CN107659366A - The method of time difference measurement system channel null value between real-time calibration star - Google Patents
The method of time difference measurement system channel null value between real-time calibration star Download PDFInfo
- Publication number
- CN107659366A CN107659366A CN201710610019.1A CN201710610019A CN107659366A CN 107659366 A CN107659366 A CN 107659366A CN 201710610019 A CN201710610019 A CN 201710610019A CN 107659366 A CN107659366 A CN 107659366A
- Authority
- CN
- China
- Prior art keywords
- satellite
- time difference
- channel
- time
- star
- 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
Links
Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04J—MULTIPLEX COMMUNICATION
- H04J3/00—Time-division multiplex systems
- H04J3/02—Details
- H04J3/06—Synchronising arrangements
- H04J3/0635—Clock or time synchronisation in a network
- H04J3/0638—Clock or time synchronisation among nodes; Internode synchronisation
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B17/00—Monitoring; Testing
- H04B17/30—Monitoring; Testing of propagation channels
- H04B17/309—Measuring or estimating channel quality parameters
- H04B17/364—Delay profiles
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/18521—Systems of inter linked satellites, i.e. inter satellite service
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04J—MULTIPLEX COMMUNICATION
- H04J3/00—Time-division multiplex systems
- H04J3/02—Details
- H04J3/06—Synchronising arrangements
- H04J3/0635—Clock or time synchronisation in a network
- H04J3/0682—Clock or time synchronisation in a network by delay compensation, e.g. by compensation of propagation delay or variations thereof, by ranging
Landscapes
- Engineering & Computer Science (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Physics & Mathematics (AREA)
- Quality & Reliability (AREA)
- Electromagnetism (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Synchronisation In Digital Transmission Systems (AREA)
Abstract
A kind of method of time difference measurement system channel null value between a kind of real-time calibration star disclosed by the invention, it is desirable to provide error link is few, the high zero method of time synchronized measurement precision.The technical scheme is that：Two-way time difference measurement system between star is built using two-way one way e measurement technology, then, the radio frequency closed loop that a baseband signal processing module is shared according to two-way time difference measurement system design system transceiver channel between star is tested oneself model；Under radio frequency closed loop self test mode, choose satellite A or satellite B transmitting cycle tests, tested oneself loop by the radio frequency of system transceiver channel, high-precision phase position estimation is carried out to the signal received through baseband signal processing module, the cycle tests timing signal sent in conjunction with base band is calculated, the time delay value that system receives transmission channel is obtained, satellite system is according to the time delay value being calculated to transceiver channel null value real-time calibration.Present invention decreases the error that system transceiver channel null value introduces.
Description
Technical field
The present invention relates to a kind of method of time difference measurement system channel null value between real-time calibration star.
Background technology
With the development of constellation, a group of stars, Satellite Formation Flying, satellite distributed networking work has become Modern Satellite development
Trend, in fields such as communication, remote sensing, navigation and electronic reconnaissances by more and more important effect.By each satellite system network
Change, realize the information sharing between each satellite, meet every military requirement of satellite.In recent years, space technology was applied to
Fruit all generates tremendous influence in communication, navigator fix, ocean, resource, meteorology, space science detection etc..Single boat
Its device can not meet inexpensive, highly reliable, the fast and efficiently demand of space technology requirement.
The relative distance and the accurate measurement of the clock face time difference of Aerospace Satellite, it is the important foundation for completing particular task.Satellite
Between time difference measurement be realize satellite Autonomous measurement, the core technology of independent navigation, and ensure distributed networked research center function
The important foundation of realization.It is the collaboration for completing distributed satellites to realize between accurate star time difference measurement and establish information exchange link
Control, improve Autonomous survival of satellite and the key of autonomous management ability.Time difference measurement is carried out using two-way one way technology, is to realize
Precise synchronization and the effective way of relative ranging between star.Distance and time difference measurement between high-precision star are to ensure to form into columns
The important foundation that flight constellation systems function is realized, is undoubtedly a kind of simple and easy method depending on baseband signal receiver altogether using GPS, but
It is that need to rely on GPS navigation satellite system.
