OPTIMAL TRAJECTORY SHAPING GUIDANCE DESIGN FOR THE HAVE DASH II MISSILE

AMERICAN GNC CORPORATION (AGNC) HEREBY PROPOSES AN INTEGRATED SCHEDULE OF MODELING, DESIGN, ANALYSIS, SIMULATION, AND EVALUATION (MDASE) OF THE PROBLEM OF MIDCOURSE AND TERMINAL GUIDANCE OF THE HAVE DASH II MISSILE. THE GUIDANCE FORMULATION INCORPORATES OBJECTIVES PERTAINING TO MINIMUM TIME, MAXIMUM VELOCITY, MAXIMUM TARGET ACQUISITION, AND MINIMUM JAMMING EFFECTS. THE OPTIMAL TRAJECTORY SHAPING GUIDANCE SYSTEM, WHICH IS DERIVED BASED ON AN ANALYTICAL SOLUTION AND SINGULAR PERTURBATION METHOD, ACHIEVES THE FOLLOWING ADVANTAGES: (1) COMBINED MINIMUM TIME AND MAXIMUM TERMINAL SPEED FOR INCREASING SURVIVABILITY OF THE LAUNCHING PLATFORM AND MAXIMUM MANEUVERABILITY OF THE MISSILE AT THE ENDGAME, (2) ROBUSTNESS AGAINST TERMINAL CONDITIONS SUCH AS TARGET ZONE UNCERTAINTY, JAMMING, AND TARGET MANEUVER, AND (3) COMPATIBILITY WITH THE TERMINAL GUIDANCE LAW, WHICH, IN TURN, SIMPLIFIES THE IMPLEMENTATION AND AVOIDS MODE SWITCHING EFFECTS. IN PHASE I THE OPTIMAL TRAJECTORY SHAPING GUIDANCE WILL BE APPLIED TO THE AIR FORCE HAVE DASH II MISSILE SYSTEM. THE PERFORMANCE THROUGH EXTENSIVE SIMULATIONS, WILL BE QUANTIFIED AND COMPARED WITH EXISTING DESIGNS. THE MIDCOURSE GUIDANCE AND TARGET ACQUISITION PROBLEMS WILL BE SIMULTANEOUSLY ADDRESSED BASED ON THE EXISTING TRAJECTORY SHAPING FRAMEWORK. THE ASSOCIATED SOFTWARE WILL BE DEVELOPED AND DELIVERED. IN PHASE II THE GUIDANCE LAW IS DEMONSTRATED IN A HARDWARE-IN-THE- LOOP ENVIRONMENT.