CA2768923C - System and/or method for reducing ambiguities in received sps signals - Google Patents
System and/or method for reducing ambiguities in received sps signals Download PDFInfo
- Publication number
- CA2768923C CA2768923C CA2768923A CA2768923A CA2768923C CA 2768923 C CA2768923 C CA 2768923C CA 2768923 A CA2768923 A CA 2768923A CA 2768923 A CA2768923 A CA 2768923A CA 2768923 C CA2768923 C CA 2768923C
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- CA
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- Prior art keywords
- timing
- reference location
- estimated
- transitions
- bit edge
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S5/00—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations
- G01S5/02—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations using radio waves
- G01S5/14—Determining absolute distances from a plurality of spaced points of known location
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/33—Multimode operation in different systems which transmit time stamped messages, e.g. GPS/GLONASS
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S1/00—Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/243—Demodulation of navigation message
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/13—Receivers
- G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
- G01S19/25—Acquisition or tracking or demodulation of signals transmitted by the system involving aiding data received from a cooperating element, e.g. assisted GPS
- G01S19/252—Employing an initial estimate of location in generating assistance data
Abstract
Systems, apparatuses, and/or methods for resolving ambiguities associated with signals received from space vehicles (SVs) in a satellite navigation system. For example, certain methods include receiving a first SV signal from a first satellite positioning system (SPS), and reducing a bit edge ambiguity of a data signal modulating a second SV signal received from a second SPS based, at least in part, on information in the received first SV signal.
Claims (10)
1. A method for position location on a mobile device comprising:
determining, using a processor of the mobile device, timing of a bit edge of a data signal modulating a first navigation signal transmitted by a first space vehicle (SV) and received at a reference location; and determining, using the processor of the mobile device, timing of transitions in an alternating Viterbi encoded signal modulating a second navigation signal, transmitted by a second SV and received at said reference location, based, at least in part, on said timing of said bit edge, wherein determining said timing of said transitions further comprises associating said timing of said bit edge with said timing of said transitions based, at least in part, on an estimated difference between a first range to said first SV from said reference location and a second range to said second SV from said reference location and on an estimated uncertainty associated with the estimated difference, the estimated uncertainty being based at least in part on an estimated azimuth angle to said first SV from said reference location, and wherein the first SV is a member of a first navigation satellite constellation and the second SV is a member of a second navigation satellite constellation.
determining, using a processor of the mobile device, timing of a bit edge of a data signal modulating a first navigation signal transmitted by a first space vehicle (SV) and received at a reference location; and determining, using the processor of the mobile device, timing of transitions in an alternating Viterbi encoded signal modulating a second navigation signal, transmitted by a second SV and received at said reference location, based, at least in part, on said timing of said bit edge, wherein determining said timing of said transitions further comprises associating said timing of said bit edge with said timing of said transitions based, at least in part, on an estimated difference between a first range to said first SV from said reference location and a second range to said second SV from said reference location and on an estimated uncertainty associated with the estimated difference, the estimated uncertainty being based at least in part on an estimated azimuth angle to said first SV from said reference location, and wherein the first SV is a member of a first navigation satellite constellation and the second SV is a member of a second navigation satellite constellation.
2. The method of claim 1, wherein said first SV is a member of a GPS
constellation and said second SV is a member of a Galileo or a Glonass constellation.
constellation and said second SV is a member of a Galileo or a Glonass constellation.
3. The method of claim 1, wherein satellites of the first navigation satellite constellation transmit a first set of pseudo-random noise (PN) codes that are different that a second set of pseudo-random noise (PN) codes transmitted by satellites of the second navigation satellite constellation.
4. The method of claim 1, wherein signals transmitted by satellites of the first navigation satellite constellation include pseudo-random noise (PN) codes that repeated over a first interval and signals transmitted by satellites of the second navigation satellite constellation include PN codes that are repeated over a second interval that has a different duration than the first interval.
5. The method of claim 1 wherein the estimated uncertainty is also based at least in part on an estimated elevation angle to said second SV from said reference location.
