CN106842249A - Aeronautical satellite correction processing method and processing device - Google Patents
Aeronautical satellite correction processing method and processing device Download PDFInfo
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- CN106842249A CN106842249A CN201611144977.6A CN201611144977A CN106842249A CN 106842249 A CN106842249 A CN 106842249A CN 201611144977 A CN201611144977 A CN 201611144977A CN 106842249 A CN106842249 A CN 106842249A
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- profile irregularity
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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
Abstract
The present invention is applied to satellite technology field, there is provided a kind of aeronautical satellite correction processing method and processing device.The method includes calculating the track profile irregularity of aeronautical satellite, carries out quantization according to the first quantified precision and broadcasts, and calculates the quantization error of the track profile irregularity；Calculate the clock error correction number of aeronautical satellite；Quantization error and the clock error correction number according to the track profile irregularity, calculate the quick correction of aeronautical satellite, and carry out quantization with the second quantified precision and broadcast；Wherein, second quantified precision is more than first quantified precision.The method can solve the problem that the quantified precision of aeronautical satellite correction in the prior art is relatively low causes the technical problem of positioning precision reduction, reaches the effect for improving positioning precision.
Description
Technical field
The present invention relates to satellite technology field, and in particular to aeronautical satellite correction processing method and processing device.
Background technology
As the application of satellite navigation system is more and more extensive, realizing the satellite navigation positioning of real-time high-precision turns into concern
Focus.The GPS wide area differential GPS positioning of GNSS (Global Navigation Satellite System, GPS)
System, can correct parameter, so as to lift user to the track of user's real-time broadcasting aeronautical satellite, clock correction and ionospheric error
Real-Time Positioning.
In traditional GNSS GPS wide area differential GPS alignment systems, satellite orbit, clock error correction number information that system is broadcast to user
It is the difference of Precise Orbit, clock correction and broadcast ephemeris, user need to find the broadcast ephemeris for matching could correctly recover accurate rail
Road and clock correction, realize high-precision positioning.Because correction is general by being broadcast after quantization, the loss meeting of relatively low quantified precision
Cause the reduction of positioning precision.
The content of the invention
In view of this, the embodiment of the present invention provides aeronautical satellite correction processing method and processing device, solves in the prior art
Clock error correction number needs matching correspondence broadcast ephemeris to use, and because quantified precision deficiency causes asking for positioning precision reduction
Topic.
A kind of first aspect of the embodiment of the present invention, there is provided aeronautical satellite correction processing method, including：
The track profile irregularity of aeronautical satellite is calculated, quantization is carried out according to the first quantified precision and is broadcast, and calculate the track
The quantization error of correction；
Calculate the clock error correction number of aeronautical satellite；
Quantization error and the clock error correction number according to the track profile irregularity, calculate the quick correction of aeronautical satellite
Count, and quantization is carried out with the second quantified precision and broadcast；
Wherein, second quantified precision is more than first quantified precision.
Preferably, the track profile irregularity for calculating aeronautical satellite is specially：
According to broadcast ephemeris and Precise Orbit value, number of the track profile irregularity on the direction of principal axis of ECEF coordinate systems three is calculated
Value.
Preferably, the clock error correction number for calculating aeronautical satellite is specially：
By formula
Calculate the clock error correction number；Wherein, Δ tpreIt is the clock error correction number, unit is rice；Δt'preIt is original essence
Close clock correction value, unit is the second；C is the light velocity；N is real number, and n>5；Represent to Δ t'pre·c/n+
The 0.5 downward round numbers of result of calculation.
Preferably, the quantization error and the clock error correction number according to the track profile irregularity, calculates aeronautical satellite
Quick correction include：
The quantization error for calculating the track profile irregularity projects to satellite numerical value in the radial direction；
Satellite numerical value in the radial direction is projected to reference to the quantization error of clock error correction number and the track profile irregularity, is counted
Calculate the quick correction.
Preferably, also include：
With reference to broadcast ephemeris, the track profile irregularity and the quick correction, Precise Orbit and clock correction value are reduced.
