CN110426720A - Cross-Link measurement realizes the motor-driven rear quick recovery method of GEO satellite - Google Patents
Cross-Link measurement realizes the motor-driven rear quick recovery method of GEO satellite Download PDFInfo
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- 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
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/27—Acquisition or tracking or demodulation of signals transmitted by the system creating, predicting or correcting ephemeris or almanac data within the receiver
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- 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
- G01S19/33—Multimode operation in different systems which transmit time stamped messages, e.g. GPS/GLONASS
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- 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
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- 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
- G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
- G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/40—Correcting position, velocity or attitude
- G01S19/41—Differential correction, e.g. DGPS [differential GPS]
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
Abstract
The present invention provides a kind of Cross-Link measurements to realize quick recovery method after GEO satellite is motor-driven, obtains GEO satellite using inter-satellite link load and can observe data by bidirectional ranging between the star between link setup big-dipper satellite；It is reference with non-maneuver big-dipper satellite track, sets up orbit determination observational equation using its H_2O maser observed quantity between GEO satellite, satellitosis time update equation can be constructed using the motor-driven rear dynamics of orbits model of GEO satellite；In conjunction with observational equation and time update equation, motor-driven rear GEO satellite Precise Orbit is obtained as parameter to be estimated without singular point orbital tracking using six, utilize improved track, by upper note differential corrections mode or orbit prediction navigation ephemeris parameter fit approach, obtain it is motor-driven after GEO satellite location information.The present invention will effectively reduce the Beidou GEO satellite navigator fix out of service time due to caused by orbit maneuver, improve the continuity and availability of satellite navigation system service.
Description
Technical field
The present invention relates to field of satellite navigation, bidirectional measurement link realizes Beidou GEO satellite between especially a kind of application star
Its quick method for restoring navigator fix service ability after orbit maneuver.
Background technique
Beidou three generations's satellite navigation system is the Global Satellite Navigation System that China is independently built.Different from GPS,
The satellite navigation systems such as GLONASS, GALILEO, Beidou satellite navigation system use GEO/IGSO/MEO hybrid constellation configuration.North
GEO satellite struggle against as navigation constellation and also needs broadcasts navigation ephemeris, needs periodically to carry out precise orbit determination and navigation ephemeris thus
Parameter is infused on updating.However due to geostationary orbits resource constraint, GEO satellite is in order to keep rail position to need periodically to carry out
Orbit maneuver, orbit maneuver mismatch the GEO broadcast ephemeris track for regularly updating upper note and actual track, broadcast orbital
Precision is unsatisfactory for user's service precision index request.Need to carry out the motor-driven rear orbit determination of GEO satellite and orbit prediction, thus so as to fast
Quick-recovery GEO satellite navigator fix service ability.Currently, the fast quick-recovery of Beidou GEO track relies primarily on ground monitoring station L-band
Pseudorange or carrier phase observe data.Since GEO satellite orbit altitude is higher, China's regional monitoring station observes GEO satellite several
What structure is poor (parameter containing clock deviation falls to position DOP value 1000 or so), and therefore, it is necessary to the sights by 24 hours or more long periods
Measured data accumulation can meet orbit determination accuracy requirement, even if increasing using star time synchronization data eliminates clock deviation, also at least need
The data accumulation for wanting 4 hours or more.Longer track recovery time directly affects the continuity and availability of GEO satellite service.
Summary of the invention
For overcome the deficiencies in the prior art, the present invention provides a kind of using Bidirectional observation data between star, at filtering
The method that reason mode determines GEO satellite navigation ephemeris orbital parameters, it is fast after can be realized Beidou three generations's GEO satellite orbit maneuver
Quick-recovery shortens the navigation Service break period, improves GEO satellite service continuity and availability.
