# Patent

## Title
GNSS signal processing with ionospheric bridging for reconvergence

## Abstract

Methods and apparatus provide for positioning of a rover antenna from GNSS data derived from multi-frequency signals and correction data derived from a network of reference stations. Rover antenna position and multi-frequency ambiguities are estimated at each epoch. An ionospheric filter models variation in ionospheric bias per satellite. A set of ionospheric carrier-phase ambiguities is estimated at least when the multi-frequency ambiguities have attained a predetermined precision. The estimated ionospheric carrier-phase ambiguities are cached. After detecting interruption of signal at the rover antenna and determining reacquisition of signals at the rover antenna, an ionospheric bias per satellite over an interruption interval is predicted. For each satellite, a cached ionospheric carrier-phase ambiguity is combined with a predicted ionospheric bias to obtain a post-interruption ionospheric ambiguity estimate. The post-interruption ionospheric ambiguity estimates are used to aid estimation of rover antenna position after signal reacquisition.

## Background
CROSS REFERENCE TO RELATED APPLICATIONS
This application is a U.S. National Stage of PCT Application No. PCT/US2012/28670, filed on Mar. 11, 2012, which claims benefit of U.S. Provisional Patent Application No. 61/466,065, filed on Mar. 22, 2011, the contents of both applications are incorporated herein by reference in their entity for all purposes.
The following are related hereto and incorporated herein in their entirety by this reference: U.S. Provisional Application for Patent No. 61/277,184 filed 19 Sep. 2009; International Patent Application PCT/US2010/02565 filed 19 Sep. 2010; International Patent Application PCT/US2010/02564 filed 19 Sep. 2010; International Patent Application PCT/US2010/02563 filed 19 Sep. 2010; International Patent Application PCT/US2010/02562 filed 19 Sep. 2010; International Patent Application PCT/US2010/02581 filed 19 Sep. 2010; U.S. Provisional Application for Patent No. 61/337,980 filed 14 Feb. 2010; International Patent Application PCT/US2011/24733 filed 14 Feb. 2011; International Patent Application PCT/US2011/24743 filed 14 Feb. 2011; International Patent Application PCT/US2011/24763 filed 14 Feb. 2011; U.S. Provisional Application for Patent No. 61/442,680 filed 14 Feb. 2011; International Patent Application PCT/US2009/059552 filed 5 Oct. 2009; U.S. Provisional Application for Patent No. 61/195,276 filed 6 Oct. 2008; International Patent Application PCT/US/2009/004471 filed 5 Aug. 2009; International Patent Application PCT/US/2009/004473 filed 5 Aug. 2009; International Patent Application PCT/US/2009/004474 filed 5 Aug. 2009; International Patent Application PCT/US/2009/004472 filed 5 Aug. 2009; International Patent Application PCT/US/2009/004476 filed 5 Aug. 2009; U.S. Provisional Application for Patent No. 61/189,382 filed 19 Aug. 2008; U.S. patent application Ser. No. 12/224,451 filed 26 Aug. 2008, United States Patent Application Publication US 2009/0027625 A1; International Patent Application PCT/US07/05874 filed 7 Mar. 2007, International Publication No. WO 2008/008099 A2; U.S. patent application Ser. No. 11/988,763 filed 14 Jan. 2008, United States Patent Application Publication US 2009/0224969 A1; International Patent Application No. PCT/US/2006/034433 filed 5 Sep. 2006, International Publication No. WO 2007/032947 A1; U.S. Pat. No. 7,432,853 granted 7 Oct. 2008; International Patent Application No. PCT/US2004/035263 filed 22 Oct. 2004 and International Publication Number WO 2005/045463 A1; U.S. Pat. No. 6,862,526 granted 1 Mar. 2005; and U.S. Provisional Application for Patent No. 61/396,676, filed 30 May 2010.


TECHNICAL FIELD
The present invention relates to the field of Global Navigation Satellite Systems (GNSS). More particularly, the present invention relates to methods and apparatus for processing of GNSS data to provide high precision positioning with rapid solution convergence.
BACKGROUND ART
Global Navigation Satellite Systems (GNSS) include the Global Positioning System (GPS), the Glonass system, the proposed Galileo system, the proposed Compass system, and others. Each GPS satellite transmits continuously using two radio frequencies in the L-band, referred to as L1 and L2, at respective frequencies of 1575.42 MHz and 1227.60 MHz. Two signals are transmitted on L1, one for civil users and the other for users authorized by the United States Department of Defense (DoD). One signal is transmitted on L2, intended only for DoD-authorized users. Each GPS signal has a carrier at the L1 and L2 frequency, a pseudo-random noise (PRN) code, and satellite navigation data. Two different PRN codes are transmitted by each satellite: a coarse acquisition code and a precision (P/Y) code which is encrypted for DoD-authorized users. Each C/A code is a unique sequence of 1023 bits, which is repeated each millisecond. New GPS satellites are able to broadcast on 3 frequencies. Other GNSS systems likewise have satellites which transmit multiple signals on multiple carrier frequencies.
FIG. 1 schematically illustrates a typical prior-art scenario to determine the position of a mobile receiver (rover). Rover 105 receives GNSS signals from one or more satellites in view, such as satellites 110, 115, 120, 125 and 130 shown. The signals pass through the earth's atmosphere 160, the upper portion is called the ionosphere, while the lower portion of the atmosphere is referred to as the troposphere. The multi-frequency GNSS PRN code and carrier phase signals are simultaneously tracked by the rover receiver and by one or more GNSS reference receivers 135 and 140. The ionosphere causes a dispersive effect whereby the code is delayed, while the carrier phase is advanced. The troposphere delays the signals with the magnitude of the effect dependent on the prevailing atmospheric temperature, pressure, relative humidity and precipitable water vapor content.
Each satellite broadcasts a prediction of its expected orbital trajectory in a navigation message. The navigation message also includes a prediction of the expected satellite clock behavior. The satellite clock, orbit and atmospheric errors can be considered as causing an apparent shift in the satellite locations 110->170, 115->175, 120->180, 125-185, 130-190, as depicted in FIG. 1.
Prior-art network GNSS processing techniques such as described in U.S. Provisional Application for Patent No. 61/277,184 filed 19 Sep. 2009, enable satellite and atmospheric errors to be estimated by first tracking the satellite signals at a network of reference stations, spatially distributed globally and/or regionally. The satellite orbit/clock and atmospheric errors are estimated in a network processor such as 145, in FIG. 1. The satellite correction data is then encoded and transmitted via antenna 150, for later reception and use by one or more rovers 105
In prior-art rover processing techniques such as described in International Patent Application PCT/US2010/02562 filed 19 Sep. 2010, the rover GNSS data is combined with the GNSS network correction data at a plurality of epochs in order to estimate the rover antenna position plus nuisance parameters such as a set of multi-frequency (carrier phase) ambiguities and tropospheric biases
FIG. 2 is a block diagram of a typical integrated receiver system 200 with GNSS rover 105 and communications antenna 202. Receiver system 200 can serve as rover 105 or as a reference station. Receiver system 200 includes a GNSS receiver 205, a computer system 210 and one or more communications links 215. Computer system 210 includes one or more processor(s) 220, one or more data storage elements 225, program code 230 for controlling the processor(s) 220, and user input/output devices 235 which may include one or more output devices 240 such as a display or speaker or printer and one or more devices 245 for receiving user input such as a keyboard or touch pad or mouse or microphone.
FIG. 3 illustrates the horizontal position accuracy convergence over time of a GNSS rover position solution based on global GNSS network correction data and precise satellite orbit and clock data. The x-axis represents time in minutes, while the y-axis represents the horizontal position accuracy in centimeters. The x-y axes are denoted 405. The trace of horizontal position accuracy is denoted 410. Many high precision applications require for example 2.5 cm (1 inch) horizontal position accuracy; this threshold is indicated by the dashed horizontal line 415. The convergence time (420) needed to achieve the position threshold is around 18 minutes in this example. A tracking interruption at the rover receiver occurs around time 40 minutes (denoted 425). The tracking interruption leads to a reconvergence period 430.
Based on GPS satellites alone, it is common to have convergence times of 10-30 minutes to achieve a horizontal position accuracy of 2.5 cm. Many GNSS applications need cm-level accuracy and therefore the convergence time hinders the usefulness of the system. It is common for satellite tracking to be interrupted from time-to-time on one or more satellites at the rover, particularly when the rover is moving. If the number of tracked satellites drops below 4, the solution is converged again as shown in FIG. 3.
In prior-art processing techniques, Geng, J, et al, 2010, Rapid re-convergences to ambiguity-fixed solutions in precise point positioning, Journal of Geodesy, Vol 84, pp 705-714, a technique is described for improving the re-convergence of precise point positioning following tracking interruptions. Specifically, the wide-lane ambiguities are estimated first with the aid of ionospheric-free code measurements. Next a linear time-window-based prediction of the ionospheric bias on each cycle slipped satellite is made. The predicted ionospheric bias is used to limit the search space of narrow-lane phase ambiguities. The reported results from ibid, show re-convergence times of 5 seconds in most tests. Few details are provided on the filtering scheme used for the PPP solution.
In prior-art processing techniques, Banville, S, and Langley, R. B., 2010, Instantaneous Cycle-Slip Correction for Real-Time PPP Applications, NAVIGATION, Journal of the US Institute of Navigation, Vol 57 No 4, Winter, pp 325-334, describe a way of repairing cycle slips in Precise Point Positioning (PPP) applications based on time-differenced phase measurements. First an attempt is made to fix the time-differenced wide-lane carrier phase ambiguities following an interruption to satellite tracking. Next the known wide-lane ambiguities are used in conjunction with the assumed time-wise change in ionospheric bias to fix the L1 and L2 on each satellite during the tracking interruption.
Precise Point Positioning (PPP) techniques involve careful modeling of various error sources affecting satellite measurements. Real-time rover processors are often limited in terms of size, weight and power and therefore careful consideration must be given to efficient data processing techniques that minimize compute power. The prior-art methods for cycle slip repair in PPP applications do not mention the use of distributed filtering for the underlying state parameter estimation.
Improved GNSS processing methods and apparatus are desired, especially to achieve faster and more efficient convergence to a solution, improved accuracy and/or greater availability.
SUMMARY
The following invention presents a way of reducing convergence/reconvergence times by taking advantage of:
predictability of the tropospheric biases over short tracking outages (tropo-bridging);
predictability of the satellite ionospheric biases over short tracking outages (iono-bridging);
predetermined knowledge of the user location (known position input).
Methods and apparatus provide for positioning of a rover antenna from GNSS data derived from multi-frequency signals and correction data derived from a network of reference stations. Rover antenna position and multi-frequency ambiguities are estimated at each epoch. An ionospheric filter models variation in ionospheric bias per satellite. A set of ionospheric carrier-phase ambiguities is estimated at least when the multi-frequency ambiguities have attained a predetermined precision. The estimated ionospheric carrier-phase ambiguities are cached. After detecting interruption of signal at the rover antenna and determining reacquisition of signals at the rover antenna, an ionospheric bias per satellite over an interruption interval is predicted. For each satellite, a cached ionospheric carrier-phase ambiguity is combined with a predicted ionospheric bias to obtain a post-interruption ionospheric ambiguity estimate. The post-interruption ionospheric ambiguity estimates are used to aid estimation of rover antenna position after signal reacquisition.



