Control of gradual plane change during aerocruise

Motivated by the continuing interest in orbital maneuvering using aerodynamic forces and the oft overlooked close relationship between performance and stability analyses, we consider the stability and control of small plane change maneuvers during aerocruise. We use a model which consists of linear equations for perturbed motion with respect to a great circle trajectory about a non-rotating earth in terms of variables which allow uncoupling of the longitudinal and lateral dynamics, and partial uncoupling of lateral dynamics. Characteristics of the perturbed motion of a hypersonic flight vehicle with respect to a great circle trajectory are reviewed, including previous results which show that a change in the orientation of the great circle plane results from a general perturbation in initial conditions. This change is analogous to the heading change and lateral displacement which occur when a conventional aircraft's motion is disturbed. A linear quadratic controller for small plane change maneuvers is obtained, and an inverse method for generating controls for a steady-state aerocruise turn is described. An example is presented which shows that the majority of the optimal maneuver is approximated very well by the steady-state turn.