CN109001760A - A kind of low orbit satellite radio news program expression - Google Patents
A kind of low orbit satellite radio news program expression Download PDFInfo
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- CN109001760A CN109001760A CN201810565447.1A CN201810565447A CN109001760A CN 109001760 A CN109001760 A CN 109001760A CN 201810565447 A CN201810565447 A CN 201810565447A CN 109001760 A CN109001760 A CN 109001760A
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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
- G01S19/02—Details of the space or ground control segments
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- Radar, Positioning & Navigation (AREA)
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- Computer Networks & Wireless Communication (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
The present invention discloses a kind of low orbit satellite radio news program expression, this method comprises: step 1, radio news program fitting is carried out based on low orbit satellite Precise Orbit, the radio news program uses the expression of compatible navigation satellite broadcasting ephemeris, increase satellite orbit major semiaxis variability, mean angular velocity of satellite motion variability, latitude argument one third week sine and cosine reconciliation correction factor, on original parameter basis to absorb the perturbation of low orbit satellite orbital period property；Step 2, track major semiaxis variability, mean angular velocity of satellite motion variability, latitude argument one third week sine and cosine reconciliation correction factor expression are carried out using retention position in navigation satellite navigation message formatting.The present invention makes full use of existing middle high rail navigation satellite ephemeris design and expression, it realizes that low orbit satellite ephemeris is compatible with the parameter of middle high rail satellite navigation ephemeris and expression way is unified, reduces the complexity of high rail navigation satellite and low orbit satellite ephemeris in the comprehensive use of user.
Description
Technical field
The present invention relates to a kind of navigation satellite orbit parameter expression technologies more particularly to a kind of low orbit satellite broadcast ephemeris to join
Number expression.
Background technique
When navigation satellite is navigated and is positioned, it is necessary to calculate the instantaneous position and speed of navigation satellite first.Satellite
Position and speed in orbit indicates that ephemeris parameter is issued in the passing of satelline with ephemeris, provides positioning in real time for user, accurately leads
The service such as boat, user calculate satellite position and speed by set formula according to the parameter of offer, referred to as navigation ephemeris.
It includes the amendment of system time, ephemeris, satellite clock that the ephemeris that navigates, which is one group broadcast from navigation satellite to user,
The binary code of the information such as parameter, navigation satellite health status and ionospheric delay model parameter.The monitoring station of navigation system
Data acquisition is carried out to satellite, and the data of acquisition are transferred to master station and are handled, obtains satellite alert track and satellite
Clock correction encodes the information such as these satellite positions and clock error correction number, then is injected its encoded information by injection station
To navigation satellite, finally uninterruptedly broadcast from normal navigation satellite in orbit is round-the-clock to visual user.
Broadcast ephemeris is obtained by the survey rail subsystem extrapolation track of satellite navigation system, over time, in advance
Report track can deviate actual track, the precision reduction of navigation and positioning, so can only guarantee the required precision in certain period of time.
Data every 2 hours of middle high rail broadcast ephemeris update once, and before and after updating epoch within the scope of each one hour, satellite position can
Reach meter accuracy.
In the navigation augmentation system based on low rail constellation, low orbit satellite will also be used as navigator fix benchmark, broadcast navigation
Ephemeris.However, existing conventional navigation satellite broadcasting ephemeris is to low orbit satellite track, there are biggish expression errors, and are not suitable for
In low orbit satellite.
Summary of the invention
The technical problem to be solved by the present invention is to propose it is a kind of it is compatible tradition in high rail navigation satellite ephemeris low orbit satellite
Radio news program expression.
In order to solve the above technical problems, the present invention adopts the following technical scheme:
The present invention provides a kind of low orbit satellite radio news program expression, comprising:
Step 1, radio news program fitting is carried out based on low orbit satellite Precise Orbit, radio news program is led using compatibility
The expression of boat satellite broadcasting ephemeris increases satellite orbit major semiaxis variability, mean motion angle speed on original parameter basis
Variability, latitude argument one third week sine and cosine reconciliation correction factor are spent, to absorb the perturbation of low orbit satellite orbital period property；
Step 2, track major semiaxis variability, average fortune are carried out using retention position in navigation satellite navigation message formatting
Dynamic angular speed variability, latitude argument one third week is sinusoidal and cosine reconciliation correction factor is expressed.
According to a kind of embodiment, navigation satellite radio news program include the ephemeris reference time, it is flat close with reference to the moment
Point angle, eccentricity, the square root of semi-major axis, the longitude of ascending node with reference to the moment, the orbit inclination angle with reference to the moment, perigee angle
Correction is reconciled away from, mean angular velocity correction, right ascension of ascending node change rate, the change rate at inclination angle, the sine of latitude argument and cosine
Coefficient, track reconcile sine from the sine and cosine of correction factor and orbit inclination angle to diameter and cosine and reconcile correction factor.
