Abstract
Aiming at the problem of the instability or even divergence of the navigation system in which the satellite navigation system is vulnerable to be interfered and the GPS system is easy to be shielded when aircraft flight in a high dynamic state, the unscented kalman filter (UKF) algorithm is used in this paper to improve the performance of the integrated navigation system based on strap down inertial system(SINS) and geomagnetic navigation system(GNS). The geomagnetic model and integrated system are modeled, and the UKF algorithm is used for navigation data fusion for the reason of high nonlinear for observation equation. A high dynamic aviation trajectory is used to verify and analyze this scheme, and the result shows the moderated accuracy for error estimation for SINS. Without using external reference signals, the new passive integrated navigation system is robust for flight environment, and it is good for engineering application in high dynamic passive navigation.
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