Patent ID: 6382554
Filing Date: 2002-05-07
Classification: F41G

Abstract:
Method for guiding a missile (1) towards a target (2), the missile having information on its own position, velocity vector and further velocity characteristic and continuously receiving information on the position and velocity vector of the target, characterised in thatfrom the information which the missile has, a point of interception (A) is predicted at which the missile is expected to strike the target, a flight time is calculated which indicates the time it will take for the missile to travel to the predicted point of interception (A), from a given criterion for the trajectory characteristics of the missile a fictitious point of interception (B) is calculated, which is situated at a higher altitude than the predicted point of interception (A) and the distance (&Dgr;) of which to the latter point is related to the calculated flight time and the missile is guided towards the said fictitious point.