Nonlinear Discrete-time Design Methods for Missile Flight Control Systems

Discrete-time designs of flight control systems are required for implementation on missile-borne computers. While extensive literature is available on linear discrete-time control system design methods, nonlinear discrete-time control system design techniques have not been discussed to the same degree. This paper presents three nonlinear, discretetime control system design methods. These are the discrete-time feedback linearization method, discrete-time state-dependent Riccatti equation method, and the discrete-time recursive backstepping technique. Nonlinear missile autopilot design for a conventional missile and an integrated guidance-control system design for a moving mass actuated missile are given as illustrative examples.