According to a kind of embodiment, satellite orbit major semiaxis variability, mean angular velocity of satellite motion variability, three points of latitude argument
One of week is sinusoidal and cosine reconciles correction factor that the different retention positions of navigation satellite text can be utilized to be indicated.
Meanwhile Error Correction of Coding is carried out using BCH (15,11,1) mode to the navigation ephemeris of low orbit satellite, it is led with middle high rail
Boat satellite message is consistent.
Compared with prior art, the main advantage of technical solution of the present invention is as follows:
1) for the fitting orbit error rule of low orbit satellite, satellite orbit major semiaxis variability, mean motion angle are increased
Velocity gradient, latitude argument one third week sine and cosine reconciliation correction factor, absorb low orbit satellite orbit error；
2) high rail navigation satellite (GPS of America, Chinese Beidou BDS, European Union Galileo, day in existing be suitble to sufficiently are accounted for
This QZSS) ephemeris format, it is only necessary to increasing by 4 additional parameters can be compatible with middle high rail satellite ephemeris realization；
3) in terms of text layout, the reserved field in middle high rail navigation satellite ephemeris is utilized, it is simple and convenient, to low rail
The navigation ephemeris of satellite carries out Error Correction of Coding using BCH (15,11,1) mode, makes the ephemeris text knot for describing low orbit satellite track
The ephemeris text structure of structure and high rail satellite orbit in description is consistent.
Detailed description of the invention
By reading the following detailed description of the preferred embodiment, various other advantages and benefits are common for this field
Technical staff will become clear.The drawings are only for the purpose of illustrating a preferred embodiment, and is not considered as to the present invention
Limitation.And throughout the drawings, the same reference numbers will be used to refer to the same parts.In the accompanying drawings:
Fig. 1 is the method flow diagram of low orbit satellite radio news program expression provided in an embodiment of the present invention；
Fig. 2 is the text frame format of navigation ephemeris provided in an embodiment of the present invention；
Fig. 3 is layout position view of the newly-increased ephemeris parameter provided in an embodiment of the present invention in text；
Fig. 4 is shown as the method flow provided in an embodiment of the present invention that Error Correction of Coding is carried out to the navigation ephemeris of low orbit satellite
Figure；
Fig. 5 is the method flow diagram of Bose-Chaudhuri-Hocquenghem Code in Error Correction of Coding mode provided in an embodiment of the present invention.
Specific embodiment
Exemplary embodiments of the present disclosure are described in more detail below with reference to accompanying drawings.Although showing the disclosure in attached drawing
Exemplary embodiment, it being understood, however, that may be realized in various forms the disclosure without should be by embodiments set forth here
It is limited.On the contrary, these embodiments are provided to facilitate a more thoroughly understanding of the present invention, and can be by the scope of the present disclosure
Completely it is communicated to those skilled in the art.
As shown in Figure 1, the low orbit satellite radio news program expression of one embodiment of the invention includes the following steps:
Step S1 carries out radio news program fitting based on low orbit satellite Precise Orbit, and the radio news program uses
The expression of compatible navigation satellite broadcasting ephemeris increases satellite orbit major semiaxis variability, average fortune on original parameter basis
Dynamic angular speed variability, latitude argument one third week sine and cosine reconciliation correction factor, to absorb the low orbit satellite orbital period
Property perturbation；
Specifically, further including attached step S0 not shown in the figure before the step S1；
Step S0 calculates the track of a low-orbit satellite.
The space environment as locating for low-orbit satellite is sufficiently complex, in addition to by usually being considered in two-body problem
It, will also be by a variety of perturbation factors such as the aspherical gravitation of the earth, atmospheric drag, lunisolar attraction, solar light pressures outside centrifugal force
It influences, thus low orbit satellite motion profile is actually very complicated space curve, which dictates that low-orbit satellite orbit determination problems
Complexity.The present invention extracts wherein main perturbative force influence factor, is low orbit satellite navigation message track Accurate Expression
Basis.
Wherein, the specific implementation of radio news program fitting is carried out based on low orbit satellite Precise Orbit are as follows: according to low orbit
The track of satellite calculates the parameters of the model of description low-orbit satellite track, including major semiaxis variability, average fortune
Dynamic angular speed variability, the one third of latitude argument week sine and cosine reconciliation correction factor.
For conventional navigation satellite 16 parameters broadcast ephemeris to the track fitting residual error of low orbit satellite, learn and defending
Tangentially there is biggish error of fitting in star orbital road, and regression criterion has certain periodical perturbation, it is therefore desirable to additional to increase
Parameter is added to absorb its orbit error.And then considers to increase by two major semiaxis variability, mean angular velocity of satellite motion variability parameters and rise
The periodic term perturbation for handing over elongation direction to increase by two one third weeks absorbs above-mentioned error, and the fitting parameter of low orbit satellite is arranged
It is 20.
