Patent Application
20240118434
The present disclosure relates to a positioning apparatus, a positioning program, and a positioning method.
Satellite positioning has a positioning technique that obtains a high-precision positioning solution by correcting an error contained in a ranging signal transmitted by a positioning satellite using positioning augmentation information (hereinafter referred to as augmentation information) and solving an indefinite integer bias in a carrier phase integrated value. Augmentation information as error information is provided as a quantity of state corresponding to each error factor, and PPP-AR (Precise Point Positioning Ambiguity Resolution) and PPP-RTK (Precise Point Positioning Real-Time Kinematic) are available as techniques for performing high-precision positioning using augmentation information.
In a PPP-AR positioning system, a positioning apparatus of a user acquires information related to a satellite orbit error δO, a satellite clock error δT, and a satellite signal bias B and corrects an error contained in a ranging signal. A satellite signal bias B as error information is different for every signal type, such as L1C/A, L2P, or L2C. For this reason, a satellite signal bias B is provided for every signal type, such as L1C/A, L2P, or L2C, to the positioning apparatus of the user. In PPP-AR, a tropospheric propagation delay error T and an ionospheric propagation delay error I (hereinafter referred to as the tropospheric delay error T and the ionospheric delay error I) are corrected with a model or are estimated and removed by an estimation filter, such as a Kalman filter.
In a PPP-RTK positioning system, error information related to a tropospheric delay error T and an ionospheric delay error I is provided, in addition to a satellite orbit error δO, a satellite clock error δT, and a satellite signal bias B. A positioning apparatus of a user can correct an error contained in a ranging signal based on these pieces of error information (δO, δT, B, T, and I).
Time difference positioning is available as a technique for implementing high-precision positioning without receiving positioning signals from a plurality of positioning satellites as a pair (for example, Patent Literature 1).
In use of a positioning technique, such as RTK, PPP-AR, or PPP-RTK, by which a high-precision positioning solution is obtained, a positioning satellite available for use in precision positioning is limited to a positioning satellite for which augmentation information is provided. That is, in the case of a positioning satellite for which augmentation information is not provided, if a positioning terminal of a user can acquire a ranging signal from the positioning satellite, for which augmentation information is not provided, the ranging signal cannot be used for precise positioning. For this reason, positioning in an urban area where a ranging signal is likely to be blocked by a building suffers from the problems of limitations to the number of satellites available for use in positioning and reduction in positioning precision. For example, in Centimeter Level Augmentation Service for quasi-zenith satellites, augmentation information to be provided to a user is limited to GPS satellites of the US, Galilean satellites of Europe, and quasi-zenith satellites of Japan. For this reason, augmentation information is not provided for GLONASS satellites of Russia, NavIC satellites of India, and Beidou satellites of China. Thus, ranging signals of GLONASS satellites, NavIC satellites, and Beidou satellites cannot be used for precise positioning.
Patent Literature 1 is confined to disclosure related to a technique for precisely determining a change of user position with time using time difference positioning and makes no disclosure of a technique for determining an absolute position.
The present disclosure has as its object to provide a positioning system which uses a ranging signal for which augmentation information is not provided together with a ranging signal for which augmentation information is provided to perform high-precision positioning in a precise positioning system which corrects a ranging signal using augmentation information.
A positioning apparatus includes:
According to the present disclosure, it is possible to provide a positioning system which uses a ranging signal for which augmentation information is not provided together with a ranging signal for which augmentation information is provided to perform high-precision positioning in a precise positioning system which corrects a ranging signal using augmentation information. For this reason, ranging signals available for use in positioning calculation increases, and the number of satellites available for use in positioning can be increased in positioning in an urban area where a ranging signal is likely to be blocked by a building.
In the description of an embodiment and the drawings, same elements and corresponding elements are denoted by same reference characters. A description of elements denoted by same reference characters will be appropriately omitted or simplified. In the following embodiment, the term “unit” may be appropriately replaced with the term “circuit”, “step”, “procedure”, “process”, or “circuitry”.
