CN109061674A - The system and method that dipper system continuous service is monitored using Constellation of Low Earth Orbit Satellites - Google Patents
The system and method that dipper system continuous service is monitored using Constellation of Low Earth Orbit Satellites Download PDFInfo
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- CN109061674A CN109061674A CN201810684256.7A CN201810684256A CN109061674A CN 109061674 A CN109061674 A CN 109061674A CN 201810684256 A CN201810684256 A CN 201810684256A CN 109061674 A CN109061674 A CN 109061674A
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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
- G01S19/03—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers
Abstract
The present invention relates to a kind of satellite navigation system continuous services to monitor system and method, method includes the following steps: step 1: the low rail constellation of design 40 to 60 satellites composition；Step 2: low orbit satellite by GNSS data, satellite laser ranging (SLR) method realize low orbit satellite in real time/high-precision orbit determination quasi real time；Step 3: carrying out the two-way timing to low all stars of rail constellation by Beidou center station, low rail system inter-satellite link, realizes time synchronization when all low orbit satellites and dipper system；Step 4: the observation data of all LEO satellites of central station are transmitted back to by inter-satellite link.The present invention realizes that continuous service monitors all-time anf all-weather to dipper system, goes out more accurate big-dipper satellite ephemeris star clock data for Back end data center processing, Beidou does method support in foreign countries' popularization and application.
Description
Method field
The present invention relates to a kind of system and methods monitored using Constellation of Low Earth Orbit Satellites to dipper system continuous service, especially
It is related to realizing the system and method for Beidou terrestrial reference observation station effect by low rail (LEO) moonlet.
Background method
Current GPS systems are mainly that the monitoring of GPS satellite is believed in comprehensive more than 200 continuous operation observation stations all over the world
Breath issues many different Precise Orbit products and precise clock correction product using interval by internet after synthesis, analysis,
For the whole world, various users provide service of goods.
Current terrestrial Beidou ground based observa tion base station has basically formed, including 150 frame net base stations and 1269 areas
Domain densification network base station, but due to being influenced to limit by factors such as geographical environment, national sovereignty, current overwhelming majority Beidou base
Quasi- station is deployed in China mainland, therefore can not achieve continuous fortune all-time anf all-weather for the Beidou navigation satellite of middle orbit
Row observation.Additionally while base station is large number of, but repeated construction, application effect is bad, especially external Beidou base station net
The serious lag of construction, constrains Beidou in the application in the whole world.
In recent years, domestic multiple multi-functional Constellation of Low Earth Orbit Satellites systems are during feasibility study, including 156 low rails
Star composition " rainbow cloud engineering " constellation, " the swan goose constellation " that is made of 60 Low earth orbit satellites.In addition as spaceborne calculate is put down
The progress of platform performance boost and the highly integrated spaceborne multimode GNSS receiver method of miniaturization, builds chance by constellation and carries hair
It penetrates, makes it possible that global real-time reception monitors GNSS signal.
In addition, current ocean two, resource three utilization GPS post-processings, satellite laser ranging (SLR) (SLR) and spaceborne Doppler
The methods of radio orbit determination positioning system (DORIS) carries out LEO to combine subsequent precise orbit determination, and test result shows low orbit satellite
Orbit determination accuracy has reached cm grades, therefore does terrestrial reference station for low orbit satellite and provide method basis.
Summary of the invention
Current Beidou base station construction there are aiming at the problem that, and the opportunity of current low rail constellation construction, the present invention mention
A kind of system and method monitored using Constellation of Low Earth Orbit Satellites to dipper system continuous service out utilizes 40 to 60 low rails
Satellite Networking is realized to Beidou navigation satellite continuous observation all-time anf all-weather, and the effect of Beidou terrestrial reference station is undertaken.
According to an aspect of the present invention, it provides and a kind of using Constellation of Low Earth Orbit Satellites dipper system continuous service is monitored
System characterized by comprising
Big-dipper satellite is monitored target, 27 middle orbit MEO satellites, five stationary orbit GEO satellites and three
Geostationary orbit IGSO satellite；
Low orbit satellite is made of for the main body being monitored to Beidou constellation 40~60 low orbit satellites, and satellite loads
High-precision Beidou monitoring receiver is completed to receive Beidou signal, and has laser corner reflector tie surface to complete itself high-precision
Orbit determination and inter-satellite link terminal realize the transmission and time service function of observation data；
Gateway station station, satellite carries out data routing function between mainly realizing different rail；
Ground laser ranging station realizes the high-precision measuring rail function to low orbit satellite；
Ground central station realizes the reception processing function of monitoring data.
