Precise Absolute Time Transfer From A Satellite System

• US 20110148701A1
• Filed: 07/09/2010
• Published: 06/23/2011
• Est. Priority Date: 05/30/2008
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Ferrell, Barton G., Gutt, Gregory M., Whelan, David A., Brumley, Robert W., Cohen, Clark E.
• Granted Patent: US 8,179,312 B2
• Time in Patent Office: Days
• US Class Current: 342/357.64
• CPC Class Codes: G01S 19/05 providing aiding data
• CPC Class Codes: G01S 19/21 Interference related issues ; Issues related to cross-correlation, spoofing or other methods of denial of service
• CPC Class Codes: G01S 19/23 Testing, monitoring, correcting or calibrating of receiver elements
• CPC Class Codes: G01S 19/256 relating to timing, e.g. time of week, code phase, timing offset

Abstract

Systems and methods according to one or more embodiments are provided for obtaining a precise absolute time using a satellite system. The precise absolute time may be used, for example, as an aid for positioning systems including navigation in attenuated or jammed environments. A method of obtaining precise absolute time transfer from a satellite according to an embodiment comprises: receiving a precision time signal from a satellite, wherein the precision time signal comprises a periodic repeating code; determining a timing phase of the code; receiving additional aiding information; and using the timing phase and the additional aiding information to determine a precise absolute time.

Claims

1. A method of performing navigation in attenuated or jammed environments, the method comprising:

detecting a frame structure of a first signal received from a first satellite;

aligning a clock of a receiver unit to the detected frame structure;

generating multiple time estimates respectively separated according to the frame structure, wherein at least one of the time estimates is aligned to a second signal of a second satellite;

providing the time estimates to system correlators of the receiver unit;

aligning the system correlators according to the time estimates; and

identifying the at least one of the time estimates that is aligned to the second signal of the second satellite, wherein the at least one of the time estimates provides aiding information to the receiver unit.

2. The method of claim 1, further comprising using the at least one time estimate to detect the second signal of the second satellite, wherein the second signal of the second satellite is a positioning signal.

3. The method of claim 1, wherein the frame structure comprises a plurality of frames repeated in a sequence.

4. The method of claim 3, wherein the frame structure is an L band frame structure.

5. The method of claim 3, wherein each frame comprises a pseudorandom code unique within the sequence.

6. The method of claim 5, wherein the time estimates comprise no more than approximately 100 time estimates corresponding to approximately 100 of the frames.

7. The method of claim 1, wherein the first satellite is a Low Earth Orbit (LEO) satellite.

8. The method of claim 7, wherein the LEO satellite is an Iridium satellite.

9. The method of claim 1, wherein the second satellite is a global positioning system (GPS) satellite.

10. The method of claim 1, wherein the receiver unit is an iGPS receiver.

11. A receiver unit adapted for use in attenuated or jammed environments comprising:

an antenna adapted to receive a first signal from a first satellite and to receive a second signal from a second satellite;

a processor; and

a memory adapted to store a plurality of computer readable instructions which when executed by the processor are adapted to case the receiver unit to;

detect a frame structure of the first signal of the first satellite;

align a clock of the receiver unit to the detected frame structure;

generate multiple time estimates respectively separated according the frame structure, wherein at least one of the time estimates is aligned to the second signal of the second satellite;

align system correlators according to the time estimates; and

identify the at least one of the time estimates that is aligned to the second signal of the second satellite, wherein the at least one of the time estimates provides aiding information to the receiver unit.

12. The receiver unit of claim 11, wherein the computer readable instructions when executed by the processor are adapted to cause the receiver unit to use the at least one time estimate to detect the second signal of the second satellite, wherein the second signal of the second satellite is a positioning signal.

13. The receiver unit of claim 11, wherein the frame structure comprises a plurality of frames repeated in a sequence.

14. The receiver unit of claim 13, wherein the frame structure is an L band frame structure.

15. The receiver unit of claim 13, wherein each frame comprises a pseudorandom code unique within the sequence.

16. The receiver unit of claim 15, wherein the time estimates comprise no more than approximately 100 time estimates corresponding to approximately 100 of the frames.

17. The receiver unit of claim 11, wherein the first satellite is a Low Earth Orbit (LEO) satellite.

18. The receiver unit of claim 17, wherein the LEO satellite is an Iridium satellite.

19. The receiver unit of claim 11, wherein the second satellite is a global positioning system (GPS) satellite.

20. The receiver unit of claim 11, wherein the receiver unit is an iGPS receiver.