A kind of second aspect of the embodiment of the present invention, there is provided aeronautical satellite correction processing unit, including：
Track profile irregularity processing module, the track profile irregularity for calculating aeronautical satellite, is carried out according to the first quantified precision
Quantization is broadcast, and calculates the quantization error of the track profile irregularity；
Clock error correction number processing module, the clock error correction number for calculating aeronautical satellite；
Quick correction processing module, for the quantization error according to the track profile irregularity and the clock error correction number,
The quick correction of aeronautical satellite is calculated, and quantization is carried out with the second quantified precision and broadcast；
Wherein, second quantified precision is more than first quantified precision.
Preferably, the track profile irregularity processing module specifically for：
According to broadcast ephemeris and Precise Orbit value, number of the track profile irregularity on the direction of principal axis of ECEF coordinate systems three is calculated
Value.
Preferably, the clock error correction number processing module specifically for：
By formula
Calculate the clock error correction number；Wherein, Δ tpreIt is the clock error correction number, unit is rice；Δt'preIt is original essence
Close clock correction value, unit is the second；C is the light velocity；N is real number, and n>5；Represent to Δ t'pre·c/n+
The 0.5 downward round numbers of result of calculation.
Preferably, the quick correction processing module includes：
Quantization error processing unit, the quantization error for calculating the track profile irregularity projects to satellite in the radial direction
Numerical value；
Quick correction computing unit, the quantization error for combining clock error correction number and the track profile irregularity is projected to
Satellite numerical value in the radial direction, calculates the quick correction.
Preferably, also include：
Recovery module, for combining broadcast ephemeris, the track profile irregularity and the quick correction, reduces Precise Orbit
With clock correction value.
Using above-mentioned technical proposal, the present invention can at least obtain following technique effects：Calculate the orbit correction of aeronautical satellite
Number, carries out quantization and broadcasts according to the first relatively low quantified precision, and calculates the quantization error of the track profile irregularity and navigation is defended
The clock error correction number of star；Then quantization error according to the track profile irregularity and the clock error correction number, calculate aeronautical satellite
Quick correction, and quantization carried out with the second quantified precision higher broadcast, therefore the embodiment of the present invention can effectively solve the problem that
Clock error correction number needs the problem that matching correspondence broadcast ephemeris is used, while solving to cause positioning precision due to quantified precision deficiency
The problem of reduction, reaches the effect for improving positioning precision.
Brief description of the drawings
Technical scheme in order to illustrate more clearly the embodiments of the present invention, institute in being described to the embodiment of the present invention below
The accompanying drawing for needing to use is briefly described, it should be apparent that, drawings in the following description are only some implementations of the invention
Example, for those of ordinary skill in the art, on the premise of not paying creative work, can also implement according to the present invention
The content and these accompanying drawings of example obtain other accompanying drawings.
Fig. 1 is the flow chart of the aeronautical satellite correction processing method described in the present embodiment；
Fig. 2 is, according to track profile irregularity and clock error correction number, to calculate the quick correction of aeronautical satellite described in the present embodiment
Several realizes flow chart；
Fig. 3 is the structured flowchart of the aeronautical satellite correction processing unit described in the present embodiment；
Fig. 4 is the structured flowchart of the quick correction processing module described in the present embodiment；
Fig. 5 is the structural representation of the aeronautical satellite correction processing unit described in the present embodiment.
Specific embodiment
The disclosure for providing description referring to the drawings to help comprehensive understanding to be limited by claim and its equivalent
Various embodiments.Hereinafter description includes the various details for helping understand, but these details will be considered as only being example
Property.Therefore, it will be appreciated by those of ordinary skill in the art that do not depart from the scope of the present disclosure and spirit in the case of, can be right
Various embodiments described herein makes various changes and modifications.In addition, in order to clear and succinct, known function and construction are retouched
Stating to be omitted.
Term and vocabulary used in following description and claims are not limited to document implication, but only by inventor
For enabling the disclosure clearly and as one man to be understood.Therefore, to those skilled in the art it should be apparent that carrying
The description of various embodiments of this disclosure is merely to exemplary purpose under being provided with, and it is unrestricted by appended claims and its
The purpose of the disclosure that equivalent is limited.