6. An apparatus comprising:
a processor configured to:
determine timing of a bit edge of a data signal modulating a first navigation signal transmitted by a first space vehicle (SV) and received at a reference location; and determine timing of transitions in an alternating Viterbi encoded signal modulating a second navigation signal, transmitted by a second SV and received at said reference location, based, at least in part, on said timing of said bit edge, wherein to determine said timing of said transitions the processor is configured to associate said timing of said bit edge with said timing of said transitions based, at least in part, on an estimated difference between a first range to said first SV from said reference location and a second range to said second SV from said reference location and on an estimated uncertainty associated with the estimated difference, the estimated uncertainty being based at least in part on an estimated azimuth angle to said first SV from said reference location, and wherein the first SV is a member of a first navigation satellite constellation and the second SV is a member of second navigation satellite constellation.
a processor configured to:
determine timing of a bit edge of a data signal modulating a first navigation signal transmitted by a first space vehicle (SV) and received at a reference location; and determine timing of transitions in an alternating Viterbi encoded signal modulating a second navigation signal, transmitted by a second SV and received at said reference location, based, at least in part, on said timing of said bit edge, wherein to determine said timing of said transitions the processor is configured to associate said timing of said bit edge with said timing of said transitions based, at least in part, on an estimated difference between a first range to said first SV from said reference location and a second range to said second SV from said reference location and on an estimated uncertainty associated with the estimated difference, the estimated uncertainty being based at least in part on an estimated azimuth angle to said first SV from said reference location, and wherein the first SV is a member of a first navigation satellite constellation and the second SV is a member of second navigation satellite constellation.
7. The apparatus of claim 6 wherein said first SV is a member of a GPS
constellation and said second SV is a member of a Galileo or a Glonass constellation.
constellation and said second SV is a member of a Galileo or a Glonass constellation.
8. An apparatus comprising:
means for determining timing of a bit edge of a data signal modulating a first navigation signal transmitted by a first space vehicle (SV) and received at a reference location; and means for determining timing of transitions in an alternating Viterbi encoded signal modulating a second navigation signal, transmitted by a second SV and received at said reference location, based, at least in part, on said timing of said bit edge, wherein the means for determining said timing of said transitions further comprises means for associating said timing of said bit edge with said timing of said transitions based, at least in part, on an estimated difference between a first range to said first SV from said reference location and a second range to said second SV from said reference location and on an estimated uncertainty associated with the estimated difference, the estimated uncertainty being based at least in part on an estimated azimuth angle to said first SV from said reference location, and wherein the first SV is a member of a first navigation satellite constellation and the second SV is a member of a second navigation satellite constellation.
means for determining timing of a bit edge of a data signal modulating a first navigation signal transmitted by a first space vehicle (SV) and received at a reference location; and means for determining timing of transitions in an alternating Viterbi encoded signal modulating a second navigation signal, transmitted by a second SV and received at said reference location, based, at least in part, on said timing of said bit edge, wherein the means for determining said timing of said transitions further comprises means for associating said timing of said bit edge with said timing of said transitions based, at least in part, on an estimated difference between a first range to said first SV from said reference location and a second range to said second SV from said reference location and on an estimated uncertainty associated with the estimated difference, the estimated uncertainty being based at least in part on an estimated azimuth angle to said first SV from said reference location, and wherein the first SV is a member of a first navigation satellite constellation and the second SV is a member of a second navigation satellite constellation.
9. The apparatus of claim 8, wherein said first SV is a member of a GPS
constellation and said second SV is a member of a Galileo or a Glonass constellation.
constellation and said second SV is a member of a Galileo or a Glonass constellation.
10. A non-transitory computer-readable storage medium, said storage medium comprising machine-readable instructions stored thereon executable by a computing platform to:
determine timing of a bit edge of a data signal modulating a first navigation signal transmitted by a first space vehicle (SV) and received at a reference location; and determine timing of transitions in an alternating Viterbi encoded signal modulating a second navigation signal, transmitted by a second SV and received at said reference location, based, at least in part, on said timing of said bit edge, wherein the instructions to cause the computing platform to determine said timing of said transitions further comprises instructions to cause the computing platform to associate said timing of said bit edge with said timing of said transitions based, at least in part, on an estimated difference between a first range to said first SV from said reference location and a second range to said second SV from said reference location and on an estimated uncertainty associated with the estimated difference, the estimated uncertainty being based at least in part on an estimated azimuth angle to said first SV from said reference location, and wherein the first SV is a member of a first navigation satellite constellation and the second SV is a member of a second navigation satellite constellation.
determine timing of a bit edge of a data signal modulating a first navigation signal transmitted by a first space vehicle (SV) and received at a reference location; and determine timing of transitions in an alternating Viterbi encoded signal modulating a second navigation signal, transmitted by a second SV and received at said reference location, based, at least in part, on said timing of said bit edge, wherein the instructions to cause the computing platform to determine said timing of said transitions further comprises instructions to cause the computing platform to associate said timing of said bit edge with said timing of said transitions based, at least in part, on an estimated difference between a first range to said first SV from said reference location and a second range to said second SV from said reference location and on an estimated uncertainty associated with the estimated difference, the estimated uncertainty being based at least in part on an estimated azimuth angle to said first SV from said reference location, and wherein the first SV is a member of a first navigation satellite constellation and the second SV is a member of a second navigation satellite constellation.
