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

Final Launch Vehicle DimensionsLength: 123.3748 inDiameter: 5.5512 inSpan Diameter: 19.0400 inMass: 26.49 lbsCenter of Gravity: 77.5333 inCenter of Pressure: 85.5750 inStatic Margin: 1.582

Rocket Rocksim DrawingKey Design FeaturesDual altimeters Payload piston ejection systemAirship inflation systemBoat-tail Airship release system

Final Motor ChoiceThe 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 stabilityRocket Flight Stability1.58

Thrust-to-Weight Ratio5.595Rail Exit Velocity53 ft/sMass StatementOur 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. Parachutes and Recovery HarnessMain Chute Skyangle Size 7 Recovery Harness Area: 56.8 sq.ftType: Tubular NylonMass: 40.9132 ozSize: 5/8 in w x 7 ft lDescent Rate: 13.72 ft/sLength: 70 in Drogue Chute Cert-3Area: 6.3 sq.ftMass: 6.00 ozDescent Rate: 83.61 ft/sKinetic EnergyRocket Descent Weight(lbm)Descent Velocity(ft/sec)KE (ft lbf)23.413.6167.30Predicted Drift from the Launch PadWind Speed (mph)Drift Drogue (ft)Drift Main (ft)Total Drift (ft)00.000.000.005327.27538.86866.1310654.551077.711732.2615981.821616.572598.39201309.102155.4223464.52Test Plans and ProceduresTestsAirship inflationVideo testingAirship release from the rocketScale Model Flight TestThe 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.

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.Final Payload Design Overview

Payload IntegrationThe 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.

Piston Ejection Testing

InterfacesRC-AirshipRC-Airship Inflation SystemRC-Airship Disconnect Video-Ground StationAltimeter On/Off Switches

Status of Requirements VerificationRequirementsStatusAltitudePending KECompleted Launch Readiness for 1 hourCompleted8 foot long railCompletedTotal Impulse