Embodiment 1 will be described with reference to
The GPS satellite 311 transmits a transmission signal 311a. The transmission signal 311a includes a L1C/A signal and a L2C signal as ranging signals. The quasi-zenith satellite 312 transmits a transmission signal 312a. The transmission signal 312a includes a L1C/A signal and a L2C signal as ranging signals and a [L6] signal as augmentation information. The [L6] signal as the augmentation information is referred to as the augmentation information [L6]. A positioning apparatus 100 receives augmentation information. The augmentation information subjected to decoding by a third decoding unit 23 of the positioning apparatus 100 is called correction data. The augmentation information [L6] includes a plurality of individual pieces of augmentation information [i] which are used for ranging signals i. The individual augmentation information [i] is decoded by the third decoding unit 23 to become correction data. The augmentation information [L6] includes augmentation information [L1C/A] and augmentation information [L2C] for a L1C/A signal and a L2C signal as ranging signals to be transmitted by the GPS satellite 311. The augmentation information [L6] includes augmentation information [L1C/A] and augmentation information [L2C] for a L1C/A signal and a L2C signal as ranging signals to be transmitted by the quasi-zenith satellite 312.
Assume below an example in which the quasi-zenith satellite 312 transmits a [L6] signal as augmentation information. Augmentation information [L6] may be information adherent to an SSR compression format (CompactSSR) corresponding to PPP-RTK capable of centimeter level positioning, as a state space representation. Note that transmission of augmentation information as a [L6] signal from the quasi-zenith satellite 312 is one example. The positioning apparatus 100 need not receive augmentation information from the quasi-zenith satellite 312 and may receive augmentation information via the Internet or from a mobile carrier communication network.
Reference is made to
If positioning using augmentation information [L6] provided in a State Space Representation (SSR) is performed, error correction cannot be performed on a ranging signal i which does not coincide with individual augmentation information [i] of any type included in the augmentation information [L6]. A description will be given with reference to
*** Description of Configuration ***
The feature of the positioning apparatus 100 is as follows. If a ranging signal i transmitted by a positioning satellite i does not coincide with any positioning satellite signal type of individual augmentation information as error information, such as “a signal bias in pseudo range” or “a signal bias in carrier phase integrated value”, included in augmentation information [L6], augmentation information [k] (k≠i) cannot be normally applied to the ranging signal i. In such a case, the positioning apparatus 100 can use the ranging signal i, for which augmentation information [i] is not provided, for precise positioning by using a time difference value ΔP in pseudo range and a time difference value Δϕ in carrier phase integrated value, as will be described later.
As shown in
The GNSS reception unit 10 includes an antenna 11, a distributor 12, a ranging signal reception unit 13, and an augmentation information reception unit 14. The antenna 11 receives the transmission signal 311a, the transmission signal 312a, and a transmission signal 313a from the GPS satellite 311, the quasi-zenith satellite 312, and the Beidou satellite 313. The distributor 12 distributes signals received by the antenna 11 between the ranging signal reception unit 13 and the augmentation information reception unit 14. The ranging signal reception unit 13 transmits, of signals distributed from the distributor 12, ranging signals to a first decoding unit 21 and a second decoding unit 22. The ranging signal reception unit 13 transmits a carrier phase integrated value t, a pseudo range P, and Doppler D to the first decoding unit 21 and transmits a navigational message to the second decoding unit 22. The augmentation information reception unit 14 transmits, of the signals distributed from the distributor 12, augmentation information [L6] to the third decoding unit 23.
The processor 20 includes the first decoding unit 21, the second decoding unit 22, the third decoding unit 23, a satellite calculation unit 24, and a positioning operation unit 25. The first decoding unit 21, the second decoding unit 22, and the third decoding unit 23 constitute a decoding unit 70. The above-described functional units are implemented by a positioning program 101. The positioning program 101 is stored in the auxiliary storage device 40. The positioning program 101 is a program which causes a computer to execute processes, procedures, or steps obtained by replacing the term “unit” in the first decoding unit 21, the second decoding unit 22, the third decoding unit 23, the satellite calculation unit 24, and the positioning operation unit 25 with the term “process”, “procedure”, or “step”. A positioning method is a method which is practiced though execution of the positioning program 101 by the positioning apparatus 100 as a computer. That is, the positioning apparatus 100 as the computer executes the positioning method. The positioning program 101 may be provided while being stored in a computer-readable recording medium or provided as a program product.