During carrying out time difference measurement between star, accurate passage null value demarcation is that system realizes the important of high-acruracy survey
Link.Satellite borne equipment passage null value refers to cause the equipment delay for setting system deviation, includes transmission channel and receiving channel
The time delay error that the devices such as wave filter, amplifier, frequency mixer introduce.The absolute latency measurement of passage null value is satellite relative measurement
The premise of positioning, its stated accuracy will directly affect the relative accuracy of satellite.It is existing at present to be demarcated for passage null value
Method has：TT＆C Transponder and ground control station system for traditional star, but it is not particularly suited for time difference measurement mark between star
It is fixed；Also have in addition in the two-way temporal frequency transmission system being directed between earth station, earth station equipment time-delay calibration, it is also and uncomfortable
Demarcated for real-time device between star.
The content of the invention
The purpose of the present invention is for influence of the channel time delay to measurement in time difference measurement system between star, there is provided a kind of error
Link is few, convenient and swift, and time synchronized measurement precision is high, the zero method of time difference measurement system channel between real-time calibration star.
Technical scheme is used by the present invention solves prior art problem：Time difference measurement system between a kind of real-time calibration star
The method of passage null value, it is characterised in that comprise the following steps：The two-way time difference surveys between building star using two-way one way e measurement technology
Amount system, then, a baseband signal processing module is shared according to two-way time difference measurement system design system transceiver channel between star
Radio frequency closed loop test oneself model；Under radio frequency closed loop self test mode, satellite A or satellite B transmitting cycle tests is chosen, passes through system
The radio frequency of transceiver channel is tested oneself loop, and high-precision phase position estimation is carried out to the signal received through baseband signal processing module, then
With reference to base band send cycle tests timing signal calculated, obtain system receive transmission channel time delay value, satellite system according to
According to the time delay value being calculated to system transceiver channel null value real-time calibration.
The present invention has the advantages that compared to prior art：
Error link is few.The present invention is using two-way time difference measurement system between two-way one way e measurement technology structure star, then, according to star
Between two-way time difference measurement system design system transceiver channel share the radio frequency closed loop of a baseband signal processing module and test oneself model；
Model completion Time Delay of Systems test is tested oneself with demarcating by radio frequency closed loop, realizes system transceiver channel null value real-time calibration, error
Link is few, can be tested oneself on satellite, and satellite system transceiver channel is demarcated, and is more suitable for time difference measurement between star.
It is convenient and swift.Radio frequency closed loop of the present invention tests oneself model can be periodically using transmitting test sequence caused by satellite base band
Row, real-time calibration is carried out to system transceiver channel null value, base band periodic transmission cycle tests is to satellite system transceiver channel null value
Demarcated, to the more convenient of satellite system passage null value demarcation.
Time synchronized measurement precision is high.The present invention chooses satellite A or satellite B transmitting under radio frequency closed loop self test mode
Cycle tests, reduce due to influence of the external environment (such as temperature, vibration, electromagnetic field) to passage null value.Satellite launch is surveyed
Try the signal of sequence to test oneself loop by the test oneself radio frequency of model transceiver channel of radio frequency closed loop, docked through baseband signal processing module
The signal received carries out high-precision phase position estimation, and the cycle tests timing signal sent in conjunction with base band is calculated, and is
System receives the time delay value of transmission channel, reduces the error of system transceiver channel null value introducing, and the time improved between satellite is same
Pacing accuracy of measurement.
Precise synchronization is surveyed with relative between the present invention can be applied to the star of a group of stars, constellation, satellite formation flying
Amount, also can expanded application in technical fields such as unmanned plane formation, opportunity of combat networkings.
Brief description of the drawings
The present invention is further described with reference to the accompanying drawings and examples.
The workflow diagram of Fig. 1 passage null value real-time calibrations of time difference measurement system between star of the present invention.
