Navigation Calculation Model for Airborne SINS and Its Accuracy Analysis

Abstract:

A study was made of the navigation calculation model in local frame and detailed steps for strapdown inertial navigation system(SINS).Then the error characteristics of SINS was analyzed through navigation calculation with the measured data.Finally,GPS/SINS loose coupling was implemented by using Kalman filter and Kalman smooth.The results show that,coordinate error of SINS grows as parabola function,in a short time it can provide accurate navigation parameters,with coordinate error less than 2 meters within one minute.SINS/GPS integrated navigation system,which combines advantages of the two systems,gains more reliability and integrity respect to each subsystem.