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University of North Dakota Frozen Fury Critical Design Review

University of North Dakota Frozen Fury Critical Design Review. January 14, 2012. Launch Vehicle Dimensions. Length: 108.50 inches Diameter: 6 inches Mass: 258.836 oz. / 16.177 lbs. Span: 22 inches Center of Gravity: 74.42 inches Center of Pressure: 90.86 inches Safety Margin: 2.74.

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University of North Dakota Frozen Fury Critical Design Review

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  1. University of North Dakota Frozen FuryCritical Design Review January 14, 2012

  2. Launch Vehicle Dimensions • Length: 108.50 inches • Diameter: 6 inches • Mass: 258.836 oz. / 16.177 lbs. • Span: 22 inches • Center of Gravity: 74.42 inches • Center of Pressure: 90.86 inches • Safety Margin: 2.74

  3. Key Design Features • Single stage launch system • Duel deployment recovery system • Payload located within nose section airframe • Mirror angled for ground imaging

  4. Final Motor Choice • AeroTech K828F-J • 54.0 mm diameter • 22.8 in. length • 1373.0 g propellant weight • 2223.0 g total weight • 862.88 N average thrust • 1303.79 N peak thrust • 2157.2 N-s total impulse • 2.5 s thrust duration • Black Max Propellant

  5. Flight Stability in Static Margin • Center of Gravity: 74.42 inches • Center of Pressure: 90.86 inches • Rocket Diameter: 6 inches • (90.86in.-74.42in.)/6in. = • Safety Margin: 2.74 *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: 95.95 ft/s • Thrust-to-Weight Ratio: 11.99

  7. Mass: Statement and Margin • Simulated weight is 16.177 lb loaded • Camera mass is 19 g each • Total camera mass of .17 lb • Total payload with batteries is estimated at 3 lb • Current motor allows for over 25% mass increase • Rocket design will accommodate larger motors as well

  8. Parachute, Harness, and Decent Rates

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

  10. Drifts from Launch Pad

  11. Test Plans and Procedures • Black Powder Charges Testing • Take place a week prior to launch • Altimeters • Static Test of Motor • Conducted at launch site • Payload Testing and Confirmation • Camera, Wiring, Storage Device, & Camera Mounts • Testing Tracking, Transmitter and Receiver • Testing of Batteries and Sensors • Full-scale flights starting in February • At least one test flight with the final rocket will take place

  12. Scale Model Flight Test

  13. Tests of Staged Recovery System • 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 • Full scale test flights

  14. Final Payload Design Overview • SMD • Arduino Mega2560 + Mircocontroller • BMP085 Pressure Sensor • TSL235R Light to Frequency Converter • UV Photodiodes JEC 0.3 A • GPS unit + Xbee pro 900 Wireless Transceiver • VALOR • IMU • GoPro Hero3 camera • Ground based targets • Fluorescent flags of 1sq. Meter

  15. Payload Integration • Design based on arduino ATmega2560 • Removable payload bays and sleds • Arming switches • Components will be friction fitted and sanded for precision fit. • Integration is planned for February 16 – February 22

  16. Interfaces: Internal and External • Internal • Friction fitted and secured with pins/screws • Aluminum rod for camera rotation • Mounts for all payload components • Quick-links for parachute connections • External • 0.25” rail beads • AT-2B transmitter for tracking • XBee Pro 900 transmitter for data • Electronics arming switch

  17. Status of Requirements Verification • Simulations indicate that the payload will reach an altitude near the 1 mile mark at subsonic speeds • Recovery system will have a drogue and main chute and be fully recoverable and reusable • The dual deployment recovery system requires further testing to guarantee proper altimeter function • Full-scale construction has commenced • Education outreach is ongoing

  18. Questions? Thank you.

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