The technical solution adopted by the present invention to solve the technical problems the following steps are included:
(1) the Ka wave band inter-satellite link load carried using Beidou three generations navigation satellite obtains the two-way essence between satellite
Close ranging observed quantity；
(2) bidirectional ranging observed quantity star is pre-processed, obtains moment star spacing；
(3) not generate the Beidou navigation satellite position of orbit maneuver as reference, it is accurate fixed to be constructed using moment star spacing
Rail measurement updaue equation；
(4) the main perturbation power magnitude Analysis result being subject to using GEO satellite constructs GEO satellite kinetic model as foundation,
And then form precise orbit determination time update equation；
(5) combination resolves GEO satellite machine using EKF filter method using measurement equation and time update equation
Precise Orbit parameter after dynamic；
(6) satellite orbit is updated using upper note differential corrections mode in the motor-driven rear setting period, is more than after setting the period
By carrying out orbit prediction and ephemeris fitting to GEO satellite Precise Orbit, improved GEO satellite radio news program is generated, so
It is periodically upper afterwards to infuse.
Beidou GEO satellite carries spaceborne Ka distance-measuring equipment in the step (1), opens up according to preset Cross-Link measurement
Flutter table obtain the more satellites in view in periphery star between bidirectional ranging observed quantity.
In the step (2), GEO satellite utilizes the navigation satellite ephemeris parameter and star prestored after orbit maneuver
Between link measure topology table, according to default during satellite navigation system conventional operation measurement interval and periphery can link setup defend
Star networking obtains bidirectional ranging observed quantity and measurement markers, satellite number information between star；And it is incited somebody to action by S-band TTC channel
Above-mentioned three kinds of observation data down transmission transports control system to ground；Ground fortune control system receive GEO satellite pass down H_2O maser data,
Markers, satellite number information are measured, combined ground transports control system, and precise orbit determination is determining to be defended using combining between star with satellite-ground link
Star Precise Orbit, satellite clock correction, inter-satellite link equipment delay parameter and the amendment of H_2O maser device antenna phase center, phase
Much information is corrected to opinion, Bidirectional observation data star are pre-processed, eliminates systematic error, GEO satellite is obtained and can build
Instantaneous H_2O maser information between chain satellite.
In the step (3), using pretreated moment H_2O maser information, measured in conjunction with being established with GEO satellite
The Beidou navigation satellite-orbit information of link, building is with the GEO satellite first kind without singular point orbital tracking (a, e cos ω, e sin
ω, i, Ω, M+ ω) be variable H_2O maser observational equation；The calculating of satellite position combines 6 using 16 radio news programs
The mode that a Nonsingular orbital elements differential corrections combination calculates.
In the step (4), it is without singular point orbital tracking using the building of GEO satellite kinetic model is simplified with the first kind
The equation of satellite motion and variation equation of variable solve the equation using numerical integration method, obtain satellite reference orbital position
And state-transition matrix.
In the step (5), linearization process, combination linearization observation side are carried out to observational equation using reference orbit
Journey and equation of satellite motion, using Kalman filter method, resolving obtains six improvement without singular point orbital tracking of GEO satellite
Number.
In the step (6), after GEO satellite is motor-driven in 1.5 hours, by 6 of step (5) acquisition without singular point track
Radical arrives satellite, other 16 nautical stars prestored in conjunction with GEO satellite as GPS wide area differential GPS correction, to infuse on 5 minutes intervals
It goes through parameter and calculates satellite accurate location；After when data accumulated time is more than 1.5 small after GEO satellite is motor-driven, then first with changing
Into without singular point orbital tracking by numerical integration method carry out orbit prediction, utilize the first 1.5 hours improved accurate rails of satellite
Combination prediction orbit in road carries out navigation ephemeris parameter fitting, whole 16 radio news programs of the GEO satellite updated；It will be wide
It broadcasts and infuses satellite on ephemeris parameter, complete navigation ephemeris parameter and update.