As will be described later in
The GNSS reception unit 10 receives a transmission signal transmitted by a positioning satellite. A navigational message and ranging signals are included in each of the transmission signal 311a of the GPS satellite 311 and the transmission signal 313a of the Beidou satellite 313. Augmentation information [L6] is included in the transmission signal 312a of the quasi-zenith satellite 312, in addition to a navigational message and ranging signals. A carrier phase integrated value ϕ, a pseudo range P, and Doppler D are included in a ranging signal to be transmitted by each positioning satellite.
An observation equation related to a pseudo range <P(tk)> of a positioning satellite SAT at a time tk corrected with augmentation information [L6] is represented by (expression 1) below:
<P(tk)>=ρ(tk)+c×δt(tk)+εp(tk) (1)
In (expression 1), ρ(tk) is a geometric distance between the positioning apparatus 100 and the positioning satellite SAT, c is a light speed, δt(tk) is a clock error of the positioning apparatus 100, and εp(tk) is an observation noise error.
The clock error of the positioning apparatus 100 may be canceled by calculating a between-satellite difference <ΔPab(tk)> between a pseudo range <Pa(tk)> of a positioning satellite SATa corrected with the augmentation signal [L6] and a pseudo range <Pb(tk)> of a positioning satellite SATb corrected with the augmentation signal [L6], as represented by (expression 2):
<ΔPab(tk)>=<Pa(tk)>−<Pb(tk)>=ρa(tk)−ρb(tk)+εpa(tk)−εpb(tk) (2)
An observation equation related to a carrier phase integrated value <ϕ(tk)> of the positioning satellite SAT at the time tk corrected with the augmentation information [L6] is represented by (expression 3) below:
<ϕ(tk)>=ρ(tk)+c×δt(tk)+λ×N(tk)+εϕ(tk) (3)
In (expression 3), ρ(tk) is the geometric distance between the positioning apparatus 100 and the positioning satellite SAT, c is the light speed, δt(tk) is the clock error of the positioning apparatus 100, and εϕ(tk) is an observation noise error.
The clock error of the positioning apparatus 100 may be canceled by calculating a between-satellite difference <Δϕab(tk)> between a carrier phase integrated value <ϕa(tk)> of the positioning satellite SATa corrected with the augmentation signal [L6] and a carrier phase integrated value <ϕb(tk)> of the positioning satellite SATb corrected with the augmentation signal [L6], as represented by (expression 2):
<Δϕab(tk)>=<ϕa(tk)>−<ϕb(tk)>=ρa(tk)−ρb(tk)+εpa(tk)−εpb(tk) (4)
Observation equations related to a time difference ΔP in a pseudo range P and a time difference Δϕ in a carrier phase integrated value ϕ will be illustrated below.
<A. Observation Model for Pseudo Range>
An observation equation for a pseudo range P(tk) at the time tk is represented by (expression 5) below. Such an observation equation is defined individually for each signal of the positioning satellite SAT.
P(tk)=ρ(tk)+δO(tk)+c×δt(tk)−c×δT(tk)+I(tk)+T(tk)+Bp(tk)+εp(tk) (5)
In (expression 5), the meanings of the symbols are as follows. ρ(tk) is the geometric distance between the positioning apparatus 100 and the positioning satellite SAT.
<B. Observation Model for Carrier Phase Integrated Value>
An observation equation for a carrier phase integrated value ϕ(tk) at the time tk is represented by (expression 6) below. Such an observation equation is defined individually for each signal of the positioning satellite SAT.
