A forebody flow control system and more particularly an aircraft or missile flow control system for enhanced maneuverability and stabilization utilizes various types of sensors and various types of activatable flow effectors to maneuver the aircraft or missile with the help of a control system. A method of operating the flow control system is also disclosed.
1. A flow control system for a missile or aircraft forebody comprising a. at least one activatable micro-vortex generator;b. at least one sensor generating a signal, the at least one sensor being used to maneuver the missile or aircraft;c. an inertial measurement unit having an output; andd. a closed loop control system;wherein the closed loop control system is used for activating and deactivating the at least one micro-vortex generator based at least in part on the signal of the at least one sensor and the output of the inertial measurement unit. 2. The...
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