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St. Vincent St. Mary CDR Presentation NASA Student Launch Initiative

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Final Launch Vehicle Dimensions Length: 123.3748 in Diameter: 5.5512 in Span Diameter: 19.0400 in Mass: 26.49 lbs Center of Gravity: 77.5333 in Center of Pressure: 85.5750 in Static Margin: 1.58

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Rocket Rocksim Drawing

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Key Design Features Dual altimeters Payload piston ejection system Airship inflation system Boat-tail Airship release system

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Final Motor Choice The final motor we are using on our full scale rocket is a Cessaroni K660. We chose the K660 because it has the ideal thrust for our full scale rocket design. The motor also has a fast burn time, allowing the rocket to reach maximum speed faster and provide better launch stability

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Rocket Flight Stability 1.58 Thrust-to-Weight Ratio 5.595 Rail Exit Velocity 53 ft/s

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Mass Statement Our mass margin is zero ( We are overweight) The rocket weighs about 26.49 pounds. The rocket is at its limit on weight, any more and it will be hard to reach the expected eight.

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Parachutes and Recovery Harness Main Chute Skyangle Size 7 Recovery Harness Area: 56.8 sq.ftType: Tubular Nylon Mass: 40.9132 ozSize: 5/8 in w x 7 ft l Descent Rate: 13.72 ft/sLength: 70 in Drogue Chute Cert-3 Area: 6.3 sq.ft Mass: 6.00 oz Descent Rate: 83.61 ft/s

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Kinetic Energy Rocket Descent Weight (lbm) Descent Velocity (ft/sec) KE (ft lbf) 23.413.6167.30

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Predicted Drift from the Launch Pad Wind Speed (mph) Drift Drogue (ft) Drift Main (ft) Total Drift (ft) 00.00 5327.27538.86866.13 10654.551077.711732.26 15981.821616.572598.39 201309.102155.4223464.52

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Test Plans and Procedures Tests Airship inflation Video testing Airship release from the rocket

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Scale Model Flight Test The half scale was changed several times over the past few months. The first version that was built was flown with a G88 Cessaroni motor. This motor proved to be very underpowered for the size and weight of the rocket. The rocket shot up 502ft (stably) and hurtled to earth, just narrowly deploying its parachute before going into the ground.

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Scale Model Flight Test Cont. Logically, a higher-powered motor was needed. The half-scales next attempt ended with a weathercocked flight that landed in a tree. The next launch did exactly the same thing, because of the higher wind speed, the strange trajectory was repeated.

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Final Payload Design Overview

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Payload Integration The airship will sit in the top of the forward rocket body tube and will rest on the main parachute. Below the main parachute is a rocket body tube coupler and bulkhead that will serve as a piston to push out the main parachute, airship, and nose cone.

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Piston Ejection Testing

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Interfaces RC-Airship RC-Airship Inflation System RC-Airship Disconnect Video-Ground Station Altimeter On/Off Switches

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Status of Requirements Verification RequirementsStatus AltitudePending KECompleted Launch Readiness for 1 hourCompleted 8 foot long railCompleted Total Impulse