Patent ID: 9637223
Date: 2017-05-02
CPC Classifications: B64C,F41G,F42B,G05D,Y02T

Claim:
1. A missile or aircraft comprising: an afterbody a forebody and at least one sensor having an electrical signal; the missile or aircraft afterbody having a boattail and tail fins; the missile or aircraft experiencing drag during flight; and at least one electromechanical activatable flow effector or electromechanical active flow control device on the boattail or tail fins, wherein the at least one sensor is positioned to measure, estimate or predict a force or flow condition the missile or aircraft's afterbody, the at least one electromechanical activatable flow effector or electromechanical active flow control device is configured and located on the boattail or tail fins to reduce the drag of the missile or aircraft by activating and deactivating the electromechanical activatable flow effector or electromechanical active flow control device to reattach flow to the surface of the missile or aircraft, and the activation or deactivation of the activatable flow effector or active flow control device is capable of reattaching detached flow to the surface of the missile or aircraft.