Patent ID: 8548650
Filing Date: 2013-10-01
Classification: F42B,G05D

Abstract:
1. A missile or a munition comprising: a. an aerodynamic surface or surfaces; b. at least two air flow control zones on one or more aerodynamic surfaces of the missile or munition, 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 surfaces of the missile or munition on or in which the activatable flow effector is located; 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; and d. a health monitoring system comprising at least one pattern recognition algorithm and at least one decision system and an output,