Control of gradual plane change during aerocruise

Control of the orbital maneuvering of flight vehicles using aerodynamic forces is most often considered from the performance point of view. This results in the relationship between performance and stability analyses often being overlooked. Here, 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 nonrotating Earth in terms of variables which allow uncoupling of the longitudinal and lateral dynamics, and partial uncoupling of lateral dynamics. Principal differences in this model and most others used to investigate aeroassisted maneuvers is that aerodynamics controls are used to produce the maneuver and the attitude dynamics of the vehicle are included explicitly. Two methods are used to determine the control moments required for a small plane change maneuver: linear optimal control and control determined using an inverse method. An example is presented to illustrate the similarities and differences of the generated maneuvers.