The beneficial effects of the present invention are: Beidou three generations's Seeds of First Post-flight Ka wave band inter-satellite link load, have between satellite
Frequent obtains the ability of bidirectional ranging data between star.Not generate the navigation satellite position of orbit maneuver as reference, star is utilized
Between ranging observe data, using Kalman filter processing mode, also can determine GEO satellite it is motor-driven after Precise Orbit.Precision determines
Satellite orbit parameter can by differential corrections mode infuse arrive satellite, realize satellite position timely update.In view of using
When inter-satellite link observed quantity, GEO satellite, which falls to position DOP value, will promote nearly 2 orders of magnitude compared to ground monitoring station data, and between star
Link observes accuracy of measurement and is better than pseudo range observed quantity.Orbit determination accuracy of this method by very big improvement GEO satellite after motor-driven, shortens orbit determination
Data accumulated time reduces GEO satellite out of service time.It is using another potential advantages of this method, it is contemplated that GEO is defended
Star platform can carry the stronger satellite-borne processor of data-handling capacity, and above-mentioned Cross-Link measurement and data handling procedure can be by defending
The in-orbit completion of star in-orbit can directly improve GEO satellite track using filtering processing mode, reduce at terrestrial data transmission and data
Manage time delay.A preset condition using this method be existing Beidou satellite navigation system have broadcast GPS wide area differential GPS correction parameter
Ability, existing Beidou three generations system has this ability.Currently, to be mainly used for navigation satellite autonomous for inter-satellite link observation data
Orbit determination or joint orbit determination, present invention firstly provides the thinkings that inter-satellite link observation data are used for fast quick-recovery after orbit maneuver
With technological approaches.
Detailed description of the invention
Fig. 1 is H_2O maser GEO orbit determination schematic illustration；
Fig. 2 is H_2O maser GEO orbit determination data flowchart.
Specific embodiment
Present invention will be further explained below with reference to the attached drawings and examples, and the present invention includes but are not limited to following implementations
Example.
The Ka wave band inter-satellite link load that the present invention utilizes Beidou three generations navigation satellite to carry, can obtain between satellite
Two-way precise distance measurement observed quantity；Bidirectional ranging observed quantity star is pre-processed, moment star spacing can be obtained；Not generate rail
The motor-driven Beidou navigation satellite position in road is reference, can construct precise orbit determination measurement updaue equation using moment star spacing；With GEO
The main perturbation power magnitude Analysis result that satellite is subject to is foundation, constructs GEO satellite kinetic model, and then form precise orbit determination
Time update equation；Combination can resolve GEO using EKF filter method and defend using measurement equation and time update equation
Precise Orbit parameter after star is motor-driven；Note differential corrections mode can be used after motor-driven in 1.5 hours to timely update satellite rail
Road, more than 1.5 hours after be fitted by carrying out orbit prediction and ephemeris to GEO satellite Precise Orbit, produce improved GEO and defend
Star radio news program, it is then periodically upper to infuse.
Inter-satellite link observation data of the present invention proposition using Beidou GEO satellite, navigation satellite precise orbit information,
Precise Orbit after quickly determining GEO satellite is motor-driven, the method for realizing GEO satellite navigation ephemeris parameter fast recovery, including it is following
Step:
(1) Beidou GEO satellite carries spaceborne Ka distance-measuring equipment, can obtain according to preset Cross-Link measurement topology table
Bidirectional ranging observed quantity between the star of the more satellites in view in periphery；Spaceborne Ka distance-measuring equipment transmitting-receiving delay parameter stability is better than
0.5ns/3 days, inter-satellite link equipment delay parameter can by star combine precise orbit determination Accurate Calibration；
(2) GEO satellite measures topology using the navigation satellite ephemeris parameter and inter-satellite link prestored after orbit maneuver
Table, according to default during satellite navigation system conventional operation measurement interval and periphery can link setup Satellite Networking, obtain star
Between bidirectional ranging observed quantity and measurement markers, satellite number information；And pass through S-band TTC channel for above-mentioned three kinds of observation number
Control system is transported according to ground is descended into；
(3) fortune control system in ground receives H_2O maser data, the measurement markers, satellite number information that GEO satellite passes down, knot
It closes between ground fortune control system utilizes star and combines between the determining satellite precise orbit of precise orbit determination, satellite clock correction, star with satellite-ground link
