Rudder blade mounting arrangement for a missile

A rudder blade mounting arrangement for a missile, comprising a rudder blade (12) and a mounting element (16) which is provided for the rudder blade foot (14) of the rudder blade (12) and which has two mutually spaced side portions (22 and 24) with mutually facing front faces (60 and 62) by which a receiving space (64) for the rudder blade foot (14) is delimited, wherein extending between the side portions (22 and 24) through the receiving space (64) is a rudder blade axis member (36) for the rudder blade (12) which is displaceable between a retracted inactive position and a deployed active position, characterised in that the axial spacing (70) between the front faces (60 and 62) of the two side portions (22 and 24) is greater than the axial thickness dimension (72) of the rudder blade foot (14), and that the rudder blade axis member (36) is arranged between the two sides portions (22 and 24) in axial limitedly movable fashion while being secured against rotation and the rudder blade foot (14) is connected in positively locking relationship to the rudder blade axis member (36) in such a way that in the deployed active position of the rudder blade (12) the rudder blade foot (14) is forced against the front face (62) of the one side portion (24) and in the retracted inactive position spaced by the positively locking connection from said front face (62) and thus the rudder blade foot (14) is axially limitedly movable with the rudder blade axis member (36) and the rudder blade (12) is freely displaceable from the retracted inactive position into the deployed active position, and wherein the rudder blade mounting arrangement characterized in that at its one end the rudder blade axis member (36) has a contact flange (34) and a blind hole (38) which differs from a circular shape and that secured to an opposite second end of the rudder blade axis member (36) is a rotation-preventing element (74) which is provided in a recess (30) in the mounting element (16).