BRIEF DESCRIPTION OF DRAWING FIGURES
Embodiments in accordance with the invention are described herein with reference to the drawing Figures, in which:
FIG. 1 schematically illustrates a GNSS rover operating with correction data in the presence of satellite error sources;
FIG. 2 schematically illustrates a typical integrated GNSS receiver system;
FIG. 3 shows convergence and reconvergence of horizontal position accuracy over a tracking interruption;
FIG. 4 schematically illustrates the use of global corrections at a rover receiver
FIG. 5 is a schematic diagram of a factorized-array multi-carrier ambiguity resolution (FAMCAR) filtering scheme used for processing of GNSS signal data;
FIG. 6 is a flow chart of geometry filter processing;
FIG. 7 is a flow chart of epoch processing of GNSS data;
FIG. 8 illustrates observed versus filtered ionospheric phase over time with a tracking interruption;
FIG. 9 is a schematic diagram of a FAMCAR filtering scheme with ionospheric bridging in accordance with some embodiments of the invention;
FIG. 10 is a flow chart of ionospheric bridging processing in accordance with some embodiments of the invention;
FIG. 11 illustrates a caching process in accordance with some embodiments of the invention;
FIG. 12 schematically illustrates a surveying scenario using a GNSS rover with correction data;
FIG. 13 illustrates a known-position aiding process in accordance with some embodiments of the invention; and
FIG. 14 schematically illustrates the use of known-position aiding in the FAMCAR process in accordance with some embodiments of the invention.



DETAILED DESCRIPTION
Global Virtual Reference Station (GVRS) Positioning Principles
Overview
FIG. 4 shows an embodiment of Global Virtual Reference Station (GVRS) rover processing with GNSS satellite corrections (taken from FIG. 38 of U.S. Provisional Application for Patent No. 61/277,184 filed 19 Sep. 2009). Rover receiver 3805 receives GNSS signals from multiple GNSS satellites, of which three are shown at 3810, 3815, 3820. Receiver 3805 derives GNSS data 3825 from code observations and carrier-phase observations of the GNSS signals over multiple epochs.
Precise satellite data 3830 for the GNSS satellites are received, via a correction message broadcast by a communication satellite 3835 in this case, or by other means, such as wireless Internet. The correction messages are decoded by a message decoder 3832. A Synthesized Base Station (SBS) module 3835 receives the precise satellite data 3830 and also receives information which it can use as a virtual base location, such as an approximate rover position with time tag 3842 generated by an optional navigation engine 3845. The approximate rover position is optionally obtained from other sources as described below.
SBS module 3835 uses the precise satellite data 3830 and the approximate rover position with time tag 3842 to synthesize base station data 3850 for the virtual base location. The base station data 3850 comprises, for example, synthesized observations of L1 code, L2 code, L1 carrier-phase and L2 carrier-phase, and optionally includes information on L1 cycle slip, L2 cycle slip and the virtual base location.
The synthesized base station data 3850 is delivered to the RTK processing engine 3855, and combined with locally collected GNSS data 3825. The combined GNSS data can be processed in a manner similar to conventional single-base real-time kinematic data in order to produce an estimate of the rover position 3860.
FAMCAR
The Factorized Multi-Carrier Ambiguity (FAMCAR) algorithm uses a distributed filtering strategy for estimating the carrier phase ambiguities, position and other parameters needed in high-precision GNSS data processing. The FAMCAR approach was originally designed for efficient single-baseline RTK processing as described in U.S. Pat. No. 7,432,853, Vollath, U., Ambiguity Estimation of GNSS Signals for Three or more Carriers. However the FAMCAR approach can readily accommodate single-baseline, virtual base processing, and global virtual reference station (GVRS) processing as described below.
FIG. 5 schematically illustrates the distributed filtering scheme used for FAMCAR-based GVRS processing. Table 1 presents a summary of the observation types processed in each filter component.







TABLE 1







Summary of observation types applied to FAMCAR


component filters for GVRS processing.











GNSS observation type
GPS L1 Band
GPS L2 Band


Filter
processed
Coefficient α
Coefficient β





Code-Carrier
Wide-lane phase combination
+1
−1



Narrow-lane code combination
+1
+1


Ionospheric
Ionospheric phase combination
+L1λ
−L2λ


Auxiliary
Ionospheric-free phase
L2λ2/(L2λ2 − L1λ2)
−L1λL2λ/(L2λ2 − L1λ2)


Code-Carrier
combination



Ionospheric-free code
L2λ2/(L2λ2 − L1λ2)
−L1λ2/(L2λ2 − L1λ2)



combination


Geometry
Ionospheric-free phase
L2λ2/(L2λ2 − L1λ2)
−L1λL2λ/(L2λ2 − L1λ2)



combination









with multi-frequency phase combinations formed as follows:

cΦ=αL1Φ+βL2Φ  (1)

and multi-frequency code combinations formed as follows:

cR=αL1R+βL2R  (2)

where:

    α, β L1 and L2 measurement band coefficients respectively,
    L1Φ, L2Φ L1 and L2 carrier phase measurements respectively,
    cΦ Carrier phase combination,
    L1λ, L2λ L1 and L2 carrier wavelengths respectively,
    L1R, L2R L1 and L2 code measurements respectively,
    cR Code combination.


