Global positioning system (GPS) and doppler augmentation (GDAUG) and space location inertial navigation geopositioning system (SPACELINGS)

• US 9,766,339 B2
• Filed: 04/28/2015
• Issued: 09/19/2017
• Est. Priority Date: 05/03/2012
• Status: Active Grant

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Robinson, Ian S., Skidmore, Mark R.
• Primary Examiner(s): LIU, HARRY K
• Application Number:
  US14/698,666
• Publication Number:
  US 20150316655A1
• Time in Patent Office: 875 Days
• Field of Search: 34235725
• CPC Class Codes: G01S 1/02 using radio waves G01S19/00 takes precedence
• CPC Class Codes: G01S 13/74 Systems using reradiation of radio waves, e.g. secondary radar systems; Analogous systems
• CPC Class Codes: G01S 19/05 providing aiding data
• CPC Class Codes: G01S 19/08 providing integrity information, e.g. health of satellites or quality of ephemeris data
• CPC Class Codes: G01S 19/11 wherein the cooperating elements are pseudolites or satellite radio beacon positioning system signal repeaters
• CPC Class Codes: G01S 19/42 Determining position
• CPC Class Codes: G01S 5/0226 Transmitters

Abstract

A global positioning system (GPS) and Doppler augmentation (GDAUG) end receiver (GDER) can include a GDAUG module. The GDAUG module can generate a GDER position using a time of flight (TOF) of a transponded GPS signal and a Doppler shift in a GDAUG satellite (GSAT) signal. The transponded GPS signal sent from a GSAT to the GDER can include a frequency shifted copy of a GPS signal from a GPS satellite to the GSAT. The GSAT signal can include a signal generated by the GSAT to the GDER.

Claims

1. A method for determining a global position of a receiver, the method comprising:

receiving, at the receiver, transponded signals from at least one relay satellite, wherein the relay satellite is configured to receive downlink signals from a high altitude satellite and generate the transponded signals from the downlink signals;

detecting, at the receiver, a first Doppler shift for the transponded signals received from the relay satellite, the first Doppler shift being from the high altitude satellite to the relay satellite;

detecting, at the receiver, a second Doppler shift for the transponded signals received from the relay satellite, the second Doppler shift being from the relay satellite to the receiver;

determining, at the receiver, an aggregate range between the high altitude satellite and the relay satellite using a time of signal flight between the high altitude satellite and the receiver, wherein the aggregate range includes a first range between the high altitude satellite and the relay satellite and a second range between the relay satellite and the receiver; and

determining, at the receiver, the global position of the receiver based on the aggregate range between the high altitude satellite and the relay satellite, the first Doppler shift for the transponded signals and the second Doppler shift for the transponded signals.

2. The method of claim 1, further comprising determining, at the receiver, an ephemeris of the high altitude satellite by despreading the transponded signals received from the relay satellite, wherein the ephemeris of the high altitude satellite is used to determine the aggregate range between the high altitude satellite and the relay satellite and the global position of the receiver.

3. The method of claim 1, further comprising determining, at the receiver, an ephemeris of the relay satellite based on the first Doppler shift from the high altitude satellite to the relay satellite, wherein the ephemeris of the relay satellite is used to determine the aggregate range between the high altitude satellite and the relay satellite and the global position of the receiver.

4. The method of claim 1, wherein the transponded signals received at the receiver from the relay satellite include transponded pseudo-random noise (PRN) signals.

5. The method of claim 1, wherein the transponded signals received at the receiver from the relay satellite include transponded global positioning system (GPS) signals.

6. The method of claim 1, wherein the downlink signals communicated from the high altitude satellite to the relay satellite include two downlink signals on at least two distinct carrier frequencies that are previously known.

7. The method of claim 6, wherein the relay satellite is configured to shift a frequency for each of the two downlink signals and combine the two downlink signals to a common frequency, wherein the common frequency is associated with two transponded signals that are received at the receiver from the relay satellite.

8. The method of claim 1, wherein the transponded signals received at the receiver are double Doppler shifted, wherein the transponded signals includes a sum of the first Doppler shift from the high altitude satellite to the relay satellite and the second Doppler shift from the relay satellite to the receiver.

9. The method of claim 1, wherein the relay satellite has a line-of-sight (LOS) to the high altitude satellite.

10. The method of claim 1, wherein the relay satellite is a CUBESAT or a low Earth orbit (LEO) satellite, wherein the CUBESAT weighs less than 5 kilograms.

11. The method of claim 1, wherein the high altitude satellite is associated with an altitude that exceeds an altitude of at least one of:

a global positioning system (GPS) satellite in a medium Earth orbit (MEO), a geostationary Earth orbit (GEO) or a high Earth orbit (HEO).