The present invention also provides a kind of method monitored using Constellation of Low Earth Orbit Satellites to dipper system continuous service, feature exists
In, comprising the following steps:
Step 1: the low rail constellation of design 40 to 60 satellites composition, including orbit altitude, orbit inclination angle, rail
Road plane quantity, every rail number of satellite, same orbit plane satellite relative phase, adjacent orbit plane satellite relative phase etc. are set
Meter, analyzes low rail constellation and base station to the time that continues to monitor of Beidou constellation by STK software emulation, then compares；
Step 2: low orbit satellite by GNSS data, satellite laser ranging (SLR) method realize low orbit satellite in real time/quasi real time
High-precision orbit determination；
Step 3: carrying out the two-way timing to low all stars of rail constellation by Beidou center station, low rail system inter-satellite link,
Realize time synchronization when all low orbit satellites and dipper system；
Step 4: the observation data of all LEO satellites of central station are transmitted back to by inter-satellite link.
Preferably, the step 1 specifically includes the following steps:
Step 101: designing low rail constellation by analysis, considers that system cost, constellation efficiency, space environment are many-sided
Factor designs low rail constellation；
Step 102: LEO constellation, earth station system, BD system model are established by STK software；
Step 103: by STK software visibility analysis module analysis LEO constellation to BD systems stay monitor situation,
Continue to monitor situation of the earth station system to BD system, in one week of simulation time, addition LEO constellation is assembly, BD system is
Assembly, earth station system are assembly；The link for establishing assembly to assembly establishes the link of assembly to assembly,
The situation Access that establishes that analysis module calculates two links of generation is reported.
Preferably, the step 101 designs the constellation parameter of low rail constellation: the total number of satellite 48, orbital plane number 6
Satellite number 8, orbit altitude 1100km, orbit inclination angle 99.9 degree, every star, four inter-satellite links of a, each orbital plane are logical
Believe terminal.
Preferably, the step 2 specifically includes the following steps:
Step 201: spaceborne high precision GNSS receiver realizes that the signal under in-orbit high dynamic receives, and completes navigation electricity
Text extracts, and obtains double frequency and surveys code pseudorange, surveys phase pseudorange original observed data；
Step 202: by star data feedback channel and inter-satellite link are infused on complete all LEO real-time receptions of constellation ground
The data such as nautical star orbital exponent data, clock deviation amendment data, ionosphere corrected value；
Step 203: data are observed by received GNSS, error correction carries out just orbit determination；
Step 204: orbit determination at the beginning of ground laser ranging station carries out laser ranging orbit determination, with GNSS to the low orbit satellite that passes by
As a result integrated treatment is carried out, the final orbit determination result of low orbit satellite is obtained.
Preferably, the step 3 specifically includes the following steps:
Step 301: to the visual low orbit satellite of central station, by star the time is same with carrying out star for radio bidirectional ranging method
Step；
Step 302: satellite not visible for ground central station, using same principle satellites in view and not visible satellite
Between time synchronization between star carried out by bidirectional measurement between star, finally realize that ground central station and the time of entirely low rail constellation are same
Step.
Preferably, the step 4 specifically includes the following steps:
01: every LEO satellite real-time perfoming space router-level topology of step 4, according to current location, target floor erect-position
It sets and constellation space configuration, calculates data back optimal path；
Step 402: having same orbital plane satellite at earth station overhead, reaches overhead LEO satellite by inter-satellite link,
LEO satellite is sent to ground central station by satellite-ground link；
Step 403: nothing, at earth station overhead, reaches arctic overhead satellite by inter-satellite link with orbital plane satellite,
Arctic overhead satellite is completed to exchange with different rail level satellite information by arctic gateway station, and then information passes through inter-satellite link between same rail
Earth station's overhead satellite is reached, ground central station is then sent to by satellite-ground link.
Advantage of the process is that
(1) this method gets rid of the limitation of traditional foundation continuous operation observation station cloth station, realizes complete to dipper system round-the-clock
The continuous service of weather monitors, and goes out more accurate big-dipper satellite ephemeris star clock data, Beidou in state for Back end data center processing
Method support is done in outer popularization and application.