The component relationship schematic diagram of Fig. 2 two-way time difference measurement systems between star of the present invention.
Fig. 3 is the two-way time difference measurement system sequence schematic diagram of the present invention.
Fig. 4 is that radio frequency closed loop of the present invention is tested oneself model schematic.
Embodiment
Reference picture 1.According to the present invention, two-way time difference measurement system between star is built using two-way one way e measurement technology, then,
The radio frequency closed loop of one baseband signal processing module is shared certainly according to two-way time difference measurement system design system transceiver channel between star
Survey model；Under radio frequency closed loop self test mode, satellite A or satellite B transmitting cycle tests is chosen, passes through penetrating for system transceiver channel
Frequency is tested oneself loop, is carried out high-precision phase position estimation to the signal received through baseband signal processing module, is sent in conjunction with base band
Cycle tests timing signal calculated, obtain the time delay value that system receives transmission channel, satellite system is according to being calculated
Time delay value is to transceiver channel null value real-time calibration.
Reference picture 2, Fig. 3.Satellite A and satellite B is utilized respectively respective equipment transmission timing signal, and receives and come from other side
Timing signal.Two-way time difference measurement system between the star built according to two-way one way e measurement technology, including：Satellite A's and satellite B
Two-way time difference measurement circuit between star, wherein, the time reference module provided with connection time difference measurement module, time reference module passes through
The closed loop of modulator test loop in sequential series, demodulator and time difference measurement module transfer Timing Signal, modulator pass through
The connected demodulator of transmission channel connection duplexer connection receiving channel forms two-way time difference measurement system between satellite A and satellite B stars.
Between star in two-way time difference measurement system, satellite A and B send timing signal according to respective time reference respectively,
And the signal that other side sends over is received simultaneously.Satellite A and B can obtain according to satellite A and satellite B bidirectional measurement principle timing diagram
The time difference that the local clock pulses and B stars of satellite A measurements send signal is T1, local clock pulses and A that satellite B measurements obtain
The time difference that star sends signal is T2,
In formula, τBAIt is timing signal from satellite B to satellite A propagation time；τABIt is timing signal from satellite A to satellite B's
Propagation time；τAFor satellite A transmission channel time delay；rAFor satellite A receiving channel time delay；τBFor satellite B transmission channel when
Prolong；rBFor satellite B receiving channel time delay；Δ t is the satellite A and satellite B time difference.
When satellite A and satellite B sends timing signal in synchronization, road is propagated between the star of two stars of satellite A and satellite B
Footpath is symmetrical or near symmetrical, it is believed that τBAAnd τABIt is equal.Two formulas in formula (1) subtract each other can obtain satellite A and
The satellite B time difference：
According to time difference measurement system and transceiver channel null value real-time calibration, the radio frequency closed loop shown in structural map 3 is tested oneself model.
Reference picture 3, design radio frequency closed loop model of testing oneself include：Sequentially gone here and there between baseband signal processing module and transmitting antenna
The radio frequency transmitting channel that digital analog converter DAC, the emitting module of connection are formed, it is suitable between reception antenna and baseband signal processing module
The radio frequency reception channel that secondary series connection receiving unit, analog-digital converter ADC are formed, radio frequency transmitting channel and radio frequency reception channel share
One baseband signal processing module.Under radio frequency closed loop self test mode, radio frequency transmitting channel and radio frequency reception channel work simultaneously,
Satellite A transmitting cycle tests is chosen, by radio frequency transmitting channel and the radio frequency closed loop of radio frequency reception channel, base band signal process mould
Block sends cycle tests by base band signal process machine, by digital analog converter DAC, radio frequency transmitting channel emitting module, transmitting
Launch after its wire delay, tested oneself loop by radio frequency, the signal of transmitting antenna can be received directly by reception antenna end；Pass through again
Radio frequency reception channel receiving unit, analog-digital converter ADC are crossed, baseband signal processing module enters to the radiofrequency signal of testing oneself received
Row processing is baseband signal, and base band signal process machine carries out high-precision phase position estimation, baseband signal to the baseband signal received
The timing signal that receiver is sent in conjunction with baseband module, be calculated satellite A radio frequency transmitting channel null value τAWith penetrate
Frequency receiving channel null value rA, satellite launch passage and receiving channel time delay value are obtained, and passage null value carries out real-time calibration.Together
Reason, satellite B progress identical, which tests oneself to demarcate, obtains satellite B transmission channel null value τBWith receiving channel null value rB。
External environment residing for satellite, such as temperature, electromagnetic field, vibration can change, it is therefore desirable to periodically to equipment
Passage null value demarcated.In order to reduce the error of system transceiver channel null value introducing, radio frequency closed loop model of testing oneself periodically weighs
Multiple above-mentioned steps, cycle tests is launched using the baseband module of satellite real-time calibration is carried out to system transceiver channel null value.
