MICROCOMPUTER-BASED EARTH-TO-ORBIT TRAJECTORY OPTIMIZATION PROGRAM

THE PRIMARY OBJECTIVE IS THE DEVELOPMENT OF AN EARTH-TO-ORBIT TRAJECTORY OPTIMIZATION PROGRAM CAPABLE OF ACCOMMODATING AIR BREATHING PROPULSION AND SUITABLE FOR PRELIMINARY DESIGN ANALYSIS. RAPID EXECUTION AND EASE-OF-USE ARE REQUIRED. A DUAL MODE APPROACH IS PROPOSED WITH THE FOLLOWING FEATURES: RAPID OPTIMIZATION MODE - PROVIDES ROBUST AND USER-FRIENDLY OPERATION FOR PRELIMINARY DESIGN TRADES AND ANALYSES. PRECISION MODE - UTILIZES RAPID MODE TO OBTAIN INITIAL GUESSES FOR FAST AND ROBUST CONVERGENCE. SERVES AS TRUTH MODEL FOR VERIFICATION OF RAPID MODE. DUAL MODE OPERATION - SYNERGISTICALLY ALLEVIATES SHORTCOMINGS OF INDIVIDUAL MODES. THE RAPID OPTIMIZATION MODE IS DELIVERED IN PHASE I. RESULTS FROM PRELIMINARY SIMULATION OF THE RAPID MODE ARE PROMISING. THE AT MICROCOMPUTER CAPACITY IS ADEQUATE WITH PRUDENT DESIGN. THE PROGRAM OFFERS SUBSTANTIAL IMPROVEMENT IN PRODUCTIVITY OVER CURRENT PERFORMANCE OPTIMIZATION PROGRAMS.