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CRITICAL DESIGN REVIEW Michigan Rocket Engineering Association USLI 2011-2012

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Final Vehicle Dimensions Total Length: 103 in Can Length: 52 in Airframe Diameter: 5.5 in Can Diameter: 2.5 in

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Key Design Features Butterfly valves Varies airflow through cans 4 Public Missile D-07 fins Preserves dual-axis symmetry Fin-through-can configuration Eases construction Allows for fillets

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Vehicle Sections Main Chute Avionics Bay Access Cut To nose To tail Motor/Fins

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Final Motor Selection Manufacturer: Cesaroni Motor Designation: L2375 Total Impulse:1093 lb-s Mass:Pre-Burn:9.4 lb Post-Burn:4 lb Retention System: Aero Pack RA75

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Rocket Flight Stability Unaltered margin of test rocket: CP: 74.5 in (RockSim) CG: 71.5 in (experimentally measured) Stability Margin: 0.55 Altered margin of test rocket: CP: 74.5 in (RockSim) CG: 66 in (measured after adding ~4lb to nose) Stability Margin: 1.55 Aiming for ~1.5 pre-launch Conservative because of unorthodox design

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Static Margin Diagram CP: 74.5665in from nosecone CG: 65.9427in from nosecone

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Thrust to Weight Ratio Average thrust of L2375 Average weight of rocket Average Thrust-to-Weight Ratio

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Rail Exit Velocity Assuming 6 x 1 x 1 rail Cesaroni L2375 Exit velocity = 81 ft/sec Test launch used 12 x 1 x 1 rail Final vehicle may use a similar rail

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