Application of Integrated Guidance and Control Schemes to a Precision Guided Missile

Three optimal integrated guidance and control (IGC) laws for a tactical missile are developed. The three IGC design models include planar intercept kinematics and missile longitudinal dynamics in one mathematical framework. A target acceleration model and missile radome error compensation scheme are inluded in the state formulations. An optimality criterion which asymptotically imposes an infinite penalty on miss distance and angle-of-attack in the endgame as time-to-intercept goes to zero is minimied. Using reasonable approximations, an analytic solution is derived which can be easily implemented as an endgame guidance law/autopilot in current missile flight computers. Nonlinear six degree-of-freedom simulation results will be presented at the session to demonstrate the performance of these three algorithms.