CN106093967A - The ionosphere delay method for solving that a kind of pseudorange phase place is comprehensive - Google Patents

The ionosphere delay method for solving that a kind of pseudorange phase place is comprehensive Download PDF

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CN106093967A
CN106093967A CN201610705331.4A CN201610705331A CN106093967A CN 106093967 A CN106093967 A CN 106093967A CN 201610705331 A CN201610705331 A CN 201610705331A CN 106093967 A CN106093967 A CN 106093967A
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ionosphere delay
epoch
pseudorange
carrier wave
formula
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陈俊平
房成贺
杨赛男
巩秀强
陈倩
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Shanghai Astronomical Observatory of CAS
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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
    • G01S19/07—Cooperating elements; Interaction or communication between different cooperating elements or between cooperating elements and receivers providing data for correcting measured positioning data, e.g. DGPS [differential GPS] or ionosphere corrections

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
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Abstract

The invention discloses the ionosphere delay method for solving that a kind of pseudorange phase place is comprehensive, it includes step: obtain ionosphere delay epoch based on Pseudo-range Observations, builds observational equation；Obtain the change of ionosphere delay between epoch based on carrier phase observable, build observational equation；Build corresponding normal equation and combine to solve and obtain the ionosphere delay that pseudorange phase place is comprehensive.The inventive method uses Pseudo-range Observations to solve ionosphere delay absolute magnitude, and between epoch, differential phase observation solves ionosphere delay variable quantity, carries out comprehensive on this basis, thus solves the convergence problem in carrier phase smoothed pseudorange observation method.It is independent of the long-time continuous of phase data, and avoids directly using carrier phase observable ambiguity resolution, improve precision and reliability that ionosphere delay solves.The inventive method can be applicable to ionosphere delay in satellite navigation basic navigation and satellite-based augmentation system and calculates, and the calculating of the Ionospheric delay correcting number in user location and service system thereof.

Description

The ionosphere delay method for solving that a kind of pseudorange phase place is comprehensive
Technical field
The present invention relates to the ionosphere delay method for solving of field of satellite navigation, particularly relate to a kind of pseudorange phase place comprehensive Ionosphere delay method for solving.
Background technology
Global navigational satellite alignment system (Global Navigation Satellite System, GNSS), refers to adopt Tellurian object is positioned by the electromagnetic wave launched with aeronautical satellite, the system with time service of navigating, and includes the U.S. at present GPS, Muscovite GLONASS, the GALILEO system in Europe and the BDS system of China.User utilizes receiver observation to obtain The distance of distance satellite and carrier phase observable, can try to achieve the position of this moment receiver.
The error source affecting satellite navigation system service performance specifically includes that satellite orbital error, satellite clock mistake are poor, right Fluid layer error, ionospheric error and observation Multipath Errors etc..Wherein ionosphere is in the range of height is about 60～1000km Ionizing atmosphere, its structure can characterize with ionospheric series of characteristics parameter, including electron density, ion concentration, Electron temperature, ion temperature etc..Ionosphere is as a kind of propagation medium, it may occur that reflects, reflect, scatters and absorb aerogram Number, electromagnetic wave propagation is had a huge impact.For single-frequency user positions, ionosphere is main error source, Its ionosphere delay caused makes range error can reach tens meters, has seriously undermined the precision of satellite navigation location with accurate Degree.
In order to ensure precision and the accuracy that satellite navigation positions, satellite navigation basic navigation and satellite-based augmentation system need Ionosphere delay calculating to be carried out, needs to carry out the calculating of Ionospheric delay correcting number in user location and service system thereof.Defend Using empirical model to correct ionosphere delay error in star navigation system basic navigation text, it typically can eliminate The ionosphere delay error of about 60%.For improving the precision that ionosphere delay error corrects, satellite-based augmentation system is in Empirical Mode On the basis of type, the method using ionosphere grid model.Ionosphere grid service area on longitude, latitude direction, according to Given interval is divided into different grid, and provides the real-time ionospheric delay error corrected value in each grid points.Ionization Layer grid typically can eliminate the ionosphere delay error of about 80%.
