Loosely Coupled GPS/INS Integrated Navigation System based on Kalman Filter and Complementary Filter for Aircraft

GPS/INS integrated system provides more precise position of an aircraft compared to individual system. The objective of this paper is to propose a loosely coupled GPS/INS integrated system with Kalman Filter (KF) and Complementary Filter (CF). The integration has been carried out in two techniques. Firstly the systems are integrated using KF. Secondly, the same is done applying both KF and CF. In this paper, a comparative study of these two techniques is addressed with the help of MATLAB simulation.