Using the navigation ephemeris of navigation satellite to the fitting orbit error rule of low orbit satellite, creatively increase latitude width
The all sinusoidal and cosine reconciliation correction factors of the one third at angle absorb low orbit satellite orbit error in a liter friendship elongation direction and increase by two
The periodic term in a one third week perturbs.Therefore, each model parameter for describing the track of low-orbit satellite includes ephemeris reference
Time te0, with reference to the mean anomaly M at moment0, eccentric ratio e, semi-major axis square rootWith reference to the longitude of ascending node at moment
Ω0, with reference to the orbit inclination angle i at moment0, argument of perigee ω, mean angular velocity correct Δ n, right ascension of ascending node change rateIncline
The change rate di/dt at angle, major semiaxis variabilityMean angular velocity of satellite motion variabilitySine and the cosine reconciliation of latitude argument change
Positive coefficient Cus,Cuc, sine from track to diameter and cosine reconcile correction factor Crs,Crc, orbit inclination angle sine and cosine reconciliation change
Positive coefficient Cis,CicAnd all sinusoidal and cosine reconciliation correction factor C of one third of latitude argumentus2,Cus2。
Wherein, with reference to the mean anomaly M at moment0, eccentric ratio e, semi-major axis square rootWith reference to the ascending node at moment
Longitude Ω0, with reference to the orbit inclination angle i at moment0And argument of perigee ω this 6 parameters are primary track parameter, i.e. Kepler
Orbital tracking；Mean angular velocity corrects Δ n, right ascension of ascending node change rateThe change rate di/dt at inclination angle, major semiaxis variability
Mean angular velocity of satellite motion variabilitySine and cosine reconciliation the correction factor C of latitude argumentus,Cuc, sine from track to diameter and
Cosine reconciliation correction factor Crs,Crc, orbit inclination angle sine and cosine reconcile correction factor Cis,CicAnd the three of latitude argument
/ mono- week sinusoidal and cosine reconciliation correction factor Cus2,Cus2This 13 parameters are perturbation reductions.
For the broadcast ephemeris of middle high 16 parameters of rail satellite, track major semiaxis, mean angular velocity of satellite motion are calculated, rises and hands over
The perturbing term formula of elongation are as follows:
δu=Cuc cos2u+Cus sin2u
For low orbit satellite, the broadcast ephemeris of newly-designed 20 parameters calculates track major semiaxis, mean motion angle speed
Degree rises the perturbing term formula for handing over elongation are as follows:
δu=Cuc cos2u+Cus sin2u+Cuc2cos6u+Cus sin6u
Step S2 carries out track major semiaxis variability using retention position in navigation satellite navigation message formatting, is averaged
Angular velocity of satellite motion variability, latitude argument one third week is sinusoidal and cosine reconciliation correction factor is expressed.
Increased 4 parameters can make full use of reserved field in existing middle high rail navigation ephemeris, and it is not necessary to modify existing
Navigation ephemeris format, parsing is convenient for users, has compatible well.Existing navigation system still generates 16 ginsengs
Several navigation ephemeris is simultaneously broadcasted by navigation satellite, and low orbit satellite generates the navigation ephemeris of 20 parameters as described above and passes through
Low orbit satellite broadcast, if the broadcast ephemeris that receiver receives existing middle high rail navigation satellite can solve existing navigation satellite
More accurate position and speed, if the broadcast ephemeris for receiving low orbit satellite can also solve the relatively accurate location of low orbit satellite
And speed, for receiver positions and tests the speed.
The present invention uses compatible navigation satellite broadcasting ephemeris expression, utilizes satellite orbit major semiaxis variability, average fortune
Dynamic angular speed variability, latitude argument one third week is sinusoidal and cosine reconciliation correction factor absorbs low orbit satellite orbital period property and takes the photograph
It is dynamic；And track major semiaxis variability, mean motion angle speed are carried out using retention position in navigation satellite navigation message formatting
Variability, latitude argument one third week sine and cosine reconciliation correction factor expression are spent, does not change text structure and original content.
