university of north dakota frozen fury preliminary design review
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University of North Dakota Frozen Fury Preliminary Design Review. October 29, 2012. 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.

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general vehicle dimensions
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
materials justifications
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
materials justifications1
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)
design justifications
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
static margin wind effects
Static Margin / Wind Effects

*The center of gravity is forward of the center of pressure (closer to the nosecone)

vehicle safety
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
vehicle testing
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
baseline motor selection and justification
Baseline motor selection and justification


  • 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
thrust to weight ratio
Thrust-to-weight ratio

S1: 340N/11.22lbs(

S2: 307/132.62oz

motor safety
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.
lv verification and test plan overview
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
recovery system
Recovery system
  • Dual Deployment
    • Drogue chute and main chute
  • Black powder charges will be calculated using and verified with ground testing
  • 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
payload concept
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.
payload design
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
    • IMU
    • GoPro Hero3 camera
    • Ground based targets
      • Fluorescent flags of 1sq. Meter
payload concerns
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
success criteria
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.
educational engagement
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.
educational engagement1
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.