CN113359160B - Geosynchronous orbit GNSS orbit determination data quality checking method - Google Patents
Geosynchronous orbit GNSS orbit determination data quality checking method Download PDFInfo
- Publication number
- CN113359160B CN113359160B CN202110718321.5A CN202110718321A CN113359160B CN 113359160 B CN113359160 B CN 113359160B CN 202110718321 A CN202110718321 A CN 202110718321A CN 113359160 B CN113359160 B CN 113359160B
- Authority
- CN
- China
- Prior art keywords
- gnss
- orbit
- orbit determination
- data
- determination data
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 238000000034 method Methods 0.000 title claims abstract description 23
- 238000005259 measurement Methods 0.000 claims abstract description 34
- 238000001514 detection method Methods 0.000 claims abstract description 8
- 238000000926 separation method Methods 0.000 claims description 3
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Images
Classifications
-
- 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
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/23—Testing, monitoring, correcting or calibrating of receiver elements
-
- 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
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/35—Constructional details or hardware or software details of the signal processing chain
- G01S19/37—Hardware or software details of the signal processing chain
Landscapes
- Engineering & Computer Science (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Signal Processing (AREA)
- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The invention discloses a geosynchronous orbit GNSS orbit determination data quality checking method, which specifically comprises the following steps: firstly, performing time scale detection, coordinate system judgment and quality statistics on GNSS orbit determination data, performing precise orbit calculation by adopting the GNSS orbit determination data, and if the orbit determination result of the GNSS data can be converged, keeping the orbit determination result; if not, discarding; performing combined orbit determination on the GNSS orbit determination data and the foundation USB external measurement data, wherein if the orbit determination result can be converged and the utilization rate exceeds 80%, the GNSS orbit determination data is reliable and can be normally used; otherwise, calibrating the GNSS orbit determination data. The method for checking the quality of the orbit determination data of the GNSS of the geosynchronous orbit can greatly improve the timeliness and the accuracy of the orbit determination of the GNSS data of the geosynchronous orbit, effectively relieve the tension of ground measurement and control resources, and have certain economic benefit on the in-orbit running of the geosynchronous orbit.
Description
Technical Field
The invention belongs to the technical field of space surveying and controlling, and particularly relates to a geosynchronous orbit GNSS orbit determination data quality checking method.
Background
At present, the technology of determining the orbit of a Low Earth Orbit (LEO) satellite by utilizing GNSS high-precision measurement data is mature, and the orbit determination precision can reach centimeter level. For the geosynchronous orbit satellite, the ground equipment can be simplified by utilizing the GNSS measurement data for orbit determination, and the orbit determination precision is improved. However, when the aircraft orbit is higher than the GNSS satellites, measurements need to be made using the "leaky" signals of the GNSS satellite transmitting antennas. Considering that the intensity of a 'leakage signal' is weak and the acting distance is increased, higher requirements are provided for the sensitivity, the dynamic property and the visibility of a GNSS receiver, so that the geosynchronous orbit GNSS orbit data quality checking method is provided for the characteristics that the GNSS orbit determination is still in the research and test stage and the like.
Disclosure of Invention
The invention aims to provide a quality checking method for orbit determination data of a geosynchronous orbit GNSS, which improves the timeliness and the accuracy of orbit determination of the geosynchronous orbit GNSS data.
The technical scheme adopted by the invention is that the method for checking the quality of the orbit determination data of the geosynchronous orbit GNSS is implemented according to the following steps:
step 1: GNSS orbit determination data time mark detection;
step 2: judging a GNSS orbit determination data coordinate system;
and step 3: GNSS orbit determination data quality statistics; converting the position speed of the GNSS orbit determination data into a quasi-average orbit root, and counting the average deviation delta and the standard deviation sigma of the semi-major axis of the quasi-average orbit root;
and 4, step 4: GNSS orbit determination data detection; adopting GNSS orbit determination data to perform precise orbit calculation, and if the GNSS orbit determination result can be converged, indicating that the GNSS orbit determination data is stable and has good consistency, and then keeping; if the GNSS data orbit determination result is not converged, discarding;
and 5: checking the orbit determination result of GNSS data; performing combined orbit determination on the GNSS orbit determination data obtained in the step 4 and the ground-based USB external measurement data, wherein if the orbit determination result can be converged and the utilization rate of the GNSS orbit determination data exceeds 80%, the GNSS orbit determination data is reliable and can be normally used; otherwise, the next step is carried out to judge the availability of the GNSS orbit determination data;
step 6: and calibrating the GNSS orbit determination data.
