Abstract: For errors accumulating over time, a simulation system of SINS/GNSS integrated navigation based VC++ is design. According to  the actual flight path of simulate aircraft flight control module, the true value of inertial measurement device is obtained. Using Visual Studio 2005, the realsolvers and GNSS simulation are finished, and the output correction is completed, enabling dynamic digital simulation of integrated navigation system. Program results show that the integrated navigation system can overcome the error accumulation feature of the inertial navigation system, navigation parameter error does not drift over time, can be used for a long time navigation.

Key words: Visual Studio 2005, Integrated modular, Integrated navigation, Kalman filter