The technology basic thought that existing ionosphere delay calculates is as described below: 1. double to receiver known to survey station position Frequently pseudorange observation data carry out every common error correction；2. the pseudo range observed quantity after correcting and survey station and the reason of satellite distance Opinion value asks difference to obtain residual error observed quantity；3. residual errors based on two frequency pseudorange observation solve ionosphere observation；4. to appointment In time period, the ionosphere observation of different survey stations is modeled, and generates and adapts to the ionosphere delay parameter that broadcast message is broadcast. Wherein, for basic navigation ionospheric model conventional for Klobuchar model, within its 1～2 hour, update once；Big Dipper satellite-based The ionosphere grid coverage that enhancing system provides is east longitude 70～145 degree, and north latitude 7.5～55 degree, by longitude and latitude 5 × 2.5 Degree divides, and forms 320 grid points, and the frequency that grid updates is 6 minutes.
The arbitrarily receiver of survey station is f to a satellite in frequency1Carrier wave L1It is f with frequency2Carrier wave L2On pseudorange Observational equation is:
P 1 = ρ + c ( δt r - δt s ) + d t r o p + I 1 + B 1 + ϵ 1 P 2 = ρ + c ( δt r - δt s ) + d t r o p + I 2 + B 2 + ϵ 2 - - - ( 1 )
In formula: P1、P2It is respectively carrier wave L1、L2On Pseudo-range Observations, ρ is satellite to the geometric distance of receiver, and c is The light velocity, δ trFor receiver clock-offsets, δ tsFor satellite clock correction, dtropFor tropospheric delay, B1、B2It is respectively carrier wave L1、L2Upper satellite Postpone with the system hardware of receiver, ε1、ε2It is respectively carrier wave L1、L2On pseudorange observation noise, I1、I2It is respectively carrier wave L1、L2 On ionosphere delay.
In formula (1), satellite clock correction δ tsCan calculate from the broadcast message that receiver receives and obtain；Tropospheric delay dtropCan Empirical model is used to correct by actual measurement meteorologic parameter；The system hardware of receiver postpones the most identical part Can be by receiver clock-offsets δ trAbsorbing, the calibration value that the difference of different frequent points is provided by receiver producer corrects；Satellite be System hardware delay can obtain from broadcast message；And ionosphere delay I1、I2Relevant with frequency, its expression formula is:
I j = 0.4028 T E C f j 2 - - - ( 2 )
In formula: IjFor the ionospheric delay values on jth frequency carrier, TEC is the total electron content in signal propagation path, fjFor carrier frequency.Obtain the ionosphere delay of arbitrary frequency carrier according to formula (2) after, other frequency carriers can be tried to achieve Ionosphere delay.
In formula (1), the Pseudo-range Observations of two frequency carriers does difference, can be with cancellation receiver clock correction δ tr, satellite orbit, defend Star clock correction δ ts, tropospheric delay dtropThe impact of equal error.Convolution (2) obtains carrier wave L1On ionosphere delay I1Expression Formula is:
I 1 = f 2 2 f 1 2 - f 2 2 [ ( P 2 - P 1 ) - ( B 2 - B 1 ) ] - - - ( 3 )
In formula (3), calculate carrier wave L initially with pseudorange observation value-based algorithm1、L2On Pseudo-range Observations P1、P2, substitute into formula (3) carry out the real-time abatement of pseudo range data Multipath Errors, substitute into carrier wave L known to formula (3) the most again1、L2Upper satellite B is postponed with the system hardware of receiver1、B2Correct, thus try to achieve carrier wave L in real time1On ionosphere delay I1, the most each The survey station ionosphere delay to every moonscope.
