university of north dakota frozen fury critical design review
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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. - PowerPoint PPT PresentationTRANSCRIPT
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January 14, 2012
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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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Single stage launch system Duel deployment recovery system Payload located within nose section
airframe Mirror angled for ground imaging
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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
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*The center of gravity is forward of the center of pressure (closer to the nosecone)
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
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Rail Exit Velocity: 95.95 ft/s Thrust-to-Weight Ratio: 11.99
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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
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Main Parachute
Drogue Parachute
Size (in. diameter)
72 (deployed at 700 ft)
36 (deployed at apogee)
Harness Type rip-stop nylon shock cord
rip-stop nylon shock cord
Harness Size (in. thickness)
1 1
Harness Length (ft.)
15 12
Descent Rates (ft/s)
27.82 49.77
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Descent (ft-lbf)
Landing (ft-lbf)
Section 1 6905.53 2157.62
Section 2 1123.34 350.99
Section 3 5650.78 1765.58
Section 1: Fin Section Section 2: Coupler Section Section 3: Nose Section
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Wind Speed Model (MPH)
Max Altitude (ft)
Range at Landing (ft)
Calm (0-2) 5250.62 130.66
Light (3-7) 5246.59 239.93
Slightly Breezy (8-14)
5147.87 1740.32
Breezy (15-25)
4988.87 1906.16
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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
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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
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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
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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
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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
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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
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Thank you.