Method for correcting the trajectory (flight path) of a missile, and a missile for carrying out this method

摘要

In order to correct the trajectory of a fin-stabilised missile, this missile is caused to oscillate intrinsically, according to the invention, by means of a control pulse. This intrinsic oscillation is either completely cancelled out again by means of a second control pulse, or a second intrinsic oscillation is induced which is superimposed on the first intrinsic oscillation in such a manner that the missile is bent in a predetermined manner for at least a short time. This bending is cancelled out again by two specific control pulses after completion of the correction process, so that there is no residual oscillation whatsoever. In this case it is not only possible to produce major changes in the trajectory, suddenly, using very simple means, but, once the control process has been completed, the trajectory and the missile longitudinal axis always point in the same direction, as a result of which the complexity required to control the projectile can be considerably reduced.