A gyroscopic stabilizer has a ring mounted at a missile rocket nozzle exit for rotation about the exit. The ring bears vanes extended inwardly into gases exiting from the nozzle and configured for rotation by the exiting gases so that the rotating mass of the ring gyroscopically stabilizes the missile. The ring may be mounted by a bearing having rolling elements or sliding surfaces. The axial length of the ring may be substantially less than its diameter. The ring has a low moment of inertia and is accelerated to stabilizing speed by vanes minimally impeding the exiting gases. When the stabilizer is used on a rocket propelled missile launched from a tube, the missile is fully stabilized in the tube before burnout and there is no rotational friction between the tube and the missile.