Design of Kalman filter for augmenting GPS to ins systems

Abstract EN

Strapdown Inertia) Navigation Systems (SDINS) and Global Posilioning Systems (GPS) both can be used for a wide range of navigation functions.

Each has its strength ,and weakness in this respect.

Kalman filter is used to incorporate information from the accelerometers and gyros at high rates and information from GPS measurements at lower rates lo improve ballistic missile strapdown navigation systems by GPS aiding.

A linearized Kalman filter model is implemented for augmented system based on the navigation frame to estimate the inertial system error based on the measurement error between the GPS and INS systems.

A three degree of freedom missile flight simulator with strapdown navigation algorithms was carried out in order to compare the proposed augmented system with other navigation algorithms.

The presents results show that the error in both position and velocity is very small compared with other algorithms.