LPV modeling of guided projectiles for terminal guidance

This article presents a detailed study concerning the equilibrium analysis and the linear parameter-varying (LPV) modeling of the six degrees-of-freedom (6DoF) nonlinear model of a fin-guided, gun-launched projectile. The equilibrium manifold of the system is obtained through a minimal vector of parameters characterizing its flight envelope and a maneuverability analysis involving the attainable vertical acceleration is presented. In the following, an analytic linear parameter varying model of the airframe yaw/pitch axes is derived and several issues concerning its scope and internal structure are discussed. Finally, an application of these results on a single trajectory point is performed and the resulting linear time-invariant (LTI) model is analyzed in terms of pole/zero location and internal stability.