-01-25 | 2014-12-31 | 华中科技大学 | Device for receiver channel group delay measurement |
| CN104917573B (en) * | 2015-05-13 | 2016-08-17 | 北京理工大学 | The absolute time delay calibrating installation of a kind of antenna beam synthesis phase 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 |
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| CN112751605B (en) * | 2020-12-29 | 2022-12-27 | 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 |
| 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 |
| 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 |
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 (8)
| Title |
|---|
| "absolute calibration of a geodetic time transfer system";Plumb, J.et al.;《IEEE Transactions on Ultrasonics, Ferroelectrics and Frequency Control》;20051130;第52卷(第11期);全文 * |
| Plumb, J.et al.."absolute calibration of a geodetic time transfer system".《IEEE Transactions on Ultrasonics, Ferroelectrics and Frequency Control》.2005,第52卷(第11期), |
| 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》.2010,(第10期), |
| 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》.2010,(第10期), * |
| 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》.2009,(第1期), |
| 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》.2009,(第1期), * |
| 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》.2010,第40卷(第5期), |
| 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》.2010,第40卷(第5期), * |
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