ADVANCED INTEGRATED FUZING AND MULTIMODE GUIDANCE SYSTEM

INTEGRATED FUZING AND MULTIMODE GUIDANCE ALGORITHMS ARE PROPOSED THAT INCLUDE A FIFTH-STATE ESTIMATOR TO SUPPLY THE AIRFRAME CONTROL INFORMATION TO GUIDE A MISSILE TO A PREDEFINED ORIENTATION, AND HENCE AID IN FUZING AND DETONATION OF AIMED WARHEADS BY REDUCING TARGET MODELING REQUIREMENTS AND ELIMINATING ENHANCED IMAGE INFORMATION REQUIREMENTS. BY DECOUPLING TARGET AND MISSILE MOTION AND USING THAT INFORMATION TO CREATE FURTHER PREDICTIVE TERMS, THE SYSTEM IS ABLE TO OVERCOME SUCH PROBLEMS AS JAMMING NEAR INTERCEPT, AND CAN INCREASE THE KILLPROBABILITY WHEN THE MISSILE VELOCITY ANGLE IS PREDICTED AND EMPLOYED IN AIMED WARHEAD APPLICATIONS. A THREE PHASE RESEARCH PROGRAM IS PROPOSED FOR WHICH THE ULTIMATE OBJECTIVE IS TO DEVELOP AN INTEGRATED SENSING, ESTIMATION, GUIDANCE AND FUZING ENGINEERING DESIGN AND EVALUATION CAPABILITIES TO SUPPORT ADVANCED MISSILE SYSTEM ENGINEERING EFFORTS. IMPROVED GUIDANCE PERFORMANCE, THROUGH REMOVAL OF THE LOS RATEBIAS EFFECTUSING THE PROPOSED SYSTEM, IS MANIFESTED IN A NUMBER OF WAYS, INCLUDING REDUCED MISS DISTANCE, REDUCED TENDENCY FOR THE MISSILE TO OSCILLATE ABOUT A NULL VALUE OF THE LOS RATE, AND REDUCED MISSILE RESPONSE TIME. THE DELIVERABLE FOR PHASE I WILL BE AN INTEGRATEDDESIGN METHODOLOGY CONSISTING OF ALL RELEVANT ALGORITHMS FOR THE SENSING, ESTIMATION, GUIDANCE AND FUZING OF THE ADVANCED MISSILE. THE EFFECTIVENESS OF THE DESIGN METHODOLOGY SHALL BE DEMONSTRATED VIA A DESIGN SAD SIMULATION EFFORT ON A GENERIC A DOF MISSILE MODEL. IN PHASE II, THE INTEGRATION SENSING, ESTIMATION, GUIDANCE AND FUZING DESIGNAND EVALUATION CAPABILITY WILL BE DEVELOPED. IN PHASE III, APPROPRIATE HARDWARE TOGETHER WITH THE CORRESPONDING VALIDATED SOFTWARE SHALLBE IMPLEMENTED SO AS TO DEMONSTRATE THE DESIGN CAPABILITY.