In FIG. 5 single-differenced GNSS observations 605, formed from the combined Synthesized Base Station Data and locally collected rover GNSS data, are fed into the FAMCAR estimation process typically at regular (for example 1 Hz) epochs. The frequency band coefficients for each of the multi-band measurement combinations needed are computed at 610. The multi-band measurement combinations are input to the Code-Carrier Filter bank 615, the Ionospheric Filter Bank 620, the Auxiliary Code-Carrier Filter Bank 625, and the Geometry Filter 630. The output of the Code-Carrier-, Ionospheric-, and Auxiliary Code-Carrier Filter banks is: Wide-Lane Phase Ambiguities 635, Ionospheric Phase Ambiguities 640, Iono-Free Phase ambiguities 645, respectively. The Geometry filter produces position and iono-free ambiguities which are contained in 650. All position and ambiguities are combined at 655 to produce the final Position & Float Ambiguity L1/L2 estimates 660.
Component Filters
Code-Carrier and Auxiliary Code-Carrier Filters
The Code-Carrier filters and Auxiliary Code-Carrier filters utilize code/carrier combinations that are matched in terms of ionospheric bias. This means that the combinations can be averaged indefinitely without ionospheric bias corrupting the estimated carrier phase ambiguity results. The precision of the carrier phase ambiguity estimates are driven largely by the precision of the underlying code measurements. In particular for the Auxiliary Code-Carrier filters, the uncertainties in the phase ambiguity estimates are typically several cycles even after convergence times of many minutes.
The output of the Code-Carrier-filter banks and the Auxiliary Code-Carrier filter banks includes:

    
    
        carrier phase ambiguity estimates;
        phase combination used;
        variance of the carrier phase ambiguity estimates;
        associated statistics.
    
    


Ionospheric Filters
For GVRS processing, the ionospheric filters are not able to readily estimate the difference in ionospheric bias between server and rover (essentially the absolute ionospheric bias at the rover). Hence, the ionospheric filter results are normally disabled via deweighting (i.e. setting their variances large=1e+4). Note that this contrasts with single-baseline RTK processing where the ionospheric biases can be tightly constrained and therefore accelerate the convergence of the final results.
The output of the Ionospheric filter banks include:

    
    
        carrier phase ambiguity estimates;
        phase combination used;
        variance of the carrier phase ambiguity estimates;
        associated statistics.
    
    


Geometry Filter
The Geometry filter state vector (x) typically includes the following parameters:

    
    
        rover position (XA,YA,ZA), given in terms of WGS84 Cartesian coordinates,
        receiver clock terms for each satellite system (i.e. TG=GPS clock bias; TR=GLONASS clock bias, etc),
        single-difference iono-free (if) carrier phase multipath biases for each satellite (Δifmi, i=1 . . . s),
        rover tropospheric scale (τs) and optionally east and north tropospheric gradient parameters (τe,τn),
        single-difference iono-free carrier phase ambiguities for each satellite (ΔifNi, i=1 . . . s).

x=[XA YA ZA TG TR Δifm1 Δifm2 . . . Δifms τs τe τn ΔifN1 ΔifN2 . . . ΔifNs]T  (3)

    
    


The Geometry filter output includes:

    
    
        position, carrier phase ambiguity estimates and tropospheric bias parameters;
        phase combination used;
        variance-covariance matrix for the estimated parameters;
        associated statistics.
    
    


Geometry Filter Processing Steps
FIG. 6 illustrates the processing steps used in the Geometry filter which follow a general
Kalman filtering approach. At each new time epoch 705, a time update of the filter occurs 735, involving:

    
    
        testing for the occurrence of cycle slips (tracking interruptions) on each satellite (710),
        initializing the ambiguity state value(s) for any cycle slipped satellite (715),
        adding process noise to the position and receiver clock states (720),
        adding process noise to the tropospheric bias parameter(s) (725),
        predicting the multipath bias state values for each satellite (730).
    
    


When GNSS code and phase measurements are available (test 740), they are used to update the filters at 745. The current filter results are made available at 750. Test 755 checks for more epochs to process. If more epochs are available, then the new epoch is handled at 705. Processing is terminated at 760 when no more data is available, i.e. when the rover receiver is turned off.
Filter Combiner
The Filter-Combiner accepts the output of component filters and forms a so-called float solution. That is, the single-difference L1 and L2 carrier phase ambiguities are estimated as floating point numbers. The position of the rover is also derived from the filter combination step. The results of the filter combination are intended to be equivalent to those that would be obtained with an analogous big-filter. i.e. a filter which models state parameters for all unknowns, rather than a distributed filtering scheme.
The position and float (floating-point) carrier phase ambiguities are forwarded on to the iFlex ambiguity search/validation component of the system at each epoch.
iFlex
In traditional carrier phase data processing, the ambiguities are resolved and constrained to a single integer candidate often called the fixed-ambiguity solution. With the carrier phase ambiguities resolved, the precision of the remaining position (and other) parameters is greatly improved. The iFlex scheme takes advantage of the integer-nature of the ambiguities without necessarily enforcing a single integer ambiguity outcome. The overall convergence of the GVRS processing is enhanced by iFlex treatment of the carrier phase ambiguities (refer to International Patent Application PCT/US/2009/004476 filed 5 Aug. 2009 for details of the iFlex technique).
FAMCAR Processing Summary
FIG. 7 illustrates the FAMCAR processing steps. At 805 a new epoch of single-difference GNSS data becomes available. The GNSS single-difference observations are used at step 810 to update the Code-Carrier-, Ionospheric-, Auxiliary Code-Carrier-, and Geometry filters. The results from each filter/filter-bank are assembled at 815, and combined at 820 in a least squares sense to form a position and float ambiguity solution. The position and float ambiguity solution is statistically tested at 825 to validate the solution quality. If the solution passes the statistical test(s), An iFlex position and ambiguity solution is generated at 830. If the float solution is deemed bad, then action is taken at 835 to isolate and reset the offending filter(s). The epoch processing loop continues if more data is available (840), otherwise processing is stopped (845).
The unknown parameters estimated in the FAMCAR combination state vector include the following:

x=[XA YA ZA ΔL1N1 ΔL2N1ΔL1N2 ΔL2N2 . . . ΔL1Ns ΔL2Ns]T  (4)

where ΔL1Ni ΔL2Ni are the single-difference L1 and L2 floating point carrier phase ambiguities, for satellites i=1 . . . s.

The uncertainty of the FAMCAR state parameters are contained within the corresponding state covariance matrix.
Troposphere Bridging
Introduction
The troposphere is considered as the lower-part of the atmosphere up to an altitude of approximately 50 km above the earth. The troposphere is composed of dry gasses and water vapour and causes a non-dispersive delay of GNSS radio waves.
Modelling the Tropospheric Bias
Although the dry component of the tropospheric delay can be well modeled via surface measurements of temperature, pressure and relative humidity; the effect of the wet component is more problematic. The wet component can be handled via the estimation of one or more tropospheric scale terms in the state vector of the Geometry filter.
The troposphere delay at any given point is often assumed as being isotropic, however experience has shown that weather fronts cause strong spatial biases. Additional east/north gradient components can be estimated in the geometry filter state vector to help address the eolotropic nature of the tropospheric wet delay. Details of horizontal tropospheric gradient estimation using a single GPS receiver are given in Bar-Sever, Y. E, et. al., 1997, Estimating Horizontal Gradients of Tropospheric Path Delay with a Single GPS Receiver, submitted to the Journal of Geophysical Research, November 7.
The tropospheric bias is generally slowly changing. Even with the passage of strong weather fronts, the tropospheric bias normally only changes <10 mm/hour1/2 [ibid]. The tropospheric bias is therefore well predicted over time once the tropospheric states have converged.
The measurement coefficients for the tropospheric parameters are given by:




  
    
      
        -
      
    
    
      
        
          τ
          s
          i
        
        =
        
          rover
          ⁢
          
            
          
          ⁢
          tropospheric
          ⁢
          
            
          
          ⁢
          model
          ⁢
          
            
          
          ⁢
          delay
        
      
    
    
      
        
          (
          
            scale
            ⁢
            
              
            
            ⁢
            parameter
            ⁢
            
              
            
            ⁢
            for
            ⁢
            
              
            
            ⁢
            satellite
            ⁢
            
              
            
            ⁢
            i
          
          )
        
        ,
      
    
  
  
    
      
        -
      
    
    
      
        
          τ
          e
          i
        
        =
        
          
            
              sin
              ⁡
              
                (
                
                  azim
                  i
                
                )
              
            
            *
            
              cos
              ⁡
              
                (
                
                  elev
                  i
                
                )
              
            
          
          
            
              [
              
                sin
                ⁡
                
                  (
                  
                    elev
                    i
                  
                  )
                
              
              ]
            
            2
          
        
      
    
    
      
        
          (
          
            east
            ⁢
            
              
            
            ⁢
            gradient
            ⁢
            
              
            
            ⁢
            parameter
            ⁢
            
              
            
            ⁢
            for
            ⁢
            
              
            
            ⁢
            satellite
            ⁢
            
              
            
            ⁢
            i
          
          )
        
        ,
      
    
  
  
    
      
        -
      
    
    
      
        
          τ
          n
          i
        
        =
        
          
            
              cos
              ⁡
              
                (
                
                  azim
                  i
                
                )
              
            
            *
            
              cos
              ⁡
              
                (
                
                  elev
                  i
                
                )
              
            
          
          
            
              [
              
                sin
                ⁡
                
                  (
                  
                    elev
                    i
                  
                  )
                
              
              ]
            
            2
          
        
      
    
    
      
        (
        
          north
          ⁢
          
            
          
          ⁢
          gradient
          ⁢
          
            
          
          ⁢
          parameter
          ⁢
          
            
          
          ⁢
          for
          ⁢
          
            
          
          ⁢
          satellite
          ⁢
          
            
          
          ⁢
          i
        
        )
      
    
  




where:

    azimi is the azimuth of satellite i with respect to (with respect to) true north at the rover location,
    elevi is the elevation of satellite i with respect to the local horizon plane of the rover.


