1. January 14, 2012

2.  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

3.  Single stage launch system  Duel deployment recovery system  Payload located within nose section airframe  Mirror angled for ground imaging

4.  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

5. *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

6.  Rail Exit Velocity: 95.95 ft/s  Thrust-to-Weight Ratio: 11.99

7.  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

8. Main ParachuteDrogue Parachute Size (in. diameter) 72 (deployed at 700 ft) 36 (deployed at apogee) Harness Typerip-stop nylon shock cord Harness Size (in. thickness) 11 Harness Length (ft.) 1512 Descent Rates (ft/s) 27.8249.77

9. Descent (ft-lbf)Landing (ft-lbf) Section 16905.532157.62 Section 21123.34350.99 Section 35650.781765.58  Section 1: Fin Section  Section 2: Coupler Section  Section 3: Nose Section

10. Wind Speed Model (MPH) Max Altitude (ft)Range at Landing (ft) Calm (0-2)5250.62130.66 Light (3-7)5246.59239.93 Slightly Breezy (8-14) 5147.871740.32 Breezy (15-25)4988.871906.16

11.  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

13.  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

14.  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

15.  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

16.  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

17.  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

18. Thank you.