Honeywell International Inc.

Honeywell G.m.b.h.

Timothy Merrill Buck

Lawrence C Vallot

Scott I Snyder

Christopher A Lund

Lloyd W Priddy

Ross Merritt

Christopher Jay Matthews

Paris D Wiley

Dang Tu Van-Cao

Lawrence Charles Vallot

A navigation system includes at least one inertial sensor configured to detect motion of the system and generate inertial data; at least one aiding device configured to generate aiding device measurement data; at least one processing unit configured to generate an un-smoothed navigation solution inclusive of navigation state variable error resets based on the inertial data and the aiding device measurement data; wherein the at least one processing unit is further configured to sum the state variable error resets into a cumulative sum of the state variable error resets; wherein the at least one processing unit is further configured to high pass filter the cumulative sum of the state variable error resets; and wherein the at least one processing unit is further configured to subtract the high pass filtered cumulative sum of the state variable error resets from the un-smoothed navigation solution to generate a smoothed navigation solution.

Smoothed navigation solution using filtered resets

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 radiation upset detector is provided. The radiation upset detector includes at least one radiation sensitive memory initialized with at least one respective known-signature word; and at least one radiation hardened logic circuitry communicatively coupled to the at radiation sensitive memory to check the known-signature word at at least a kHz rate to detects errors. Responsive to detecting an error in the known-signature word in the radiation sensitive memory, the radiation hardened logic circuitry sends an action command. At least one of: a memory size of the memory; a number of circuits in the logic circuitry; a clock rate for the checking the known-signature word; and at least one corruption threshold is selected based on system reliability requirements of the protected system including at least one of: an overall operational reliability requirement of the protected system; a probability of detection success; false alarm rates; and a required speed of detection.

Radiation upset detection

A disturbance correction device comprises a disturbance detector configured to detect and output a high frequency component of a measurement signal from an inertial sensor and a level converter coupled to the output of the disturbance detector. The level converter is configured to convert the high frequency component to a direct current (DC) signal. The disturbance correction device also comprises a compensator coupled to an output of the level converter and configured to compare the DC signal with a plurality of thresholds. When the DC signal passes one of the plurality of thresholds, the compensator is further configured to output a respective process noise increment to a Kalman filter. The respective process noise increment corresponds to the passed threshold.

High frequency disturbance detection and compensation

Systems and methods are provided for compensating nonlinearities in a navigational model. In one embodiment, a system comprises an inertial measurement unit configured to measure inertial motion of a vehicle and an aiding source configured to provide observational measurements of vehicle motion. Further, the system comprises a navigation computer coupled to the inertial measurement unit and the aiding source, wherein the navigation computer is configured to calculate a predicted state and an error covariance data based on the measured inertial motion received from the inertial measurement unit and the observational measurements from the aiding source and calculate variance increments based on attitude uncertainty in the predicted state. Also, the navigation computer is configured to add the variance increments into a process noise covariance matrix for the predicted state and calculate an update for the vehicle motion based on the predicted state, the error covariance data, and the observational measurements.

Systems and methods for compensating nonlinearities in a navigational model

A system comprises a Global Navigation Satellite System (GNSS) receiver configured to acquire and track a unique radio frequency (RF) signal for each of a plurality of channels, wherein the GNSS receiver is configured to provide one or more system state measurements based on the unique RF signals; processing functionality configured to calculate a respective code delay error for each of the plurality of channels based on the respective unique RF signal; and micro jump detection functionality configured to calculate an average code delay error across all of the plurality of channels based on the plurality of calculated code delay errors, wherein the micro jump detection functionality is further configured to compare the calculated average code delay error to an error threshold to detect a micro jump event when the calculated average code delay error exceeds the error threshold.

System and method of compensating for micro-jump events

RLG beam intensity monitor in which the beam intensity information is derived from the a.c. output of the RLG angular rate sensor.

Growing community of inventors

Oakdale, MN, United States of America

Timothy Merrill Buck