The tropospheric bias states can be suitably modeled as random walk, autoregressive, or Gauss-Markov processes. Table 2 contains an acceptable model for the tropospheric bias parameters.
The tropospheric states are updated during the Geometry Filter time-update step, as shown by 725 in FIG. 6. When measurement updates are missed (see test 740 in FIG. 6), i.e. when there are data gaps, the uncertainty in the tropospheric parameters is increased by time-update of the Geometry Filter.
The tropospheric parameters re-converge with the application of measurement data. Given the appropriate measurement and system modeling of the tropospheric states, the Kalman filtering process automatically handles tropospheric bridging in the Geometry filter. That is, the change in the satellite tropospheric biases can be accurately predicted across tracking interruptions of several minutes.







TABLE 2







Suitable tropospheric state definition. (ScaleFactor = 0.40)










Tropospheric State
System Model
Initial State



Parameter
Type
Variance
System Model Parameters





Scale
Random Walk
ScaleFactor *
DrivingNoiseVariance =




0.0019
DeltaTime2 * ScaleFactor * 1.0e−8


East Gradient
First-Order
ScaleFactor * 5.0e−6
CorrelationTime = 1800 sec



Gauss-Markov

Correlated Variance = ScaleFactor *





5.0e−6


North Gradient
First-Order
ScaleFactor * 5.0e−6
CorrelationTime = 1800 sec



Gauss-Markov

Correlated Variance = ScaleFactor *





5.0e−6









Ionospheric Bridging
Introduction
On short-baseline RTK processing, the ionospheric bias is well known and therefore, the ionospheric filter ambiguity estimates are rapidly determined with high precision. The float-ambiguity solution is quickly determined as a result of the high precision ionospheric filter ambiguity estimates. For GVRS processing, the ionospheric filter results are heavily deweighted (essentially ignored) because of a lack of ionospheric bias information. However, once the float solution has converged the ionospheric bias for each observed satellite can be determined as described below.
Once the satellite ionospheric biases have been determined, the ionospheric bridging approach relies on the predictability of the ionosphere to accelerate re-convergence of the float solution immediately following a tracking interruption.
Estimation of Ionospheric Phase Ambiguities
Recall from (4), that the FAMCAR estimation process yields L1 and L2 float(ing point) carrier phase ambiguities for each satellite observed:

ΔL1N1 ΔL2N1 ΔL1N2 ΔL2N2 . . . ΔL1Ns ΔL2Ns 

The formal precision of the L1 and L2 ambiguities is available from the ambiguity partition (Qnn) of the state vector covariance matrix:




  
    
      
        Q
        =
        
          [
          
            
              
                
                  Q
                  xx
                
              
              
                
                  Q
                  xn
                
              
            
            
              
                
                  Q
                  nx
                
              
              
                
                  Q
                  nn
                
              
            
          
          ]
        
      
    
    
      
        (
        5
        )
      
    
  




where:

    Qxx Covariance partition for the position unknowns (3×3);
    Qxn Covariance partition for the position/ambiguity unknowns (3×a);
    Qnx Covariance partition for the ambiguity/position unknowns (a×3);
    Qnn Covariance partition for the ambiguity unknowns (a×a);
    a number of ambiguity states.


The iFlex processing scheme can be used to generate improved estimates of the state parameters which includes the carrier phase ambiguities. Let the iFlex L1 and L2 ambiguities be denoted with a symbol {hacek over ( )} as follows:

ΔL1{hacek over (N)}1 ΔL2{hacek over (N)}1 ΔL1{hacek over (N)}2 ΔL2{hacek over (N)}2 . . . ΔL1{hacek over (N)}s ΔL2{hacek over (N)}s  (6)

The iFlex scheme can also yield the covariance matrix of the unknown parameters, hence the formal precision of the iFlex ambiguities is known and this allows an assessment to be made as whether or not the iFlex ambiguities are sufficiently close to their true integer values.
With the iFlex carrier phase ambiguities well known, the single-difference ambiguity term on satellite i, can be computed for the ionospheric phase combination as:

ΔionoNi=L1λL1{hacek over (N)}i−L2λL2{hacek over (N)}i  (7)

The ionospheric biases can be estimated on each single-difference (server-rover) satellite measurement according to:

ΔionoIi(t)=ΔionoΦi(t)−ΔionoNi(t)−Δionobi(t)  (8)

where:

    ΔionoIi(t)—the single-difference ionospheric delay, at time t, for satellite i;
    ΔionoNi(t)—the single-difference ionospheric ambiguity, for satellite i;
    ΔionoΦi(t)—the single-difference ionospheric phase at time t, for satellite i;
    Δionobi(t)—the single-difference ionospheric phase bias at time t, for satellite i.


The single-difference ionospheric phase bias term (Δionobi(t)) in (8) includes non-integer biases of rover and server, and phase wind-up effects induced on the rover receiver antenna. Phase wind-up effects change with rotation of the rover antenna, however the effect is identical for all satellites observed at the rover and therefore cancel with double-differencing. Server biases are enforced to be constant, through the treatment of the satellite phase clock terms. The single-difference ionospheric ambiguity term (ΔionoNi(t)) is constant so long as carrier phase tracking is maintained.
The single-difference ionospheric delay (ΔionoIi(t)) changes with time as the ionospheric bias at the rover changes. Multipath bias is also included in the single-difference ionospheric delay, a component that typically has a magnitude of for example 1-5 cm and a correlation time of 10-60 s.
If tracking is interrupted at the rover, the single-difference ionospheric ambiguity term in (8) changes. The single-difference ionospheric ambiguity term can be re-established after a tracking interruption by using predicted ionospheric delay and observed ionospheric carrier phase:

ΔionoNi(t1)=ΔionoNi(t0)+ΔionoΦi(t1)−{ΔionoΦi(t0)+ΔionoIi(t1)−ΔionoIi(t0)}  (9)

where:

    ΔionoNi(t0)—single-difference ionospheric ambiguity, at time t0;
    ΔionoNi(t)—single-difference ionospheric ambiguity, at time t1 (iono-bridged ambiguities);
    ΔionoΦi(t0)—single-difference ionospheric phase, observed at time t0;
    ΔionoΦi(t1)—single-difference ionospheric phase, observed at time t1;
    ΔionoIi(t1)−ΔionoIi(t0)—change in single-difference ionospheric delay between times 0 and 1.


The single-difference ionospheric ambiguity terms (ΔionoNi(t1)), for each satellite are used in place of the heavily deweighted ionospheric filter ambiguity estimates in the filter combination step (refer to 640 in FIG. 5). The precision of the resulting float solution is improved by the ionospheric ambiguity aiding.
Predicting the Change in Ionospheric Delay
The variation in the single-difference ionospheric delay over time [ΔionoIi(t1)−ΔionoIi(t0)] should be precisely modeled. The ionosphere is considered as that part of the atmospheric from around 50-1000 km above the earth. Radiation from the sun causes ionization of particles which then result in a frequency-dependent bias on radio waves passing through the medium. The complex physical structure of the ionosphere and the influence of variable solar radiation levels make accurate ionospheric delay modeling difficult. Nevertheless, for the purposes of predicting the ionospheric bias it is possible to just model the variation of the single-difference ionospheric delay for each satellite, without considering the underlying physical causes of the variation.
A simple 2-state Kalman filter can be used to model single-difference ionopheric phase and ionospheric phase rate (these filters are designated as—iono predictor/filters), with a state vector:




  
    
      
        x
        =
        
          [
          
            
              
                
                  
                    Δ
                    iono
                  
                  ⁢
                  
                    
                      Φ
                      i
                    
                    ⁡
                    
                      (
                      t
                      )
                    
                  
                
              
            
            
              
                
                  
                    Δ
                    iono
                  
                  ⁢
                  
                    
                      
                        Φ
                        .
                      
                      i
                    
                    ⁡
                    
                      (
                      t
                      )
                    
                  
                
              
            
          
          ]
        
      
    
    
      
        (
        10
        )
      
    
  




with the state transition matrix (M) defined as:





  
    
      
        M
        =
        
          [
          
            
              
                1
              
              
                
                  Δ
                  ⁢
                  
                    
                  
                  ⁢
                  t
                
              
            
            
              
                0
              
              
                1
              
            
          
          ]
        
      
    
    
      
        (
        11
        )
      
    
  




the system driving noise covariance matrix given by:





  
    
      
        
          Q
          w
        
        =
        
          ξ
          ⁡
          
            [
            
              
                
                  
                    Δ
                    ⁢
                    
                      
                    
                    ⁢
                    
                      
                        t
                        3
                      
                      /
                      3
                    
                  
                
                
                  
                    Δ
                    ⁢
                    
                      
                    
                    ⁢
                    
                      
                        t
                        2
                      
                      /
                      2
                    
                  
                
              
              
                
                  
                    Δ
                    ⁢
                    
                      
                    
                    ⁢
                    
                      
                        t
                        2
                      
                      /
                      2
                    
                  
                
                
                  
                    Δ
                    ⁢
                    
                      
                    
                    ⁢
                    t
                  
                
              
            
            ]
          
        
      
    
    
      
        (
        12
        )
      
    
  




where the spectral density of the driving noise (ξ) defines the level of filtering applied. A suitable value for ξ=4.0e−5.

