AERODYNAMIC CONTROL SURFACE OF GUIDED MISSILE Russian patent published in 2006 - IPC F42B15/00 

FIELD: armament.

SUBSTANCE: the aerodynamic control surface of guided missile installed on a shaft has swept leading and trailing edges. The control surface consists of successively positioned monoplane and biplane lifting surfaces made in the form of a spatial frame, which are rigidly coupled by the on-board and terminal side struts and installed on the rotary shaft made on the on-board side strut located in the plane of symmetry of the profile of the aerodynamic control surface. The plane of symmetry of the biplane lifting surface coincides with the plane of symmetry of the profile of the monoplane lifting surface made with a leading-edge sweep angle of 55 to 65 deg. and a trailing-edge sweep angle of 43 to 47 deg. The biplane surface is made with a leading-edge sweep angle equal to the trailing-edge sweep angle of 5 to 30 deg.

EFFECT: enhanced efficiency of missile aerodynamic control at the subsonic and supersonic flight speeds.

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