Missile tracking device

Abstract

A device for seeking and tracking targets from airborne missiles, which comprises one or two optical sensing units, each comprising a sensor barrel covered by a dome, a detector, drive means for rotating the sensor barrel about two perpendicular axis, and a processor for processing the signals produced by the detector and guiding the missile accordingly. The drive means comprise two motors for imparting to the barrel a pitching and a rolling motion. To eliminate aerodynamic drag, each sensing unit may be displaceable between a position retracted within the missile envelope and an extended position, in which part of its dome extends from the missile envelope. When two sensing units are provided, a target is tracked by operating only one of them, and when the target moves out of its field-of-regard, deactivating it and activating the other unit to continue tracking the target. When the sensing units are displaceable, they are in retracted position when the missile is launched, and, when the intended target is at close enough range, the unit on the side of the target is extended outside the missile envelope.

1 . Seeker and tracker device for airborne missiles, which comprises: 
 I—at least an optical sensing unit comprising a sensor barrel;    II—a dome, projecting from the side of the missile and covering said sensor barrel, said barrel extending into said dome beyond the side surface of the missile;    III—a detector;    III—drive means for rotating said sensor barrel about two perpendicular axis; and    IV—a processor for processing the signals produced by the detector and guiding the missile accordingly.    
     
     
         2 . Device according to    claim 1   , wherein the sensor barrel has an axis in a transverse plane of the missile.  
     
     
         3 . Device according to    claim 1   , wherein the detector is coaxial with the missile and provided with an ocular lens.  
     
     
         4 . Device according to    claim 1   , further comprising drive means for the sensing unit, which drive means comprise a pitch motor for imparting to said barrel a pitching motion, and a roll motor for imparting to said barrel a rolling motion.  
     
     
         5 . Device according to    claim 3   , wherein the sensor unit comprises an objective lens, and which further comprises optical deviating means for transmitting the optical signals sensed by said objective lens to the detector, which receives them through the ocular lens.  
     
     
         6 . Device according to    claim 1   , comprising at least two sensing units are provided, angularly spaced about the periphery of the missile.  
     
     
         7 . Device according to    claim 6   , comprising two sensing units which are coaxial and on opposite sides of the missile.  
     
     
         8 . Device according to    claim 6   , her comprising optical means for selectively rendering one or the other of the sensing units operative, by directing to the detector only the optical signals originating from it.  
     
     
         9 . Device according to    claim 6   , further comprising shutter means for preventing optical signals, received by the sensing unit that is not operative, from interfering with the optical signals transmitted by the operative sensing unit.  
     
     
         10 . Device according to    claim 7   , wherein each of the two sensing units has a field-of-regard that approaches 180×360°.  
     
     
         11 . Device according to    claim 1    or    6   , wherein the sensing units are located in an intermediate portion of the missile and antenna means, chosen from a radar antenna dish and conformal antenna strips, is housed in the portion of the missile forward of the sensing units.  
     
     
         12 . Device according to    claim 1    or    6   , further comprising cooling means for the sensing unit, which comprise a cowling for directing a flow of coolant fluid to the rear surface of the dome and motor and transmission means for rotating the dome about its axis, whereby every portion of its surface in turn will come into contact with the coolant.  
     
     
         13 . Device according to    claim 12   , wherein a gap is left between the fore edge of the cowling and the rear surface of the dome, to permit the cooling fluid to be discharged to the environment.  
     
     
         14 . Method of tracking targets from missiles, which comprises providing in the missile two optical sensors having complementary and symmetrical fields-of-regard; tracking a target by means of an operative optical sensor while maintaining the other sensor inoperative; and when a target moves out of the field-of-regard of said operative optical sensor, deactivating it and activating the other optical sensor to continue tracking the target.