The measurement model for the filter is defined as:




  
    
      
        
          
            Δ
            iono
          
          ⁢
          
            
              Φ
              i
            
            ⁡
            
              (
              t
              )
            
          
        
        =
        
          
            
              [
              
                1
                ⁢
                
                  
                
                ⁢
                0
              
              ]
            
            ⁡
            
              [
              
                
                  
                    
                      
                        Δ
                        iono
                      
                      ⁢
                      
                        
                          Φ
                          i
                        
                        ⁡
                        
                          (
                          t
                          )
                        
                      
                    
                  
                
                
                  
                    
                      
                        Δ
                        iono
                      
                      ⁢
                      
                        
                          
                            Φ
                            .
                          
                          i
                        
                        ⁡
                        
                          (
                          t
                          )
                        
                      
                    
                  
                
              
              ]
            
          
          +
          
            
              v
              i
            
            ⁡
            
              (
              t
              )
            
          
        
      
    
    
      
        (
        13
        )
      
    
  




with

vi(t) measurement residual for satellite i, at time t.

The Kalman filter provides a way of reducing high-frequency noise on the measurements and enables the prediction of the change in ionospheric phase delay across tracking interruptions. FIG. 8 illustrates the observed ionospheric phase for a single satellite. The variation in the observations is due mainly to changes in the ionospheric delay as well as carrier phase multipath. The filtered estimates track the general trend of the ionospheric phase observations. Immediately following the tracking interruption, the difference between the predicted and actual ionospheric phase measurement provides an estimate of the approximate change in carrier phase ambiguity.
Using the Bridged Ionospheric Ambiguities
Once the rover FAMCAR solution has converged sufficiently and the ionospheric ambiguities are well known, each single-difference satellite ionospheric phase ambiguity is cached. If an outage occurs on tracked satellites, the ionospheric carrier phase ambiguity estimates generated after the tracking outage [ΔionoNi(t1) from (9)] are used to replace the normally deweighted ionospheric filter information (see 640 in FIG. 5).
The precision of the position and ambiguity estimates obtained from the FAMCAR process with ionospheric bridging is far better than those that would derive without bridging.
FIG. 9 schematically illustrates the FAMCAR filtering process with iono bridging functionality added. FIG. 9 is an extension of the standard FAMCAR filtering schematic shown in FIG. 5. In FIG. 9, the Ionospheric bridging processor 1005, accepts prepared single-difference GNSS observations, plus the deweighted ionospheric phase ambiguities 640. When ionospheric bridging is needed and possible, the bridged ionospheric ambiguities 1010 are used to replace the deweighted ionospheric phase ambiguities from 640. The bridged ionospheric ambiguities help to improve the FAMCAR float solution produced by the filter combiner at 655.
Bridging Timeout
The bridged ambiguities are applied to the FAMCAR process every epoch immediately following the outage in order to gain rapid re-convergence of the position estimates. However, it is important to limit the amount of time that the bridged ambiguities are applied to the FAMCAR solution. If for example there is an error in one or more of the bridged ambiguities, this error will propagate indefinitely forward and result in position errors of a few centimeters up to several decimeters.
The ionospheric bridging can be stopped as soon as the geometry filter naturally re-converges to a level where the bridged ambiguities no longer provide an improvement to the results.
Detailed Flowchart for Ionospheric Bridging Process
FIG. 10 contains a detailed flowchart for the ionospheric bridging process. Note that the first step of the ionospheric bridging process (815); and the last step 820, relate to FIG. 8.
The test at 1105 is used to determine if the Geometry filter has converged, if so, then ionospheric bridging is no longer needed. A test is made at 1110 to see if iFlex ambiguities have already been cached. iFlex ambiguities are cached to be able to run the ionospheric bridging process. The ionospheric bias is predicted at 1115 for each cached satellite according to the approach defined by equations 9-13. If the cached ionospheric ambiguities are out of date (test 1120) then a further test is made at 1125 to see if the predicted ionospheric ambiguities are sufficiently well known. If the ionospheric ambiguities are well known, then they are stored at 1130.
The deweighted ionospheric filter ambiguities are replaced by bridged ionospheric ambiguities at 1135, when possible. The ionospheric bias filters are updated for each tracked satellite at 1140. Finally, the FAMCAR filter results are combined at 820.
FIG. 11 presents a flowchart describing the iFlex ambiguity caching process. The flowchart is an expansion of steps 830 and 840 in FIG. 8.
A test is made at 1205 to see if the number of iFlex ambiguities has settled. If the number of satellites is changing, this generally indicates a poor tracking environment and compromised iFlex ambiguity estimates. If the iFlex ambiguities are well known, then they can be assumed to approach a single integer candidate (test 1210) and therefore the iFlex ambiguities can be cached at 1215. The cycle slip counters are stored with the iFlex ambiguities for later use in the iono bridging process.
If the number of satellites tracked is inconsistent, or the iFlex ambiguities are not well enough known, caching is skipped until another epoch of data is processed.
The ionospheric bridging process enables centimeter level horizontal positioning accuracy to be reestablished within 5-30 s after tracking interruptions. Tracking interruptions up to 2 minutes can be readily bridged as long as the ionospheric delays are smoothly changing.
Known Position Techniques
Background Art
Known position initialization techniques have been used since the first RTK products were sold. In a prior-art method Allison, M. T. et al., 1994, Determination of phase ambiguities in satellite ranges, U.S. Pat. No. 5,359,332, Issued October 25, the distance and orientation of a rover antenna relative to a reference antenna is used in the estimation of the carrier phase ambiguities on GNSS signals for the purposes of centimeter level positioning. An apparatus is also described in which an azimuth measuring device is coupled with a fixed distance rover antenna mount. The method and apparatus described focuses on single reference (base) RTK positioning and does not address the estimation process needed for GVRS positioning.
Known Position Input
Introduction
FIG. 12 schematically illustrates a scenario using a GNSS rover with correction data for point surveying. A user 1100 has a rover receiver (rover) 1105 which is mounted on a range pole 1110 or in some cases is a hand-held, or machine-mounted unit without a range pole. Rover 1105 includes a GNSS antenna 1115 and a communications antenna 1120. Rover 1105 receives at its GNSS antenna 1115 the signals from GNSS satellites 1125, 1130, 1135, 1140, 1145, etc. Rover 1105 also receives at its communications antenna 1120 correction data from a corrections source 1150 via a communications link 1155. The communications link is, for example, a radio link or mobile telephone link, or any other suitable means of conveying the correction data to the rover 1105. The correction data can be of any suitable type for improving the positioning accuracy of rover 1105, such as: differential base station data from a base station serving as corrections source 1150, or virtual reference station data from a network of reference stations serving as corrections source 1150 (WAAS is one example), or precise orbits and clocks data from a GVRS service such as that described in U.S. Provisional Application for Patent No. 61/277,184 filed 19 Sep. 2009. In the example of FIG. 12, the phase center of GNSS antenna 1115 is determined and reduced for the height and orientation of the range pole 1110 to the survey point 1160. The position of the rover can be determined at each measurement epoch while static or kinematic. In this example, the location of point 1160 is determined via static occupation, followed by a segment of kinematic positioning, then another static occupation of point 1170. The location of occupied points is often saved as part of a measurement process.
There are several applications that can take advantage of knowledge of the user location in order to reduce solution convergence times. For example, machine control operators from time-to-time need to stop and shut down their machine during meal times or overnight. The position of the machine is therefore often accurately known prior to the tracking interruption. Similarly, a surveyor often measures the location of points of interest via static occupation, separated by periods of kinematic positioning. If tracking is interrupted while moving, the surveyor can return to a previously surveyed mark (like point 1160 or point 1170 in FIG. 12) and restart operation. The use of known position information can accelerate re-convergence of the estimation process.
The Known Position Input scheme presented below is applicable to GVRS rover processing, but it can also be used for single-base, VRS, and all RTK techniques.
Geometry Filter Seeding
The known rover position information can be used to seed the (X,Y,Z) position states of the Geometry Filter via tightly constrained position covariance terms. The known position in this case would help to accelerate the convergence of all states in the Geometry Filter and therefore the overall Float filter and iFlex solution.
The disadvantage of position seeding is that if the input coordinates are incorrect, this will corrupt the Geometry filter into the future, unless the filter is reset.
Known Position Input Via Auxiliary Code-Carrier Filter Aiding
The auxiliary code-carrier filter results can be used to provide a means of inputting position information to the FAMCAR process. An advantage of this approach is that the position aiding process does not alter the underlying filters, but rather is just applied to the output of the Auxiliary Code-Carrier Filters. The position aiding process is analogous to that used for iono-bridging. In the case of position aiding, the Auxiliary Code-Carrier filter results are modified, whereas for iono-bridging, the ionospheric filter results are modified.
The Auxiliary Code-Carrier filter bank normally produces iono-free ambiguity estimates for each tracked satellite based on iono-free code measurements. Iono-free code is inherently noisy and therefore the iono-free ambiguity estimates of the Auxiliary Code-Carrier filters are also noisy and only contribute a small amount of information to the float solution.
When the position of the rover (A) is known, the geometric range from rover to each satellite is given by:

