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A system for navigation and tracking may include an inertial navigation system adapted to generate a replica GNSS signal and a global navigation satellite system. The global navigation satellite system may include a module to digitize a GNSS signal received from a constellation of global navigation

A system for navigation and tracking may include an inertial navigation system adapted to generate a replica GNSS signal and a global navigation satellite system. The global navigation satellite system may include a module to digitize a GNSS signal received from a constellation of global navigation satellites. A correlator receives the digitized GNSS signal and the replica GNSS signal. The correlator correlates the digitized GNSS signal to the replica GNSS signal to generate a correlated GNSS signal. A coherent integration module coherently integrates the correlated GNSS signal to generate an integrated signal having a predetermined rate. A filter receives the integrated signal and generates a data signal for navigation and tracking. An output device may present the navigation and tracking information based on the data signal, or the navigation and tracking information may be used to provide guidance for a vehicle or may be used to track a target.

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1. A system for navigation and tracking, comprising: an inertial navigation system adapted to generate a replica GNSS signal;a global navigation satellite system, wherein the global navigation satellite system comprises: a module to digitize a GNSS signal received from a constellation of global navi

1. A system for navigation and tracking, comprising: an inertial navigation system adapted to generate a replica GNSS signal;a global navigation satellite system, wherein the global navigation satellite system comprises: a module to digitize a GNSS signal received from a constellation of global navigation satellites;a correlator to receive the digitized received GNSS signal and to receive the replica GNSS signal from the inertial navigation system, wherein the correlator correlates the received GNSS signal to the replica GNSS signal to generate a correlated GNSS signal;a coherent integration module to coherently integrate the correlated GNSS signal from the correlator to generate an integrated signal having a predetermined rate, wherein the predetermined rate is a function of at least receiver clock performance of the inertial navigation system and the global navigation satellite system;a filter to receive the integrated signal and to generate a data signal for navigation and tracking; andan output device to present navigation and tracking information based on the data signal, to provide guidance for a vehicle or to track a target. 2. The system of claim 1, further comprising: a switching unit to alternately connect and disconnect the coherent integration module to the filter; anda non-linear transformation module to receive the integrated signal from the coherent integration module and to generate a discriminated signal for code phase error and carrier phase error, wherein the discriminated signal for code phase error and carrier phase error is transmitted to the filter to generate the data signal for navigation and tracking. 3. The system of claim 2, wherein the non-linear transformation module comprises a non-linear full range discriminator to generate the discriminated signal for code phase error and carrier phase error. 4. The system of claim 2, wherein the non-linear transformation module is adapted to generate a measured, averaged pseudo-range error and carrier phase error signal from the integrated signal from the coherent integration module. 5. The system of claim 2, wherein the non-linear transformation module comprises a non-linear full range discriminator to perform linearization of the pseudo-range error and carrier phase error, the linearization permitting the filter to operate in a substantially larger dynamic range between about +180 degrees and about −180 degrees of code phase or carrier phase error during operation, wherein the substantially larger dynamic range provides a substantially maximum anti-jamming capability of the system. 6. The system of claim 1, wherein the correlator receives I and Q signals of the GNSS signal and I and Q signals of the replica GNSS signal, wherein correlated I and Q signal results of the GNSS signal and the replica GNSS signal from the correlator indicate a tracking accuracy between the replica GNSS signal and the received GNSS signal. 7. The system of claim 6, wherein the filter comprises a Kalman Filter, and wherein the coherent integration module accumulates and averages the correlated GNSS signals to permit the Kalman Filter to operate below a rate of about 50 Hz. 8. The system of claim 6, wherein the filter comprises a Kalman Filter, and wherein the coherent integration module accumulates and averages the correlated GNSS signals to permit the Kalman Filter to operate in a range between about 0.1 Hz and about 1.0 Hz. 9. The system of claim 6, wherein the coherent integration module is adapted to accumulate and average each of the I and Q signals to provide integrated signals and to sample the integrated signals at the predetermined rate, wherein the predetermined rate permits the filter to operate at a substantially reduced rate corresponding substantially to the predetermined rate. 10. The system of 1, wherein the inertial navigation system comprises: an inertial measurement unit to perform measurements of movement of the vehicle associated with the system;an inertial navigation module to generate at least a position estimate and a velocity estimate of the vehicle from the measurements by the inertial measurement unit; anda code and carrier tracking loop steering module, wherein the code and carrier tracking loop steering module is adapted to predict at least a GNSS signal pseudo-range, a pseudo-range rate and a carrier phase using the position estimate and the velocity estimate from the inertial navigation module, and a time estimate, the GNSS signal pseudo-range, pseudo-range rate and the carrier phase are used to control generation of the of the replica GNSS signal so that the replica GNSS signal substantially matches the received digitized GNSS signal. 