The invention is also characterized in that:
in the step 1, the method specifically comprises the following steps: determining whether the satellite GNSS orbit determination data time scale and the ground time scale are synchronous by adopting a quadratic polynomial fitting method, wherein the parameters comprise yearly yyyy, monthly mm, daily day, hour hh, min, sec, X-direction position X, Y-direction position Y, Z-direction position Z and X-direction speed V X Velocity V in Y direction Y Z direction velocity V Z 。
In the step 2, an initial orbit or a theoretically controlled orbit of a satellite-rocket separation point is utilized, orbit determination software is used for predicting a satellite ephemeris with a measurement arc section same as that of satellite downloading, a speed item of satellite downloading GNSS orbit determination data is compared with a speed item of the theoretically predicted ephemeris, and a coordinate system of the satellite downloading GNSS orbit determination data is judged according to whether magnitude of the comparison speed item is consistent or not.
In step 3, the calculation formulas of the average deviation delta and the standard deviation sigma are respectively shown as formula (1) and formula (2):
in the formula, n is the number of GNSS data points downloaded by the satellite; a is i Is the difference between the semimajor axis of the satellite quasi-average orbit number and the average value thereof,
X i is the semi-major axis of the pseudo-average orbital element of the satellite,
is the average value of the semimajor axis of the satellite quasi-average orbit root.
In step 6, the method specifically comprises the following steps: the GNSS orbit determination data quality is analyzed by using the ranging, speed measuring, azimuth angle and pitch angle data of the USB equipment; and calculating the measurement values-calculation values of the distance measurement, the speed measurement, the azimuth angle and the pitch angle according to the ground-based system precise ephemeris file, the USB measurement data file and the station address coordinate of the GNSS, counting corresponding root mean square errors, and judging whether the system difference and the random difference of the distance measurement, the speed measurement, the azimuth angle and the pitch angle data of the USB equipment are normal and reasonable.
The method for checking the quality of the geosynchronous orbit GNSS orbit determination data has the advantages that the timeliness and the accuracy of the geosynchronous orbit GNSS data orbit determination can be greatly improved, the tension of ground measurement and control resources can be effectively relieved, and certain economic benefits are brought to the on-orbit running of the geosynchronous orbit.
Drawings
FIG. 1 is a semi-major axis diagram of pseudo-average orbit roots of GNSS orbit determination data in an embodiment of the present invention.
Detailed Description
The present invention will be described in detail with reference to the following detailed description and accompanying drawings.
The invention relates to a geosynchronous orbit GNSS orbit determination data quality checking method which is implemented according to the following steps:
step 1: GNSS orbit determination data time mark detection;
the method comprises the following specific steps: determining whether the satellite GNSS orbit determination data time scale and the ground time scale are synchronous by adopting a quadratic polynomial fitting method, wherein the parameters comprise yearly yyyy, monthly mm, daily day, hour hh, min, sec, X-direction position X, Y-direction position Y, Z-direction position Z and X-direction speed V X Velocity V in Y direction Y Z direction velocity V Z ；
Step 2: judging a GNSS orbit determination data coordinate system; predicting a satellite ephemeris (comprising a J2000.0 coordinate system and a ground fixation system) with the same measurement arc section as the satellite download by using the initial orbit or the theoretically controlled orbit of the satellite-rocket separation point by using orbit determination software, comparing a speed item of the satellite download GNSS orbit determination data with a speed item of the theoretically predicted ephemeris, and judging a coordinate system of the satellite download GNSS data by judging whether the magnitude of the speed item is consistent or not;
and step 3: the method comprises the following steps of performing quality statistics on GNSS orbit determination data, converting position and speed of the GNSS orbit determination data into a quasi-average orbit number, and performing statistics on average deviation delta and standard deviation sigma of a semi-major axis of the quasi-average orbit number, wherein calculation formulas of the average deviation delta and the standard deviation sigma are respectively shown as formula (1) and formula (2):
in the formula, n is the number of points of GNSS orbit determination data downloaded by a satellite; a is i Is the difference between the semimajor axis of the satellite quasi-average orbit number and the average value thereof,
X i is the semi-major axis of the pseudo-average orbital element of the satellite,
the mean value of the semimajor axis of the satellite quasi-mean orbit number;
and 4, step 4: and detecting GNSS orbit determination data. Adopting GNSS orbit determination data to perform precise orbit calculation, and if the GNSS orbit determination result can be converged, indicating that the GNSS orbit determination data is stable and has good consistency, and then keeping; if the GNSS data orbit determination result is not converged, discarding;
when the GNSS data orbit determination result is not converged, which indicates that the GNSS measurement data in the arc segment are unavailable, the arc segment of the GNSS measurement data needs to be shortened, the length of the measurement arc segment cannot be less than 30 minutes, otherwise, the precision of satellite GNSS data orbit determination is reduced;
and 5: and checking the orbit determination result of the GNSS data. Performing combined orbit determination on the GNSS orbit determination data obtained in the step 4 and the ground-based USB external measurement data, wherein if the orbit determination result can be converged and the utilization rate of the GNSS orbit determination data exceeds 80%, the GNSS orbit determination data is reliable and can be normally used; otherwise, the next step is carried out to judge the availability of the GNSS orbit determination data;
step 6: and calibrating the GNSS orbit determination data. And analyzing the quality of GNSS measurement data by using the ranging, speed measuring, azimuth angle and pitch angle data of the USB equipment. And calculating O-C (measured value-calculated value) of the distance measurement and speed measurement and the azimuth angle and pitch angle according to the ground-based system precise ephemeris file, the USB measurement data file and the station address coordinate of the GNSS, counting corresponding root mean square errors, and judging whether the system difference and the random difference of the distance measurement, speed measurement, azimuth angle and pitch angle data of the USB equipment are normal and reasonable.