Generally the data used that calculate of ionosphere delay error are Pseudo-range Observations, and its precision is by pseudo range measurement noise Impact.For reducing pseudorange effect of noise, carrier phase smoothed pseudorange observation (CNMC, Code Noise and can be used Multipath Correction).The effectiveness of carrier phase smoothed pseudorange observation algorithm relies heavily on phase data Seriality.It is critical only that by calculating the difference between pseudorange and high-precision phase position of carrier phase smoothed pseudorange observation algorithm, asks Take the probit of fuzziness in phase observations.The precision using this algorithm phase ambiguity to ask for depend on the precision of pseudorange with And data length.High 2 orders of magnitude of carrier phase observable ratio of precision Pseudo-range Observations precision, but owing to carrier phase observable comprises not The integer ambiguity parameter known, therefore processing in real time of phase data generally there are longer convergence time, and number is occurring According to starting, interrupt or in the case of cycle slip/new fuzziness occur, carrier phase smoothed pseudorange observation needing again to restrain, and leads Cause a period of time internal ionization layer and postpone the reduction of correction calculation accuracy.Therefore pseudo-based on raw pseudo range observation or smoothing pseudorange Ionosphere delay treatment technology away from observation is the most relatively low in precision or reliability.Process in view of above phase data Complexity, the processing scheme of existing satellite navigation system ionosphere delay is all based only on Pseudo-range Observations.
Summary of the invention
It is an object of the invention to provide the ionosphere delay method for solving that a kind of pseudorange phase place is comprehensive, this ionosphere delay is asked Solution method can improve ionosphere delay solving precision and reliability.
According to foregoing invention purpose, the present invention proposes the ionosphere delay method for solving that a kind of pseudorange phase place is comprehensive, its Including step:
Process segmental arc is divided into n epoch ti, wherein i=1,2 ... n；
T epoch is obtained based on Pseudo-range ObservationsiIonosphere delayAnd by this ionosphere delayAs observation structure Build observational equation:
I ^ t i - I c , t i = v c , t i - - - ( 4 ) ,
Wherein:For t epochiThe actual value of ionosphere delay,For residual error；
T epoch is obtained based on carrier phase observableiAnd ti-1Between the change of ionosphere delayAnd by this ionization The change that layer postponesAs observation structure observational equation:
Wherein:WithIt is respectively t epochiAnd ti-1The actual value of ionosphere delay,For residual error；
With t each epochiVariance matrix PiAs power battle array, based on formula (4) and formula (5) to all n epoch tiSuperposition, then:
Normal equation is obtained by formula (4):
E T P c E I ^ = E T P c I c - - - ( 6 ) ,
Normal equation is obtained by formula (5):
Wherein: E is the unit matrix of n × n, A is the factor arrays corresponding with formula (5), for
A = - 1 1 0 ... 0 0 0 - 1 1 ... 0 0 ... ... ... ... ... ... ... ... ... ... ... ... 0 0 0 ... - 1 1 ( n - 1 ) × n ,
PcBattle array is weighed for the pseudorange piecemeal corresponding with formula (4),Weigh battle array for the phase place piecemeal corresponding with formula (5), and have:
Association type (6) and formula (7) solve and obtain the ionosphere delay that pseudorange phase place is comprehensive
The comprehensive ionosphere delay method for solving of pseudorange phase place of the present invention uses Pseudo-range Observations to solve ionosphere Postponing absolute magnitude, between epoch, differential phase observation solves ionosphere delay variable quantity, carries out two kinds of results on this basis Comprehensively, thus solve convergence problem present in current carrier phase smoothed pseudorange observation method.Pseudorange phase of the present invention The comprehensive ionosphere delay method for solving in position be not need to rely on phase data long-time continuously, and avoid and directly use phase The resolving of position observation fuzziness, algorithm is easy, improves precision and reliability that ionosphere delay solves.