Link device delay parameter and the amendment of H_2O maser device antenna phase center, relativistic revision much information, between double star
Pre-processed to observation data, eliminate systematic error, obtain GEO satellite and can the instantaneous H_2O maser between link setup satellite believe
Breath；
(4) pretreated moment H_2O maser information is utilized, in conjunction with the Beidou navigation for establishing measurement link with GEO satellite
Satellite-orbit information, building are without singular point orbital tracking (a, e cos ω, e sin ω, i, Ω, M+ ω) with the GEO satellite first kind
The H_2O maser observational equation of variable；The calculating of satellite position combines 6 Nonsingular orbital elements poor using 16 radio news programs
Divide the correction mode that combination calculates；
(5) it is transported without singular point orbital tracking as the satellite of variable using simplified GEO satellite kinetic model building using the first kind
Dynamic equation and variation equation solve the equation using numerical integration method, obtain satellite reference orbital position and state transfer square
Battle array；
(6) linearization process, combination linear observational equation and satellite motion are carried out to observational equation using reference orbit
Equation, using Kalman filter method, resolving obtains six improvement numbers without singular point orbital tracking of GEO satellite；
(7) after GEO satellite is motor-driven in 1.5 hours, using 6 of step (6) acquisition without singular point orbital tracking as wide area
Differential corrections arrive satellite to infuse on 5 minutes intervals, and the other 16 navigation ephemeris parameters calculating prestored in conjunction with GEO satellite is defended
Star accurate location；After when the motor-driven rear data accumulated time of GEO satellite is more than 1.5 small, then first with improved no singular point rail
Road radical carries out orbit prediction by numerical integration method, combines forecast rail using first 1.5 hours improved satellite precise orbits
Road carries out navigation ephemeris parameter fitting, whole 16 radio news programs of the GEO satellite updated.It will be on radio news program
Satellite is infused, navigation ephemeris parameter is completed and updates.
The embodiment of the present invention proposes to utilize fast quick-recovery after H_2O maser observed quantity realization Beidou GEO satellite orbit maneuver
The method of navigation ephemeris parameter, this method can quickly determine GEO satellite rail using Cross-Link measurement geometry preferably feature
Road, the track that quickly upper note updates in the way of differential corrections, so as to shorten GEO satellite unavailable time.Specific implementation process
It is as follows:
(1) Beidou three generations navigation satellite carry Ka wave band H_2O maser load, can timesharing can link setup satellite structure to periphery
Cross-Link measurement and communication link are built, Bidirectional observation data between star are obtained；The data periodically pass through TTC channel and descend into ground fortune
Control system, when satellite does not generate orbit maneuver, ground transports control system and combines orbit determination with carrying out star using more day datas, determines
Precise satellite track, satellite clock correction, inter-satellite link equipment delay straggling parameter etc., are fitted prediction orbit and clock deviation, produce
Raw navigation ephemeris parameter and upper note arrive satellite, and completion navigation ephemeris parameter updates.
(2) after GEO satellite generates orbit maneuver, according to the Cross-Link measurement topology table during conventional operation, GEO equally may be used
Cross-Link measurement link is established with periphery satellite, obtains bidirectional ranging data, measurement moment time scale information, measurement satellite number between star
Information；Since GEO satellite is visual to ground control station nearly singular integral, above-mentioned three category informations can be (5 minutes in time by TTC channel
Within) it is transmitted to ground fortune control system；
(3) fortune control system in ground receives the motor-driven rear inter-satellite link acquired of GEO satellite and observes data, time scale information, satellite
Number has the Precise Orbit of (combining orbit determination by first step star), precise clock correction, inter-satellite link using ground fortune control system
Equipment delay information measures time delay amendment, antenna phase center amendment, the theory of relativity to GEO satellite H_2O maser observed quantity
Amendment；And epoch naturalization is measured to inter-satellite link observation data using above- mentioned information, signal transmission delay error is eliminated, is obtained
To moment interstellar distance observed quantity；
WhereinStar spacing between satellite k and j after measuring moment naturalization,For by systematic error, propagation
The revised moment star spacing of time delay,Respectively satellite k and j position vector, Δ tk、ΔtjFor satellite clock correction,Respectively satellite k transmitting and reception delay parameter,For satellite j transmitting and reception delay, δlnkBetween star
Measurement system error, εlnkFor H_2O maser random error.