It should be understood that unless context is clearly indicated in addition, otherwise singulative also includes plural.Thus, for example,
Reference to " assembly surface " includes the reference to one or more such surfaces.
Embodiment one
Fig. 1 is the flow chart of the present embodiment aeronautical satellite correction processing method.
With reference to Fig. 1, the aeronautical satellite correction processing method described in the present embodiment comprises the following steps：
Step S101, calculates the track profile irregularity of aeronautical satellite, carries out quantization according to the first quantified precision and broadcasts, and calculates
The quantization error of the track profile irregularity.
In this step, the track profile irregularity for calculating aeronautical satellite is specifically as follows：
According to broadcast ephemeris and Precise Orbit value, track profile irregularity is calculated in ECEF (earth-centered, earth-
Fixed, ECEF coordinate system) numerical value on three change in coordinate axis direction.
Carry out quantization according to the first quantified precision and broadcast specifically, described, can be realized by formula (1)：
Wherein, under Δ X, Δ Y and Δ Z are ECEF coordinate systems, track profile irregularity quantify in three axial directions after numerical value, it is single
Position is rice；[Xpre Ypre Zpre] it is satellite precise coordinate, unit is rice；[Xbrd Ybrd Zbrd] it is satellite broadcasting coordinate, unit
It is rice；UnitorbIt is the first quantified precision of track profile irregularity, precision is relatively low, for example, be chosen as 0.1 meter；Represent to A to
Under round.
It is corresponding, the quantization error of the track profile irregularity can be calculated by formula (2)：
Wherein, [δ x δ y δ z] is quantization error of the track profile irregularity on each axial direction, and unit is rice.
Step S102, calculates the clock error correction number of aeronautical satellite.
Wherein it is possible to the statistical property using satellite broadcasting clock correction error better than 5 meters, precise clock correction is to modulo n, completion number
According to interception, and using interception value as clock error correction number.Wherein, n is real number, and n>5, it is chosen as 10.Precise clock correction takes to n
Mould, can break away from the thinking that traditional satellite clock correction correction is resolved using precise clock correction with broadcast clock correction difference, using satellite
Clock correction short-term stability is good, and statistical property of the broadcast clock correction precision better than 5 meters, by way of data cutout, only broadcasts reality
When precise clock correction reduce coding to the numerical value after modulo n, effectively and digit and broadcast data volume.
Specifically, the clock error correction number can be calculated by formula (3)：
Wherein, Δ tpreIt is the clock error correction number, unit is rice；Δt'preIt is original precise clock correction value, unit is the second；c
It is the light velocity, unit is meter per second；N is real number, and n>5, n can value be 10；Represent to Δ t'pre·
The downward round numbers of result of calculation of c/n+0.5.
Step S103, quantization error and the clock error correction number according to the track profile irregularity calculate aeronautical satellite
Quick correction, and quantization is carried out with the second quantified precision broadcast.
Wherein, second quantified precision is more than first quantified precision.Quick correction includes clock error correction number
With the quantization error value of track profile irregularity, and carry out quantization according to the second quantified precision higher and broadcast, therefore, it is possible to correct rail
Influence of the quantization error in road to positioning precision.
Referring to Fig. 2, in one embodiment, step S103 can include procedure below：
Step S201, the quantization error for calculating the track profile irregularity projects to satellite numerical value in the radial direction.
In one embodiment, the quantization error that can calculate the track profile irregularity by formula (4) projects to satellite footpath
To the numerical value on direction：
Wherein, Δ R projects to satellite numerical value in the radial direction for the quantization error of track profile irregularity, and unit is rice；
It is three axle quantisation error vectors under ECEF coordinate systems, each element unit is rice；It is satellite position to the unitization of the earth's core
Vector, i.e. radial vector.
In the present embodiment,
Wherein, R is the distance of the satellite position heart on earth, and unit is rice；[Xsat Ysat Zsat] it is defending under ECEF coordinate systems
Star coordinate vector, each element unit is rice；
Step S202, satellite is projected in the radial direction with reference to the quantization error of clock error correction number and the track profile irregularity
Numerical value, calculate the quick correction.
In this step, the quick correction can be calculated by formula (5)：
Δ Fcor'=Δs tpre-ΔR (5)
Wherein, Δ Fcor' is quick correction, and unit is rice；ΔtpreIt is the precise clock correction value after interception, unit is rice.