In the ionosphere delay method for solving that pseudorange phase place of the present invention is comprehensive, obtain ionization based on Pseudo-range Observations The absolute value that layer postpones, then obtains the variable quantity between high accuracy ionosphere delay epoch based on carrier phase observable.Prolong in ionosphere Late between epoch in result of variations, as long as the absolute value of known wherein any one epoch, all formed together with this epoch continuously The ionosphere delay of observation is the most just determined, and this is just attributed to benchmark problem in adjustment field.Solution may is that utilization The result of pseudorange is as initial value, when initial value is more than one, can be weighted as dummy observation by Pseudo-range Observations, finally adopt Solve with least square.
The comprehensive ionosphere delay method for solving of pseudorange phase place of the present invention can be applicable to satellite navigation basic navigation And ionosphere delay in satellite-based augmentation system calculates, and the Ionospheric delay correcting number in user location and service system thereof Calculating.
Further, in the ionosphere delay method for solving that pseudorange phase place of the present invention is comprehensive, based on survey station to defending The double frequency carrier wave L of star1And L2, obtain t epoch according to following formulaiIonosphere delay
I c , t i = f 2 2 f 1 2 - f 2 2 [ ( P t i , 2 - P t i , 1 ) - ( B 2 - B 1 ) ] - - - ( 8 ) ,
Wherein:For t epochiAt carrier wave L1On ionosphere delay, f1And f2It is respectively carrier wave L1And L2Frequency, WithIt is respectively t epochiAt carrier wave L1And L2On Pseudo-range Observations, B1And B2It is respectively carrier wave L1And L2On satellite and connect The system hardware of receipts machine postpones.
In such scheme, formula (8) is utilized to obtain the absolute value of ionosphere delay based on Pseudo-range Observations.
Further, in the ionosphere delay method for solving that above-mentioned pseudorange phase place is comprehensive, carrier phase smoothed pseudorange is used to see Measured value algorithm obtains t epochiAt carrier wave L1And L2On Pseudo-range ObservationsWith
In such scheme, use carrier phase smoothed pseudorange observation algorithm to carry out data smoothing, reduce its noise, improve data Precision.
Further, in the ionosphere delay method for solving that pseudorange phase place of the present invention is comprehensive, based on survey station to defending The double frequency carrier wave L of star1And L2, obtain t epoch according to following formulaiAnd ti-1Between the change of ionosphere delay
Wherein: Δ is difference operator, f1And f2It is respectively carrier wave L1And L2Frequency, λ1And λ2It is respectively carrier wave L1And L2's Wavelength,WithIt is respectively carrier wave L1And L2On carrier phase observation data.
In such scheme, utilize formula (9) to use phase difference to obtain high accuracy ionosphere delay based on carrier phase observable and go through Variable quantity between unit.
Same formula (8) is similar, and any survey station is to carrier wave L in the signal propagation path of a satellite1On ionosphere delay, can Being calculated by dual-frequency carrier observation, its expression formula is:
In formula: Δ is difference operator, f1And f2It is respectively carrier wave L1And L2Frequency, λ1And λ2It is respectively carrier wave L1And L2's Wavelength,WithIt is respectively carrier wave L1And L2On carrier phase observation data, N1、N2It is respectivelyInitial integral circumference ambiguity Degree.Compared with formula (8), many integer ambiguity parameters in expression formula.
Comparing formula (8) pseudorange equation, carrier phase observable contains the process of fuzziness.The premise of cycle slip is not had in fuzziness Under, adjacent epoch is made difference by formula (10), available above-mentioned formula (9).It can be seen that pass through difference between epoch, firmly from formula (9) The parameters constant between epoch such as part delay and fuzziness are eliminated.Owing to there is no the parameter of fuzziness, therefore more than There is not constringent problem in equation solver.The processing method consistent with pseudorange can be used, obtain ionosphere delay between epoch High accuracy changing value.Additionally, the formula of employing (9), in the case of loss of data or cycle slip, the place of an epoch only can be affected Reason, thus ensure that the reliability that data process.
