Method for Analyzing the Influence of the Errors Induced by the Gyroscopic Channel of a Strapdown INS in the Autonomous Mode

We describe a method, which allows analyzing the influence of the errors induced by gyroscopic channel of strapdown inertial navigation system (strapdown INS) on the errors of INS autonomous mode. The method is implemented using a computer simulator of the SINS. A general approach to the procedure for modeling errors in a computer simulator with a zero test is developed. Simulation made it possible to identify the inertial errors of the INS dead reckoning in cases of various types of aircraft trajectories when digital data processing is applied in the gyroscopic channels of the laser angular rate sensors.