12. A receiver operable to determine a global position, the receiver comprising:

a transponded signal receiver operable to receive transponded pseudo-random noise (PRN) signals from at least one relay satellite, wherein the relay satellite is configured to receive downlink PRN signals from a high altitude satellite and generate the transponded PRN signals from the downlink PRN signals;

a Doppler shift module operable to;

detect a first Doppler shift for the transponded PRN signals received from the relay satellite, the first Doppler shift being from the high altitude satellite to the relay satellite;

detect a second Doppler shift for the transponded PRN signals received from the relay satellite, the second Doppler shift being from the relay satellite to the receiver;

a range estimator operable to determine an aggregate range between the high altitude satellite and the relay satellite based on a time of signal flight between the high altitude satellite and the receiver, wherein the aggregate range includes a first range between the high altitude satellite and the relay satellite and a second range between the relay satellite and the receiver; and

a receiver location estimator operable to determine the global position of the receiver based on the aggregate range between the high altitude satellite and the relay satellite, the first Doppler shift for the transponded PRN signals and the second Doppler shift for the transponded PRN signals.

13. The receiver of claim 12, further comprising a signal despreader operable to despread the transponded PRN signals received from the relay satellite.

14. The receiver of claim 13, further comprising an ephemeris estimator operable to:

determine an ephemeris of the high altitude satellite based on the transponded PRN signals that are despreaded; and

determine an ephemeris of the relay satellite based on the first Doppler shift from the high altitude satellite to the relay satellite,

wherein the ephemeris of the high altitude satellite and the ephemeris of the relay satellite are used to determine the aggregate range between the high altitude satellite and the relay satellite and the global position of the receiver.

15. The receiver of claim 12, wherein the transponded PRN signals received at the receiver are double Doppler shifted, wherein the transponded PRN signals includes a sum of the first Doppler shift from the high altitude satellite to the relay satellite and the second Doppler shift from the relay satellite to the receiver.

16. A relay satellite operable to facilitate position determination for a receiver, the relay satellite comprising:

a signal receiver operable to receive downlink signals from a high altitude satellite, wherein the downlink signals received from the high altitude satellite include two downlink signals on at least two distinct carrier frequencies that are previously known;

a frequency shifter operable to shift a frequency for the downlink signals and combine the downlink signals to a common frequency, thereby generating transponded signals; and

a transponded signal transmitter operable to send the transponded signals to the receiver,

wherein the receiver is operable to determine a global position of the receiver based on a first Doppler shift of the transponded signals from the high altitude satellite to the relay satellite, a second Doppler shift of the transponded signals from the relay satellite to the receiver, and an aggregate range between the receiver and the high altitude satellite.

17. The relay satellite claim 16, wherein the transponded signals include transponded pseudo-random noise (PRN) signals or transponded global positioning system (GPS) signals.

18. The relay satellite claim 16, further comprising an amplifier operable to amplify at least one of the downlink signals received from the high altitude satellite or the transponded signals to be sent to the receiver.

19. The relay satellite claim 16, wherein the relay satellite has a line-of-sight (LOS) to the high altitude satellite.

20. The relay satellite claim 16, wherein the relay satellite is a low Earth orbit (LEO) satellite.

21. A method for determining a global position of a receiver, the method comprising:

generating, at a ground site, at least one uplink pseudo-random noise (PRN) signals on a specified carrier frequency;

receiving, at one or more high altitude satellites, the at least one PRN signal as transmitted by a transmitter at the ground site;

generating, at the high altitude satellite, one or more transponded PRN signals on a different carrier frequency;

transmitting, from the high altitude satellite, the transponded PRN signals to a space location inertial navigation geopositioning system (SLS) satellite;

generating, at the SLS satellite, transponded signals on a different carrier frequency; and

transmitting the transponded signals on the different carrier frequency to at least one of a ground station or an end ground receiver.

22. The method of claim 21, further comprising transmitting, from the high altitude satellite, the downlink PRN signals to the SLS satellite.

23. The method of claim 21, further comprising receiving, at the ground site, signals from one or more low Earth orbit (LEO) or SLS satellites, and determining the ephemeris of the LEO or SLS satellites.

24. The method of claim 23, further comprising including at least one of the ephemeris information of the LEO or SLS satellites, the location of the high altitude satellite and the location of the ground site in the uplinked PRN signal from the ground site.

25. The method of claim 21, wherein the high altitude satellite is associated with an altitude that exceeds an altitude of at least one of:

a global positioning system (GPS) satellite in a medium Earth orbit (MEO), a geostationary Earth orbit (GEO) or a high Earth orbit (HEO).

26. The method of claim 21, wherein the uplink PRN signal generated at the ground site is generated on a carrier frequency different from H1 or H2.

27. The method of claim 21, further comprising estimating the ephemeris of the SLS satellite using the double Doppler shift of the SLS transponded signal.

28. The method of claim 21, further comprising encoding in the uplink PRN signal at least one of the ephemeris date of the SLS satellite, the ephemeris of the high altitude satellite and the location of the ground site.

29. The method of claim 28, further comprising computing, at the end ground receiver and using the PRN signal, a super-duper range including a signal path from the ground site to the high altitude satellite to the SLS satellite to the end ground receiver.

30. The method of claim 29, further comprising extracting a component of the Doppler shift from the SLS satellite to the end ground receiver using known transponder or frequency shifts and the ephemeris of the SLS satellite and the high altitude satellite.

31. The method of claim 21, further comprising estimating a position of the end ground receiver using, at the end ground receiver, a range and Doppler time history from the SLS.