Method for steering a missile towards a flying target

Abstract

A method steers a missile towards a flying target. In order to permit precise flight to the target even under poor visibility conditions owing to the weather, a radar which is remote from the missile detects the target and transmits data relating to a first location area of the target to the missile. The missile determines, from the data of its own missile radar, a second location area of the target, processes both location areas to form a target area and flies to the target area.

1 . A method for steering a missile towards a flying target, which comprises the steps of:
 detecting, via a remote radar being remote from the missile, the flying target and transmitting data relating to a first location area of the flying target to the missile;   determining, via the missile, from data of its own missile radar, a second location area of the flying target;   processing both the first and second location areas to form a target area; and   flying the missile to the target area.   
     
     
         2 . The method according to  claim 1 , which further comprises combining position-resolved location probabilities of the flying target in the first and second location areas in the missile to form a superordinate, position-resolved location probability. 
     
     
         3 . The method according to  claim 2 , which further comprises:
 measuring, via the missile radar, a distance from the flying target; and   linking the position-resolved location probability of the first location area to a location probability resulting from a distance measurement.   
     
     
         4 . The method according to  claim 2 , wherein the missile has at least three forward-oriented radar sensors, and the forward-oriented radar sensors each monitor just one spatial segment of at least three spatial segments lying one next to another. 
     
     
         5 . The method according to  claim 4 , which further comprises:
 determining the spatial segment with a highest segment probability of the flying target being disposed in the spatial segment from signals; and   using a segment probability during a determination of the position-resolved location probability of the flying target in the target area.   
     
     
         6 . The method according to  claim 4 , which further comprises using the missile radar as a direction-sensitive proximity sensor for controlling direction-dependent firing of a charge of the missile within a predetermined distance of the missile from the flying target. 
     
     
         7 . The method according to  claim 6 , which further comprises determining the spatial segment in which the flying target is disposed as the missile flies past the flying target, and firing of a explosive charge is controlled at least largely into the spatial segment. 
     
     
         8 . The method according to  claim 1 , wherein directional control of a flight of the missile takes place in an alignment phase by means of the data of only the remote radar, in a subsequent middle phase only by linking the data of the remote radar and that of the missile radar, and in a subsequent final phase by linking the data of the missile radar and of an image-resolving IR homing system of the missile. 
     
     
         9 . The method according to  claim 1 , which further comprises providing the missile with an infrared (IR) homing system having two-dimensional resolution, and the missile flies at least largely under radar control to the target area before the flying target can be sighted optically in the IR homing system, and after optical detection of the flying target by the IR homing system the missile flies at least largely under optical control to the flying target. 
     
     
         10 . The method according to  claim 1 , which further comprises providing the missile with an infrared (IR) homing system having two-dimensional resolution, and a position of the second location area of the flying target, which is determined by the missile radar, is used to control a viewing direction of the IR homing system relative to a missile axis. 
     
     
         11 . The method according to  claim 1 , which further comprises providing the missile with an infrared (IR) homing system having two-dimensional resolution, and the missile is steered to the flying target with data of the IR homing system by proportional navigation, and a distance and/or approach speed of the missile to the flying target, which are determined by the missile radar, are used as parameters for controlling a flight of the missile. 
     
     
         12 . The method according to  claim 11 , which further comprises using the parameter as an agility parameter of a surface control system. 
     
     
         13 . A missile, comprising:
 a missile radar;   an infrared (IR) homing system with two-dimensional resolution;   control surfaces for controlling a steered flight of the missile; and   a control unit for generating steering signals from data received from said missile radar and said IR homing system for actuating said control surfaces with said control signals.   
     
     
         14 . The missile according to  claim 13 , further comprising at least three forward-oriented radar sensors each defining a scanning region lying in each case in just one spatial segment of at least three spatial segments lying one next to one another. 
     
     
         15 . The missile according to  claim 14 , further comprising:
 a missile head;   a missile body; and   a transition cone, said forward-oriented radar sensors are disposed in a region of said transition cone between said missile head and said missile body.