In the present embodiment, after calculating the quick correction, the quick correction is carried out with the second quantified precision
After quantization, you can broadcast to user.The quick correction can be quantified by formula (6)：
Wherein, Δ Fcor is the quick correction after quantifying, and unit is rice；Δ Fcor' is non-quantized quick correction,
Unit is rice；UnitclkIt is the second quantified precision of quick correction, precision is higher, for example, be chosen as 0.001 meter；Represent
A is rounded downwards.
Further, after step s 103, the aeronautical satellite correction processing method can also include：
With reference to broadcast ephemeris, the track profile irregularity and the quick correction, Precise Orbit and clock correction value are reduced.
Wherein, the numerical value that Precise Orbit can be by broadcast ephemeris with track profile irregularity on each axial direction is added realization also
It is former.Clock error correction number can utilize n meters of above numerical value for broadcasting clock correction that the preliminary reduction of realization is added with quick correction.Then,
Preliminary reducing value to clock error correction number carries out data validation, if reducing value is differed no more than n with broadcast clock correction, obtains accurate
Clock correction；Otherwise, the amendment of ± n is carried out with the difference of broadcast clock correction according to reducing value, precise clock correction value is obtained.
Specifically, Precise Orbit can be reduced by formula (7)：
Wherein, [Xpre Ypre Zpre] it is precise satellite orbital position, each element unit is rice；[Xbrd Ybrd Zbrd] it is wide
Satellite orbital position is broadcast, each element unit is rice；[ΔXsat ΔYsat ΔZsat] it is the track profile irregularity of satellite, each element list
Position is rice.
Clock error correction number is reduced by formula (8)：
Wherein, Δ t is the true precise clock correction value of final reduction, and unit is rice；ΔtbrdIt is broadcast ephemeris clock correction value, it is single
Position is the second；C is the light velocity；Δ t' is the precise clock correction after preliminary reduction, and unit is rice, and Δ t'=int (Δ tbrd·c/n)·n
+Δtpre, n is real number, and n>5, it is chosen as 10.
It should be understood that can simply recover Precise Orbit and clock correction value using broadcast ephemeris, and positioning calculation is carried out,
So as in solving conventional method, be jumped because broadcast ephemeris and clock error correction number mismatch the Static Precise Point Positioning result for causing
Change problem, while user's positioning precision is improved, effectively reduces coding occupy-place.
Above-mentioned aeronautical satellite correction processing method, calculates the track profile irregularity of aeronautical satellite, with the first relatively low quantization
Precision is broadcast, and calculates the quantization error of track profile irregularity and the clock error correction number of aeronautical satellite；Then according to the rail
The quantization error of road correction and the clock error correction number, calculate the quick correction of aeronautical satellite, and amendment quantization error is to fixed
The influence of position, lifts correction effect, and carries out quantization with the second quantified precision higher and broadcast, additionally it is possible to break away from user terminal to wide
The dependence of ephemeris age is broadcast, user's Static Precise Point Positioning result jump problem caused by difference text time sequential is solved, while
The influence of orbit correction quantization error, lifting correction precision are eliminated, and by way of data cutout, reduces the number broadcast
According to value, the coding digit of text is reduced.
It should be understood that the size of the sequence number of each step is not meant to the priority of execution sequence, each process in above-described embodiment
Execution sequence should determine that the implementation process without tackling the embodiment of the present invention constitutes any limit with its function and internal logic
It is fixed.
Embodiment two
Corresponding to the aeronautical satellite correction processing method described in foregoing embodiments, Fig. 3 shows embodiment of the present invention institute
The structured flowchart of the aeronautical satellite correction processing unit stated.For convenience of description, illustrate only portion related to the present embodiment
Point.
With reference to Fig. 3, the aeronautical satellite correction processing unit described in the present embodiment can include that track profile irregularity processes mould
Block 301, clock error correction number processing module 302 and quick correction processing module 303.Wherein：
Track profile irregularity processing module 301, the track profile irregularity for calculating aeronautical satellite, enters according to the first quantified precision
Row quantization is broadcast, and calculates the quantization error of the track profile irregularity.