ϕ(tk)=ρ(tk)+δO(tk)+c×δt(tk)−c×δT(tk)−I(tk)+T(tk)+Bϕ(tk)+λ×N(tk)+εϕ(tk) (6)
In (expression 6), ρ(tk) is the geometric distance between the positioning apparatus 100 and the positioning satellite SAT. δO(tk) is the orbit error of the positioning satellite SAT, c is the light speed, δt(tk) is the clock error of the positioning apparatus 100, δT(tk) is the clock error of the positioning satellite SAT, I(tk) is the ionospheric delay error, T(tk) is the tropospheric delay error, Bϕ(tk) is a carrier phase integrated value bias error of the positioning apparatus 100 and the positioning satellite SAT, λ is a carrier phase wavelength, N(tk) is ambiguity, and εϕ(tk) is the observation noise error.
<C. Expression for Time Difference Value ΔP in Pseudo Range>
If a difference between a time tk−1 and the time tk is sufficiently small, a time difference ΔP(tk−1,tk) between a pseudo range at the time tk−1 and a pseudo range at the time tk can be approximated as in (expression 7) below. Note that the clock error δT of the positioning satellite SAT in (expression 5) is corrected based on a navigational message.
ΔP(tk−1,tk)=P(tk)−P(tk−1)=ρ(tk)−ρ(tk−1)+εp(tk)−εp(tk−1) (7)
If frequency stability of the positioning apparatus 100 is low, a time difference in clock error c×δt(tk)−c×δt(tk−1) of the positioning apparatus 100 cannot be canceled. Thus, the clock error of the positioning apparatus 100 can be completely canceled by calculating a between-satellite difference Δ∇Pab(tk−1,tk) between a time difference ΔPa(tk−1,tk) of the positioning satellite SATa and a time difference ΔPb(tk−1,tk) of the positioning satellite SATb. Δ∇Pab can be calculated from (expression 8):
Δ∇Pab(tk−1,tk)=ΔPa−ΔPb=ρa(tk)−ρa(tk−1)−ρb(tk)+ρb(tk−1)+εpa(tk)−εpa(tk−1)−εpb(tk)+εpb(tk−1) (8)
<D. Expression for Time Difference Value Δϕ in Carrier Phase Integrated Value>
If the difference between the time tk−1 and the time tk is sufficiently small, and no cycle slip occurs between the time tk−1 and the time tk, a time difference Δϕ(tk−1,tk) between a carrier phase integrated value at the time tk−1 and a carrier phase integrated value at the time tk can be approximated as in (expression 9) below. Note that the clock error δT of the positioning satellite SAT in (expression 6) is corrected using a navigational message.
Δϕ(tk−1,tk)=ϕ(tk)−ϕ(tk−1)=ρ(tk)−ρ(tk−1)+εp(tk)−εp(tk−1) (9)
If the frequency stability of the positioning apparatus 100 is low, the time difference in clock error c×δt(tk)−c×δt(tk−1) of the positioning apparatus 100 cannot be canceled. Thus, the clock error of the positioning apparatus 100 can be completely canceled by calculating a between-satellite difference Δ∇ϕab(tk−1,tk) between a time difference Δϕa(tk−1,tk) of the positioning satellite SATa and a time difference Δ*ab(tk−1,tk) of the positioning satellite SATb. Δ∇ϕab(tk−1,tk) can be calculated from (expression 10):
Δ∇ϕab(tk−1,tk)=Δϕa−Δϕb=ρa(tk)−ρa(tk−1)−ρb(tk)+ρb(tk−1)+εϕa(tk)−εϕa(tk−1)−εϕb(tk)+εϕb(tk−1) (10)
<F. Calculation of User Position>
ρ(tk) is a function of a user position u(tk) at the time tk, and ρ(tk−1) is a function of a user position u(tk−1) at the time tk−1. Given that u(tk−1) is already known, the user position u(tk) at the time tk and the ambiguity N(tk) at the time tk are calculated from simultaneous equations of (expression 2), (expression 4), (expression 7), and (expression 9), using the least squares method and a Kalman filter. Since (expression 7) and (expression 9) can be formulated for a ranging signal which does not coincide with augmentation information [L6], a user position can be calculated using more ranging signals.
