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

A flow control system for a missile or aircraft afterbody comprising

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

A method of maneuvering a missile or aircraft comprising the steps of

• a. activating at least one activatable flow effector located on a missile or aircraft afterbody to create forces or flow conditions on the missile or aircraft afterbody;
• b. estimating or determining forces or flow conditions on the missile or an aircraft afterbody based at least in part on a signal from at least one sensor, the at least one sensor being positioned to detect side forces or flow separation on the missile or aircraft afterbody;
• and
• c. deactivating the at least activatable one flow effector in response to changed side forces or flow conditions.