1 / 22

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

cairo-woods
Download Presentation

University of North Dakota Frozen Fury Flight Readiness Review

An Image/Link below is provided (as is) to download presentation Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author. Content is provided to you AS IS for your information and personal use only. Download presentation by click this link. While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server. During download, if you can't get a presentation, the file might be deleted by the publisher.

E N D

Presentation Transcript


  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.

More Related