Guidance of missiles

Claim 1

A MISSILE GUIDANCE SYSTEM COMPRISING A YAW DETECTION MEANS FOR MEASURING CHANGES IN DISTANCE FROM A PRESLECTED YAW PLANE WHICH EXTENDS THROUGH THE LAUNCH AND TARGET POINTS AND GENERATING SIGNALS INDICATIVE THEREOF; YAW COMPUTER AND CONTROL MEANS FOR CONVERTING SAID YAW SIGNALS INTO MISSILE YAW CONTROL SIGNALS TO KEEP SAID MISSILE IN SAID YAW PLANE; A FIRST PITCH DISTANCE DETECTION MEANS FOR MEASURING CHANGES IN DISTANCE ALONG AN AXIS IN SAID YAW PLANE PERPENDICULAR TO A PRESELECTED STRAIGHT LINE PITCH COURSE AND GENERATING FIRST PITCH SIGNALS INDICAIVE THEREOF; A SECOND PITCH DETECTION MEANS FOR MEASURING CHANGES IN DISTANCE ALONG A LINE IN THE YAW PLANE PERPENDICULAR TO A SECOND PRESELECTED STRAIGHT LINE COURSE AND GENERATING SECOND PITCH SIGNALS INDICATIVE THEREOF; A DIGITAL COMPUTER MEANS FOR DETECTING THE SIGNALS OF SAID FIRST AND SECOND PITCH DETECTION MEANS, SAID COMPUTER INCLUDING MEANS PRE-SET TO DEFINE A PREDETERMINED CONIC PATH RELATIONSHIP BETWEEN THE SAID SIGNALS, AND FURTHER INCLUDING COMPARISON MEANS, INCLUDING A COMMON REGISTER CONNECTED TO RECEIVE SAID SIGNALS TO COMPARE SAID CONIC PATH RELATIONSHIP WITH THAT BETWEEN SAID FIRST AND SECOND SIGNALS AND TO PRODUCE A DIFFERENTIAL OUTPUT; AND A PITCH CONTROL MEANS FOR POSITIONING THE MISSILE; SAID REGISTER PROVIDING AN OUTPUT TO SAID PITCH CONTROL MEANS TO CONTROL SAID MISSILE IN SAID CONIC PATH.