Claims (10)
1. a kind of method of time difference measurement system channel null value between real-time calibration star, it is characterised in that comprise the following steps：Using
Two-way time difference measurement system between two-way one way e measurement technology structure star, then, according to two-way time difference measurement system design system between star
The radio frequency closed loop that system transceiver channel shares a baseband signal processing module is tested oneself model；Under radio frequency closed loop self test mode, choosing
Take satellite A or satellite B to launch cycle tests, tested oneself loop by the radio frequency of system transceiver channel, through baseband signal processing module
High-precision phase position estimation is carried out to the signal received, the cycle tests timing signal sent in conjunction with base band is calculated, and is obtained
The time delay value of transmission channel is received to system, satellite system is according to the time delay value being calculated to transceiver channel null value real-time calibration.
2. the method for time difference measurement system channel null value between real-time calibration star as claimed in claim 1, it is characterised in that：Satellite
A and satellite B is utilized respectively respective equipment transmission timing signal, and receives the timing signal from other side.
3. the method for time difference measurement system channel null value between real-time calibration star as claimed in claim 1, it is characterised in that：Between star
Two-way time difference measurement system, including：Two-way time difference measurement circuit between satellite A and satellite B star, wherein, surveyed provided with the connection time difference
The time reference module of module is measured, time reference module passes through modulator test loop in sequential series, demodulator and time difference measurement
The closed loop of module transfer Timing Signal, modulator connect duplexer by transmission channel and connect the connected demodulator of receiving channel
Form two-way time difference measurement system between satellite A and satellite B stars.
4. the method for time difference measurement system channel null value between real-time calibration star as claimed in claim 1, it is characterised in that：In star
Between in two-way time difference measurement system, satellite A and B send timing signal according to respective time reference respectively, and receive simultaneously pair
The signal just sended over.
5. the method for time difference measurement system channel null value between real-time calibration star as claimed in claim 1, it is characterised in that：Satellite
A and B can obtain the local clock pulses of satellite A measurements according to satellite A and satellite B bidirectional measurement principle timing diagram and B stars are sent
The time difference of signal is T1, the time difference of local clock pulses and A stars transmission signal that satellite B measurements obtain is T2,
In formula, τBAIt is timing signal from satellite B to satellite A propagation time；τABIt is timing signal from satellite A to satellite B biography
Between sowing time；τAFor satellite A transmission channel time delay；rAFor satellite A receiving channel time delay；τBFor satellite B transmission channel when
Prolong；rBFor satellite B receiving channel time delay；Δ t is the satellite A and satellite B time difference.
6. the method for time difference measurement system channel null value between real-time calibration star as claimed in claim 5, it is characterised in that：When defending
Star A and satellite B when synchronization sends timing signal, between the star of two stars of satellite A and satellite B propagation path be it is symmetrical or
Near symmetrical, τBAAnd τABIt is equal.
