2-27] 



ANALYSIS OF THE CONVERSION PROBLEM 



19 



STEP 3. 



STEP 4. 



The target is assumed to have two possible types of trajectories 

 during the weapon time of flight: (a) a straight line, and (b) a 

 maneuver at the maximum permissible target aircraft load 

 factor. These trajectories can be plotted as functions of time 

 after weapon launch. 



Now we may plot the missile performance diagram on a 

 transparent sheet, using the same scale as the target and firing 

 circle diagram. The origin of the missile performance diagram 

 is made to coincide with a point on the firing circle. The missile 

 performance diagram overlay can then be rotated with respect 

 to the target and firing circle diagram to determine the maxi- 

 mum aiming errors that would still permit interception of the 

 target by the guided missile. An interception is defined as any 

 point within the missile performance contour where a missile 

 time-of-flight line and the time marker on the target trajectory 

 are equal. This procedure may be repeated for a number of 

 points on the firing circle. 



STEP 5. The foregoing steps may be repeated for a number of assumed 

 ranges-to-impact and for all the assumed altitude and speed 

 conditions. Using maximum allowable aiming error as a 

 parameter, we may plot range against angle off the target's nose 



50 



40 



30 



20 



10 



12 LU 



10 o 



s 



'I 

 4 5 



S 





 Head-On 



30 



60 



90 120 150 



Beam 

 ANGLE OFF TARGET'S NOSE, d (deg) 



180 



♦ 



Tail-On 



Fig. 2-42 Missile Launch Zones and Launching Tolerances; 50,000-Ft Altitude. 