Clock error correction number processing module 302, the clock error correction number for calculating aeronautical satellite.
Quick correction processing module 303, for the quantization error according to the track profile irregularity and the clock error correction
Count, calculate the quick correction of aeronautical satellite, and quantization is carried out with the second quantified precision and broadcast.
Wherein, second quantified precision is more than first quantified precision.
In one embodiment, the track profile irregularity processing module 301 specifically can be used for：
According to broadcast ephemeris and Precise Orbit value, the track profile irregularity on the direction of principal axis of ECEF coordinate systems three is calculated.
In one embodiment, the clock error correction number processing module 302 specifically can be used for：
By formula
Calculate the clock error correction number；Wherein, Δ tpreIt is the clock error correction number, unit is rice；Δt'preIt is original essence
Close clock correction value, unit is the second；C is the light velocity；Represent to Δ t'preThe result of calculation of c/n+0.5 is downward
Round numbers；N is real number, and n>5, it is chosen as 10.
Referring to Fig. 4, in one embodiment, it is single that the quick correction processing module 303 can include that quantization error is calculated
Unit 401 and quick correction computing unit 402.Wherein：
Quantization error computing unit 401, the quantization error for calculating the track profile irregularity.
Quick correction computing unit 402, for the quantization error of the track profile irregularity to be projected into satellite radial direction side
Upwards, and with reference to clock error correction number, the quick correction is calculated.
Further, the aeronautical satellite correction processing unit can also include recovery module.Wherein：
The recovery module, for combining broadcast ephemeris, the track profile irregularity and the quick correction, reduction is accurate
Track and clock correction value.
Embodiment three
It is the schematic block diagram of the aeronautical satellite correction processing unit that the embodiment of the present invention three is provided referring to Fig. 5.Such as Fig. 5
Shown aeronautical satellite correction processing unit can include：One or more processors 501 (only show one) in figure；One
Or multiple input equipments 502 (is only shown in figure), one or more output equipments 503 (one is only shown in figure) and storage
Device 504.Above-mentioned processor 501, input equipment 502, output equipment 503 and memory 504 are connected by bus 505.Memory
504 are used for store instruction, and processor 501 is used to perform the instruction of the storage of memory 504.Wherein：
The processor 501, the track profile irregularity for calculating aeronautical satellite, is set according to the first quantified precision by output
Standby 503 carry out quantization broadcasts, and calculates the quantization error of the track profile irregularity and the clock error correction number of aeronautical satellite.The place
Reason device 501, is additionally operable to the quantization error and the clock error correction number according to the track profile irregularity, calculates the quick of aeronautical satellite
Correction, and quantization is carried out by output equipment 503 with the second quantified precision broadcast.Wherein, second quantified precision is more than
First quantified precision.
Optionally, the processor 501 is specifically for according to broadcast ephemeris and Precise Orbit value, calculating the orbit correction
Numerical value of the number on the direction of principal axis of ECEF coordinate systems three.
Optionally, the processor 501 specifically for：By formula
Calculate the clock error correction number；Wherein, Δ tpreIt is the clock error correction number, unit is rice；Δt'preIt is original essence
Close clock correction value, unit is the second；C is the light velocity；Represent to Δ t'preThe result of calculation of c/n+0.5 to
Lower round numbers；N is real number, and n>5, it is chosen as 10.
Optionally, the processor 501 projects to satellite footpath specifically for calculating the quantization error of the track profile irregularity
To the numerical value on direction, and satellite radial direction is projected to reference to the quantization error of clock error correction number and the track profile irregularity
On numerical value, calculate the quick correction.
Further, the processor 501 is additionally operable to combine broadcast ephemeris, the track profile irregularity and the quick correction
Number, reduces Precise Orbit and clock correction value.
The memory 504, for storing software program, module and the network interaction data, the processor 501 leads to
Software program and unit of the operation storage in the memory 504 are crossed, so that various function application and data processing are performed,
Realize the information exchange function of terminal.
