Aircraft and missile forebody flow control device and method of controlling flow

A flow control system for a missile or aircraft forebody comprising

• a. at least one activatable flow effectors;
• b. at least one sensor having a signal, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody;
• and
• c. an inertial measurement unit having an output;
• d. a closed loop control system;
• wherein the closed loop control system is used for activating and deactivating the at least one flow effector based on at least in part the signal of the at least one sensor and the output of the inertial measurement unit.

A method of stabilization for a missile or aircraft forebody comprising the steps of

• a. estimating or determining side forces on a missile or an aircraft forebody based at least in part on a signal from at least one sensor, the at least one sensor being positioned to detect flow separation on the missile or aircraft forebody;
• the missile or aircraft forebody further comprising at least one flow effector and a closed loop control system for controlling the flow effectors;
• b. activating the at least one flow effectors to counteract the side forces by oscillation of the at least one flow effector with the closed loop controller based on at least in part the signal of the at least sensor;
• and
• c. re-estimating or determining side forces on the missile or aircraft forebody based at least in part on a signal from the at least one sensor;
• and
• d. deactivating the at least one flow effector in response to reduced or changed side forces.