US Patent 8371324 Collapsible supersonic inlet centerbody

A collapsible flow control structure for an axisymmetric inlet employs trapezoidal alternating actuated and non-actuated strips having leading edges hinged to a missile forebody and free trailing edges extending into an inlet aperture, the strips positionable to form a variable angle frustum of a cone. An interengagement mechanism secures adjacent strips and actuators are attached to an inner surface of the actuated strips for urging the strips between a collapsed, retracted position for a first angle frustrum to an extended position for a second angle frustrum for aerodynamic flow control.