Patent ID: 6202958
Filing Date: 2001-03-20
Classification: F42B

Abstract:
A mounting arrangement for pivotally movable pairs of rudder blades (14) of a guided missile (12) which is fired through the intermediary of a propellent charge gas pressure, wherein each said rudder blade (14) is mounted pivotally openable to a rudder blade holder (16) having a trunnion (20) with a first annular shoulder (24), the trunnion (20) extending radially into a tail structure (10) of the projectile (12), the tail structure (10) is formed with a second annular shoulder (26), a ring element (28) constituted of an inelastic material is arranged between the first and second annular shoulders (24, 26) and the trunnion (20) of each of the rudder blade holders (16) of the pair of rudder blades are axially aligned and the trunnions (20) operatively associated therewith are non-rotatably interconnected by a coupling element (32), wherein a spacing between the first and second annular shoulders (24, 26) of each said trunnion (20) and the tail structure (10) is slightly greater than the thickness of the ring element (28) therebetween so that there is an axial tolerance play (30) between the ring element (28) and the first and second annular shoulders (24, 26), the minions (20) of the respective pair of trunnions are rigidly connected to the coupling element (32), and wherein the coupling element (32) is resilient in the radial direction of the projectile (12).