Kalman Filter and Proportional Navigation Based Missile Guidance System

Missile Guidance involves guiding the missile to its target. The target's accuracy has a huge impact on its effectiveness. In this paper, the Kalman Filter and the Proportional Navigation (PN) algorithm are used for missile guidance. It is a guidance, navigation, and control (GNC) system for a missile. A fully adaptive Kalman filter that processes a measurement every n milli-second is designed. The Kalman filter estimates the guidance signals for an augmented PN, the rate of the line of sight (LOS), and the target's normal acceleration. A comparative study for missile guidance was done by using different navigation algorithms and filters.