1
John W Diesel: Assured-integrity monitored-extrapolation navigation apparatus. Litton Systems December 10, 1996: US05583774 (44 worldwide citation)

The assured-integrity monitored-extrapolation (AIME) navigation apparatus selectively utilizes measurements provided by ancillary sources at periodic intervals in determining the state of the platform on which the apparatus is mounted. The measurements have attributes which are measures of quality, ...


2
John W Diesel: 3D AIME.TM. aircraft navigation. Litton Systems July 25, 2000: US06094607 (35 worldwide citation)

The apparatus of the present invention uses radar altimeter measurements and stored terrain altitude profiles to provide pre-filtered observations to a Kalman filter for estimating barometric offset at the airport runway, and barometric scale factor for offsets above the runway. These offsets are us ...


3
John W Diesel, Gregory P Dunn: Method for in-field updating of the gyro thermal calibration of an intertial navigation system. Litton Systems June 18, 1996: US05527003 (24 worldwide citation)

An in-field method for correcting the thermal bias error calibration of the gyros of a strapdown inertial navigation system. The method is begun after initial alignment while the aircraft remains parked with the inertial navigation system switched to navigation mode. Measurements are made of navigat ...


4
John W Diesel: Integrated inertial/GPS navigation system. Litton Systems July 9, 2002: US06417802 (19 worldwide citation)

The invention is a method and apparatus for adjusting the phase and frequency of a received GPS signal in an inertial-GPS navigation system by inputting a delta-phase at delta-time intervals into the received satellite signal. The method comprises the steps of determining two delta-phase components: ...


5
John W Diesel: Failure detection system. Litton Systems October 2, 2001: US06298316 (12 worldwide citation)

The invention is a method and apparatus for determining a failure in a subsystem that is part of a system, the system being characterized in terms of a state vector comprising a plurality of state variables. The state vector is updated at times (jK+k)T&Dgr;t using one or more Kalman filter proc ...


6
John W Diesel: Method and apparatus for calibrating the gyros of a strapdown inertial navigation system. Litton Systems November 12, 1996: US05574650 (11 worldwide citation)

A method and apparatus for minimizing the effect of lateral velocity transients upon an aircraft inertial instrument calibration process of the type in which cross-track velocity is measured and utilized to correct for the east component of gyro bias error. A "cross-track position" value is obtained ...


7
John W Diesel, Gregory P Dunn: Instrument calibration method including compensation of centripetal acceleration effect. Litton Systems April 9, 1996: US05505410 (3 worldwide citation)

A method and apparatus are provided for addressing the effect of centripetal acceleration upon estimates of cross-track velocity, for determination of east gyro bias error, generated with a taxiing aircraft. After initial estimates of crab angle, ratio of crab angle to centripetal acceleration and l ...


8
John W Diesel: 3D AIMEā„¢ aircraft navigation. Northrop Grumman Guidance and Electronics Company November 1, 2011: USRE042891

The apparatus of the present invention uses radar altimeter measurements and stored terrain altitude profiles to provide pre-filtered observations to a Kalman filter for estimating barometric offset at the airport runway, and barometric scale factor for offsets above the runway. These offsets are us ...


9
John W Diesel: Assured-integrity monitored-extrapotion navigation apparatus. Litton Systems November 5, 1996: CN95190564

The assured-integrity monitored-extrapolation (AIME) navigation apparatus selectively utilizes measurements provided by ancillary sources at periodic intervals in determining the state of the platform on which the apparatus is mounted. The AIME apparatus therefore determines the platform's state in ...


10
John W Diesel: Integrated inertial/gps navigation system. August 15, 2002: US20020109628-A1

The invention is a method and apparatus for adjusting the phase and frequency of a received GPS signal in an inertial-GPS navigation system by inputting a delta-phase at delta-time intervals into the received satellite signal. The method comprises the steps of determining two delta-phase components: ...



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