It is possible to completely cancel the clock error of the positioning apparatus 100 and obtain a higher-precision user position from simultaneous equations of (expression 2), (expression 4), (expression 8), and (expression 10), using the least squares method and the Kalman filter.
<G. Drift Correction of Pseudo Range>
If the difference between the time tk−1 and the time tk is large or if positioning over a long time is performed by time difference positioning alone, a drift error bp(tk,tk−1) which is an error generated in a time difference value and is an error varying with passage of time becomes non-negligible, as indicated by (expression 11), and (expression 7) and (expression 9) cannot be approximated. Note that the drift error bp(tk−1,tk) as a pseudo range error is defined individually for a signal of the positioning satellite SAT.
ΔP(tk−1,tk)=P(tk)−P(tk−1)=ρ(tk)−ρ(tk−1)+c×δt(tk)−c×dt(tk−1)+bp(tk−1,tk)+εp(tk)−εp(tk−1) (11)
bp(tk−1,tk) may be approximated by a linear expression of time using a coefficient kp, as in (expression 12):
bp(tk−1,tk)=kp×(tk−tk−1) (12)
The drift error bp(tk−1,tk) in (expression 11) can be removed at the time of time difference positioning by estimating in advance the drift error coefficient kp. bp(tk−1,tk) is not limited to a linear expression of time and may be a polynomial of time. The time difference value in clock error c×δt(tk)−c×δt(tk−1) of the positioning apparatus 100 may be canceled by taking an intersatellite single difference for (expression 11), like (expression 8) above.
Δ∇Pab(tk−1,tk)=ΔPa−ΔPb=ρa(tk)−ρa(tk−1)−ρb(tk)+ρb(tk−1)+kpa×(tk−tk−1)−kpb×(tk−tk−1)+εpa(tk)−εpa(tk−1)−εpb(tk)+εpb(tk−1) (13)
In (expression 13), kpa is a drift error coefficient for a pseudo range of the positioning satellite SATa, and kpb is a drift error coefficient for a pseudo range of the positioning satellite SATb.
<H. Drift Correction of Carrier Phase Integrated Value>
Like drift correction of a pseudo range, an observation equation for a carrier phase integrated value with a drift error bϕ(tk−1,tk) of a carrier phase integrated value taken into account is indicated by (expression 14) below:
Δϕ(tk−1,tk)=ϕ(tk)−ϕ(tk−1)=ρ(tk)−ρ(tk−1)+c×δt(tk)−c×δt(tk−1)+bϕ(tk−1,tk)+εp(tk)−εp(tk−1) (14)
bϕ(tk−1,tk) may be approximated by a linear expression of time, as in (expression 12).
bϕ(tk−1,tk)=kϕ×(tk−tk−1) (15)
The drift error bϕ(tk−1,tk) in (expression 14) can be removed by estimating in advance a drift error coefficient kϕ for a carrier phase integrated value. bϕ(tk−1,tk) is not limited to a linear expression of time and may be a polynomial of time. The time difference value in clock error c×δt(tk)−c×δt(tk−1) of the positioning apparatus 100 may be canceled by taking an intersatellite single difference for (expression 14), like (expression 10) above.
Δ∇ϕab(tk−1,tk)=Δϕa−Δϕb=ρa(tk)−ρa(tk−1)−ρb(tk)+ρb(tk−1)+kϕa×(tk−tk−1)−k+b×(tk−tk−1)+εϕa(tk)−εϕa(tk−1)−εϕb(tk)+εϕb(tk−1) (16)
In (expression 16), kϕa is a drift error coefficient for a carrier phase integrated value of the positioning satellite SATa, and kϕb is a drift error coefficient for a carrier phase integrated value of the positioning satellite SATb.
<1. Calculation of User Position by Drift Correction>
If the drift error coefficient kp for a pseudo range error and the drift error coefficient kϕ for a carrier phase integrated value are determined in advance, a user position can be obtained with high precision by the least squares method or formulation of a Kalman filter on the basis of simultaneous equations of (expression 2), (expression 4), (expression 13), and (expression 16) even in a case where the difference between the time tk−1 and the time tk is large.