The comprehensive ionosphere delay method for solving of pseudorange phase place of the present invention has the following advantages and beneficial effect:
(1) compared with using raw pseudo range observation calculating ionosphere delay algorithm, present invention employs precision higher Carrier phase observable, therefore ionosphere delay calculation accuracy can be greatly promoted.
(2) compared with using carrier phase smoothed pseudorange observation calculating ionosphere delay algorithm, the present invention improves ionosphere The reliability of Delay computing.Carrier phase smoothed pseudorange algorithm data process start during or the feelings of carrier phase observable generation cycle slip Under condition, fuzziness needs a period of time to restrain, namely carrier phase smoothed pseudorange observation needs one section of convergence time, and this will lead Cause this section of time internal ionization layer and postpone the reduction of calculation accuracy.The present invention obtains high-precision by difference between the epoch of carrier phase observable The ionosphere delay variable quantity of degree, and utilize ionosphere delay variable quantity that ionosphere delay absolute value is retrained.Phase place is seen Other epoch, in the disappearance of some epoch, will not be impacted by measured value.
Accompanying drawing explanation
Fig. 1 is pseudorange phase place of the present invention comprehensive ionosphere delay method for solving stream under a kind of embodiment Journey schematic diagram.
Fig. 2 is the ionosphere delay side of solving that the pseudorange phase place corresponding based on Fig. 1 of survey station xiam to No. 30 satellite is comprehensive The carrier wave direction of propagation ionosphere delay comparison diagram that method and ionosphere delay method for solving based on simple pseudorange calculate.
Fig. 3 is the ionosphere delay side of solving that the pseudorange phase place corresponding based on Fig. 1 of survey station xzar to No. 06 satellite is comprehensive The carrier wave direction of propagation ionosphere delay comparison diagram that method and ionosphere delay method for solving based on simple pseudorange calculate.
Fig. 4 is the ionosphere delay side of solving that the pseudorange phase place corresponding based on Fig. 1 of survey station lnjz to No. 15 satellite is comprehensive The carrier wave direction of propagation ionosphere delay comparison diagram that method and ionosphere delay method for solving based on simple pseudorange calculate.
Fig. 5 is the ionosphere delay side of solving that the pseudorange phase place corresponding based on Fig. 1 of survey station xzgz to No. 15 satellite is comprehensive The carrier wave direction of propagation ionosphere delay comparison diagram that method and ionosphere delay method for solving based on simple pseudorange calculate.
Detailed description of the invention
Below in conjunction with the ionosphere that Figure of description and specific embodiment are comprehensive to pseudorange phase place of the present invention Postpone method for solving to be described in further detail.
Fig. 1 illustrates the comprehensive ionosphere delay method for solving of pseudorange phase place of the present invention under a kind of embodiment Flow process.
As it is shown in figure 1, the comprehensive ionosphere delay method for solving of pseudorange phase place of the present invention is at a kind of embodiment Under flow process include step:
Process segmental arc is divided into n epoch ti, wherein i=1,2 ... n；
T epoch is obtained based on Pseudo-range ObservationsiIonosphere delayAnd by this ionosphere delayAs observation structure Build observational equation:
I ^ t i - I c , t i = v c , t i - - - ( 4 ) ,
Wherein:For t epochiThe actual value of ionosphere delay,For residual error；
T epoch is obtained based on carrier phase observableiAnd ti-1Between the change of ionosphere delayAnd by this ionization The change that layer postponesAs observation structure observational equation:
Wherein:WithIt is respectively t epochiAnd ti-1The actual value of ionosphere delay,For residual error；
With t each epochiVariance matrix PiAs power battle array, based on formula (4) and formula (5) to all n epoch tiSuperposition, then:
Normal equation is obtained by formula (4):
E T P c E I ^ = E T P c I c - - - ( 6 ) ,
Normal equation is obtained by formula (5):
Wherein: E is the unit matrix of n × n, A is the factor arrays corresponding with formula (5), for
A = - 1 1 0 ... 0 0 0 - 1 1 ... 0 0 ... ... ... ... ... ... ... ... ... ... ... ... 0 0 0 ... - 1 1 ( n - 1 ) × n ,
PcBattle array is weighed for the pseudorange piecemeal corresponding with formula (4),Weigh battle array for the phase place piecemeal corresponding with formula (5), and have:
Association type (6) and formula (7) solve and obtain the ionosphere delay that pseudorange phase place is comprehensive
In above-mentioned embodiment, based on the survey station double frequency carrier wave L to satellite1And L2, obtain t epoch according to following formulaiIonosphere Postpone
I c , t i = f 2 2 f 1 2 - f 2 2 [ ( P t i , 2 - P t i , 1 ) - ( B 2 - B 1 ) ] - - - ( 8 ) ,
Wherein:For t epochiAt carrier wave L1On ionosphere delay, f1And f2It is respectively carrier wave L1And L2Frequency, WithIt is respectively t epochiAt carrier wave L1And L2On Pseudo-range Observations, B1And B2It is respectively carrier wave L1And L2On satellite and connect The system hardware of receipts machine postpones.
