1. U NIVERSITY OF F LORIDA I NTIMI GATOR PDR

2. O UTLINE Project Organization Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work

3. P ROJECT O RGANIZATION

4. O UTLINE Project Organization Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work

5. M ATERIAL AND D IMENSIONS Material: Blue tube Diameter: 6 inches Length: 115 inches Weight: 29 lbs ComponentWeight (lbs) Fins (2 with rollerons and 2 without)5 Pneumatics Bay1.5 Main Parachute/Shock Cord and Piston3 Avionics Bay3.25 Payload and Main Drogue Parachute Piston0.25 Payload Main Parachute and Housing4 Drogue Parachutes and Shock Cord1.5 Nosecone and Pressure Payload4.25 Body Tube6.25 Total29 SectionLength (in) Nosecone24 Upper Airframe44 Avionics Bay3 Mid Airframe16 Lower Airframe28

6. S YSTEM B REAKDOWN

7. S TATIC S TABILITY M ARGIN CG CP The center of pressure (CP) is located 89.16" from the nose tip The center of gravity (CG) is located 71.73" from the nose tip The static stability margin is 2.87 which is within the stable range of 1 to 3

8. 1-Slots in fin align with barrel bolts 2-Fin slides forward and down 3-Set screw holds fin in place F INS Fins and mount made from ABS plastic on a rapid prototype machine

9. O UTLINE Project Organization Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work

10. S CIENCE M ISSION D IRECTORATE P AYLOAD Rests in the upper airframe on top of the piston Ejects from the rocket at apogee Dual deployment recovery

11. S CIENCE M ISSION D IRECTORATE P AYLOAD Payload legs spring open upon ejection Electronics requiring sunlight are mounted on the lid Body made from blue tube in order to not interfere with measurements

12. S CIENCE M ISSION D IRECTORATE P AYLOAD D ESIGN 1 Arduino Microcontroller to sample analog sensors and read output from Weatherboard and GPS Analog sensors will be compared to the pre- programmed output from the Weatherboard All data is sent back to ground station via the XBEE Pro 900 Camera attached to inside of payload bay looking out

14. L ATERAL F LIGHT D YNAMICS P AYLOAD Purpose: Introduce a determinable roll rate during flight Evaluate roll dampening using rollerons Ailerons deflect with an impulse to induce roll Uses rollerons to in-actively dampen roll rate Compares the rockets natural dampening to that of rollerons

15. L ATERAL F LIGHT D YNAMICS P AYLOAD All components are locally manufactured Wheel on MillFinished Wheel Casing

16. L ATERAL F LIGHT D YNAMICS Uses pneumatic actuators to unlock rollerons and deflect ailerons Rollerons are locked using a cager Rolleron Cager Aileron Aileron Actuator

17. F LOW A NGULARITY P AYLOAD Purpose is to use pressure transducers to determine orientation of rocket Transducer on nose cone tip measures stagnation pressure Dynamic pressure varies based on pitch and yaw Significant calibration necessary Wind tunnel testing to create non-dimensional coefficients Gyroscope onboard to cross-check data

18. F LOW A NGULARITY AND B OUNDARY L AYER D EVELOPMENT P AYLOAD I NTEGRATION P LAN Self contained unit in nose cone Pressure transducers, microprocessor, battery supply, analog data storage device Transducers mounted flush with the surface of the nose cone All other electronics mounted to a bulkhead at the nose cone’s base Still allows ejection through nose cone Useful data ends at apogee

19. O UTLINE Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work

20. R ECOVERY Dual Deployment on Vehicle and SMD Payload Drogue released at apogee (both) Main released at 700 ft (both)

21. V EHICLE R ECOVERY Drogue Parachute 36 inches in diameter Descent velocity of 65 ft/s Main parachute 96 inches in diameter Descent velocity 18 ft/s

22. V EHICLE R ECOVERY S YSTEMS Drogue parachute directly below nosecone Released during first separation event Main parachute housed in middle airframe between avionics bay and pneumatics bay Released during second separation event Separation between pneumatics bay and middle airframe

24. SMD P AYLOAD R ECOVERY Drogue Parachute 36 inches in diameter Descent rate of 25 ft/s Main Parachute 36 inches in diameter Descent rate of 12.5 ft/s

25. SMD P AYLOAD R ECOVERY S YSTEMS Drogue released during first separation event Housed directly below vehicle main parachute Main released from parachute housing during secondary payload separation event Main parachute will be stored in housing and ejected using a piston system

26. SMD M AIN P ARACHUTE H OUSING

27. O UTLINE Project Organization Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work

28. C OMPONENT T ESTS Wind Tunnel TestingAlex Fins, Body Tube, Camera Shroud 2/1/2012 Simulation of Rocket LaunchAnthonyAccelerometer, R-DAS1/10/2012 Wireless Data TransmissionAnthonyXBee's1/10/2012 Static Motor Test (Full Scale)JasonMotor1/6/2012 Parachute TestingLaurenParachutes1/15/2012 Shear Pins (Full Scale)RobertBody tube2/4/2012

29. O UTLINE Project Organization Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work

30. P LANNED F LIGHT December 10 th, Bunnell, FL Testing: Fin mount assembly SMD Payload main parachute deployment Dual separation Live data transmission

31. O UTLINE Project Organization Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work

32. F LIGHT S IMULATIONS Used RockSim and MATLAB to simulate the rocket’s flight MATLAB code is 1-DOF that uses ode45 Allows the user to vary coefficient of drag for different parts of the rocket After wind tunnel testing, can get fairly accurate CD values that can be used in the program

33. P RELIMINARY R ESULTS MATLAB code is compared with RockSim Maximum altitude approximately 200 ft. lower than RockSim but still slightly higher than a mile

34. O UTLINE Project Organization Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work

35. C OMMUNITY O UTREACH Gainesville High School 400 students throughout the school’s 6 periods Interactive PowerPoint Presentation covering the basics of rocketry Derivations of relatable equations Model rocket launches

36. C OMMUNITY O UTREACH PK Yonge Developmental and Research School 150 6 th grade students Interactive PowerPoint Presentation with videos Model rocket launches

37. O UTLINE Project Organization Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work

38. F UTURE W ORK Use wind tunnel data and subscale launch data to further refine MATLAB code Use RockSim to simulate various wind conditions and launch angles Design for a static stability margin between 1 and 3