Trajectory optimization of a ramjet-powered missile using singular perturbation methods

A nonlinear optimal control law is derived for a ramjet powered missile using singular perturbation theory. The singular perturbation analysis, together with multiple time scaling converts the solution of the two point boundary value problem into the extremization of nonlinear algebraic equations. The derivation of the control law takes into account the various operational constraints and an algorithm is outlined describing the various steps in the computation of the control law. The control law has a feedback form and is a good candidate for real-time implementation.