Patent ID: 6796525
Filing Date: 2004-09-28
Classification: F42B

Abstract:
Fin-stabilized missile (1) which is intended to be fired at high acceleration towards a target alone its trajectory and which can be guided in the trajectory, comprising:a main part and a rear part; stabilizing fins (3, 32) arranged at a rear end of the missile for stabilizing the missile; and control elements (6, 7) which are arranged at a front end of the missile and are arranged to guide the missile, wherein the rear part of the missile comprises a body part (4, 31) which can rotate freely relative to the main part (1, 29) of the missile about a bearing (14, 36) arranged concentric to the longitudinal axis (L) of the missile (1), the stabilizing fins are secured to the rear part of the missile, the bearing (14, 36) is arranged near a dividing plane between the body part (4, 31) and a remainder of the missile (1) and has a large diameter compared with its length in the longitudinal direction of the missile, the bearing is designed with a slight axial clearance, both forwards and rearwards of the bearing, in the main part of the missile and in said body part there are peripheral annular contact surfaces (20, 21 and 27, 28) which in pairs are brought to bear against each other immediately before said axial clearance reaches its respective end positions in the bearing in order to transfer forces acting between the main part (1, 29) of the missile and said body part (4, 31) or parts thereof, contact surfaces (20, 21) which limit the removal of the main part (1) of the missile and the body part (4) from each other are frustoconical in shape, and contact surfaces (27, 28) which limit the pressing-together of the two parts are flat and annular.