Timothy John Buck

US Patent:

8248300, Aug 21, 2012

Filed:

Jun 2, 2010

Appl. No.:

12/792546

Inventors:

Timothy M Buck - Oakdale MN, US
Lawrence C. Vallot - Lake Elmo MN, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

G01S 19/23

US Classification:

34235762

Abstract:

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.

US Patent:

8457891, Jun 4, 2013

Filed:

Jun 19, 2012

Appl. No.:

13/527136

Inventors:

Lawrence Charles Vallot - Lake Elmo MN, US
Timothy Merrill Buck - Oakdale MN, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

G01C 21/10

US Classification:

701501

Abstract:

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.

US Patent:

51002353, Mar 31, 1992

Filed:

Jul 24, 1990

Appl. No.:

7/557281

Inventors:

Lloyd W. Priddy - Mahtomedi MN
Timothy M. Buck - Blaine MN

Assignee:

Honeywell Inc. - Minneapolis MN

International Classification:

G01B 902

US Classification:

356350

Abstract:

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

US Patent:

20160239455, Aug 18, 2016

Filed:

Feb 13, 2015

Appl. No.:

14/622571

Inventors:

- Morristown NJ, US
Christopher Jay Matthews - Minneapolis MN, US
Dang Tu Van-Cao - Champlin MN, US
Christopher A. Lund - Otsego MN, US
Timothy Merrill Buck - Oakdale MN, US

International Classification:

G06F 13/42
G06F 12/02
G06F 13/30
G11C 7/10
G06F 13/16

Abstract:

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.

US Patent:

20160077125, Mar 17, 2016

Filed:

Aug 14, 2012

Appl. No.:

13/585453

Inventors:

Timothy Merrill Buck - Oakdale MN, US
Lawrence Charles Vallot - Lake Elmo MN, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

G01P 21/00

Abstract:

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.