University of North Dakota Frozen Fury Preliminary Design Review

1. University of North Dakota Frozen FuryPreliminary Design Review October 29, 2012

2. General Vehicle Dimensions • Length: 108.50 inches • Diameter: 6 inches • Mass: 277.42 oz. / 17.34lbs. • Span: 18 inches • Center of Gravity: 80.52 inches • Center of Pressure: 69.28 • Safety Margin: 1.87

3. Flight Profile

4. Flight Profile

5. Materials & Justifications • Airframe – carbon fiber • superior strength to weight ratio • Ease of workability • Fins – birch plywood in carbon fiber • Combines the strength of both materials for a more rigid, strong, and lightweight fin • Bulk-Head/Centering ring – 0.5 inch birch plywood • Cabinet quality grain, few knots, and locally available

6. Materials & Justifications • Nosecone • Will be purchased to insure proper functionality • West Systems Epoxy • Used to bind the above materials together as well as some hardware (bolts, nuts, threaded rods)

7. Design Justifications • Fins – symmetric shape and quantity allows for ease of construction, trapezoidal shape limits potential damage to fins upon landing • Diameter – 6” diameter allows for ease of assembly and plenty of work space. • Also allows for better utilization of scrap components, and expansion of internal components if necessary

8. Static Margin / Wind Effects *The center of gravity is forward of the center of pressure (closer to the nosecone)

9. Plan for Vehicle Safety Verification and Testing

10. Vehicle Safety • Minimum velocity for stable flight: 43.9 ft/s • Exit rail velocity: 52.29 ft/s • A series of 3 rail beads will be used to ensure the rocket reaches adequate speed off of the rail while maintaining proper orientation

11. Vehicle Testing • A series of sub-scale launches are planned and will be conducted to verify design • Construction and test of the sub-scale will take place from 11/23-12/14 • Planning for construction of full-scale starting 12/14 • At least one test flight with the final rocket will take place

12. Baseline motor selection and justification Justifications • 54.0 mm diameter allows for easy down-scaling • Black Max Propellant provides the high visibility tracking of dense black exhaust 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

13. Thrust-to-weight ratio S1: 340N/11.22lbs( S2: 307/132.62oz

14. Motor safety • The handling of the motors, including purchasing and assembly, will be under the supervision of our NDRA members. • North Dakota Rocketry Association (NDRA) Section #628 • Certified NDRA team mentor: • Dr. Tim Y. #76791 Level 2 • We are planning to test fire the K828 motor in our static ground test. We are not planning a test of the sub-scale motor.

15. LV Verification and Test Plan Overview • Sub-scale launch – November 23rd to December 14th • Full-scale test flight #1 – February 22nd to March 8th • Full-scale test flight #2 – March 18th to April 11th • Final launch – April 21

16. Recovery system • Dual Deployment • Drogue chute and main chute • Black powder charges will be calculated using vernk.com and verified with ground testing

17. Avionics • Duel deployment system • Two MAWD altimeters used for redundancy • Measures barometric pressure • “Mach” delay for safety • Deploys drogue parachute at apogee • Deploys main parachute at 700 ft AGL • Will be programmed and Pre-tested for scale launch

18. Payload Concept • NASA Science Mission Directorate (SMD) Sensory Array/Horizon Camera. • The payload is designed around the Arduino Mega 2560 prototyping platform and four different sensors with a data logger • Visual Aerial Locator Rocket (VALOR) Payload • Integration of an inertial measurement unit (IMU) and a high resolution camera in order to determine the precise location of predetermined objects within the increased visual field of the rocket as it approaches apogee.

19. Payload design • 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

20. Payload verification and test plan overview

21. Payload concerns • Video camera is as of yet undecided • Video quality due to vibration • Integration with IMU data • Exposing sensors to the environment • Affect on data obstructed by the airframe • Data storage – there will be a lot of HD high-res, high-speed data to handle • Mounting a rotating structure– difficult to adjust/control

22. Success criteria • Rocket launch • Reaching an altitude at apogee within ± 3.00% of 5280 feet • Rocket recovery • The recovery system deploying properly at the appropriate altitude and recovering the rocket on the ground such that it is deemed reusable for future launches • Payload • The collection of usable data to complete the SMD and VALOR payload objectives.

23. Educational Engagement • Physics Day at UND - November 12, 2012 • This is a program for local middle school to high school students to learn about the many different facets of physics. • We will give a presentation about rocketry • Introduce them to the USLI program and share our past history with the competition • Display rockets from the previous years • Split the students into groups and have them build simple rockets to see which group will fly the highest • Have a Q & A session • Expect to reach about 50-100 students.

24. Educational Engagement • Outreach at Grand Forks Area middle school • Our team is in the process of scheduling a date to visit the local middle schools. • For an entire day, we will teach a science class. • Give a brief lecture about rocketry • Prior to us visiting, we will have the students design rockets out of 2 liter pop bottles. • We will supervise and moderate the launch water rockets • Have a Q & A session on why some rockets did work and other did not. • Expect to reach about 30-80 students.

25. Questions?