Optimal guidance laws and autopilots for missiles are typically developed separately. Since this separation may result in an inefficient implementation, it is desirable to investigate integrated design approaches. In this paper, a simplified planar model for missile intercept dynamics is examined. Feedback linearization and simple linear approximations are considered for transforming the dynamics into a linear form suitable for the application of optimal control techniques. Control commands are then computed to minimize miss distance directly, without intermediate acceleration commands. Preliminary results obtained from simulations of an aerodynamically stable vehicle against non-maneuvering targets indicate that this implementation is comparable to traditional proportional navigation with a high navigation gain. For unstable systems, however, achieving both target intercept and attitude stabilization proves problematic because of limitations inherent in the problem formulation.