(2) this method combines precise orbit determination method using GPS, SLR, measures rail by GPS or ground relative to simple, fixed
Rail precision improves two orders of magnitude, improves from m grades to cm grades, has important scientific value.
Detailed description of the invention
Fig. 1 is that laser distance measurement method carries out Orbit determination for LEOs schematic diagram.
Fig. 2 is two-way time synchronization and range measurement principle.
Specific embodiment
Embodiment in order to better illustrate the present invention with reference to the accompanying drawing does further specifically the present invention
It is bright.
The present invention includes: using the system that Constellation of Low Earth Orbit Satellites monitors dipper system continuous service
Big-dipper satellite is monitored target, and 27 middle orbit MEO satellites, 5 stationary orbit GEO satellites and 3 earth are same
Walk track IGSO satellite.
Low orbit satellite is made of for the main body being monitored to Beidou constellation 40~60 low orbit satellites, and satellite loads
High-precision Beidou monitoring receiver is completed to receive Beidou signal, and has laser corner reflector tie surface to complete itself high-precision
Orbit determination and inter-satellite link terminal realize the transmission and time service function of observation data.
Gateway station station, satellite carries out data routing function between mainly realizing different rail.
Ground laser ranging station realizes the high-precision measuring rail function to low orbit satellite.
Ground central station realizes the reception processing function of monitoring data.
As shown in Figure 1, the invention proposes a kind of sides observed using Constellation of Low Earth Orbit Satellites dipper system continuous service
Method, comprising the following steps:
Step 1: the low rail constellation of design 40 to 60 satellites composition, including orbit altitude, orbit inclination angle, rail
Road plane quantity, every rail number of satellite, same orbit plane satellite relative phase, adjacent orbit plane satellite relative phase etc. are set
Meter, analyzes low rail constellation and base station to the time that continues to monitor of Beidou constellation by STK software emulation, then compares.Step
Rapid one the following steps are included:
Step 101: designing low rail constellation, mainly considers system cost, constellation integrally to ground-to-air observation efficiency, fortune
The many factors such as emissivities, space environment are carried, constellation is designed, it is desirable that 100% real-time all standing can be achieved to the whole world in constellation,
Van Allen belt is avoided in orbit altitude consideration, and orbit inclination angle mainly considers to facilitate the sun-synchronous orbit of satellite thermal control design.
Design parameter is as follows: the total number of satellite 48, orbital plane number 6, each orbital plane satellite number 8, orbit altitude
1100km, orbit inclination angle 99.9 degree, every star, four inter-satellite link communication terminals.
Step 102: LEO constellation, earth station system, BD system model are established by STK software；LEO constellation is using step
The 48 star schemes designed in rapid 1, every star are added one to day sensor Sensor, and Sensor field angle is positive and negative 85
Degree；BD system is using 27 MEO+5 GEO+3 IGSO scheme after following build up, orbit altitude 21500km；System of earth station
+ 1269,150 frame station of the Beidou regional station scheme that system is completed using current China, earth station are set as just day field angle
Minus 85 degree, earth station location is determines according to actual conditions.
Step 103: by STK software visibility analysis module analysis LEO constellation to BD systems stay monitor situation,
Continue to monitor situation of the earth station system to BD system, in one week of simulation time, addition LEO constellation is assembly, BD system is
Assembly, earth station system are assembly；The link ChainLEO_BD for establishing assembly to assembly, establishes assembly to group
Fit link ChainStation_BD, the situation Access that establishes that analysis module calculates two links of generation are reported.
Step 2: low orbit satellite by the methods of GNSS data, satellite laser ranging (SLR) (SLR) realize low orbit satellite in real time/
High-precision orbit determination quasi real time.Step 2 the following steps are included:
Step 201: spaceborne high precision GNSS receiver realizes that the signal under in-orbit high dynamic receives, and completes navigation electricity
Text extracts, and obtains double frequency and surveys code pseudorange, surveys phase pseudorange original observed data.
Step 202: by star data feedback channel and inter-satellite link are infused on complete all LEO real-time receptions of constellation ground
The data such as nautical star orbital exponent data, clock deviation amendment data, ionosphere corrected value.
Step 203: data are observed by received GNSS, error correction carries out just orbit determination.
