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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University of north dakota frozen fury preliminary design review

University of North Dakota Frozen FuryPreliminary Design Review

October 29, 2012

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.