<J. Estimation of Drift Error>
The drift error coefficient kp for a pseudo range error and the drift error coefficient ko for a carrier phase integrated value are estimated during a time period when sufficient ranging signals coincident with augmentation information [L6] can be secured in, for example, an open sky environment by the procedures below. The user position u(tk−1) at the time k−1 and the user position u(tk) at the time k are obtained by the least squares method or a Kalman filter based on simultaneous equations of (expression 2) and (expression 4). Geometric distances ρa(tk), ρa(tk−1), ρb(tk), and ρb(tk−1) are obtained by substituting the obtained user positions u(tk−1) and u(tk) into (expression 13) and (expression 16). At this time, unknown quantities in (expression 13) and (expression 16) are kpa, kpb, kϕa, and kϕb. kpa, kpb, kϕa, and kϕb can be estimated by using the least squares method or a Kalman filter based on simultaneous equations of (expression 13) and (expression 16).
*** Description of Operation ***
Note that a L1C/A signal of the GPS satellite 311 and a B1C signal of the Beidou satellite 313 are assumed below as ranging signals and that a [L6] signal of the quasi-zenith satellite 312 is assumed as augmentation information.
<Time tk−1 and Time tk in GPS Satellite 311>
The GPS satellite 311 transmits the transmission signal 311a including a L1C/A signal at the time tk−1. In
As shown in
<Time tk−1 and Time tk in Beidou Satellite 313>
The Beidou satellite 313 transmits the transmission signal 313a including a BIC signal at the time tk−1. The transmission signal 313a is received by the antenna 11, passes through the distributor 12, and is subjected to signal processing in the ranging signal reception unit 13. Observation data is generated from the transmission signal 313a subjected to the signal processing by the first decoding unit 21. The observation data is stored in the ranging signal table 31 of the main storage device 30. A navigational message is generated from the transmission signal 313a subjected to the signal processing by the second decoding unit 22 and is passed to the satellite calculation unit 24. The satellite calculation unit 24 passes a satellite position and a satellite time to the positioning operation unit 25. Similarly, observation data is generated at the time tk by the first decoding unit 21 and is stored in the ranging signal table 31 of the main storage device 30. Operation of the second decoding unit 22 and the third decoding unit 23 at the time tk is the same as the operation at the time tk−1.
<Step S11>
At each of a plurality of times, the decoding unit 70 decodes augmentation information to generate correction data obtained by decoding the augmentation information, decodes a first ranging signal for which augmentation information is provided to generate observation data of the first ranging signal, and decodes a second ranging signal for which augmentation information is not provided to generate observation data of the second ranging signal.
The error correction unit 27 corrects an error in observation data of a first ranging signal on the basis of correction data. The positioning filter 26 performs a positioning operation using the observation data of the first ranging signal, the error of which is corrected by the error correction unit 27, time difference data between pieces of observation data of first ranging signals, and time difference data between pieces of observation data of second ranging signals. As will be described later, time difference data is calculated by the time difference calculation unit 28. A specific description will be given below.
<Step S11>
In step S11, the positioning operation unit 25 receives, from the ranging signal table 31, a L1C/A(tk−1) signal at the time tk−1 of the GPS satellite 311 as a satellite to be augmented and a L1C/A(tk) signal at the time tk of the GPS satellite 311. The term “satellite to be augmented” means that the positioning apparatus 100 can receive a ranging signal i and augmentation information [i] for the positioning satellite in question and that the positioning apparatus 100 can correct an error in the ranging signal i using the augmentation information [i]. Similarly, the positioning operation unit 25 receives, from the ranging signal table 31 at the time tk, a B1C(tk−1) signal at the time tk−1 of the Beidou satellite 313 as a satellite not to be augmented and a B1C(tk) signal at the time tk of the Beidou satellite 313.
The term “satellite not to be augmented” means a positioning satellite in which the positioning apparatus 100 cannot receive augmentation information [i] for a ranging signal i of the positioning satellite in question, and the positioning apparatus 100 cannot correct an error in the ranging signal i using the augmentation information [i].