Existing middle high rail navigation satellite ephemeris design and expression are made full use of, realizes low orbit satellite ephemeris and middle high rail satellite navigation
The parameter of ephemeris is compatible and expression way is unified, reduces answering for high rail navigation satellite and low orbit satellite ephemeris in the comprehensive use of user
Polygamy
Broadcasting for navigation message follows rigorous text structure, and the navigation message of one embodiment of the invention is by superframe, master
Frame and subframe composition.Each superframe is 36000 bits, lasts 12 minutes, each superframe is made of 24 prime frames；Each prime frame is
1500 bits last 30 seconds, and each prime frame is made of 5 subframes；Each subframe be 300 bits, last 6 seconds, each subframe by
10 word compositions；Each word is 30 bits, lasts 0.6 second.Each word is made of navigation message data and check code two parts.It leads
The ephemeris that navigates is included in two subframes of navigation message, and text frame format is as shown in Figure 2.Preceding the 15 of the 1st word of each subframe
Bit information carries out error correction, the information of the 1st word using BCH (15,11,1) mode without Error Correction of Coding, rear 11 bit information
Position totally 26 bit；Other 9 words are all made of BCH (15,11,1) plus interleaving mode carries out Error Correction of Coding, other 9 each words of word
Information bit totally 22 bit.For 4 ephemeris parameters newly increased, the reserved page that can use subframe 5 carries out layout and broadcasts,
Its specific layout position is referring to Fig. 3.
As shown in figure 4, the method for carrying out Error Correction of Coding to the navigation ephemeris of low orbit satellite includes the following steps:
Step 1, the generator polynomial of (15,11,1) BCH: g (x)=x is determined4+x+1；
Step 2, by navigation almanac data code according to 11 bit sequential packets；
Step 3, the Error Correction of Coding of (15,11,1) BCH is carried out respectively to two groups of the front and back numeric data code in step 42；
Step 4, output is interleaved by 1 bit sequence to two groups of the front and back BCH code in step 43, forms 30 bit code lengths
Interlaced code.The wherein Bose-Chaudhuri-Hocquenghem Code in step 43 can carry out, detailed process according to the process of Fig. 5 are as follows:
(1) encoder is initialized, sets full 0 for 4 grades of shift registers D0, D1, D2 and D3, door 1 is opened, and door 2 closes；
(2) the information group of 11 bits of displacement input, information parts pass through all the way at two-way or door directly export, another way
Into g (x) division circuit；
(3) 11 bit information groups are all sent into circuit after 11 displacements, and what is retained in shift register at this time is school
Test position；
(4) door 1 closes, and door 2 is opened；
(5) 4 displacements are carried out again, and the check bit of shift register is all exported, is formed with 11 original bit informations
One a length of 15 bit BCH code.
(1)~(5) are complete BCH (15,11,1) coding process, and the repetition process, which can be realized, counts nautical star one by one
According to the Bose-Chaudhuri-Hocquenghem Code of code.
The present invention creatively proposes on the basis of analyzing and investigating comprehensively existing middle high rail navigation ephemeris orbit statement
For the navigation ephemeris and its method of combination of low orbit satellite, new navigation ephemeris will take into account senior middle school's low-orbit satellite, calculate
During can very easily the realizing using upper user of navigation satellite position is transitioned into from existing middle high rail navigational satellite system
Height rail navigational satellite system.
The above description is only an embodiment of the present invention, is not intended to limit the scope of the invention, all to utilize this hair
Equivalent structure or equivalent flow shift made by bright specification and accompanying drawing content is applied directly or indirectly in other relevant skills
Art field, is included within the scope of the present invention.
Claims (3)
1. a kind of low orbit satellite radio news program expression, which is characterized in that the described method includes:
Step 1, radio news program fitting is carried out based on low orbit satellite Precise Orbit, the radio news program is led using compatibility
The expression of boat satellite broadcasting ephemeris increases satellite orbit major semiaxis variability, mean motion angle speed on original parameter basis
Variability, latitude argument one third week sine and cosine reconciliation correction factor are spent, to absorb the perturbation of low orbit satellite orbital period property；
Step 2, track major semiaxis variability, mean motion angle are carried out using retention position in navigation satellite navigation message formatting
Velocity gradient, latitude argument one third week is sinusoidal and cosine reconciliation correction factor is expressed.
2. a kind of low orbit satellite radio news program expression as described in claim 1, which is characterized in that the navigation is defended
Original parameter of star broadcast ephemeris include the ephemeris reference time, the mean anomaly with reference to the moment, eccentricity, semi-major axis square
Root, the longitude of ascending node with reference to the moment, the orbit inclination angle with reference to the moment, the argument of perigee, mean angular velocity correction, ascending node are red
Varied rate, the change rate at inclination angle, the sine of latitude argument and cosine reconcile correction factor, sine from track to diameter and cosine tune
With correction factor and the sine and cosine of orbit inclination angle reconciliation correction factor.
3. a kind of low orbit satellite radio news program expression as described in claim 1, which is characterized in that the satellite rail
Road major semiaxis variability, mean angular velocity of satellite motion variability, the one third of latitude argument week is sinusoidal and cosine reconciliation correction factor can
It is indicated using the different retention positions of navigation satellite text.
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| CN109932734A (en) * | 2019-04-09 | 2019-06-25 | 桂林电子科技大学 | A kind of calculation method suitable for pseudo satellite, pseudolite position |
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