Author Description

Requirements for next generation guided weapons, particularly with respect to their capability to engage high speed, highly agile targets and achieve precision end-game trajectory has prompted a revision of the way in which the guidance and autopilot design is undertaken. This book considered the derivation of mathematical models for a missile autopilot for autopilot in State Space form. The basic model developed was highly nonlinear and is difficult to analyze analytically. Therefore Jacobian linearization technique was used to linear the model.The models developed are useful for further research on precision optimum guidance and control. The model will provide more accurate presentations of missile autopilot dynamics and can be used for adaptive and integrated guidance and control of agile missiles.