VECTOR TRACKING LOOP OPERABILITY THROUGH OSCILLATOR MICRO-JUMP EVENT

• US 20150301188A1
• Filed: 04/16/2014
• Published: 10/22/2015
• Est. Priority Date: 04/16/2014
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Broderick, James B., Vallot, Lawrence Charles
• Granted Patent: US 9,476,989 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: G01S 19/23 Testing, monitoring, correcting or calibrating of receiver elements
• CPC Class Codes: G01S 19/47 the supplementary measurement being an inertial measurement, e.g. tightly coupled inertial

Abstract

A navigation system comprises a GNSS receiver that receives GNSS signals on multiple tracking channels, an INS that generates inertial data, and a processor. A micro jump detection and correction module comprises an oscillator micro jump detector that monitors estimates of C/N₀ in all tracking channels, and detects a micro-jump event when there is an abrupt decrease of C/N₀ in all tracking channels. An offsets module defines a plurality of carrier NCO command offsets to search over signal Dopplers in all available tracking channels after the micro jump event is detected, and sends the carrier NCO command offsets to the GNSS receiver to be added to nominal carrier NCO commands. The micro jump detector selects a tracking channel with the highest C/N₀ after carrier NCO command offsets are added to nominal carrier NCO commands, computes corrections for clock error estimates, and sends the corrections for the clock error estimates to a GNSS/inertial Kalman filter.

Claims

1. A navigation system, comprising:

a global navigation satellite system (GNSS) receiver configured to receive multiple GNSS signals on a plurality of signal tracking channels;

an inertial navigation system (INS) configured to generate inertial data;

a processor in operative communication with the GNSS receiver and the INS; and

a micro jump detection and correction module in operative communication with the processor and comprising;

an oscillator micro jump detector configured to;

monitor estimates of carrier to noise density (C/N₀) ratios in all of the signal tracking channels; and

detect onset of a micro jump event when there is an abrupt decrease in the C/N₀ ratios in all of the signal tracking channels;

a carrier numerically controlled oscillator (NCO) command offsets module in operative communication with the micro jump detector and configured to;

define a plurality of carrier NCO command offsets to search over signal Dopplers in all available signal tracking channels after the micro jump event is detected; and

send the carrier NCO command offsets to the GNSS receiver to be added to nominal carrier NCO commands;

wherein the micro jump detector is further configured to;

select a signal tracking channel with the highest C/N₀ ratio after the carrier NCO command offsets are added to the nominal carrier NCO commands;

compute corrections for clock error estimates; and

send the corrections for the clock error estimates to a GNSS/inertial Kalman filter.

2. The navigation system of claim 1, wherein the GNSS receiver, the INS, and the processor are configured in an ultra-tightly-coupled (UTC) navigation and signal tracking loop.

3. The navigation system of claim 2, wherein the GNSS receiver comprises:

a correlators module configured to receive downconverted and sampled GNSS signals; and

a code and carrier replica generator configured to output satellite signal replicas to the correlators module;

wherein the correlators module compares each generated signal replica with a respective downconverted signal, and based on the comparison, outputs inphase (I) and quadrature phase (Q) data for multiple signal tracking channels and multiple code delay taps per channel.

4. The navigation system of claim 3, wherein the I and Q data is supplied to the Kalman filter and a C/N₀ estimator.

5. The navigation system of claim 4, wherein the Kalman filter sends clock error estimates to an NCO command generator, and sends navigation reset data to the INS.

6. The navigation system of claim 5, wherein the C/N₀ estimator outputs the C/N₀ ratios for all of the signal tracking channels to the micro jump detector and to the Kalman filter.

7. The navigation system of claim 6, wherein the NCO command generator computes NCO commands based on the clock error estimates from the Kalman filter and an inertial navigation solution generated by the INS.

8. The navigation system of claim 6, wherein the carrier NCO command offsets are each assigned to respective UTC tracking channels, with each of the carrier NCO command offsets being a unique integer multiple of a common frequency offset quanta.

