1. St. Vincent – St. Mary FRR Presentation NASA Student Launch Initiative

2. Final Launch Vehicle Dimensions Length: 127.6 in Diameter: 5.54 in Span Diameter: 19.0400 in Mass: 29.5 lbs. with ballast Center of Gravity: 82.1 in Center of Pressure: 90.4 in Static Margin: 1.5

3. Rocket Rocksim Drawing

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

5. 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

6. Rocket Flight Stability Margin 1.5 Thrust-to-Weight Ratio Rail Exit Velocity 38.09 ft/s 5.46

7. Mass Statement Our 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.

8. 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 25 ft l Descent Rate: 13.84 ft Drogue Chute – Cert-3 Area: 6.3 sq.ft Mass: 6.00 oz Descent Rate: 75.5ft/s

9. Kinetic Energy After drogue parachute is deployed Rocket SectionKinetic 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 deployed Rocket SectionKinetic 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

10. Predicted Altitude of Launch Vehicle Wind Speed (mph)Altitude (ft) 54468.5 104429.2 154359.4 204257.1

11. 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 15981.821616.572487.67 201309.102155.4223464.52

12. Test Plans and Procedures Tests – Airship inflation – Airship release from the rocket

13. Full Scale Flight Test Flight 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.

14. Final Payload Design Overview

15. Payload Integration The 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.

16. Recovery Testing Recovery System Testing Results Electronics/Ejection Test1(drogue1) 1.41g(12psi) Test2(main1).191g(4psi) Test3(main2).286g(6psi) Test4(drouge2).469g(4psi)

17. Interfaces RC-Airship RC-Airship Inflation System RC-Airship Disconnect Altimeter On/Off Switches

18. Status of Requirements Verification RequirementsStatus AltitudePending KECompleted Launch Readiness for 1 hourCompleted 8 foot long railCompleted Total Impulse <2560 n-sCompleted 10% BallastCompleted ½ Scale FlightsCompleted Drift RateCompleted GPSCompleted Full Scale test launchCompleted

19. Basic Funding Plan Company Sponsorships Travel est. $6,330 Ask for about $1000 if possible Major Companies- Timken, Birdgestone, Ohio Space Consortium, STVM

20. 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

21. 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

22. 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?

23. End