Pieces of information to be acquired from the ranging signal table 31 are as follows. The first decoding unit 21 as a detection unit detects first pseudo ranges P1 and first carrier phase integrated values ϕ1 from first ranging signals which are ranging signals of a first positioning satellite received at a plurality of times and for which augmentation information for correction is provided. The first positioning satellite here is the GPS satellite 311. Each first ranging signal is a L1C/A signal. The augmentation information for the L1C/A signal is augmentation information [L1C/A].
The first decoding unit 21 also detects second pseudo ranges P2 and second carrier phase integrated values ϕ2 from second ranging signals which are ranging signals of a second positioning satellite received at a plurality of times and for which augmentation information for correction is not provided. The second positioning satellite here is the Beidou satellite 313. Each second ranging signal is a B1C signal. Augmentation information is not provided for the B1C signal.
The first pseudo range P1 and the first carrier phase integrated value ϕ1, and the second pseudo range P2 and the second carrier phase integrated value ϕ2 are acquired from the ranging signal table 31 by the positioning operation unit 25.
An outline of step S11 and subsequent steps is as follows. The positioning operation unit 25 generates a first observation equation for the GPS satellite 311 as the first positioning satellite, using a first pseudo range P1 corrected with augmentation information and a first carrier phase integrated value ϕ1 corrected with the augmentation information. The positioning operation unit 25 also generates a second observation equation for the Beidou satellite 313 as the second positioning satellite, using a time difference value ΔP2 in second pseudo range P2 and a time difference value Δϕ2 in second carrier phase integrated value ϕ2. The positioning operation unit 25 performs positioning through execution of a filter operation using the first observation equation and the second observation equation by the positioning filter 26. The positioning operation unit 25 outputs an operation result as a position estimation result 25A.
<Step S12>
The error correction unit 27 corrects the L1C/A(tk) signal at the time tk of the GPS satellite 311 with correction data [L1C/A] transmitted from the third decoding unit 23, thereby generating a <L1C/A> signal obtained by correcting the L1C/A signal. The generated <L1C/A> signal is input to a Kalman filter which is the positioning filter 26 by the error correction unit 27.
A specific description will be given as follows.
In the positioning operation unit 25, the error correction unit 27 acquires correction data [L1C/A] for a L1C/A signal generated from augmentation information [L1C/A] provided for the L1C/A signal of the GPS satellite 311 that is a first ranging signal, and a first pseudo range P1 and a first carrier phase integrated value ϕ1 detected by the first decoding unit 21 as the detection unit. The first pseudo range P1 is a pseudo range of the L1C/A signal, and the first carrier phase integrated value ϕ1 is a carrier phase integrated value of the L1C/A signal. The error correction unit 27 corrects the first pseudo range P1 and the first carrier phase integrated value ϕ1, using the correction data [L1C/A]. The error correction unit 27 inputs the corrected first pseudo range P1 and first carrier phase integrated value ϕ1 to the positioning filter 26. As will be described in step S15, the positioning operation unit 25 generates a first observation equation using the first pseudo range P1 and the first carrier phase integrated value ϕ1 corrected by the error correction unit 27 and executes a filter operation.
<Step S13>
The time difference calculation unit 28 receives the L1C/A(tk−1) signal of the GPS satellite 311 at the time tk−1, the L1C/A(tk) signal of the GPS satellite 311 at the time tk, the B1C(tk−1) signal of the Beidou satellite 313 at the time tk−1, and the B1C(tk) signal of the Beidou satellite 313 at the time tk.
<Step S14>
The time difference calculation unit 28 calculates a time difference value between the ranging signals at the times tk and tk−1.
That is, the time difference calculation unit 28 calculates a time difference value ΔP(tk−1,tk) and a time difference value Δϕ(tk−1,tk for pseudo ranges and carrier phase integrated values at the times tk and tk−1. The time difference calculation unit 28 inputs the calculated ΔP(tk−1,tk) and A+(tk−1,tk) to the positioning filter 26.
