Fin-stabilized guidable missile

Abstract

The present invention relates to a fin-stabilized missile ( ) of the type which is intended to be fired at high acceleration towards a defined target along its trajectory and which can be guided in the trajectory and which, for stabilizing it in the trajectory, is provided with stabilizing fins ( ) arranged at its rear end, and control elements ( ) which are arranged at its front end and are intended to guide the latter, and whose rear part, in which the fins are secured, consists of a body part ( ) which can rotate freely relative to the main part ( ) of the missile about a bearing ( ) arranged concentric to the longitudinal axis (L) of the missile ( ). According to the invention, said bearing ( ) is arranged near the dividing plane between the missile ( ) and the body part ( ) and has a short length in the longitudinal direction of the missile, this having been made possible by the fact that it has been given a large diameter compared with its length and it has been designed with special load-bearing contact surfaces ( ) which limit the stresses during ramming and firing and during the flight of the missile ( ) through the air. The freely rotatable body part ( ) for the fins ( ) can then in turn be axially displaced from a launch position located inside the missile to a flight position where the fins ( ) are pushed out behind the rear plane of the missile, where they can rotate freely.