System and method for geo-locating a receiver with reduced power consumption

• US 20100302099A1
• Filed: 08/16/2010
• Published: 12/02/2010
• Est. Priority Date: 02/13/2008
• Status: Active Grant

• Current Assignee: the united states of america as represented by the secretary of the navy
• Original Assignee: the united states of america as represented by the secretary of the navy
• Inventors: Williams, Brian T., Hunt, Barry R., Fronk, Alan, Buck, Heidi L., Fleizach, Gregory, Fong, Matthew, Grossnickle, Peter C., Nicholson, Matthew
• Granted Patent: US 8,009,086 B2
• Time in Patent Office: Days
• US Class Current: 342/357.46
• CPC Class Codes: G01S 19/09 providing processing capability normally carried out by the receiver
• CPC Class Codes: G01S 19/30 code related G01S19/246 takes precedence
• CPC Class Codes: G01S 19/42 Determining position

Abstract

A system and process for the geo-location of an asset given no a priori knowledge regarding time and location of the asset with minimized power consumption is disclosed. In the preferred embodiment, the system is accurate to about 30 meters CEP (50% circular error probable) using just a short segment, e.g., 100-200 ms, of digitized GPS L1 signal data.

Claims

1. A system for determining a position estimate for a remote asset comprising:

at least one receiver located on the remote asset for collecting GPS signal information from multiple space vehicles and generating a set of signal delays for each of the multiple space vehicles;

at least one transmitter located on the remote asset for transmitting the set of signal delays;

a ground station including a geo-location processor and a navigation database for receiving the set of signal delays and computing a position estimate for the remote asset.

2. The system according to claim 1, wherein the GPS signal information is a transmitted from each of the multiple space vehicles at a signal frequency of 1575.42 MHz and is collected by the at least one receiver for a period of approximately 100-200 ms.

3. The system according to claim 1, wherein the length of the collected GPS signal information is approximately 160 ms.

4. The system according to claim 1, wherein position is estimated to approximately 30 meters CEP (50% circular error probable).

5. A method for determining a position estimate for a remote asset comprising:

collecting GPS signal information from multiple space vehicles at the remote asset, the GPS signal information being transmitted from each of the multiple space vehicles at a known signal frequency;

extracting a set of signal delays for each of the multiple space vehicles;

transmitting the set of signal delays and identification information for each of the multiple space vehicles to a ground station;

processing the set of signal delays for each of the multiple space vehicles;

retrieving information from a navigation database; and

computing a position estimate for the remote asset using the set of signal delays, the information from the navigation database, and an estimated time of data collection at the remote asset.

6. The method according to claim 5, wherein for each of the multiple space vehicles extracting a set of signal delays comprises:

acquiring course delay and measured frequency, wherein coarse delay is the number of samples to the next first symbol, symbol=1 ms, 1023 chip, GPS C/A code epoch, and measured frequency is the frequency offset from the known signal frequency; and

estimating the signal delay for each of the multiple space vehicles.

7. The method according to claim 6, wherein estimating the signal delay for each of the multiple space vehicles includes:

determining the number of symbols to a first bit boundary; and

estimating fine delay.

8. The method according to claim 6, further comprising filtering the set of extracted signal delays prior to transmitting to the ground station.

9. The method according to claim 8, wherein filtering includes determining for a maximum five space vehicles, the signal delay information that is to be transmitted to the ground station using at least two error metrics.

10. The method according to claim 9, wherein the at least two error metrics are delay error and signal-to-noise ratios and the method further comprises:

calculating a ratio of the delay error for each space vehicle to the median delay error across all of the space vehicles for each space vehicle;

identifying the space vehicles having delay error ratios less than 2.5;

listing the space vehicles having ratios less than 2.5 in order of descending signal-to-noise ratio; and

selecting at most five space vehicles having the highest signal-to-noise ratio with delay error ration less than 2.5.

11. The method according to claim 10, further comprising assembling a binary message including the extracted signal delays for at most five space vehicles.

12. The method according to claim 11, wherein assembling the binary message includes:

normalizing the extracted signal delay information for the at most five space vehicles to that of the space vehicle having the highest signal-to-noise ratio; and

reducing the extracted signal delay information to a predetermined number of bits.

13. The method according to claim 12, wherein the predetermined number of bits is 21.

14. The method according to claim 10, wherein processing the set of signal delays for each of the multiple space vehicles comprises:

reading the identification information for each of the selected space vehicles;

reading the time of arrival of the signal delays at the ground station;

reading the time delay to first bit boundary for each of the selected space vehicles;

adding a known constant to each of the time delays to create a pseudorange for each time delay;

calculating the GPS data collection time at the remote asset.

15. The method according to claim 14, wherein retrieving information from a navigation database includes retrieving ephemeris data for the selected space vehicles.

16. The method according to claim 15, wherein computing a position estimate comprises:

discarding the pseudorange if abs(min-mix)>

19 ms, leaving remaining pseudoranges;

calculating M possible position estimates using remaining pseudoranges;

comparing an altitude for each of the M possible solutions to a predetermined altitude range and selecting the solution that falls within the predetermined altitude range as the estimated position of the remote asset.

17. The method according to claim 16, wherein if more than one of M possible solutions fall within the predetermined altitude range, selecting the estimate position of the remote asset using prior position data.

18. The method according to claim 14, wherein the known constant is 70 ms.

19. The method according to claim 16, wherein calculating M possible position estimates using any remaining pseudoranges further includes:

iteratively inputting time of collection of GPS signal information at the remote asset for each space vehicle associated with each of the remaining pseudoranges into a process routine;

iteratively inputting the remaining pseudoranges into the process routine, wherein the pseudorange input includes the pseudoranges and associated space vehicle identification information; and

iteratively inputting ephemeris data associated with each space vehicle.