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University of North Dakota Frozen Fury Flight Readiness Review

University of North Dakota Frozen Fury Flight Readiness Review. March 18, 2013. Launch Vehicle Design and Dimensions. Length: 108.50 inches Diameter: 6 inches Mass: 276.272 oz. / 17.267 lbs. Span: 22 inches Center of Gravity: 69.693 inches Center of Pressure: 90.9737 inches

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University of North Dakota Frozen Fury Flight Readiness Review

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  1. University of North Dakota Frozen FuryFlight Readiness Review March 18, 2013

  2. Launch Vehicle Design and Dimensions • Length: 108.50 inches • Diameter: 6 inches • Mass: 276.272 oz. / 17.267 lbs. • Span: 22 inches • Center of Gravity: 69.693 inches • Center of Pressure: 90.9737 inches • Safety Margin: 3.55

  3. Key Design Features

  4. Motor Description • AeroTech K1050W • 54.0 mm diameter • 25 in. length • 1373.0 g propellant weight • 2259.0 g total weight • 1025.22 N average thrust • 1468.5 N peak thrust • 2522.04 N-s total impulse • 2.5 s thrust duration • White Lightning

  5. Flight Stability in Static Margin • Center of Gravity: 69.693 inches • Center of Pressure: 90.9737 inches • Rocket Diameter: 6 inches • (90.9737in.-69.693in.)/6in. = • Safety Margin: 3.55 *The center of gravity is forward of the center of pressure (closer to the nosecone)

  6. Thrust-to-Weight Ratio and Rail Exit Velocity • Rail Exit Velocity: 100.7412 ft/s • Thrust-to-Weight Ratio: 13.53

  7. Mass Statement*

  8. ParachuteSizes and Decent Rates

  9. Kinetic Energy • Section 1: Fin Section • Section 2: Coupler Section • Section 3: Nose Section

  10. Wind Drift Effects

  11. Test Plans and Procedures • Black Powder Charges Testing • Take place a week prior to launch • Altimeters • Payload Testing and Confirmation • Camera, Wiring, Storage Device, & Camera Mounts • Testing Tracking, Transmitter and Receiver • Testing of Batteries and Sensors • Full-scale flights

  12. Full Scale Flight Test

  13. Recovery System Tests • Black Powder Charges Testing • 2 charges in each section • Main: 2.65g and 3.00g • Drogue: 1.97g and 2g • Vacuum testing for Stratologger Altimeters • Pressure changes trigger altimeter activity • Discussion of full scale test flights results

  14. Summary of Requirements Verification (Launch Vehicle) • Deliver Payload to 5,280ft • We have simmed our rocket so that the apogee is around 5,319 feet. This will be verified with onboard altimeter readings. • Recovery System • The rocket will be equipped with two altimeters that will be activated by a switch on the exterior of the rocket. • The rocket will be tracked using a Rocket Hunter.

  15. Payload Design and Dimensions

  16. Interfaces with Ground Systems • AT-2B transmitter for tracking • XBee Pro 900 transmitter for data • Rocket Hunter Tracker • Laptop • 0.25” rail beads (interfaces with launch rail) • Electronics arming switch

  17. Requirements Verification (Payload) • Simulations indicate that the payload will reach an altitude near the 1 mile mark at subsonic speeds • Ground Testing • Test Launches • Comparisons to known values

  18. Questions? Thank you.

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