Reducing the navigational error of a flying object in space by using an integration of GPS and INS data

摘要

The most important and applicable navigation system in space is inertial navigation system but due to the significant growth in error of velocity and position parameters of the navigation over the time in the inertial navigation systems, this system solely are not able to define the position and velocity of flying object with high accuracy. From one hand global positioning system can offer the position and velocity of flying object navigation in the space with a limited error. But satellite position system cannot determine, attitude of the flying object in the space so by integration of data, the inertia navigation system and positioning satellite can take advantage of both navigation system with less expenses. In this article, one Algorithm has been suggested to integrate of GPS and INS using extended Kalman filter to reduce the navigation error in the space. The results of simulation for 100 seconds flying according to the suggested method indicated that this integration algorithm can make the inertia navigation error convergent and finally provide the navigation goals in the flying object with high accuracy.