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St. Vincent – St. Mary CDR Presentation

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

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

  2. 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

  3. Rocket Rocksim Drawing

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

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

  7. 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.

  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 7 ft l Descent Rate: 13.72 ft/s Length: 70 in Drogue Chute – Cert-3 Area: 6.3 sq.ft Mass: 6.00 oz Descent Rate: 83.61 ft/s

  9. Kinetic Energy

  10. Predicted Drift from the Launch Pad

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

  12. 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.

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

  14. Final Payload Design Overview

  15. 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.

  16. Piston Ejection Testing

  17. Interfaces • RC-Airship • RC-Airship Inflation System • RC-Airship Disconnect • Video-Ground Station • 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, Goodyear, Lockheed Martin, Boeing

  20. Project Funding • Timken: $750 • Magni-Power: $250 • Ohio Aerospace Institute: $1500 (pending) • Expecting 15% profits- Buffalo Wild Wings • Lockheed Martin- possible contact, $ • Metallic Resources, Inc.: expecting $500 • Expected Total to Date: $3500

  21. Fundraising Methods • Letters sent with flyers and press release- 30 letters pending • 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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