ρAi=√{square root over ((xi−XA)2+(yi−YA)2+(zi−ZA))}2   (14)

where:

    (xi,yi,zi) Cartesian WGS84 coordinates of satellite i, given by the satellite ephemeris,
    (XA,YA,ZA) Cartesian WGS84 coordinates of the rover (known position).


The reference receiver (R) location is also known and the geometric range from reference receiver to each satellite is given as:

ρRi√{square root over ((xi−XR)2+(yi−YR)2+(zi−ZR))}2  (15)

where:

    (XR,YR,ZR) Cartesian WGS84 coordinates of the reference receiver. Note that in the case of GVRS processing, the reference receiver is synthetic, nevertheless the reference receiver coordinates are defined.


The single difference iono-free carrier phase ambiguities are estimated for each satellite via the following equation (with all quantities given in meters):

ΔifNRAi=ΔifΦRAi−└ΔρRAi+ΔτRAi+ΔκRA┘  (16)

where:

    ΔifNRAi single-difference iono-free carrier phase ambiguity for satellite i,
    ΔifΦRAi single-difference iono-free carrier phase observation for satellite i,
    ΔρRAi single-difference geometric range for satellite i (ΔρRAi=ρAi−ρRi),
    ΔτRAi single-difference tropospheric bias for satellite i, based on a tropospheric model (e.g. Hopfield, Goad-Goodman, etc), or based on the estimated tropospheric bias parameters from the Geometry Filter,
    ΔκRA single-difference receiver clock bias (=reference receiver clock bias minus the rover receiver clock bias).


The uncertainty of the rover location is expressed in terms of the following position covariance matrix:




  
    
      
        
          Q
          p
        
        =
        
          [
          
            
              
                
                  q
                  xx
                
              
              
                
                  q
                  xy
                
              
              
                
                  q
                  xz
                
              
            
            
              
                
                  q
                  yx
                
              
              
                
                  q
                  yy
                
              
              
                
                  q
                  yz
                
              
            
            
              
                
                  q
                  zx
                
              
              
                
                  q
                  zy
                
              
              
                
                  q
                  zz
                
              
            
          
          ]
        
      
    
    
      
        (
        17
        )
      
    
  




where qxx refers to the variance of the x-coordinate, qxy, refers to the covariance of the x and y coordinates etc.

The variance of the rover-satellite geometric range is obtained by projecting the rover position covariance matrix into the direction of the satellite according to:




  
    
      
        
          σ
          
            ρ
            A
            i
          
          2
        
        =
        
          
            
              [
              
                
                  a
                  x
                  i
                
                ⁢
                
                  
                
                ⁢
                
                  a
                  y
                  i
                
                ⁢
                
                  
                
                ⁢
                
                  a
                  z
                  i
                
              
              ]
            
            ⁡
            
              [
              
                
                  
                    
                      q
                      xx
                    
                  
                  
                    
                      q
                      xy
                    
                  
                  
                    
                      q
                      xz
                    
                  
                
                
                  
                    
                      q
                      yx
                    
                  
                  
                    
                      q
                      yy
                    
                  
                  
                    
                      q
                      yz
                    
                  
                
                
                  
                    
                      q
                      zx
                    
                  
                  
                    
                      q
                      zy
                    
                  
                  
                    
                      q
                      zz
                    
                  
                
              
              ]
            
          
          ⁡
          
            [
            
              
                
                  
                    a
                    x
                    i
                  
                
              
              
                
                  
                    a
                    y
                    i
                  
                
              
              
                
                  
                    a
                    z
                    i
                  
                
              
            
            ]
          
        
      
    
    
      
        (
        18
        )
      
    
  




where:





  
    a
    x
    i
  
  =
  
    
      -
      
        (
        
          
            x
            i
          
          -
          
            X
            A
          
        
        )
      
    
    
      ρ
      A
      i
    
  




     Partial derivative of the rover-satellite geometric range with respect to the rover XA coordinate;






  
    a
    y
    i
  
  =
  
    
      -
      
        (
        
          
            y
            i
          
          -
          
            Y
            A
          
        
        )
      
    
    
      ρ
      A
      i
    
  




     Partial derivative of the rover-satellite geometric range with respect to the rover YA coordinate;






  
    a
    z
    i
  
  =
  
    
      -
      
        (
        
          
            z
            i
          
          -
          
            Z
            A
          
        
        )
      
    
    
      ρ
      A
      i
    
  




     Partial derivative of the rover-satellite geometric range with respect to the rover ZA coordinate.


The variance of the computed single difference iono-free carrier phase ambiguity is computed by applying the law of propagation of variances to (16):

σΔifNRAi2=σΔifΦRAi2+σΔρRAi2+σΔτRAi2+σΔκRA2  (19)

where:

    σΔifNRAi2 variance of the single-difference iono-free carrier phase ambiguity for satellite i;
    σΔifΦRAi2 variance of the single-difference iono-free carrier phase measurement for satellite i;
    σΔρRAi2 variance of the single-difference geometric range term for satellite i;
    σΔτRAi2 variance of the single-difference tropospheric model value for satellite i;
    σΔκRA2 variance of the single-difference receiver clock bias term.


Normally the dominant errors in (19) relate to the geometric-range term σΔρRAi2, and the carrier phase measurement σΔifΦRAi2; the other error sources are often ignored.
FIG. 13 illustrates the use of known position information in the updating of the auxiliary code-carrier filter results. This flowchart is an expansion of steps 815 and 820 in FIG. 7.
The position aiding process is terminated as soon as the geometry filter has sufficiently converged. The geometry filter convergence test is conducted at 1305. If known position is available (1310), then at 1320 ionospheric-free carrier phase ambiguities are computed based on the known position input. The ionospheric-free carrier phase ambiguities are stored to the Geometry Cache as part of step 1320.
It is important to monitor cycle slips in the multi-frequency bands to ensure that the ionospheric-free carrier phase ambiguities stored in the Geometry cache are consistent with the current phase (1325). The Auxiliary Code-Carrier Filter ambiguity results are updated with the Geometry Cached ambiguities in step 1330. The results of the Auxiliary Code-Carrier Filters are posted at 1335, and used in the FAMCAR combination step 820.
FIG. 14 schematically describes the FAMCAR filtering process with position aiding FIG. 14 is derived from the standard FAMCAR filtering process shown in FIG. 5. The known position processor, 1405, accepts single-differenced ionospheric-free phase data from 605/610, plus the ionospheric-free phase ambiguities 645 produced by the Auxiliary Code-Carrier Filter bank 625. When known position information 1402 is provided to the known position processor, it produces ionospheric-free phase ambiguities that replace those produced by the Auxiliary Code-Carrier Filter bank (1410). The known position aided ambiguities are used in the FAMCAR combination step 655. Finally, the position and float ambiguity estimates are reported at step 660.
Known Position Input Via Code-Carrier Filters
The low accuracy of the Auxiliary Code-Carrier Filter ambiguity results normally means that they don't contribute significantly to the final FAMCAR combined float solution. This makes the Auxiliary Code-Carrier Filter results well suited to use for known position input. Furthermore, the iono-free carrier phase combination used in the Auxiliary Code-Carrier Filters, means that the known position range computations can be formed without being impacted by ionospheric bias. Ionospheric bias is a significant error source for GVRS processing.
The known position input could also be handled by modifying the Code-Carrier Filter results, in a manner which is analogous to that used in the Auxiliary Code-Carrier Filter results. The disadvantage of this approach is that the Code-Carrier Filters nominally use the wide-lane carrier phase combination, which contains an ionospheric bias. Second, the code-carrier filter results contribute significantly to the FAMCAR combined float solution therefore this information would be compromised if replaced by the known position input.
Rather than replacing the Auxiliary Code-Carrier Filter results with known position information, an alternative is to generate a parallel bank of Auxiliary Code-Carrier Filter results devoted to known position information input.
Termination of the Known Position Aiding Process
The known position aiding process outlined does not corrupt any FAMCAR component filter, just the uncombined filter results (output) are modified prior to the FAMCAR filter combination step. The known position aiding process is automatically terminated when:

    
    
        The known position is deemed to be incorrect;
        The Geometry filter has converged sufficiently that the known position aiding is no longer required.
    
