The present invention relates to a missile or munition with a hierarchical, modular, closed-loop flow control system, more particularly to aircraft or munition with flow control system for enhanced aerodynamic control, maneuverability and stabilization. The present invention further relates to a method of operating the flow control system. Various embodiments of the flow control system involve elements including flow sensors, active flow control devices or activatable flow effectors, and logic devices with closed loop control architecture. The sensors are used to estimate or determine flow conditions on the surfaces of a missile or munition. The active flow control device or activatable flow effectors create on-demand flow disturbances, preferably micro-disturbances, at different points along the various aerodynamic surfaces of the missile or aircraft to achieve a desired stabilization or maneuverability effect. The logic devices are embedded with a hierarchical control structure allowing for rapid, real-time control at the flow surface.
This information is part of a study by Oasis Global, Inc. of all space inventions filed at the United States Patent and Trademark Office, and is provided for informational purposes only. It is not an endorsement of any particular assignee, inventor or invention. Although Peter A. Koziol represents inventors and assignees of space inventions he does not represent all of the inventors and assignees listed. The prosecuting attorney agent or firm for each patent is identified by the United States Patent and Trademark Office in the patent specfication, which can be viewed by clicking on the patent image or downloading the patent document. For more information regarding Mr. Koziol's background and experience, or to learn more about space inventions, please contact Mr. Koziol.
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