Step 204: orbit determination at the beginning of ground laser ranging station carries out laser ranging orbit determination, with GNSS to the low orbit satellite that passes by
As a result integrated treatment is carried out, the final orbit determination result of low orbit satellite is obtained.
Step 3: carrying out the two-way timing to low all stars of rail constellation by Beidou center station, low rail system inter-satellite link,
Realize time synchronization when all low orbit satellites and dipper system；Step 3 the following steps are included:
Step 301: to the visual low orbit satellite of central station, by star the time is same with carrying out star for radio bidirectional ranging method
Step.Principle is as shown in Fig. 2, visual low orbit satellite A and ground central station B installation radio transmitter and receiver, visual low rail
Satellite A and earth station B receive the time synchronization and ranging letter of other side simultaneously to other side's launch time is synchronous and distance measuring signal
Number, available following formula (1):
In formula (1): Δ t is the clock deviation of satellite A and ground central station B, T1Emit timing signal for satellite A and receives ground
The time difference of the timing signal of central station B transmitting, t2Emit equipment delay, τ for ground central station BBAFor earth station B to satellite A
Propagation delay, r1For satellite A receiving device time delay, δ1For other time delays；T2 is that ground central station B emits timing signal and connects
Receive the time difference of the timing signal of satellite A transmitting, t1Emit equipment delay, τ for satellite AABIt is satellite A to ground central station B's
Propagation delay, r2For earth station B receiving device time delay, δ2For other time delays.
The clock deviation Δ t that ground central station B Yu satellite A can be obtained after arrangement, such as following formula (2):
In formula (2): T1,T2It is obtained by each measurement of satellite A, ground central station B, t1, r1And t2, r2It can basis respectively
The frequency of satellite and ground central station transmitting and receiving signal realizes calibration, as known quantity.When satellite A and ground central station B are mutual
The frequency for sending out time synchronization and distance measuring signal is close, and link is symmetrical, and propagation delay is approximately equal, there is τAB=τBA, ignore simultaneously
Other time delays δ1δ2Influence, the clock deviation Δ t of satellite A and ground central station can be found out, so far complete star ground time synchronization.
Step 302: satellite not visible for ground central station, using same principle satellites in view and not visible satellite
Between time synchronization between star carried out by bidirectional measurement between star, finally realize that ground central station and the time of entirely low rail constellation are same
Step.
Step 4: the GNSS monitoring data of all LEO satellites of central station are transmitted back to by inter-satellite link.
Step 4 the following steps are included:
01: every LEO satellite real-time perfoming space router-level topology of step 4, according to current location, target floor erect-position
It sets and constellation space configuration, calculates data back optimal path.
Step 402: having same orbital plane satellite at earth station overhead, reaches overhead LEO satellite by inter-satellite link,
LEO satellite is sent to ground central station by satellite-ground link.
Step 403: nothing, at earth station overhead, reaches arctic overhead satellite by inter-satellite link with orbital plane satellite,
Arctic overhead satellite is completed to exchange with different rail level satellite information by arctic gateway station, and then information passes through inter-satellite link between same rail
Earth station's overhead satellite is reached, ground central station is then sent to by satellite-ground link.
Observation data are passed back ground central station by inter-satellite link by complete all LEO stars of constellation in real time.Routing policy on star
Are as follows: the most short strategy in path is calculated on star in real time and is currently numbered with ground central station visible satellite, and optimal path is selected to be transmitted to this
Then star passes channel transfer to ground central station by the star number, so far completes the real-time continuous operational monitoring to dipper system.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (7)
1. a kind of system monitored using Constellation of Low Earth Orbit Satellites to dipper system continuous service characterized by comprising
Big-dipper satellite is monitored target, 27 middle orbit MEO satellites, five stationary orbit GEO satellites and three earth
Geo-stationary orbit IGSO satellite；
Low orbit satellite is made of for the main body being monitored to Beidou constellation 40~60 low orbit satellites, and satellite loads high-precision
It spends Beidou monitoring receiver to complete to receive Beidou signal, and there have laser corner reflector tie surface to complete itself to be high-precision fixed
Rail and inter-satellite link terminal realize the transmission and time service function of observation data；
Gateway station station, satellite carries out data routing function between mainly realizing different rail；
Ground laser ranging station realizes the high-precision measuring rail function to low orbit satellite；
Ground central station realizes the reception processing function of monitoring data.