(4) using with treated instantaneous H_2O maser observed quantity, building is with the GEO satellite first kind without singular point orbital tracking
(a、e cosω、e sinω、Ω, M+ ω) be variable H_2O maser observational equation, observational equation form is as follows:
WhereinFor by pretreatment after moment star spacing,Respectively satellite k and j position vector, xk、yk、zk、
xj、yj、zjRespectively satellite k and j three-dimensional coordinate,For satellite j true anomaly, rjFor orbit radius,
The orbit inclination angle and right ascension of ascending node rate respectively provided in navigation ephemeris parameter, Orbit radius, the true anomaly, orbit inclination angle cycle correction system respectively provided in navigation ephemeris parameter
Number, Δ rj、Δuj、ΔijFor corresponding correction amount.ωeFor earth rate, teFor ephemeris moment, t0When being referred to for ephemeris
Between.
(5) using GEO satellite kinetic model is simplified, building is with the first kind without singular point orbital tracking (a, e cos ω, e
sinω、Ω, M+ ω) be variable satellite motion kinetic model, Cambium periodicity observational equation and state transition equation；
Using numerical integration method integrating state equation of transfer, satellite reference track and state-transition matrix are obtained.
Wherein a, e,Ω, ω, M are six orbital trackings, and S, T, W are respectively orbital plane radial direction, along mark, three direction of normal direction
Perturbative force, ξ=e cos ω, η=e sin ω, λ=M+ ω, p=a (1-e2), n is satellite average angular rate, and u is true near point
Angle.
(6) linearization process is carried out to observational equation using reference orbit, obtains linearisation observational equation；Combination linear
Observational equation and equation of satellite motion, using Kalman filter method, resolving obtains GEO satellite six and changes without singular point orbital tracking
Positive number；
WhereinFor star spacing residual error, ε is measurement noise,For dynamics noise, H is observational equation design matrix, M
For kinetics equation linear segment, For satellite position vector.
(7) after GEO satellite orbit maneuver (attitude control and rail control jet terminate, and satellite is only by terrestrial gravitation, lunisolar attraction, too
The routine perturbative force such as positive solar radiation perturbation influences) start Cross-Link measurement accumulation, and simultaneously under 5 minutes interval starting observation data
It carries, infuse a series of process flows of satellite in motor-driven orbit determination data processing and orbit determination result；Data accumulated time after orbit maneuver
When less than 1.5 hours, letter is corrected directly as GPS wide area differential GPS without singular point orbital tracking correction using what above-mentioned (6) step obtained
A part of breath arrives GEO satellite, the comprehensive navigation ephemeris parameter prestored using GEO satellite of user with note on differential correcting information
Accurate satellite orbit is calculated with the differential correcting information broadcast；When data accumulated time is greater than 1.5 hours after orbit maneuver,
Ground transport control system using (6) step obtain without singular point orbital tracking correction as initial value, in conjunction with GEO satellite track movement side
Cheng Jinhang numerical integration obtains being greater than 2 hours prediction orbits.Then normal navigation ephemeris parameter approximating method is utilized, to current
The track and prediction orbit combination in 2 hours that 1 hour orbit determination determines before epoch are fitted, and the GEO satellite that can be updated is wide
Broadcast ephemeris parameter.Satellite will be infused on radio news program, is completed navigation ephemeris parameter and is updated.
