Integration of INS and GPS for Radar Aided Inertial Navigation System
Balwinder Singh, P. M. Menghal, Naveen Suri · 2022 IEEE 7th International conference for Convergence in Technology (I2CT) · 2022
Inertial navigation has been a key element in missile navigation system to achieve positional accuracy with a primary objective to monitor a moving missile state trajectory. Missile motion and its observations can be reflected by mathematical models with adequate accuracy. Inaccurate knowledge of the missile dynamics may cause a particular algorithm to fail miserably. This paper covers the fundamental aspects of KF (Kalman Filter) essential for GPS/INS integration, its mathematical foundations and basic implementation methods. It also presents techniques for sensor integration and how implementation includes its own performance evaluation. Both INS and GPS are different position estimation technologies with their own benefits and drawbacks. An amalgamation of both will provide a optimal navigation /solution with both complementing each other. This research paper carries out an investigation of the performance of an integrated system GPS/INS when changes are made in the algorithm update rate and compare different integration algorithm namely KF and RNN (Recurrent Neural Network).