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St. Vincent – St. Mary FRR Presentation

St. Vincent – St. Mary FRR Presentation . NASA Student Launch Initiative. Final Launch Vehicle Dimensions. Length: 127.6 in Diameter: 5.54 in Span Diameter: 19.0400 in Mass: 29.5 lbs. w ith ballast Center of Gravity: 82.1 in Center of Pressure: 90.4 in Static Margin: 1.5.

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St. Vincent – St. Mary FRR Presentation

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  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 5.46 Rail Exit Velocity 38.09 ft/s

  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.ft Type: Tubular Nylon Mass: 40.9132 oz Size: 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 After main parachute is deployed

  10. Predicted Altitude of Launch Vehicle

  11. Predicted Drift from the Launch Pad

  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

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

  18. Status of Requirements Verification

  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

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