7. the method for time difference measurement system channel null value between real-time calibration star as claimed in claim 5, it is characterised in that：By formula
(1) Two formulas are subtracted each other to obtain satellite A and satellite the B time difference：
8. the method for time difference measurement system channel null value between real-time calibration star as claimed in claim 1, it is characterised in that：Radio frequency
Closed loop model of testing oneself includes：Digital analog converter DAC in sequential series, transmitting group between baseband signal processing module and transmitting antenna
The radio frequency transmitting channel that part is formed, receiving unit in sequential series, analog-to-digital conversion between reception antenna and baseband signal processing module
The radio frequency reception channel that device ADC is formed, radio frequency transmitting channel and radio frequency reception channel share a baseband signal processing module.
9. the method for time difference measurement system channel null value between real-time calibration star as claimed in claim 1, it is characterised in that：Base band
The cycle tests that signal processing module is sent by base band signal process machine, sent out by digital analog converter DAC, radio frequency transmitting channel
Launch after penetrating component, transmitting antenna delay, tested oneself loop by radio frequency, the signal of transmitting antenna is directly by reception antenna end
Receive；Tested oneself again by radio frequency reception channel receiving unit, analog-digital converter ADC, baseband signal processing module to what is received
It is baseband signal that radiofrequency signal, which carries out processing,.
10. the method for time difference measurement system channel null value between real-time calibration star as claimed in claim 1, it is characterised in that：Base
The baseband signal that band signal processor pair receives carries out high-precision phase position estimation, and baseband signal receiver is in conjunction with baseband module
The timing signal of transmission, be calculated satellite A radio frequency transmitting channel null value τAWith radio frequency reception channel null value rA, obtain
Satellite launch passage and receiving channel time delay value, and passage null value carries out real-time calibration, similarly, satellite B carries out identical and tested oneself
Demarcation obtains satellite B transmission channel null value τBWith receiving channel null value rB。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710610019.1A CN107659366A (en) | 2017-07-25 | 2017-07-25 | The method of time difference measurement system channel null value between real-time calibration star |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710610019.1A CN107659366A (en) | 2017-07-25 | 2017-07-25 | The method of time difference measurement system channel null value between real-time calibration star |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107659366A true CN107659366A (en) | 2018-02-02 |
Family
ID=61127863
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710610019.1A Pending CN107659366A (en) | 2017-07-25 | 2017-07-25 | The method of time difference measurement system channel null value between real-time calibration star |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107659366A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109347535A (en) * | 2018-07-02 | 2019-02-15 | 成都国恒空间技术工程有限公司 | A kind of method that the non-blind demodulation of PCMA sends signal delay adjustment |
| 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 |
| CN111614407A (en) * | 2020-03-30 | 2020-09-01 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Automatic monitoring method for zero value of base band of aircraft measurement and control system |
| CN111638502A (en) * | 2020-04-29 | 2020-09-08 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Time-base-based transmitting one-way zero-value ranging system for measurement and control communication ground station |
| CN112468243A (en) * | 2020-11-20 | 2021-03-09 | 西安空间无线电技术研究所 | Zero value measuring method and system for distance measuring equipment |
| CN113959431A (en) * | 2021-10-22 | 2022-01-21 | 浙江大学 | High-precision inter-satellite distance and time difference combined measurement method |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030138189A1 (en) * | 2002-01-22 | 2003-07-24 | D. A. Rockwell | Optical cross-connect switch for high-bit-rate space-based communications |
| CN104935391A (en) * | 2015-04-27 | 2015-09-23 | 中国电子科技集团公司第五十四研究所 | Self-closed-loop time synchronization method of indoor pseudo-satellites |
-
2017
- 2017-07-25 CN CN201710610019.1A patent/CN107659366A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030138189A1 (en) * | 2002-01-22 | 2003-07-24 | D. A. Rockwell | Optical cross-connect switch for high-bit-rate space-based communications |