<Step S15>
The positioning filter 26 performs a positioning operation on the basis of <L1C/A> input in step S12 and ΔP(tk−1,tk) and Δϕ(tk−1,tk) input in step S14 and outputs a position estimate 25a of the positioning apparatus 100 at the time tk.
<Modification>
<Step S14a>
In step S14a, the time difference calculation unit 28 outputs calculated ΔP(tk-1,tk) and A+(tk−1,tk) to the drift correction unit 29.
<Step 14b>
In step S14b, the drift correction unit 29 estimates drift errors using a positioning solution obtained by the positioning filter 26 and ΔP(tk−1,tk) and Δϕ(tk−1,tk) calculated in step S14a and corrects the drift errors in ΔP(tk−1,tk) and Δϕ(tk−1,tk). The drift correction unit 29 outputs ΔP(tk−1,tk), the drift error of which is corrected, and Δϕ(tk−1,tk), the drift error of which is corrected, to the positioning filter 26.
A specific description will be given as follows.
The drift correction unit 29 corrects drift errors which are errors generated in respective time difference values of a time difference value ΔP1 in a first pseudo range P1 that is a pseudo range of a L1C/A signal, a time difference value Δϕ1 in a first carrier phase integrated value ϕ1 that is a carrier phase integrated value of the L1C/A signal, a time difference value ΔP2 in a second pseudo range P2 that is a pseudo range of a B1C signal, and a time difference value Δϕ2 in a second carrier phase integrated value ϕ2 that is a carrier phase integrated value of the B1C signal and are errors varying with passage of time, for the respective time difference values.
The positioning operation unit 25 generates a third observation equation for a L1C/A signal, that is, the GPS satellite 311 that transmits a L1C/A signal and generates a second observation equation for a B1C signal, that is, the Beidou satellite 313 that transmits a B1C signal, using respective time difference values, drift errors of which are corrected by the drift correction unit 29.
Note that, as described above, the drift correction unit 29 corrects drift errors for respective time difference values, using a positioning solution as a result of executing a filter operation by the positioning filter 26.
<Step 15a>
In step S15a, the positioning filter 26 performs a positioning operation on the basis of <L1C/A> input in step S12 and ΔP(tk−1,tk) and Δϕ(tk−1,tk), drift errors of which are corrected, input in step S14b and outputs the position estimate 25a of the positioning apparatus 100 at the time tk.
*** Description of Advantageous Effects of Embodiment 1 ***
According to the positioning apparatus 100 of Embodiment 1, a time difference value in pseudo range and a time difference value in carrier phase integrated value are used for a “satellite not to be augmented”, in addition to use of a pseudo range and a carrier phase integrated value corrected with augmentation data for a “satellite to be augmented”. This makes it possible to perform precise positioning using, for positioning, a ranging signal i for which augmentation information [i] cannot be received together with a ranging signal k for which augmentation information [k] can be received.
Since ΔP(tk−1,tk) and Δϕ(tk−1,tk), drift errors of which are corrected by the drift correction unit 29, are used, positioning precision can be enhanced.
δt: satellite clock error; δO: satellite orbit error; B: satellite signal bias; I: ionospheric error; T: tropospheric delay error; P: pseudo range; ϕ: carrier phase integrated value; 10: GNSS reception unit; 11: antenna; 12: distributor; 13: ranging signal reception unit; 14: augmentation information reception unit; 20: processor; 21: first decoding unit; 22: second decoding unit; 23: third decoding unit; 24: satellite calculation unit; 25: positioning operation unit; 25a: position estimate; 26: positioning filter; 27: error correction unit; 28: time difference calculation unit; 29: drift correction unit; 30: main storage device; 31: ranging signal table; 40: auxiliary storage device; 60: signal line; 70: decoding unit; 100: positioning apparatus; 311: GPS satellite; 311a: transmission signal; 312: quasi-zenith satellite; 312a: transmission signal; 313: Beidou satellite; 313a: transmission signal
| Number | Date | Country | Kind |
|---|---|---|---|
| PCT/JP2021/012377 | Mar 2021 | WO | international |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/JP2021/036546 | 10/4/2021 | WO |
