ROCKET DELIVERED DISPERSED PENATRATOR TRAJECTORIES AND TERMINAL EFFECTS ASSESSMENT MODEL

PHASE I WILL PRODUCE AN INITIAL ROCKET PROPELLED, PENETRATOR DAMAGE EFFECTS MODEL. IT WILL BE COMPOSED OF COMPUTER PROGRAM ELEMENTS EXTRACTED FROM SIMILAR SUBMUNITION PROGRAMS FOR WHICH OTI HAS CURRENT TECHNICAL AND MAINTENANCE RESPONSIBILITY. A THREE-DIMENSIONAL, FOURTH ORDER RUNGE-KUTTA INTEGRATION TECHNIQUE WILL BE USED TO COMPUTE THE PATHS OF THE LAUNCH AIRCRAFT, THE ROCKET, THE PENETRATORS, AND THE MANEUVERING TARGET. THE ATTACKER, ROCKET AND TARGET CAN MANEUVER DURING THE ENCOUNTER. LAUNCH DISTURBANCES ON THE ROCKET ARE MODELED. AT DISPERSION, THE PENETRATORS FORMING THE BOUNDARIES OF THE PENETRATOR "CLOUD" ARE TRACKED. THE 3-DIMENSIONAL CLOUD ENCOUNTERS THE TARGET AND THE PART OF THE CLOUD SWEPT BY THE CRITICAL TARGET COMPONENTS IS EVALUATED TO DETERMINE HIT PROBABILITY AND SPEED AT THE TARGET. THE DAMAGE FUNCTION IS COMPUTED FROM EACH TARGET COMPONENT VULNERABILITY BASED ON IMPACT VELOCITY, TARGET MOTION, IMPACT DIRECTIONS, PENETRATOR MASS, AND THE NUMBER OF HITS. ONE OF FOUR AVAILABLE DISPERSION MECHANISM MODELS (DRAG ON THE ROCKET, SPIN, FORCED OR EXPLOSIVE EJECTION) WILL BE USED (WEAPON DEPENDENT). ONE OF TWO DAMAGE ASSESSMENT MODELS WILL BE USED (SAFE ESCAPE, OR AN ADAPTATION OF THE VULNERABLE TECHNIQUES USING JMEN METHODOLOGY).