The above-mentioned technical proposal provided through the invention can provide following beneficial to effect for the motor-driven rear orbit determination of Beidou GEO satellite
Fruit: firstly, for GEO satellite, preferably observation geometry than star is measured since Cross-Link measurement is capable of providing, and between star
Range accuracy is better than pseudorange measurement accuracy, therefore, realizes that peer-level GEO satellite track determines precision, the number that this method needs
It is less according to integration time；Secondly, directly satellite will be arrived as note on differential corrections without singular point orbital tracking, use can not changed
Guarantee the motor-driven rear precise orbit information of user's quick obtaining GEO under the premise of the operating specification of family.Above two resolution policy can pole
Big unavailable time after reducing GEO satellite orbit maneuver, improves the continuity and availability of GEO satellite service.
Claims (7)
1. a kind of Cross-Link measurement realizes the motor-driven rear quick recovery method of GEO satellite, it is characterised in that the following steps are included:
(1) the Ka wave band inter-satellite link load carried using Beidou three generations navigation satellite obtains the two-way accurate survey between satellite
Away from observed quantity；
(2) bidirectional ranging observed quantity star is pre-processed, obtains moment star spacing；
(3) it not generate the Beidou navigation satellite position of orbit maneuver as reference, is surveyed using moment star spacing building precise orbit determination
Measure renewal equation；
(4) the main perturbation power magnitude Analysis result being subject to using GEO satellite constructs GEO satellite kinetic model, in turn as foundation
Form precise orbit determination time update equation；
(5) combination is using measurement equation and time update equation, using EKF filter method resolve GEO satellite it is motor-driven after
Precise Orbit parameter；
(6) satellite orbit is updated using upper note differential corrections mode in the setting period after motor-driven, more than passing through after setting the period
Orbit prediction and ephemeris fitting are carried out to GEO satellite Precise Orbit, generate improved GEO satellite radio news program, it is then fixed
It is infused on phase.
2. Cross-Link measurement according to claim 1 realizes the motor-driven rear quick recovery method of GEO satellite, it is characterised in that: institute
Beidou GEO satellite carries spaceborne Ka distance-measuring equipment in the step of stating (1), obtains week according to preset Cross-Link measurement topology table
Bidirectional ranging observed quantity between the star of the more satellites in view in side.
3. Cross-Link measurement according to claim 1 realizes the motor-driven rear quick recovery method of GEO satellite, it is characterised in that: institute
In the step of stating (2), GEO satellite is measured after orbit maneuver using the navigation satellite ephemeris parameter and inter-satellite link prestored
Topology table, according to default during satellite navigation system conventional operation measurement interval and periphery can link setup Satellite Networking, obtain
Take bidirectional ranging observed quantity and measurement markers, satellite number information between star；And above-mentioned three kinds are seen by S-band TTC channel
Measured data descends into ground fortune control system；Ground fortune control system receive GEO satellite pass down H_2O maser data, measurement markers,
Satellite number information, the satellite precise rail that combined ground fortune control system is determined using precise orbit determination is combined between star with satellite-ground link
Road, satellite clock correction, inter-satellite link equipment delay parameter and the amendment of H_2O maser device antenna phase center, relativistic revision
Much information pre-processes Bidirectional observation data star, eliminate systematic error, obtain GEO satellite with can link setup satellite it
Between instantaneous H_2O maser information.
4. Cross-Link measurement according to claim 1 realizes the motor-driven rear quick recovery method of GEO satellite, it is characterised in that: institute
In the step of stating (3), using pretreated moment H_2O maser information, in conjunction with the Beidou for establishing measurement link with GEO satellite
Navigation satellite orbit information, building is with the GEO satellite first kind without singular point orbital tracking (a, e cos ω, e sin ω, i, Ω, M+
It is ω) the H_2O maser observational equation of variable；The calculating of satellite position is using 16 radio news programs in conjunction with 6 without singular point root
The mode that number differential corrections combination calculates.
