DEMONSTRATION DESIGN

THIS ACTIVITY WILL DEFINE A LOW COST DEMONSTRATION TO BE USED AS A PROOF OF PRINCIPLE OF MID AIR SEPARATION STABILITY. THE LAUNCH DYNAMICS OF THE LAUNCH TUBE TO MISSILE CANISTER AND THE MISSILE CANISTERTO MISSILE IS A VERY COMPLEX TECHNICAL CHALLENGE. THIS IS ESPECIALLY TRUE WHEN THE LAUNCH ANGLE IS SIGNIFICANTLY DIFFERENT THAN VERTICLE, E.G. 45 DEG OFF VERTICLE. IN THIS PHASE A DETAILED ANALYSIS AND MODELING EFFORT WOULD BE CONDUCTED OF THE GAS DYNAMICS AND RESULTANT TUMBLING MOTION ASSOCIATED WITH OFF VERTICLE LAUNCH. ALL THE PREVIOUS RELATED WORK IN THIS AREA WOULD BE REVIEWED AS A BASIS FOR THE ANALYSIS. THE ICBM DEEP BASING GAS PROPELLED LAUNCHER FEASIBILITY DEMONSTRATION PROGRAM WOULD BE MONITORED FOR APPLICABLE DATA. IN PARTICULAR, THE ANALYSIS WOULD EXAMINE IN DETAIL A VARIETY OF OFFVEHICLE LAUNCH DYNAMICS INCLUDING 45 DEG. THE RESULTS OF THE ANALYSIS WOULD BE THE BASIS TO LAYOUT A DETAILED TEST PLAN FOR PHASE II. THE PHASE II WOULD CONTAIN A LARGE AMOUNT OF TESTING ON A LARGE NTS CENTRIFUGE. THIS TESTING WOULD INCLUDE THE LAUNCH TUBE/CANISTER AND CANISTER/MISSILE DYNAMICS. THE REASON FOR THE CENTRIFUGE IS TO ENSURE THE EFFECTS OF GRAVITY ARE CORRECTLY ACCOUNTED FOR IN THE TEST SITUATION OF A SCALED VERSION OF HARDWARE. THIS TECHNIQUE COULD BUILD UPON/VERIFY THE RESULTS OF THE PHASE I WITHOUT REQUIRING EXPENSIVE FULL SCALE HARDWARE. THE PHASE II PLAN WOULD BE DEVELOPED AND COSTED AT THE COMPLETION OF PHASE I.