Wherein, carrier phase smoothed pseudorange observation algorithm is used to obtain t epochiAt carrier wave L1And L2On Pseudo-range Observations With
In above-mentioned embodiment, based on the survey station double frequency carrier wave L to satellite1And L2, obtain t epoch according to following formulaiAnd ti-1 Between the change of ionosphere delay
Wherein: Δ is difference operator, f1And f2It is respectively carrier wave L1And L2Frequency, λ1And λ2It is respectively carrier wave L1And L2's Wavelength,WithIt is respectively carrier wave L1And L2On carrier phase observation data.
In above-mentioned embodiment, the data in 9min before process node when processing segmental arc treating excess syndrome, by each in these data The data of a star of standing are as a processing unit, and association type (6) and formula (7) use least square to solve to obtain in this process segmental arc The ionosphere delay that the pseudorange phase place under time series on star wrong path footpath, each station one is comprehensive
Fig. 2～Fig. 5 shows that the carrier wave that the comprehensive ionosphere delay method for solving of pseudorange phase place corresponding for Fig. 1 calculates is propagated Direction ionosphere delay A, also show the carrier wave propagation side that ionosphere delay method for solving based on simple pseudorange calculates simultaneously To ionosphere delay B.
Based on above-mentioned embodiment, example is verified as a example by choosing state net xiam, xzar, lnjz, xzgz station, land, its In, Fig. 2 is the data of survey station xiam to No. 30 satellite, and Fig. 3 is the data of survey station xzar to No. 06 satellite, and Fig. 4 is survey station lnjz To the data of No. 15 satellites, Fig. 5 is the data of survey station xzgz to No. 15 satellite.Fig. 2～Fig. 5 showed in Beijing time simultaneously Ionosphere delay method for solving and the puppet of the present invention of simple pseudorange it is based respectively in the process segmental arc of about 02:00 and 14:00 The ionosphere delay method for solving comprehensive away from phase place comprehensive pseudorange phase place resolves the station star oblique path direction ionosphere delay obtained Time series B and A, abscissa is Time, and unit is hour (hour), and vertical coordinate is ionospheric delay values, and unit is m (rice).Can be seen that for the most still night-time observation, the ionization based on simple pseudorange of difference station star from Fig. 2～Fig. 5 The ionosphere delay noise that layer delay method for solving calculates is the biggest, and uses the pseudorange phase place comprehensive pseudorange phase place of the present invention Comprehensive ionosphere delay method for solving resolves the ionosphere delay the most very smooth steady obtained, and this has benefited from high-precision double frequency Phase observations data.
It should be noted that the listed above specific embodiment being only the present invention, it is clear that the invention is not restricted to above enforcement Example, has the similar change of many therewith.If those skilled in the art directly derives from present disclosure or joins The all deformation expected, all should belong to protection scope of the present invention.

