INS Velocity Correction Using Stabilized Seeker Data

One of the most important features that affect the performance, range and accuracy of a tactical missile system is the navigation capability of the missile system. Today, navigation systems use inertial measurement units as basic sensors. In this paper, seeker stabilized LOS calculations are used to correct the velocity components of the navigation solution through a Kalman filter to improve navigation accuracy using a control grade IMU in the presence of an electronic warfare environment. This work presents a new method that aims to improve the accuracy of INS speed results without relying on GPS signals. The filter works great even when the exact location of the reference point is unknown. The effect of IMU biases, false target data, and flight path on the performance and observability of the filter is extensively investigated through extensive simulation studies using a 6-degree-of-freedom model assuming a flat earth scenario. The findings of this study highlight the potential of the proposed method to effectively integrate seeker measurements into missile applications, thereby increasing the accuracy of INS velocity results. The ability to bypass the need for GPS signals offers a significant advantage in scenarios where GPS signals are unavailable or unreliable.