Honeywell International Inc.

Christopher A Lund

Lawrence C Vallot

Wayne A Soehren

Brian W Schipper

Charles T Bye

Mario B Ignagni

Scott I Snyder

Timothy Merrill Buck

Ross Merritt

Richard S Russell

Christopher Jay Matthews

Dang Tu Van-Cao

A multiple processor architecture with flexible external input/output interface is provided. In one embodiment, an open flexible processor architecture avionics device comprises: a multiple processor architecture having a primary processor, a secondary processor, a random access memory (RAM) coupled to at least the secondary processor, and a shared memory coupled to the primary and secondary processor; and a flexible input/output (I/O) interface coupled to the multiple processor architecture, wherein the flexible I/O interface provides I/O access to the primary processor using a fixed I/O protocol, and provides I/O access to the secondary processor using at least one re-configurable I/O protocol; wherein the primary processor is dedicated to executing embedded software for implementing a primary base functionality, the primary processor has read and write access to the shared memory, and the primary processor is not reprogrammable; and wherein the secondary processor has read-only access to the shared memory and is programmable.

Multiple processor architecture with flexible external input/output interface

A relative navigation system and method are disclosed. The relative navigation system includes a first sensor unit responsive to a motion of a first position, a second sensor unit responsive to a motion of a second position, and a first processing unit associated with at least one of the first sensor unit and the second sensor unit and communicatively coupled to the first sensor unit and the second sensor unit. The first processing unit is configured to generate relative navigation solution information associated with first sensor unit information and second sensor unit information.

System and method for high accuracy relative navigation

A relative navigation system including a first unit responsive to the motion of a first position, a second unit responsive to the motion of a second position and a processing unit that generates a relative navigation solution as a function of first unit information and second unit information. The generated relative navigation solution is indicative of at least one of: a relative position vector of the second position relative to the first position, a relative velocity of the second position relative to the first position, and a relative attitude of the first unit at the first position relative to the second unit at the second position.

Method and apparatus for high accuracy relative motion determination using inertial sensors

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

A method and systems for processing Global Positioning System (GPS) signals is provided. The method includes determining if two signals or more signals with the same pseudorandom number bit sequence (PRN) are detected by a GPS receiver.

Global navigation satellite system repeater disruption monitoring

A navigation system includes a Kalman filter to compensate for bias errors in inertial sensing elements. An observed pitch, roll or heading change is input to the Kalman filter either from an aiding source or when the navigation system is in a known condition. The Kalman filter generates a correction signal that is provided to the navigation computation system.

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Otsego, MN, United States of America

Christopher A Lund