Claims (4)

1. the ionosphere delay method for solving that a pseudorange phase place is comprehensive, it is characterised in that include step:
Process segmental arc is divided into n epoch ti, wherein i=1,2 ... n；
T epoch is obtained based on Pseudo-range ObservationsiIonosphere delayAnd by this ionosphere delayBuild as observation and see Survey equation:
I ^ t i - I c , t i = v c , t i - - - ( 1 ) ,
Wherein:For t epochiThe actual value of ionosphere delay,For residual error；
T epoch is obtained based on carrier phase observableiAnd ti-1Between the change of ionosphere delayAnd by this ionosphere delay ChangeAs observation structure observational equation:
Wherein:WithIt is respectively t epochiAnd ti-1The actual value of ionosphere delay,For residual error；
With t each epochiVariance matrix PiAs power battle array, based on formula (1) and formula (2) to all n epoch tiSuperposition, then:
Normal equation is obtained by formula (1):
E T P c E I ^ = E T P c I c - - - ( 3 ) ,
Normal equation is obtained by formula (2):
Wherein: E is the unit matrix of n × n, A is the factor arrays corresponding with formula (2), for
A = - 1 1 0 ... 0 0 0 - 1 1 ... 0 0 ... ... ... ... ... ... ... ... ... ... ... ... 0 0 0 ... - 1 1 ( n - 1 ) × n ,
PcBattle array is weighed for the pseudorange piecemeal corresponding with formula (1),Weigh battle array for the phase place piecemeal corresponding with formula (2), and have:
Association type (3) and formula (4) solve and obtain the ionosphere delay that pseudorange phase place is comprehensive
2. the ionosphere delay method for solving that pseudorange phase place as claimed in claim 1 is comprehensive, it is characterised in that based on survey station pair The double frequency carrier wave L of satellite1And L2, obtain t epoch according to following formulaiIonosphere delay
I c , t i = f 2 2 f 1 2 - f 2 2 [ ( P t i , 2 - P t i , 1 ) - ( B 2 - B 1 ) ] - - - ( 5 ) ,
Wherein:For t epochiAt carrier wave L1On ionosphere delay, f1And f2It is respectively carrier wave L1And L2Frequency,WithIt is respectively t epochiAt carrier wave L1And L2On Pseudo-range Observations, B1And B2It is respectively carrier wave L1And L2On satellite and reception The system hardware of machine postpones.
3. the ionosphere delay method for solving that pseudorange phase place as claimed in claim 2 is comprehensive, it is characterised in that use phase place to put down Sliding pseudorange observation value-based algorithm obtains t epochiAt carrier wave L1And L2On Pseudo-range ObservationsWith
4. the ionosphere delay method for solving that pseudorange phase place as claimed in claim 1 is comprehensive, it is characterised in that based on survey station pair The double frequency carrier wave L of satellite1And L2, obtain t epoch according to following formulaiAnd ti-1Between the change of ionosphere delay
Wherein: Δ is difference operator, f1And f2It is respectively carrier wave L1And L2Frequency, λ1And λ2It is respectively carrier wave L1And L2Wavelength,WithIt is respectively carrier wave L1And L2On carrier phase observation data.
CN201610705331.4A 2016-08-22 2016-08-22 The ionosphere delay method for solving that a kind of pseudorange phase place is comprehensive Pending CN106093967A (en)

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CN110300901A (en) * 2017-02-22 2019-10-01 罗伯特·博世有限公司 Method for determining the electron density distribution in earth atmosphere
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CN110865401A (en) * 2019-10-25 2020-03-06 上海市计量测试技术研究院 Method for evaluating influence of pseudo-range measurement deviation on satellite TGD parameter resolving precision
CN111679295A (en) * 2020-07-29 2020-09-18 航天科工通信技术研究院有限责任公司 Reliability evaluation method for communication network of satellite-based augmentation system
CN116840872A (en) * 2023-08-30 2023-10-03 哈尔滨工业大学(深圳)(哈尔滨工业大学深圳科技创新研究院) Ionosphere disturbance detection method and device
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