2-27] 



ANALYSIS OF THE CONVERSION PROBLEM 



117 



Defined by 

 Prior Study" 



Probability of 



Conversion 



System Model 



P (Achieved) 



P, = 0.825 



Fixed Elements 



Heading Errors 

 at Lock-on 

 Target Characteristics 

 Interceptor Charac- 

 teristics 



Pilot Characteristics 



Assumed 



System 



Goal 



(Para. 2.22) 



— System 

 Deficiencies 



Variable Elements 



Al Radar 



Lock-on Range 

 Look Angle 

 Stabilization 

 Display 

 Tracking Ace. 

 Dynamic Range 



Attack Doctrine 



Missile Launch 

 Requirements 



Study Output 

 Fig. 2-39 Plan for the Analysis of Conversion Probability. 



1. The minimum required AI radar lock-on range 



2. The fire-control computer requirements 



3. The attack display requirements 



4. The missile launching and illumination requirements 



5. The radar tracking and stabilization requirements 



Attack Phase System Logic. The flow of information and the 

 allocation of function during the attack phase are shown in Fig. 2-40. 

 Following AI radar lock-on, the AI radar measures target range, lead angle. 



Target 

 Input 



AI 

 Radar 



Measured 



Target 



Info 



Aircraft 

 Flight 1^— 

 Data 



(Speed, Altitude, etc.) 



Fire 



Control 



Computer 



Auxiliary 

 Signals 



1 



1. 



Error 

 Signal 



Display 



Aircraft 



Control I — I Aircraft 



System 



Aircraft Heading 



Aircraft 

 Heading 





Missile 

 System 



Fig. 2-40 Interceptor System Logic Diagram During Attack Phase. 