    


The known position information is deemed suspect or incorrect if the float/iFlex solution fails a statistical test of the mean and/or variance.
When the position states of the Geometry filter have converged, i.e. all variances < for example 0.002 m2. In this case, the position aiding no longer adds significant information to the float solution.
Performance of Known Position Input processing
As illustrated in FIG. 3, convergence and re-convergence of the horizontal position accuracy can take 15-20 minutes to achieve centimeter-level. With known position input, the convergence time is normally reduced to a few seconds up to for example 1 minute.
Following is a summary of some of the inventive concepts described herein:
[Iono Bridging]

    
    
        1. A positioning method, comprising
        
            a. Obtaining GNSS data derived from multi-frequency signals received at a rover antenna,
            b. Obtaining correction data derived from a network of reference stations,
            c. At each of a plurality of epochs, using the GNSS data and the correction data to estimate values defining a rover antenna position and a set of multi-frequency ambiguities,
            d. Using an ionospheric filter to model variation in ionospheric bias per satellite,
            e. Estimating a set of ionospheric carrier-phase ambiguities at least when the multi-frequency ambiguities have attained a predetermined precision,
            f. Caching the estimated ionospheric carrier-phase ambiguities,
            g. Detecting an interruption of signal received at the rover antenna,
            h. Determining reacquisition of signals received at the rover antenna,
            i. Predicting an ionospheric bias per satellite over an interruption interval,
            j. For each satellite, combining a cached ionospheric carrier-phase ambiguity with a predicted ionospheric bias to obtain a post-interruption ionospheric ambiguity estimate,
            k. Using the post-interruption ionospheric ambiguity estimates to aid estimation of at least a rover antenna position subsequent to the reacquisition.
        
        
        2. The method of 1, wherein aiding comprises, at each of a plurality of epochs after reacquisition of signals, using the GNSS data and the correction data and the post-interruption iono ambiguity estimates to estimate values defining an aided rover antenna position and an aided set of multi-frequency ambiguities.
        3. The method of 2, further comprising determining a precision of the post-interruption rover antenna position and of each of the multi-frequency ambiguities.
        4. The method of 3, wherein when the precisions of the post-interruption rover antenna position and of each of the multi-frequency ambiguities has achieved a predetermined threshold, using the post-interruption ionospheric ambiguity estimates to aid estimation is terminated.
        5. The method of one of 1-4, wherein rover-satellite ionospheric biases are substantially uncorrelated with reference station-satellite ionospheric biases.
        6. The method of one of 1-5, wherein the ionospheric filter models an ionospheric bias per satellite which is single-differenced between rover data and correction data.
        7. The method of one of 1-6, wherein the set of ionospheric carrier-phase ambiguities comprises a single-differenced ionospheric ambiguity per satellite.
        8. The method of one of 1-7, wherein detecting an interruption comprises determining that fewer than four satellites are continuously observed over a predetermined interval.
        9. The method of one of 1-8, wherein determining reacquisition comprises determining that at least four satellites are continuously observed over a predetermined interval.
        10. The method of one of 1-9, wherein the estimated rover antenna position has a precision which is better than a precision that would be obtained without use of the generated set of ionospheric ambiguity estimates.
        11. The method of one of 1-10, further comprising terminating using the post-interruption ionospheric ambiguity estimates to aid estimation when substantially no further benefit is obtained therefrom.
        12. The method of one of 1-11, wherein the values defining the rover antenna position are estimated in a filter, the method further comprising monitoring precisions of the values estimated and terminating using the post-interruption ionospheric ambiguity estimates to aid estimation of rover antenna position when a precision threshold is achieved for values defining the rover position.
        13. The method of one of 10-11 wherein terminating using the post-interruption ionospheric ambiguity estimates to aid estimation of rover antenna position comprises continuing to use the GNSS data and the correction data to estimate values defining a rover antenna position.
        14. The method of one of 1-13, further comprising predicting tropospheric bias and using predicted tropospheric bias to aid the estimation of at least a rover antenna position subsequent to the reacquisition.
        15. The method of one of 1-14, wherein the set of ionospheric carrier-phase ambiguities is determined as a weighted average of integer ambiguity candidate sets.
        16. The method one of 1-15, wherein caching of the estimated ionospheric phase ambiguities is deferred until satellite tracking is determined to be stable and within predetermined parameters.
        17. The method of one of 1-16, further comprising estimating time-wise variation of an ionospheric bias per satellite.
        18. The method of one of 1-17, further comprising estimating a change in ionospheric carrier-phase ambiguities after detecting an interruption of signal received at the rover antenna.
        19. The method of one of 1-18, wherein using the post-interruption ionospheric ambiguity estimates to aid estimation of at least a rover antenna position subsequent to the reacquisition comprises combining the post-interruption ionospheric ambiguity estimates with estimates of other parameters from a set of factorized filters.
        20. The method of 19, wherein the post-interruption ionospheric ambiguity estimates are substituted for estimates from a bank of ionospheric filters.
        21. Apparatus for performing a method according to one of 1-20.
        22. A computer program comprising instructions for causing an apparatus to perform a method according to one of 1-20.
        23. A computer program product comprising a tangible computer-readable medium embodying instructions for causing an apparatus to perform a method according to one of 1-20.
    
    


[Known Position]

    
    
        1. A positioning method, comprising
        
            a. Obtaining GNSS data derived from multi-frequency signals received at a rover antenna,
            b. Obtaining correction data derived from a network of reference stations,
            c. At each of a plurality of epochs, using the GNSS data and the correction data to estimate values defining a rover antenna position and a set of multi-frequency ambiguities,
            d. Estimating an ionospheric-free carrier-phase ambiguity per satellite based on a known rover antenna position, and
            e. Using the estimated ionospheric-free carrier-phase ambiguities to assist in determining an aided rover antenna position.
        
        
        2. The method of 1, wherein using the estimated ionospheric-free carrier-phase ambiguities to assist in determining an aided rover antenna position comprises combining the estimated ionospheric-free carrier-phase ambiguity with an estimated widelane ambiguity and with an estimated ionospheric-free ambiguity and with values defining the known rover antenna position to obtain values defining an aided rover antenna position and aided multi-frequency ambiguities.
        3. The method of one of 1-2, further comprising terminating using the estimated ionospheric-free carrier-phase ambiguities to assist in determining an aided rover antenna position when substantially no further benefit is obtained therefrom.
        4. The method of one of 1-3, further comprising monitoring precision of an unaided rover antenna position estimate to determine when substantially no further benefit is obtained from using the estimated ionospheric-free carrier-phase ambiguities to assist in determining an aided rover antenna position.
        5. The method of one of 2-4, wherein the widelane ambiguities are estimated in a set of code-carrier filters.
        6. The method of one of 2-5, wherein the ionospheric-free ambiguities are estimated in a geometry filter.
        7. The method of one of 1-6, wherein the ionospheric-free carrier-phase ambiguity per satellite based on a known rover antenna position is computed using the known rover antenna position and observed carrier-phase measurements.
        8. The method of one of 1-7, wherein the ionospheric-free carrier-phase ambiguity for at least one satellite based on a known rover antenna position is improved using a prevailing tropospheric bias on the respective satellite.
        9. The method of one of 1-8, wherein using the estimated ionospheric-free carrier-phase ambiguities to assist in determining an aided rover antenna position estimated ionospheric-free carrier-phase ambiguity estimates with estimates of other parameters from a set of factorized filters.
        10. The method of 9, wherein the estimated ionospheric-free carrier-phase ambiguity estimates are substituted for estimates from a bank of auxiliary code-carrier filters.
        11. The method of 10, further comprising creating a separate bank of auxiliary code carrier filter results for the known position results so that normal auxiliary code carrier filter results remain unaffected.
        12. Apparatus for performing a method according to one of 1-11.
        13. A computer program comprising instructions for causing an apparatus to perform a method according to one of 1-11.
        14. A computer program product comprising a tangible computer-readable medium embodying instructions for causing an apparatus to perform a method according to one of 1-11.
    
