Rockwell Collins, Inc.

Rockwell International Corporation

Patrick Y Hwang

Gary A McGraw

David A Anderson

Vladislav Gavrilets

James H Doty

Bernard A Schnaufer

Joseph M Kelly

R Grover Brown

Robert J Frank

Douglas A Bell

Shih-Yih Young

Scott J F Zogg

Guolin Peng

Gina M Reyes

Juergen M Bruckner

Paul J Ronan

Brent Disselkoen

Karl Ulmer

Jason H Timmerman

A system detects slowly diverging navigational signals by updating the current location from purely internal navigational aids for a period of time. The updated location compared to a continuously corrected current location; if the comparison indicates a deviation outside an expected boundary threshold, the external source is excluded from further measurements. Multiple monitoring elements may be staggered such that one or more monitoring elements are always sequestered for future comparisons. The multiple monitoring elements may monitor different external sources with different weights to identify a specific faulty external source.

Staggered examination of non-trusted receiver information

Systems and methods for navigation of a vehicle use a processing system. The systems and methods can allow an aircraft to take-off in low visibility conditions. The processing system includes a cross tracker, an error processor and an error estimator. The cross tracker is configured to determine a cross track deviation using a hybrid positon and runway heading data. The error processor is configured to determine the hybrid positon from inertial reference system data and corrected error data, and the error estimator is configured to provide the corrected error data using estimates derived from delta range data from a global navigation satellite system receiver.

Guidance system and method for low visibility takeoff

Systems and methods for navigation of a vehicle may carry out one or more operations including, but not limited to: obtaining coordinates of a vector connecting two points in space using carrier phase measurements from global navigation system satellites (GNSS); setting the vector as an intended path of a vehicle; storing carrier phase signals from a GNSS receiver received at a first position of the vehicle; receiving carrier phase signals from a GNSS receiver at a second position of the vehicle; and determining a position of the vehicle relative to the intended path from one or more carrier phase signals received at the second position and one or more stored carrier phase signals received at the first position.

GPS carrier-phase based relative navigation

Systems and related methods for simultaneous high precision synchronization and syntonization of multiple sensors or clocks utilize a precision estimator that receives clock signals and time mark signals from both sensors (a reference sensor and a clock to be measured against the reference sensor). A precision time and frequency estimator determines a time offset, frequency offset, and phase offset of the measured sensor relative to the reference sensor. Associated systems can additionally determine the propagation delay between two remote subsystems connected by a communications channel. The communications channel may be a bidirectional duplexed or multiplexed channel allowing for mutual exchange of timing information along a single non-dedicated cable between sensors. Sensors may be synchronized to within 10 ps of each other without the need for THz clocks or fiber-optic cabling.

Picosecond clock synchronization technique for communication and navigation platform equipment

A geo-registration system with a camera receives an image of a scene, identifies features in the image, and computes vectors for each feature based on the known location and orientation of the camera. The system then compares the computed vectors to vectors associated with the same features identified in prior images. The geo-registration system then uses stochastic kriging techniques to create a geo-registration model based on the vectors.

Real-time image geo-registration processing

A system and method are disclosed for autonomous authentication of a received signal based on characteristics of the signal. The method receives, acquires and tracks a signal to first determine if a carrier clock phase variable associated with the signal meets a phase consistency threshold. If so, the signal is labeled authentic and configured for output to a positioning system. Second and optionally, the system may determine if a data set measurement associated with a unique satellite identification of the signal meets a data set threshold. If not, the signal is labeled as inconsistent and discarded. The system and method continuously monitors the signal for consistency as well as authenticity based on the data set threshold and the phase consistency threshold. Should any tracked signal fall below either threshold, the signal is discarded from the possible positioning solution.