It should be appreciated that in embodiments of the present invention, alleged processor 501 can be CPU (Central
Processing Unit, CPU), the processor can also be other general processors, digital signal processor (Digital
Signal Processor, DSP), application specific integrated circuit (Application Specific Integrated Circuit,
ASIC), ready-made programmable gate array (Field-Programmable Gate Array, FPGA) or other FPGAs
Device, discrete gate or transistor logic, discrete hardware components etc..General processor can be microprocessor or this at
Reason device can also be any conventional processor etc..
Input equipment 502 can include that Trackpad, fingerprint adopt sensor (finger print information and fingerprint for gathering user
Directional information), microphone etc., output equipment 503 can be including display (LCD etc.), loudspeaker etc..
The memory 504 can include read-only storage and random access memory, and to processor 501 provide instruction and
Data.The a part of of memory 504 can also include nonvolatile RAM.For example, memory 504 can also be deposited
Store up the information of device type.
In implementing, processor 501, input equipment 502, the and of output equipment 503 described in the embodiment of the present invention
Memory 504 can perform the realization described in the embodiment of aeronautical satellite correction processing method provided in an embodiment of the present invention
Mode, also can perform the implementation described in the embodiment of aeronautical satellite correction processing unit, will not be repeated here.
In sum, above-mentioned aeronautical satellite correction processing unit, calculates the track profile irregularity of aeronautical satellite, with relatively low
First quantified precision is broadcast, and calculates the quantization error of track profile irregularity and the clock error correction number of aeronautical satellite；Then root
According to the quantization error and the clock error correction number of the track profile irregularity, the quick correction of aeronautical satellite is calculated, amendment quantifies
Influence of the error to positioning, lifts correction effect, and carries out quantization with the second quantified precision higher and broadcast, additionally it is possible to break away from use
Dependence of the family end to broadcast ephemeris age, user's Static Precise Point Positioning result saltus step is asked caused by breaking away from difference text time sequential
Topic, while the influence of orbit correction quantization error is eliminated, lifting correction precision, and by way of data cutout, reduce
The data value broadcast, reduces the coding digit of text.
It should be noted that the various embodiments of the disclosure as described above are generally related to input data to a certain extent
Treatment and output data generation.The treatment of this input data and output data generation can be in hardware or soft with combination of hardware
Realized in part.For example, can in mobile device or similar or related circuit using specific electronic components for realize with
The function of the various embodiments association of the disclosure as described above.Alternatively, according to the instruction for being stored operate one or more
Multiple processors can realize the function of being associated with the various embodiments of the disclosure as described above.If it is, then these instructions
Can be stored on one or more non-transitory processor readable mediums, this is in the scope of the present disclosure.Processor can
The example for reading medium includes read-only storage (ROM), random access memory (RAM), CD-ROM, tape, floppy disk and optics number
According to storage device.In addition, for realizing that functional computer program, instruction and the instruction segment of the disclosure can be by disclosure arts
Programmer easily explain.
Although the various embodiments with reference to the disclosure have shown and described the disclosure, those skilled in the art will manage
Solution, in the case where the spirit and scope of the present disclosure being defined by the appended claims and the equivalents thereof are not departed from, can enter to it
Various changes in row form and details.
Claims (10)
1. a kind of aeronautical satellite correction processing method, it is characterised in that including：
The track profile irregularity of aeronautical satellite is calculated, quantization is carried out according to the first quantified precision and is broadcast, and calculate the orbit correction
Several quantization errors；
Calculate the clock error correction number of aeronautical satellite；
Quantization error and the clock error correction number according to the track profile irregularity, calculate the quick correction of aeronautical satellite, and
Quantization is carried out with the second quantified precision to broadcast；
Wherein, second quantified precision is more than first quantified precision.
2. method as claimed in claim 1, it is characterised in that the track profile irregularity of the calculating aeronautical satellite is specially：
According to broadcast ephemeris and Precise Orbit value, numerical value of the track profile irregularity on the direction of principal axis of ECEF coordinate systems three is calculated.
3. method as claimed in claim 1, it is characterised in that the clock error correction number of the calculating aeronautical satellite is specially：
By formula
Calculate the clock error correction number；Wherein, Δ tpreIt is the clock error correction number, unit is rice；Δt'preIt is original accurate clock
Difference, unit is the second；C is the light velocity；N is real number, and n>5；Represent to Δ t'preC/n+0.5's
The downward round numbers of result of calculation.