5. Cross-Link measurement according to claim 1 realizes the motor-driven rear quick recovery method of GEO satellite, it is characterised in that: institute
In the step of stating (4), constructed using the first kind without singular point orbital tracking using GEO satellite kinetic model is simplified as the satellite of variable
The equation of motion and variation equation solve the equation using numerical integration method, obtain satellite reference orbital position and state transfer
Matrix.
6. Cross-Link measurement according to claim 1 realizes the motor-driven rear quick recovery method of GEO satellite, it is characterised in that: institute
In the step of stating (5), linearization process, combination linear observational equation and satellite fortune are carried out to observational equation using reference orbit
Dynamic equation, using Kalman filter method, resolving obtains six improvement numbers without singular point orbital tracking of GEO satellite.
7. Cross-Link measurement according to claim 1 realizes the motor-driven rear quick recovery method of GEO satellite, it is characterised in that: institute
In the step of stating (6), after GEO satellite is motor-driven in 1.5 hours, using 6 of step (5) acquisition without singular point orbital tracking as wide
Domain differential corrections arrive satellite to infuse on 5 minutes intervals, and the other 16 navigation ephemeris parameters prestored in conjunction with GEO satellite calculate
Satellite accurate location；After when the motor-driven rear data accumulated time of GEO satellite is more than 1.5 small, then first with improved no singular point
Orbital tracking carries out orbit prediction by numerical integration method, combines forecast using first 1.5 hours improved satellite precise orbits
Track carries out navigation ephemeris parameter fitting, whole 16 radio news programs of the GEO satellite updated；By radio news program
Upper note satellite is completed navigation ephemeris parameter and is updated.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110927756A (en) * | 2019-11-25 | 2020-03-27 | 上海华测导航技术股份有限公司 | Satellite orbit maneuvering detection method, device, equipment and storage medium |
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| CN110927756A (en) * | 2019-11-25 | 2020-03-27 | 上海华测导航技术股份有限公司 | Satellite orbit maneuvering detection method, device, equipment and storage medium |
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| CN111505677A (en) * | 2020-04-15 | 2020-08-07 | 中国科学院国家授时中心 | Ground reference station observation-based GEO satellite orbit maneuvering repairing method |
| CN111522036A (en) * | 2020-04-30 | 2020-08-11 | 中国科学院微小卫星创新研究院 | Satellite-usable Beidou satellite centralized constellation autonomous navigation system and navigation method |
| CN111522037A (en) * | 2020-04-30 | 2020-08-11 | 中国科学院微小卫星创新研究院 | Autonomous navigation method and navigation system for constellation co-orbital plane satellite |
| CN111522037B (en) * | 2020-04-30 | 2022-08-02 | 中国科学院微小卫星创新研究院 | Autonomous navigation method and navigation system for constellation co-orbital plane satellite |
| CN112987044A (en) * | 2021-02-25 | 2021-06-18 | 中国科学院微小卫星创新研究院 | Constellation ephemeris on-orbit updating method |
| CN113253311B (en) * | 2021-04-06 | 2024-02-06 | 探索数据科技(深圳)有限公司 | Combined satellite navigation method, system, electronic equipment and storage medium |
| CN113253311A (en) * | 2021-04-06 | 2021-08-13 | 探索数据科技(深圳)有限公司 | Joint satellite navigation method, system, electronic device and storage medium |
| CN114002709A (en) * | 2021-10-20 | 2022-02-01 | 上海航天空间技术有限公司 | Singularity removing method suitable for recursive calculation of satellite orbit parameters |
| CN115598676B (en) * | 2022-10-17 | 2023-05-05 | 北京航天飞行控制中心 | Satellite-borne multimode GNSS fusion precise orbit determination method and device |
| CN115598676A (en) * | 2022-10-17 | 2023-01-13 | 北京航天飞行控制中心（Cn） | Satellite-borne multimode GNSS fusion precise orbit determination method and device |
| CN115808675A (en) * | 2023-01-17 | 2023-03-17 | 湖南迈克森伟电子科技有限公司 | Laser ranging error compensation method |
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