Examples
The implementation is carried out by adopting GNSS data of a certain geosynchronous satellite more than 8000 km away from the ground. The method comprises the following specific steps:
(1) GNSS data time mark detection;
(2) Judging a GNSS orbit determination data coordinate system;
(3) Performing quality statistics on GNSS orbit determination data;
(4) GNSS orbit determination data detection;
(5) Checking the orbit determination result of GNSS data;
(6) And calibrating the GNSS orbit determination data under the given convergence condition.
Quality checks were performed using one thousand more minute GNSS orbit determination data and the results are shown in figure 1 and table 1 below. It can be seen that the precision of the quasi-average orbit number semi-major axis of the GNSS orbit data for one thousand minutes or more is within 50-100m (fig. 1), the ranging, speed measuring and angle measuring conditions of three USB measuring stations of 0001, 0002 and 0003 are calibrated by using the GNSS orbit ephemeris data and are shown in table 1, as can be seen from the table, the random difference of ranging is within 30m, the random difference of speed measuring is within 1cm/s, and the angle measuring is within 200arc sec, which indicates that the calibration result is more consistent with the actual USB measurement precision;
according to the verification of the measured data, the quality checking method for the orbit determination data of the GNSS in the geosynchronous orbit is accurate and credible, and meets the orbit determination precision requirement of the geosynchronous orbit satellite.
TABLE 1 ground tracking station measurement device accuracy statistics
Claims (2)
1. A geosynchronous orbit GNSS orbit determination data quality checking method is characterized by comprising the following steps:
step 1: GNSS orbit determination data time mark detection; the method specifically comprises the following steps: determining whether the satellite GNSS orbit determination data time scale and the ground time scale are synchronous by adopting a quadratic polynomial fitting method, wherein the parameters comprise yearly yyyy, monthly mm, daily day, hour hh, min, sec, X-direction position X, Y-direction position Y, Z-direction position Z and X-direction speed V X Velocity V in Y direction Y Z direction velocity V Z ；
Step 2: judging a GNSS orbit determination data coordinate system;
predicting a satellite ephemeris with a measuring arc section which is the same as the satellite download by using an initial orbit or a theoretically controlled orbit of a satellite-rocket separation point by using orbit determination software, comparing a speed item of the satellite download GNSS orbit determination data with a speed item of the theoretically predicted ephemeris, and judging a coordinate system of the satellite download GNSS orbit determination data by judging whether the magnitude of the speed item is consistent or not;
and step 3: performing GNSS orbit determination data quality statistics; converting the position speed of the GNSS orbit determination data into a quasi-average orbit root, and counting the average deviation delta and the standard deviation sigma of the semi-major axis of the quasi-average orbit root;
and 4, step 4: GNSS orbit determination data detection; adopting GNSS orbit determination data to perform precise orbit calculation, and if the GNSS orbit determination result can be converged, indicating that the GNSS orbit determination data is stable and has good consistency, and then keeping; if the GNSS data orbit determination result is not converged, discarding;
and 5: checking the orbit determination result of GNSS data; performing combined orbit determination on the GNSS orbit determination data obtained in the step 4 and the ground-based USB external measurement data, wherein if the orbit determination result can be converged and the utilization rate of the GNSS orbit determination data exceeds 80%, the GNSS orbit determination data is reliable and can be normally used; otherwise, the next step is carried out to judge the availability of the GNSS orbit determination data;
and 6: calibrating GNSS orbit determination data; the method specifically comprises the following steps: the GNSS orbit determination data quality is analyzed by using the ranging, speed measuring, azimuth angle and pitch angle data of the USB equipment; and calculating the measurement value-calculation value of the distance measurement and speed measurement and the azimuth angle and pitch angle according to the ground-fixed system precise ephemeris file, the USB measurement data file and the station address coordinates of the GNSS, counting the corresponding root mean square error, and judging whether the system difference and the random difference of the distance measurement, speed measurement, azimuth angle and pitch angle data of the USB equipment are normal and reasonable.
