University of Florida IntimiGATOR PDR

1. University of Florida IntimiGATORPDR

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

3. Project Organization

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

5. Material and Dimensions • Material: Blue tube • Diameter: 6 inches • Length: 115 inches • Weight: 29 lbs

6. System Breakdown

7. Static Stability Margin 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. Fins 1-Slots in fin align with barrel bolts2-Fin slides forward and down3-Set screw holds fin in place Fins and mount made from ABS plastic on a rapid prototype machine

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

10. Science Mission Directorate Payload • Rests in the upper airframe on top of the piston • Ejects from the rocket at apogee • Dual deployment recovery

11. Science Mission Directorate Payload • 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. Science Mission Directorate Payload Design • 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. Lateral Flight Dynamics Payload • 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. Lateral Flight Dynamics Payload • All components are locally manufactured Wheel on Mill Finished Wheel Casing

16. Lateral Flight Dynamics • Uses pneumatic actuators to unlock rollerons and deflect ailerons • Rollerons are locked using a cager Rolleron Cager Aileron Aileron Actuator

17. Flow Angularity Payload • 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. Flow Angularity and Boundary Layer Development Payload Integration Plan • 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. Outline • Vehicle Design • Payload Design • Recovery System • Component Testing • Subscale Flight • Simulations • Outreach • Future Work

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

21. Vehicle Recovery • Drogue Parachute 36 inches in diameter • Descent velocity of 65 ft/s • Main parachute 96 inches in diameter • Descent velocity 18 ft/s

22. Vehicle Recovery Systems • 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 Payload Recovery • 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 Payload Recovery Systems • 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 Main Parachute Housing

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

28. Component Tests

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

30. Planned Flight • December 10th, Bunnell, FL • Testing: • Fin mount assembly • SMD Payload main parachute deployment • Dual separation • Live data transmission

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

32. Flight Simulations • 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. Preliminary Results • MATLAB code is compared with RockSim • Maximum altitude approximately 200 ft. lower than RockSim but still slightly higher than a mile

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

35. Community Outreach • 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. Community Outreach • PK Yonge Developmental and Research School • 150 6th grade students • Interactive PowerPoint Presentation with videos • Model rocket launches

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

38. Future Work • 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