GNSS receiver autonomous signal authentication using signal stability analysis system and related method

A method for providing collaborative PNT for a plurality of nodes in a distributed sensing system is disclosed. The method may include receiving carrier phase and pseudorange measurements from a first node and a second node of the plurality of nodes; providing a process model for each node, where the process model for each node is configured for modeling error characteristics associated with that node; determining an error covariance between the first node and the second node; and estimating a PNT solution for the first node and a PNT solution for the second node based on: the carrier phase and pseudorange measurements received from the first node, the carrier phase and pseudorange measurements received from the second node, the process model for the first node, the process model for the second node, and the error covariance between the first node and the second node.

Collaborative positioning, navigation and timing

A navigation system/solution, suitable for use in a GPS-denied environment, may be implemented via a node, the node being mounted on-board a vehicle, such as a tactical aircraft. The system/solution allows for a single component of the node to obtain/determine a bearing measurement (via an orientation transfer scheme) and a range measurement (via a round trip timing scheme) based upon signals transmitted between the node and a second node, and further allows for the bearing and range measurements to be received and processed by a navigation processor of the node for determining a location of the node.

Tactical relative navigation using orientation transfer and ranging

The present invention is a geolocation system for providing coordinated sensing and precision geolocation of a target emitter. The system may include a Quint Networking Technology (QNT) subsystem which may be configured receiving, detecting and identifying a target emitter signal. The QNT subsystem may be further configured for extracting a carrier phase of the signal. The system may further include a Real Time Kinematic Global Positioning System (RTK GPS) subsystem for determining a position of the geolocation system relative to a position of a second geolocation system. Further, the system may be configured for communicating with the second geolocation system via a QNT communication data link for: determining a QNT time difference via signal carrier phase differencing for calculating a time difference between the geolocation systems and geolocating the target emitter based on both the relative position information of the geolocation systems and the calculated time difference between the geolocation systems.

Coordinated sensing and precision geolocation of target emitter

The present invention is a targeting system for tracking angle changes from a reference azimuth. The system includes a mount. The mount may be configured for supporting a sighting scope. The system further includes an angle encoder which is integrated within the mount and is configured for tracking angle changes from the reference azimuth. The system further includes an inertial sensor which is communicatively which is also integrated within the mount and is configured for tracking angle changes from the reference azimuth. The system may be configured for selectively relying on angle change tracking provided by either the angle encoder or the inertial sensor.

Low-cost integration of inertial sensor with angle encoder on a swivel mount to accurately track angle changes from a reference bearing

A vertical integrity monitoring method and system are described. The vertical integrity monitoring method includes determining a noise sigma ratio parameter. The method also includes determining two vertical protection limit slopes and an associated covariance matrix. The method further includes determining a vertical integrity limit and set of weights based on the VPL slopes, covariance and the parameter; and applying the set of weights based on the parameter to calculate a vertical solution. An integrity monitoring system may have hardware and/or software embodying the one or more methods described.

Integrity-optimized receiver autonomous integrity monitoring (RAIM) for vertical integrity monitoring

An integrity monitoring method for an aircraft is disclosed. The integrity monitoring method includes determining a set of non-uniform weights. The non-uniform weights are based on a least squares approximation of a linearized measurement equation. The integrity monitoring method also includes applying the non-uniform weights in a receiver autonomous integrity monitoring (RAIM) system. Further, the integrity monitoring method includes determining a reduced integrity limit based on the output of the RAIM system.

Integrity-optimized receiver autonomous integrity monitoring (RAIM)

A method and apparatus for improving differential navigation accuracy uses time transfer over a two-way communications link. The communications link transmits an overall time offset between a differential reference station and a remote user. A differential navigation position solution is modified at the remote user with the overall time offset to improve the differential navigation accuracy. A first time offset between a first communications device and a first navigation receiver at the remote user is determined. A second time offset between the first communications device at the remote user and a second communications device at the differential reference station is determined. A third time offset between the second communications device and a second navigation receiver at the differential reference station is determined. An overall time offset from the first time offset, the second time offset, and the third time offset is computed and used to improve the differential navigation accuracy.

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Cedar Rapids, IA, United States of America

Patrick Y Hwang