2. The method as claimed in claim 1, wherein in step 3, the calculation formulas of the mean deviation Δ and the standard deviation σ are respectively expressed by the following formulas (1) and (2):
in the formula, n is the number of points of GNSS data downloaded by the satellite; a is i Is the difference between the semimajor axis of the satellite quasi-average orbit number and the average value thereof,
X i is the semi-major axis of the pseudo-average orbit number of the satellite,
is the average value of the semimajor axis of the satellite quasi-average orbit root.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110718321.5A CN113359160B (en) | 2021-06-28 | 2021-06-28 | Geosynchronous orbit GNSS orbit determination data quality checking method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110718321.5A CN113359160B (en) | 2021-06-28 | 2021-06-28 | Geosynchronous orbit GNSS orbit determination data quality checking method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113359160A CN113359160A (en) | 2021-09-07 |
| CN113359160B true CN113359160B (en) | 2022-11-29 |
Family
ID=77536815
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110718321.5A Expired - Fee Related CN113359160B (en) | 2021-06-28 | 2021-06-28 | Geosynchronous orbit GNSS orbit determination data quality checking method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113359160B (en) |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9057780B2 (en) * | 2013-04-18 | 2015-06-16 | California Institute Of Technology | Real-time and post-processed orbit determination and positioning |
| CN103424116B (en) * | 2013-07-23 | 2015-09-23 | 中国西安卫星测控中心 | A kind of geostationary satellite precise orbit determination method adapting to orbit maneuver |
| CN106338753B (en) * | 2016-09-22 | 2019-03-12 | 北京航空航天大学 | One kind being based on earth station/inter-satellite link/GNSS combined measurement geostationary orbit constellation orbit determination method |
| CN109582029A (en) * | 2018-12-28 | 2019-04-05 | 西安四方星途测控技术有限公司 | Method for determining GEO satellite orbit state through TLE data |
| CN110553653B (en) * | 2019-08-23 | 2021-04-23 | 上海航天控制技术研究所 | Spacecraft orbit determination method based on multi-source data driving |
| CN111505679B (en) * | 2020-04-20 | 2022-05-03 | 中国科学院国家空间科学中心 | Satellite-borne GNSS-based LEO initial orbit determination method |
-
2021
- 2021-06-28 CN CN202110718321.5A patent/CN113359160B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN113359160A (en) | 2021-09-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108196281B (en) | Single-frequency dynamic cycle slip detection and restoration method based on position domain curve constraint | |
| RU2479855C2 (en) | Distance dependant error mitigation in real-time kinematic positioning | |
| CN101971047A (en) | Device and method for the real-time monitoring of the integrity of a satellite navigation system | |
| CN105607093A (en) | Integrated navigation system and method for acquiring navigation coordinate | |
| CN107607969B (en) | Four-system pseudo range positioning method based on DCB correction | |
| CN109669196B (en) | Multi-antenna GNSS carrier phase precision attitude measurement method considering baseline deformation | |
| CN106052717B (en) | A kind of radio wave refractive correction effect scaling method using accurate trajectory | |
| CN107402394B (en) | Satellite-borne frequency measurement positioning error source on-orbit calibration method and device | |
| CN109613582B (en) | Vehicle-mounted real-time single-frequency meter-level pseudo-range positioning method | |
| CN110673170A (en) | Method and terminal for testing dynamic single-point positioning accuracy | |
| CN116182795B (en) | Precision measurement method for vertical section of common speed railway | |
| CN103529482A (en) | Method for determining dynamic accelerated speed of carrier precisely | |
| CN115657097A (en) | Orbit constraint-based rapid reconvergence method for orbit determination ambiguity of LEO geometric method | |
| CN110058270B (en) | Navigation deception signal generation method based on clock error fitting | |
| CN111522032A (en) | Optimization method and optimization device for Beidou third-generation system user integrity processing | |
| Li et al. | Precise orbit determination for the Haiyang-2D satellite using new onboard BDS-3 B1C/B2a signal measurements | |
| US8519886B2 (en) | System and method for using GPS interferometry to determine atmospheric conditions | |
| CN105044733B (en) | A kind of high-precision aeronautical satellite TGD parameter calibration methods | |
| CN112556636B (en) | Method for calibrating receiving antenna by using GPS data provided by satellite | |
| CN113359160B (en) | Geosynchronous orbit GNSS orbit determination data quality checking method | |
| CN209802285U (en) | Monitoring system for deformation of communication base station antenna | |
| CN106814376B (en) | Rapid and accurate centimeter-level single-point positioning method | |
| CN107478904B (en) | Atmospheric phase disturbance correction method based on satellite positioning system difference | |
| CN113777636B (en) | Double-smooth pseudo range domain detection method for GBAS ionosphere delay gradient | |
| CN111337955B (en) | Satellite-borne single-satellite frequency measurement passive positioning receiver test method |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20221129 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |