Patent ID: 8190305

Claim:
A missile or a munition comprising a. an aerodynamic surface or aerodynamically-coupled surfaces; b. at least two air flow control zones on the same aerodynamic surface or aerodynamically-coupled surfaces, at least one of the at least two air flow control zones comprising at least one activatable flow effector capable of being activated and deactivated, wherein the at least one activatable flow effector is deactivated when the activatable flow effector is flush or nearly flush to the aerodynamic surface or aerodynamically-coupled surfaces of the missile or munition on or in which the activatable flow effector is located; and c. one or more digital logic devices, the digital logic devices having a separate local, closed loop control system for each flow control zone for activating and deactivating the at least one activatable flow effector to, in part, maneuver the missile or munition, and a global control system to coordinate the local control systems.