4. method as claimed in claim 1, it is characterised in that the quantization error and the clock according to the track profile irregularity
Difference correction, the quick correction for calculating aeronautical satellite includes：
The quantization error for calculating the track profile irregularity projects to satellite numerical value in the radial direction；
Satellite numerical value in the radial direction is projected to reference to the quantization error of clock error correction number and the track profile irregularity, institute is calculated
State quick correction.
5. method as claimed in claim 1, it is characterised in that also include：
With reference to broadcast ephemeris, the track profile irregularity and the quick correction, Precise Orbit and clock correction value are reduced.
6. a kind of aeronautical satellite correction processing unit, it is characterised in that including：
Track profile irregularity processing module, the track profile irregularity for calculating aeronautical satellite, is quantified according to the first quantified precision
Broadcast, and calculate the quantization error of the track profile irregularity；
Clock error correction number processing module, the clock error correction number for calculating aeronautical satellite；
Quick correction processing module, for the quantization error according to the track profile irregularity and the clock error correction number, calculates
The quick correction of aeronautical satellite, and quantization is carried out with the second quantified precision broadcast；
Wherein, second quantified precision is more than first quantified precision.
7. device as claimed in claim 6, it is characterised in that the track profile irregularity processing module specifically for：
According to broadcast ephemeris and Precise Orbit value, numerical value of the track profile irregularity on the direction of principal axis of ECEF coordinate systems three is calculated.
8. device as claimed in claim 6, it is characterised in that the clock error correction number processing module specifically for：
By formula
Calculate the clock error correction number；Wherein, Δ tpreIt is the clock error correction number, unit is rice；Δt'preIt is original accurate clock
Difference, unit is the second；C is the light velocity；N is real number, and n>5；Represent to Δ t'preC/n+0.5's
The downward round numbers of result of calculation.
9. device as claimed in claim 6, it is characterised in that the quick correction processing module includes：
Quantization error processing unit, the quantization error for calculating the track profile irregularity projects to satellite number in the radial direction
Value；
Quick correction computing unit, the quantization error for combining clock error correction number and the track profile irregularity projects to satellite
Numerical value in the radial direction, calculates the quick correction.
10. device as claimed in claim 6, it is characterised in that also include：
Recovery module, for combining broadcast ephemeris, the track profile irregularity and the quick correction, reduces Precise Orbit and clock
Difference.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108761508A (en) * | 2018-03-09 | 2018-11-06 | 羲和时空（武汉）网络科技有限公司 | A kind of satellite position restores with satellite clock correction and track clock error correction number representation method |
| WO2019033883A1 (en) * | 2017-08-14 | 2019-02-21 | 千寻位置网络有限公司 | Method and apparatus for generating long-term satellite orbit and clock offset, based on ground tracking station |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| WO2019033883A1 (en) * | 2017-08-14 | 2019-02-21 | 千寻位置网络有限公司 | Method and apparatus for generating long-term satellite orbit and clock offset, based on ground tracking station |
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| CN108761508A (en) * | 2018-03-09 | 2018-11-06 | 羲和时空（武汉）网络科技有限公司 | A kind of satellite position restores with satellite clock correction and track clock error correction number representation method |
| CN111142124A (en) * | 2018-11-02 | 2020-05-12 | 千寻位置网络有限公司 | Global satellite navigation system state space expression mode integrity monitoring method and device |
| CN111025341A (en) * | 2019-11-22 | 2020-04-17 | 中国科学院上海天文台 | Error refinement method for satellite orbit |
| CN111025341B (en) * | 2019-11-22 | 2023-04-07 | 中国科学院上海天文台 | Error refinement method for satellite orbit |
| CN116299586A (en) * | 2022-12-07 | 2023-06-23 | 中国科学院上海天文台 | Precise single-point positioning method, receiver, equipment and medium based on broadcast ephemeris |
| CN116299586B (en) * | 2022-12-07 | 2023-11-03 | 中国科学院上海天文台 | Precise single-point positioning method, receiver, equipment and medium based on broadcast ephemeris |
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