Abstract: The invention is a method and apparatus for improving the accuracy of an inertial navigation system. The method comprises (1) obtaining a measure of the angular velocity of a body frame of reference having a first axis, a second axis, and a third axis, (2) obtaining a measure of the acceleration of a first reference point in the direction of the first axis, a second reference point in the direction of the second axis, and a third reference point in the direction of the third axis, the first, second, and third reference points being fixed in the body frame, and (3) determining compensated acceleration values. A compensated acceleration value is the difference of the measure of acceleration of a reference point and a compensation quantity. A compensation quantity is an estimate of the portion of the acceleration of the reference point resulting from the rotation of the body frame. The method further comprises establishing the optimum navigation center based on a criterion of goodness.

Abstract: The invention is a method and apparatus for processing signals with frequencies fL and fR from a multioscillator ring laser gyro, the method being repeated at regular time intervals. The difference f&Dgr;&thgr;, of fL and fR is a measure of the angular rotation rate of the ring laser gyro and the sum fF of fL and fR divided by 2 is the Faraday bias frequency. The first step of the method comprises determining two or more of the values MLP, MRP, MFP, and M&Dgr;&thgr;P of a set of functions ML(fL), MR(fR), MF(fF), and M&Dgr;&thgr;(f&Dgr;&thgr;). The second step comprises storing two or more processed values MLS, MRS, MFS, and M&Dgr;&thgr;S of the functions ML(fL), MR(fR), MF(fF), and M&Dgr;&thgr;(f&Dgr;&thgr;) if the corresponding values of MLP, MRP, MFP, and M&Dgr;&thgr;P are valid. A processed value is derived from the value for the present time interval and zero or more processed values for prior time intervals.

Abstract: A system and method for improving the accuracy of altitude determinations in an inertial navigation system. The system utilizes pressure measurements which are taken by a barometric altimeter and converted into an estimated pressure altitude using any known pressure-to-altitude conversion. A pressure correction value is then generated using a correction value generating formula that is a function of altitude. The pressure correction value is then multiplied by a pressure offset value for the barometric altimeter to generate a pressure offset error for the barometric altimeter. This pressure offset error is used in the present invention to modify the pressure altitude estimation in order to generate an altitude determination having an improved accuracy. The present invention further determines an amount of observation noise in the barometric altimeter that is a function of pressure noise and altitude, where the altitude estimation is further modified to account for the observation noise.

Abstract: A system and method for improving the accuracy of altitude determinations in an inertial navigation system. Pressure measurements available to the inertial navigation system are used to initially calculate an estimated pressure altitude using the standard day model for the atmosphere. Temperature measurements are further utilized in the physical relationship between temperature, pressure, and altitude to compute a second computed altitude. A change between subsequent second computed altitudes is calculated and compared with a respective change in the computed pressure altitude in order to generate a correction value. The correction value is then used to modify the computed pressure altitude to generate a more accurate determination of the absolute altitude of the inertial navigation system.