11. A method for navigation and tracking, comprising: generating a replica GNSS signal;receiving a GNSS signal from a constellation of global navigation satellites;digitizing the received GNSS signal;correlating the replica GNSS signal and the digitized received GNSS signal to generate a correlated GNSS signal;coherently integrating the correlated GNSS signal to generate an integrated signal having a predetermined rate, wherein the predetermined rate is a function of at least receiver clock performance of an inertial navigation system and global navigation satellite system;generating data for navigation and tracking from the integrated signal; andperforming one of presenting the navigation and tracking data, guiding a vehicle or tracking a target. 12. The method of claim 11, further comprising: selecting one of: to coherently linearize the integrated signal or to not coherently linearize the integrated signal; andgenerating a discriminated signal for code phase error and carrier phase error in response to selecting to coherently linearize the integrated signal. 13. The method of claim 12, further comprising generating a measured, averaged pseudo-range error and carrier phase error signal from the integrated signal in response to selecting to coherently linearize the integrated signal. 14. The method of claim 12, wherein generating the data for navigation and tracking comprises performing a linearization of the pseudo-range error and carrier phase error, the linearization permitting a Kalman Filter to operate in a substantially larger dynamic range between about +180 degrees and about −180 degrees of code phase or carrier phase error during operation, wherein the substantially larger dynamic range provides a substantially maximum anti jamming capability. 15. The method of claim 11, wherein correlating the replica GNSS signal and the digitized received GNSS signal comprises correlating I and Q signals of the digitized received GNSS signal and I and Q signals of the replica GNSS signal, wherein correlated I and Q signal results of the received GNSS signal and the replica GNSS signal indicate a tracking accuracy between the replica GNSS signal and the received GNSS signal. 16. The method of claim 15, wherein, a Kalman Filter generates the data for navigation and tracking from the integrated signal, and wherein coherently integrating the correlated signals comprises accumulating and averaging the correlated GNSS signals to permit the Kalman to operate below a rate of about 50 Hz. 17. The method of claim 15, wherein a Kalman Filter generates the data for navigation and tracking from the integrated signal, and wherein coherently integrating the correlated signals comprises accumulating and averaging the correlated GNSS signals to permit the Kalman to operate in a range between about 0.1 Hz and about 1.0 Hz. 18. The method of claim 15, wherein a Kalman Filter generates the data for navigation and tracking from the integrated signal, and wherein coherently integrating the correlated GNSS signal comprises: accumulating and averaging each of the I and Q signals to provide integrated signals; andsampling the integrated signals at the predetermined rate, wherein the predetermined rate permits the Kalman Filter to operate at a substantially reduced rate corresponding substantially to the predetermined rate. 19. The method of claim 11, wherein generating the replica GNSS signal comprises: sensing movement of the vehicle;generating at least a position estimate and a velocity estimate of the vehicle from the sensed movement of the vehicle;predicting at least a GNSS signal pseudo-range, a pseudo-range rate and a carrier phase using the position estimate and the velocity estimate, and a time estimate; andusing the GNSS signal pseudo-range, pseudo-range rate and the carrier phase to control generation of the of the replica GNSS signal so that the replica GNSS signal substantially matches the digitized received GNSS signal. 20. The method of claim 11, further comprising: accumulating I and Q signals embodying navigation data by buffering the navigation data;performing a discrete Fourier transformation (DFT) on the buffered navigation data;searching for a maximum signal power from results of the discrete Fourier transformation, the maximum signal power corresponding to an integrated I and Q signal; andusing a corresponding frequency error where the maximum signal power is achieved as a measurement to the Kalman Filter. 21. A computer program product for navigation and tracking, the computer program product comprising: a computer readable storage medium having computer readable program code embodied therewith, the computer readable program code comprising: computer readable program code configured to generate a replica GNSS signal;computer readable program code configured to receiving a GNSS signal from a constellation of global navigation satellites;computer readable program code configured to digitize the received GNSS signal;computer readable program code configured to correlate the replica GNSS signal and the digitized received GNSS signal to generate a correlated GNSS signal;computer readable program code configured to coherently integrate the correlated GNSS signal to generate an integrated signal having a predetermined rate, wherein the predetermined rate is a function of at least receiver clock performance of an inertial navigation system and global navigation satellite system;computer readable program code configured to generate data for navigation and tracking from the integrated signal; andcomputer readable program code configured to perform one of presenting the navigation and tracking data, guiding a vehicle or tracking a target.