2. a kind of method monitored using Constellation of Low Earth Orbit Satellites to dipper system continuous service, which is characterized in that including following step
It is rapid:
Step 1: the low rail constellation of design 40 to 60 satellites composition, including orbit altitude, orbit inclination angle, track are flat
The design such as face quantity, every rail number of satellite, same orbit plane satellite relative phase, adjacent orbit plane satellite relative phase,
Low rail constellation and base station are analyzed to the time that continues to monitor of Beidou constellation by STK software emulation, are then compared；
Step 2: low orbit satellite by GNSS data, satellite laser ranging (SLR) method realize low orbit satellite in real time/quasi real time high-precision
Spend orbit determination；
Step 3: carrying out the two-way timing to low all stars of rail constellation by Beidou center station, low rail system inter-satellite link, realizes
Time synchronization when all low orbit satellites and dipper system；
Step 4: the observation data of all LEO satellites of central station are transmitted back to by inter-satellite link.
3. the method according to claim 2 monitored using Constellation of Low Earth Orbit Satellites to dipper system continuous service, feature
Be, the step 1 specifically includes the following steps:
Step 101: designing low rail constellation by analysis, consider system cost, constellation efficiency, space environment many factors,
Design low rail constellation；
Step 102: LEO constellation, earth station system, BD system model are established by STK software；
Step 103: situation, ground are monitored to BD systems stay by STK software visibility analysis module analysis LEO constellation
Continue to monitor situation of the system of standing to BD system, in one week of simulation time, addition LEO constellation is assembly, BD system is combination
Body, earth station system are assembly；The link for establishing assembly to assembly establishes the link of assembly to assembly, analysis
The situation Access that establishes that module calculates two links of generation is reported.
4. the method according to claim 3 monitored using Constellation of Low Earth Orbit Satellites to dipper system continuous service, feature
It is, the step 101 designs the constellation parameter of low rail constellation: the total number of satellite 48, orbital plane number 6, each track
Satellite number 8, orbit altitude 1100km, orbit inclination angle 99.9 degree, every star, four inter-satellite link communication terminals in face.
5. the method according to claim 2 monitored using Constellation of Low Earth Orbit Satellites to dipper system continuous service, feature
Be, the step 2 specifically includes the following steps:
Step 201: spaceborne high precision GNSS receiver realizes that the signal under in-orbit high dynamic receives, and completes navigation message and mentions
It takes, obtains double frequency and survey code pseudorange, survey phase pseudorange original observed data；
Step 202: by star data feedback channel and inter-satellite link, the navigation infused on complete all LEO real-time receptions of constellation ground
The data such as star orbital exponent data, clock deviation amendment data, ionosphere corrected value；
Step 203: data are observed by received GNSS, error correction carries out just orbit determination；
Step 204: orbit determination result at the beginning of ground laser ranging station carries out laser ranging orbit determination, with GNSS to the low orbit satellite that passes by
Integrated treatment is carried out, the final orbit determination result of low orbit satellite is obtained.
6. the method according to claim 2 monitored using Constellation of Low Earth Orbit Satellites to dipper system continuous service, feature
Be, the step 3 specifically includes the following steps:
Step 301: to the visual low orbit satellite of central station by star radio bidirectional ranging method progress star time synchronization；
Step 302: satellite not visible for ground central station is logical using same principle satellites in view and not visible inter-satellite
Bidirectional measurement carries out time synchronization between star between crossing star, finally realizes the time synchronization of ground central station and entire low rail constellation.
7. the method according to claim 2 monitored using Constellation of Low Earth Orbit Satellites to dipper system continuous service, feature
Be, the step 4 specifically includes the following steps:
01: every LEO satellite real-time perfoming space router-level topology of step 4, according to current location, target floor station location and
Constellation space configuration calculates data back optimal path；
Step 402: having same orbital plane satellite at earth station overhead, reaches overhead LEO satellite by inter-satellite link, LEO is defended
Star is sent to ground central station by satellite-ground link；
Step 403: nothing, at earth station overhead, reaches arctic overhead satellite, the arctic by inter-satellite link with orbital plane satellite
Overhead satellite is completed to exchange with different rail level satellite information by arctic gateway station, and then information is reached by inter-satellite link between same rail
Earth station's overhead satellite, is then sent to ground central station by satellite-ground link.
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