Infrared detection system for use in early stages of missile launching

Claim 1

A METHOD OF IMPROVING THE ACQUISITION CAPABILITIES OF A MISSILE TRACKING SYSTEM COMPRISING THE STEPS OF SENSING RADIATION EMANATING FROM THE ENGINES OF A MISSILE WITH AN INFRARED SENSITIVE DEVICE LOCATED UPON THE ELECTRICAL AXIS OF THE ANTENNA OF A TRACKING SYSTEM; OBTAINING SIGNALS INDICATIVE OF ENERGIZATION OF THE INDIVIDUAL QUADRANTS OF THE INFRARED SENSITIVE DEVICE; COMPUTING THE RELATIVE POSITIONS OF THE ANTENNA AND THE MISSILE FROM SIGNALS PRODUCED BY THE INFRARED TRACKING DEVICE; COMPUTING AN AZIMUTH ANGLE DISPLACEMENT ERROR SIGNAL BY ADDING TOGETHER CERTAIN ONES OF THE QUADRANT SIGNALS; COMPUTING AN ELEVATION ANGLE DISPLACEMENT ERROR SIGNAL BY ADDING TOGETHER CERTAIN OTHER ONES OF THE QUADRANT SIGNALS; APPLYING THE AZIMUTH AND ELEVATION ERROR SIGNALS TO CONTROL CIRCUITRY WITHIN THE TRACKING SYSTEM WHEREBY THE ANTENNA MOVES IN A MANNER SUCH THAT THE MISSILE PATH IS FOLLOWED THEREBY; COMPUTING A REFERENCE SIGNAL INDICATIVE OF THE LEVEL OF RADIATION SENSED BY THE INFRARED DEVICE BY ADDING TOGETHER STILL OTHER ONES OF THE QUADRANT SIGNALS; AND DEENERGIZING THE INFRARED SENSITIVE DEVICE UPON RECEIPT OF RELIABLE SIGNALS FROM SOME OTHER TRACKING MEANS FORMING A PORTION OF THE SYSTEM.

Claim 2

A METHOD OF IMPROVING THE ACQUISITION CAPABILITIES OF A MISSILE TRACKING SYSTEM COMPRISING THE STEPS OF SENSING RADIATION EMANATING FROM THE ENGINES OF A MISSILE WITH AN INFRARED SENSITIVE DEVICE LOCATED UPON THE ELECTRICAL AXIS OF THE ANTENNA OF A TRACKING SYSTEM; OBTAINING SIGNALS INDICATIVE OF ENERGIZATION OF THE INDIVIDUAL QUADRANTS OF THE INFRARED SENSITIVE DEVICE; COMPUTING THE RELATIVE POSITIONS OF THE ANTENNA AND THE MISSILE FROM SIGNALS PRODUCED BY THE INFRARED TRACKING DEVICE; COMPUTING AN AZIMUTH ANGLE DISPLACEMENT ERROR SIGNAL BY ADDING TOGETHER CERTAIN ONES OF THE QUADRANT SIGNALS; COMPUTING AN ELEVATION ANGLE DISPLACEMENT ERROR SIGNAL BY ADDING TOGETHER CERTAIN OTHER ONES OF THE QUADRANT SIGNALS; APPLYING THE AZIMUTH AND ELEVATION ERROR SIGNALS TO CONTROL CIRCUITRY WITHIN THE TRACKING SYSTEM WHEREBY THE ANTENNA MOVES IN A MANNER SUCH THAT THE MISSILE PATH IS FOLLOWED THEREBY; COMPUTING A REFERENCE SIGNAL INDICATIVE OF THE LEVEL OF RADIATION SENSED BY THE INFRARED DEVICE BY ADDING TOGETHER STILL OTHER ONES OF THE QUADRANT SIGNALS; AND DEENERGIZING THE INFRARED SENSITIVE DEVICE UPON RECEIPT OF RELIABLE SIGNALS FROM SOME OTHER TRACKING MEANS FORMING A PORTION OF THE SYSTEM.