.ins / Gps Real-time Simulation System

The single navigation can hardly to meet the requirement of controlling andguiding modern airplane or missile, for example: the precision, the reliability and the applicability. If the high-precision GPS and high-reliability INS can be combined, a kind of more ideal navigation system will be constituted. To develop the INS/GPS integrated navigation simulator, which is similar to the real-system at the aspects of time and structure by using modern simulating technology, is significantly important for studying INS/GPS integrated navigation system which can fulfill the requirement.This thesis is mainly about studying "INS navigation simulating subsystem" for "the studying of "INS/GPS integrated navigation simulator". Based on this main idea, first the thesis discusses the mathematics model of gyro and accelemeter, the initial alignment of north-pointed strapdown inertial navigation system, the method of calculation navigation, the method of generating flight orbit data, the method of INS/GPS integrated navigation in detail. Then the thesis develops the system generating flight orbit data and the system of real-time simulating strapdown inertial navigation with VC++6.0. The simulating system combines the inertial sensor real-time simulator and strapdown inertial navigation real-time simulator. Its functions are: the setup of sensor performance parameter, the simulating data dynamic and real-time display and output, real-time save, simulating data to. disk, the function of data show-back. The result shows that the simulating system is steady and reliable and the simulating result is satisfying.