Honeywell International Inc.

Richard S Russell

Michael Ray Elgersma

Lawrence C Vallot

Vijay Venkataraman

Scott I Snyder

Christopher A Lund

Thandava Krishna Edara

Andrew Stewart

Arjun Bindu Jyothikumar

Christopher Jay Matthews

Tom Jakel

Moses Bangura

Saul Cooper

Ctibor Mazal

Systems and methods for the external aiding of inertial navigation systems are described herein. In certain embodiments, a device includes an inertial navigation system. In some embodiments, the inertial navigation system includes one or more inertial sensors and an input interface for receiving measurements. In further embodiments, the measurements include at least one of delta attitude and/or delta position measurements from an external system, and position and attitude information in an arbitrary map frame. In certain embodiments, the inertial navigation system includes a computation device that is configured to calibrate the errors from the one or more inertial sensors using the received measurements.

Delta position and delta attitude aiding of inertial navigation system

A computing system obtains asset information, unmanned aerial vehicle (UAV) information, and regulation information, and determines, based on the obtained information, a 3-D global asset-inspection plan including a plurality of UAV route segments and respective UAV launch locations.

UAV flight management planner

A system comprises a plurality of reference navigation systems, each reference navigation system configured to generate a respective reference navigation solution. The system also comprises a test navigation system, the test navigation system configured to generate a test navigation solution; and a processing unit configured to compare the test navigation solution to each of the respective reference navigation solutions to estimate one or more errors in the differences between the test navigation solution and the respective reference navigation solutions. The processing unit is further configured to update the respective reference navigation solutions to account for the corresponding one or more estimated errors. The processing unit is also configured to compare the test navigation solution to the updated reference navigation solutions to generate a performance score representative of the performance of the test navigation system.

Multiple truth reference system and method

A method of determining an operational state of a navigation system of a platform is provided. The method comprises testing at least a portion of hardware in the navigation system. Additionally, a measurement of at least one navigation variable from an inertial sensor is combined with a measurement of another navigation variable. A plurality of residuals for the measurement of at least one navigation variable and the measurement of another navigation variable are determined with a blending filter. An error for the measurement of at least one navigation variable is estimated based on the plurality of residuals. The method also predicts an error for the measurement of at least one navigation variable while the navigation system is in route. A determination is made as to whether the navigation system meets operational standards based on testing at least a portion of hardware, estimating an error for the measurement of at least one navigation variable, and predicting an error for the measurement of at least one navigation variable. Finally, one of a first state and a second state of the navigation system is output, the first state indicating that the navigation system does meet operational standards and the second state indicating that the navigation system does not meet operational standards.

Method and apparatus for determining the operational state of a navigation system

Growing community of inventors

Roseville, MN, United States of America

Richard S Russell