Manuel Fernandez

US Patent:

60320990, Feb 29, 2000

Filed:

Nov 2, 1996

Appl. No.:

8/747008

Inventors:

Manuel Fernandez - Studio City CA

International Classification:

G06F16500

US Classification:

701220

Abstract:

Processes and algorithms to determine and correct key error sources in an inertial navigator. These key error sources are azimuth misalignment error and all gyro drift rate errors ("North", "East" and "Down"). Thus the invention provides improved directional accuracy and improved navigation performance. The processes and algorithms can be implemented within the system computer to determine and correct for the system error sources thus determined automatically.

US Patent:

59419350, Aug 24, 1999

Filed:

Sep 23, 1996

Appl. No.:

8/717858

Inventors:

Manuel Fernandez - Studio City CA

International Classification:

G06F16500

US Classification:

701220

Abstract:

A process and algorithms to determine and correct for azimuth-axis drift rate in an inertial navigator. The process and algorithms may be implemented as an automatic sequence within the system computer to determine and correct the system errors thus determined. These actions provide the system with improved directional accuracy and improved navigation performance.

US Patent:

57896712, Aug 4, 1998

Filed:

Aug 15, 1996

Appl. No.:

8/698395

Inventors:

Manuel Fernandez - Studio City CA

International Classification:

G01C 2100
G01C 1938

US Classification:

73180

Abstract:

A process and algorithms to determine and correct for the error in azimuth alignment and the errors in "North" and "East" Gyro Drift Rates in an inertial navigator which has been aligned via gyrocompassing, or via the "Stored Heading" technique, with the system "at rest". The process and algorithms may be implemented as an automatic sequence within the system computer to determine and correct the system errors thus determined. These actions make the inertial navigator more accurately represented by the model of an ideal navigation system with a pure and singular initial azimuth misalignment error. Thus the inertial navigator's inital azimuth misalignment error can be more accurately determined and corrected by the model.