Selection of the Filtering Correction Cycle to Improve INS/GPS Integrated Navigation Accuracy

In order to improve the accuracy of INS/GPS integrated navigation system, especially in such a case when it works from the integrated navigation into the pure inertial navigation, the schemes of the Kalman filter correction cycle is proposed. Based on detail analysis on the error rule of INS and the error feature of the GPS output signal from several flight-test data, a reasonable correction cycle is selected. In the end, many flight-test data validate the scheme, and the result show it can make pure inertial system reach further high accuracy