9. The navigation system of claim 6, wherein the corrections for the clock error estimates comprise corrections for clock frequency and clock phase errors in a state vector of the Kalman filter.

10. A method for micro jump detection and resolution, the method comprising:

monitoring estimates of carrier to noise density (C/N₀) ratios in a plurality of signal tracking channels in a global navigation satellite system (GNSS) receiver that is integrated with an inertial navigation system (INS);

determining whether any previous C/N₀ ratio is greater than or equal to an upper threshold and whether all current C/N₀ ratios are less than a lower threshold;

detecting onset of an oscillator micro jump event in the GNSS receiver when any previous C/N₀ ratio is greater than or equal to the upper threshold and all current C/N₀ ratios are less than a lower threshold;

assigning all available signal tracking channels different frequency command offsets to search over signal Dopplers in all available signal tracking channels after the micro jump event is detected;

adding the frequency command offsets with nominal carrier commands in the GNSS receiver;

selecting a signal tracking channel with the highest C/N₀ ratio after the frequency command offsets are added to the nominal carrier commands;

determining whether the highest C/N₀ ratio is greater than or equal to the upper threshold;

declaring the micro-jump event resolved when the highest C/N₀ ratio is greater than or equal to the upper threshold;

computing corrections for clock error estimates after resolution of the micro-jump event; and

sending the corrections for the clock error estimates to a GNSS/inertial Kalman filter.

11. The method of claim 10, wherein the GNSS receiver and the INS are configured in an ultra-tightly-coupled (UTC) navigation and signal tracking loop.

12. The method of claim 11, wherein after the micro jump event is detected, an unresolved micro jump flag is set to true, and an onset time of the micro-jump event is saved.

13. The method of claim 12, wherein the frequency command offsets are each assigned to respective UTC tracking channels, with each of the frequency command offsets being a unique integer multiple of a frequency offset quanta.

14. The method of claim 12, wherein after resolution of the micro jump event, the unresolved micro jump flag is set to false.

15. The method of claim 14, wherein the corrections for the clock error estimates comprise corrections for clock frequency and clock phase errors in a state vector of the Kalman filter.

16. The method of claim 13, wherein if the highest C/N₀ ratio is not greater than or equal to the upper threshold, the unresolved micro jump flag remains set as true, and a determination is made whether a pre-defined maximum time limit for the duration of the unresolved micro jump has been reached or exceeded.

17. The method of claim 16, wherein if the maximum time limit for the duration of the unresolved micro jump has been reached or exceeded, all of the signal tracking channels are released from UTC control.

18. A non-transitory computer readable medium including instructions executable by a processor to perform a method for micro jump detection and resolution, the method comprising:

monitoring estimates of carrier to noise density (C/N₀) ratios in a plurality of signal tracking channels in a global navigation satellite system (GNSS) receiver that is integrated with an inertial navigation system (INS);

detecting onset of an oscillator micro jump event in the GNSS receiver when any previous C/N₀ ratio is greater than or equal to an upper threshold and all current C/N₀ ratios are less than a lower threshold;

assigning all available signal tracking channels different frequency command offsets to search over signal Dopplers in all available signal tracking channels after the micro jump event is detected;

adding the frequency command offsets with nominal carrier commands in the GNSS receiver;

selecting a signal tracking channel with the highest C/N₀ ratio after the frequency command offsets are added to the nominal carrier commands;

declaring the micro-jump event resolved when the highest C/N₀ ratio is greater than or equal to the upper threshold;

computing corrections for clock error estimates after resolution of the micro-jump event; and

sending the corrections for the clock error estimates to a GNSS/inertial Kalman filter.

19. The non-transitory computer readable medium of claim 19, wherein the GNSS receiver and the INS are configured in an ultra-tightly-coupled (UTC) navigation and signal tracking loop.

20. The non-transitory computer readable medium of claim 19, wherein the frequency command offsets are each assigned to respective UTC tracking channels, with each of the frequency command offsets being a unique integer multiple of a frequency offset quanta.