| CN104935391A (en) * | 2015-04-27 | 2015-09-23 | 中国电子科技集团公司第五十四研究所 | Self-closed-loop time synchronization method of indoor pseudo-satellites |
Non-Patent Citations (1)
| Title |
|---|
| 刘长水等: "星间时间同步系统及零值标定研究", 《宇航计测技术》 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109347535A (en) * | 2018-07-02 | 2019-02-15 | 成都国恒空间技术工程有限公司 | A kind of method that the non-blind demodulation of PCMA sends signal delay adjustment |
| 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 |
| CN111614407A (en) * | 2020-03-30 | 2020-09-01 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Automatic monitoring method for zero value of base band of aircraft measurement and control system |
| CN111614407B (en) * | 2020-03-30 | 2022-04-01 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Automatic monitoring method for zero value of base band of aircraft measurement and control system |
| CN111638502A (en) * | 2020-04-29 | 2020-09-08 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Time-base-based transmitting one-way zero-value ranging system for measurement and control communication ground station |
| CN111638502B (en) * | 2020-04-29 | 2023-09-05 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Emission unidirectional zero value ranging system based on time base for measurement and control communication ground station |
| CN112468243A (en) * | 2020-11-20 | 2021-03-09 | 西安空间无线电技术研究所 | Zero value measuring method and system for distance measuring equipment |
| CN112468243B (en) * | 2020-11-20 | 2022-06-03 | 西安空间无线电技术研究所 | Zero value measuring method and system for distance measuring equipment |
| CN113959431A (en) * | 2021-10-22 | 2022-01-21 | 浙江大学 | High-precision inter-satellite distance and time difference combined measurement method |
| CN113959431B (en) * | 2021-10-22 | 2023-10-03 | 浙江大学 | High-precision inter-satellite distance and time difference combined measurement method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107659366A (en) | The method of time difference measurement system channel null value between real-time calibration star | |
| CN107664947B (en) | Device and method for calibrating satellite two-way time comparison system | |
| CN102023290B (en) | High-precision distributed pulse signal time difference of arrival detection system | |
| CN107395309A (en) | High accuracy relative ranging and method for synchronizing time based on inter-satellite link | |
| CN105911858B (en) | A kind of subnanosecond grade remote time comparison/transmission system error testing method | |
| CN109031198B (en) | Method for realizing positioning by using non-cooperative satellite signal | |
| CN102540227A (en) | Method and system for the geolocation of a radio beacon in a search and rescue system | |
| JP2015155897A (en) | Radio frequency method and system for determining, by pair of spacecrafts, relative angular position between plurality of remote spacecrafts | |
| CN107070567B (en) | Satellite ground station inter-station time delay calibration method based on pseudo satellite | |
| CN103097906A (en) | Method and apparatus for determining the position and orientation of a mobile transmitter | |
| CN103344942A (en) | Control node, method and system for asynchronous positioning | |
| CN101629999A (en) | Method for communicating and positioning target by satellites | |
| CN110018505A (en) | A method of ship location is realized using telecommunication satellite interferometry | |
| CN104730551B (en) | Space-ground bistatic differential interferometry baseline coordinate and deformation quantity measurement method | |
| CN108613621A (en) | GNSS receiver array and high-precision deformation monitoring method based on GNSS receiver array | |
| CN109085563B (en) | WLAN ranging method based on software radio platform | |
| CN103257340B (en) | Method for calibrating amplitude consistency of a plurality of ground receivers with radar satellite | |
| CN104702401B (en) | A kind of synchronous method of ground base navigation system time | |
| CN109752737B (en) | Preprocessing method for inter-satellite Ka-band bidirectional measurement pseudo range of navigation satellite | |
| CN111638502A (en) | Time-base-based transmitting one-way zero-value ranging system for measurement and control communication ground station | |
| CN201945685U (en) | High-accuracy time difference of arrival (TDOA) measuring system for distribution type pulse signals | |
| CN107390506B (en) | Real-time measurement device and method for time comparison precision of time service system | |
| CN104459682A (en) | Distance measurement method for automatically eliminating dynamic distance zero value | |
| RU2478979C1 (en) | Range radiotechnical system of short-range navigation of aircrafts | |
| Yaowei et al. | Integrated method for measuring distance and time difference between small satellites |
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: 20180202 |
|
| WD01 | Invention patent application deemed withdrawn after publication |