    


The foregoing description of embodiments is not intended as limiting the scope of but rather to provide examples of the invention as defined by the claims.

## Claims

1. A method of estimating a position of a rover antenna using a computer processor, the method comprising:
receiving GNSS data derived from multi-frequency signals received at the rover antenna over a plurality of epochs;
receiving correction data for the GNSS data from a network of reference stations over the plurality of epochs;
at each of the plurality of epochs, estimating values defining a rover antenna position and a set of multi-frequency ambiguities using the GNSS data and the correction data;
modeling variation in ionospheric bias per satellite using an ionospheric filter;
estimating a set of ionospheric carrier-phase ambiguities;
upon determining that the set of ionospheric carrier-phase ambiguities have converged, caching the set of ionospheric carrier-phase ambiguities;
detecting an interruption of signal received at the rover antenna;
determining reacquisition of signals received at the rover antenna;
predicting an ionospheric bias per satellite over an interruption interval;
for each satellite, combining a cached ionospheric carrier-phase ambiguity with the predicted ionospheric bias to obtain a post-interruption ionospheric ambiguity estimate; and
estimating a position of the rover antenna subsequent to the reacquisition using the post-interruption ionospheric ambiguity estimates.

2. The method of claim 1, wherein estimating the position of the rover antenna position subsequent to the reacquisition comprises, at each of a plurality of epochs after reacquisition of signals, using the GNSS data, the correction data, and the post-interruption ionospheric ambiguity estimates to estimate values defining an aided rover antenna position and an aided set of multi-frequency ambiguities.

3. The method of claim 2, further comprising determining an accuracy of the post-interruption rover antenna position and an accuracy of each of the multi-frequency ambiguities.

4. The method of claim 3, further comprising, upon determining that the accuracy of the post-interruption rover antenna position and the accuracy of each of the multi-frequency ambiguities has each achieved a predetermined level, terminating the estimation of the position of the rover antenna position subsequent to the reacquisition.

5. The method of claim 4, wherein the values defining the rover antenna position are estimated in a filter, the method further comprising monitoring accuracies of the estimated values and terminating the estimation of the values when a predetermined accuracy level is achieved.

6. The method of claim 5, further comprising continuing the estimation of the values defining a rover antenna position after terminating the estimation of the position of the rover antenna position subsequent to the reacquisition.

7. The method of claim 1, wherein rover-satellite ionospheric biases are substantially uncorrelated with reference station-satellite ionospheric biases.

8. The method of claim 1, wherein the ionospheric filter models an ionospheric bias per satellite which is single-differenced between rover data and correction data.

9. The method of claim 1, wherein the set of ionospheric carrier-phase ambiguities comprises a single-differenced ionospheric ambiguity per satellite.

10. The method of claim 1, wherein detecting the interruption comprises determining that fewer than four satellites are continuously observed over a predetermined interval.

11. The method of claim 1, wherein determining the reacquisition comprises determining that at least four satellites are continuously observed over a predetermined interval.

12. The method of claim 1, wherein the estimated rover antenna position subsequent to the reacquisition has a precision which is better than a precision that would be obtained without use of the post-interruption ionospheric ambiguity estimates.

13. The method of claim 1, further comprising predicting a tropospheric bias, and wherein the predicted tropospheric bias is used in the estimation of the rover antenna position subsequent to the reacquisition.

14. The method of claim 1, wherein the set of ionospheric carrier-phase ambiguities is estimated as a weighted average of integer ambiguity candidate sets.

15. The method of claim 1, further comprising deferring caching of the estimated ionospheric phase ambiguities until satellite tracking is determined to be stable and within predetermined parameters.

16. The method of 1, further comprising estimating time-wise variation of an ionospheric bias per satellite.

17. The method of claim 1, further comprising estimating a change in ionospheric carrier-phase ambiguities after detecting an interruption of signal received at the rover antenna.

18. The method of claim 1, wherein estimating the position of the rover antenna subsequent to reacquisition comprises combining the post-interruption ionospheric ambiguity estimates with estimates of other parameters from a set of factorized filters.

19. The method of claim 18, wherein the post-interruption ionospheric ambiguity estimates are substituted for estimates from a bank of ionospheric filters.

20. An apparatus comprising:
a receiver configured to:
receive GNSS data derived from multi-frequency signals received at a rover antenna; and
receive correction data for the GNSS data derived from a network of reference stations; and

a processor coupled to the receiver, the processor configured to:
at each of a plurality of epochs, estimate values defining a rover antenna position and a set of multi-frequency ambiguities using the GNSS data and the correction data;
model variation in ionospheric bias per satellite using an ionospheric filter;
estimate a set of ionospheric carrier-phase ambiguities until the multi-frequency ambiguities have converged;
cache the estimated ionospheric carrier-phase ambiguities;
detect an interruption of signal received at the rover antenna;
determine reacquisition of signals received at the rover antenna;
predict an ionospheric bias per satellite over an interruption interval;
for each satellite, combine a cached ionospheric carrier-phase ambiguity with a predicted ionospheric bias to obtain a post-interruption ionospheric ambiguity estimate; and
estimate a position of the rover antenna subsequent to the reacquisition using the post-interruption ionospheric ambiguity estimates.

21. The apparatus of claim 20, wherein estimating the position of the rover antenna subsequent to the reacquisition comprises, at each of a plurality of epochs after reacquisition of signals, using the GNSS data and the correction data and the post-interruption ionospheric ambiguity estimates to estimate values defining an aided rover antenna position and an aided set of multi-frequency ambiguities.

22. The apparatus of claim 21, wherein the processor is further configured to determine an accuracy of the position of the rover antenna subsequent to the reacquisition and an accuracy of each of the multi-frequency ambiguities.

23. The apparatus of claim 22, wherein the processor is further configured to terminate the estimation of the position of the rover antenna subsequent to the reacquisition when the accuracy of the position of the rover antenna subsequent to the reacquisition and the accuracy of each of the multi-frequency ambiguities has each achieved a predetermined level.

24. The apparatus of claim 23, wherein the values defining the position of the rover antenna are estimated in a filter operated by the processor, wherein the processor is further configured to monitor precisions of the estimated values and to terminate the estimation of the values when the precisions of the values have reached a predetermined level.

25. The apparatus of claim 24, wherein the processor is further configured to continue estimating values defining a rover antenna position after terminating the estimation of the position of the rover antenna subsequent to the reacquisition.

26. The apparatus of claim 20, wherein rover-satellite ionospheric biases are substantially uncorrelated with reference station-satellite ionospheric biases.

27. The apparatus of claim 20, wherein the ionospheric filter models an ionospheric bias per satellite which is single-differenced between rover data and correction data.

28. The apparatus of claim 20, wherein the set of ionospheric carrier-phase ambiguities comprises a single-differenced ionospheric ambiguity per satellite.

29. The apparatus of claim 20, wherein detecting an interruption comprises determining that fewer than four satellites are continuously observed over a predetermined interval.

30. The apparatus of claim 20, wherein determining reacquisition comprises determining that at least four satellites are continuously observed over a predetermined interval.

31. The apparatus of claim 20, wherein the estimated position of the rover antenna subsequent to the reacquisition has a precision which is better than a precision that would be obtained without use of the post-interruption ionospheric ambiguity estimates.

32. The apparatus of claim 20, wherein the processor is further configured to predict tropospheric bias, and wherein the predicted tropospheric bias is used in the estimation of the rover antenna position subsequent to the reacquisition.

33. The apparatus of claim 20, wherein the processor determines the set of ionospheric carrier-phase ambiguities as a weighted average of integer ambiguity candidate sets.

34. The apparatus of claim 20, wherein caching of the estimated ionospheric phase ambiguities is deferred until the processor determines satellite tracking to be stable and within predetermined parameters.

35. The apparatus of claim 20, wherein the processor is further configured to estimate time-wise variation of an ionospheric bias per satellite.

36. The apparatus of claim 20, wherein the processor is further configured to estimate a change in ionospheric carrier-phase ambiguities after detecting an interruption of signal received at the rover antenna.

37. The apparatus of claim 20, wherein estimating the position of the rover antenna subsequent to reacquisition comprises combining the post-interruption ionospheric ambiguity estimates with estimates of other parameters from a set of factorized filters.

38. The apparatus of claim 20, wherein the processor is further configured to substitute the post-interruption ionospheric ambiguity estimates for estimates from a bank of ionospheric filters.

39. A computer program product comprising a non-transitory computer-readable medium embodying instructions for causing an apparatus to perform the method of claim 1.