Applications Claiming Priority (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US83985406P | 2006-08-23 | 2006-08-23 | |
| US60/839,854 | 2006-08-23 | ||
| US11/842,759 | 2007-08-21 | ||
| US11/842,759 US7817084B2 (en) | 2006-08-23 | 2007-08-21 | System and/or method for reducing ambiguities in received SPS signals |
| CA2659229A CA2659229C (en) | 2006-08-23 | 2007-08-23 | System and/or method for reducing ambiguities in received sps signals |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2659229A Division CA2659229C (en) | 2006-08-23 | 2007-08-23 | System and/or method for reducing ambiguities in received sps signals |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2768923A1 CA2768923A1 (en) | 2008-02-28 |
| CA2768923C true CA2768923C (en) | 2014-10-14 |
Family
ID=39092666
Family Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2768930A Active CA2768930C (en) | 2006-08-23 | 2007-08-23 | System and/or method for reducing ambiguities in received sps signals |
| CA2768923A Active CA2768923C (en) | 2006-08-23 | 2007-08-23 | System and/or method for reducing ambiguities in received sps signals |
| CA2659229A Active CA2659229C (en) | 2006-08-23 | 2007-08-23 | System and/or method for reducing ambiguities in received sps signals |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2768930A Active CA2768930C (en) | 2006-08-23 | 2007-08-23 | System and/or method for reducing ambiguities in received sps signals |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2659229A Active CA2659229C (en) | 2006-08-23 | 2007-08-23 | System and/or method for reducing ambiguities in received sps signals |
Country Status (9)
| Country | Link |
|---|---|
| US (4) | US7817084B2 (en) |
| EP (4) | EP2482100B1 (en) |
| JP (3) | JP5535629B2 (en) |
| KR (3) | KR101159569B1 (en) |
| AT (1) | ATE556331T1 (en) |
| BR (1) | BRPI0715739A2 (en) |
| CA (3) | CA2768930C (en) |
| RU (2) | RU2438146C2 (en) |
| WO (1) | WO2008024939A2 (en) |
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2007
- 2007-08-21 US US11/842,759 patent/US7817084B2/en active Active
- 2007-08-23 BR BRPI0715739-8A2A patent/BRPI0715739A2/en not_active IP Right Cessation
- 2007-08-23 EP EP12165708.4A patent/EP2482100B1/en active Active
- 2007-08-23 KR KR1020117007871A patent/KR101159569B1/en active IP Right Grant
- 2007-08-23 KR KR1020117007872A patent/KR101159570B1/en active IP Right Grant
- 2007-08-23 AT AT07841292T patent/ATE556331T1/en active
- 2007-08-23 RU RU2009110147/09A patent/RU2438146C2/en active
- 2007-08-23 EP EP12165703.5A patent/EP2482099B1/en active Active
- 2007-08-23 CA CA2768930A patent/CA2768930C/en active Active
- 2007-08-23 JP JP2009525787A patent/JP5535629B2/en active Active
- 2007-08-23 CA CA2768923A patent/CA2768923C/en active Active
- 2007-08-23 EP EP07841292A patent/EP2062065B1/en active Active
- 2007-08-23 CA CA2659229A patent/CA2659229C/en active Active
- 2007-08-23 EP EP12165704.3A patent/EP2485068B1/en active Active
- 2007-08-23 KR KR1020097004673A patent/KR101102283B1/en active IP Right Grant
- 2007-08-23 WO PCT/US2007/076690 patent/WO2008024939A2/en active Application Filing
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2010
- 2010-09-17 US US12/885,157 patent/US8188915B2/en active Active
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2011
- 2011-08-30 RU RU2011136135/07A patent/RU2490666C2/en active
- 2011-11-17 US US13/299,200 patent/US20120300885A1/en not_active Abandoned
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2012
- 2012-01-10 US US13/347,509 patent/US20120119947A1/en not_active Abandoned
- 2012-05-01 JP JP2012104802A patent/JP5536139B2/en active Active
- 2012-05-01 JP JP2012104801A patent/JP5536138B2/en active Active
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