Download - St. Vincent – St. Mary FRR Presentation
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St. Vincent – St. Mary FRR Presentation
NASA Student Launch Initiative
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Final Launch Vehicle DimensionsLength: 127.6 inDiameter: 5.54 inSpan Diameter: 19.0400 inMass: 29.5 lbs. with ballastCenter of Gravity: 82.1 inCenter of Pressure: 90.4 inStatic Margin: 1.5
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Rocket Rocksim Drawing
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Key Design Features• Dual altimeters • Payload piston ejection system• Airship inflation system• Airship release system• Boat-tail
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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 stability
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Rocket Flight Stability Margin
1.5Thrust-to-Weight Ratio
Rail Exit Velocity38.09 ft/s
5.46
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Mass StatementOur mass margin is zero ( We are
overweight)
The rocket weighs about 29.5 pounds. The
rocket is at its limit on weight, any more and it will be hard to reach the expected height.
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Parachutes and Recovery HarnessMain Chute – Skyangle Size 7 Recovery Harness – Area: 56.8 sq.ft Type: Tubular NylonMass: 40.9132 oz Size: 5/8 in w x 25 ft lDescent Rate: 13.84 ft Drogue Chute – Cert-3Area: 6.3 sq.ftMass: 6.00 ozDescent Rate: 75.5ft/s
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Kinetic EnergyAfter drogue parachute is deployedRocket Section Kinetic Energy
(ft-lb)
Section 1(nose cone, forward payload tube, electronics bay, aft payload tube)
2048.58
Section 2(booster tube)
697.87
After main parachute is deployedRocket Section Kinetic Energy
(fl-lb)
Section 1(nose cone)
2.27
Section 2(forward payload tube, electronics bay, aft payload tube)
52.93
Section 3(booster tube)
18.81
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Predicted Altitude of Launch Vehicle
Wind Speed (mph) Altitude (ft)
5 4468.5
10 4429.2
15 4359.4
20 4257.1
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Predicted Drift from the Launch Pad
Wind Speed (mph)
Drift Drogue (ft)
Drift Main (ft)
Total Drift (ft)
0 0.00 0.00 0.005 327.27 538.86 866.1310 654.55 1077.71 1732.2615 981.82 1616.57 2487.6720 1309.10 2155.42
23464.52
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Test Plans and Procedures• Tests–Airship inflation–Airship release from the rocket
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Full Scale Flight TestFlight Information
• Motor Used: Cesaroni 1635k445
• Altitude: 2000 ft.
• The rocket was fired without the payload. Bags of sand were used as weights to simulate the payload in the rocket.
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Final Payload Design Overview
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Payload IntegrationThe main parachute will sit in the top
of the forward rocket body tube and will rest on the airship. Below the airship 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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Recovery TestingRecovery System Testing Results
Electronics/EjectionTest1(drogue1) 1.41g(12psi)
Test2(main1) .191g(4psi)
Test3(main2) .286g(6psi)
Test4(drouge2) .469g(4psi)
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Interfaces• RC-Airship• RC-Airship Inflation System• RC-Airship Disconnect • Altimeter On/Off Switches
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Status of Requirements VerificationRequirements StatusAltitude Pending KE Completed Launch Readiness for 1 hour Completed8 foot long rail CompletedTotal Impulse <2560 n-s Completed10% Ballast Completed½ Scale Flights CompletedDrift Rate CompletedGPS CompletedFull Scale test launch Completed
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Basic Funding Plan• Company Sponsorships• Travel est. $6,330• Ask for about $1000 if possible• Major Companies- Timken,
Birdgestone, Ohio Space Consortium, STVM
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Project Funding• Timken: $1000• Magni-Power: $250• Ohio Aerospace Institute: $1500• Metallic Resources, Inc. $100• Bridgestone:$1025• STVM:$1000• Therapeutic Associates: $250• NASA: $3700• Expected Total to Date: $8825
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Fundraising Methods• Letters sent with flyers and press
release- 30 letter• Phone calls/ emails- made after
letters sent• Presentation to companies• Sponsors listed on website and t-
shirts
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Educational Outreach• October 6th- Cub Scout Pack 3206 of
Medina• October 14th- IX Center• November 26th- St. Francis de Sales
School• December 7th- Sacred Heart of Mary
School• December 13th- St. Vincent Elementary• Goal of 100 met• Total of 360 students met so far• More to come?
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End