1. University of Florida PDR Presentation

2. Vehicle Design Diameter: 5.86 Length: 135 Static Stability Margin: 1.4 Total Weight: 23.6 lbs

3. Payload Bay Inside RocketSeparated From Rocket

4. Vehicle Materials Airframe: phenolic tube with fiberglass reinforcement Fins: 1/8 G-10 fiberglass Bulkheads and Centering Rings: Birch Plywood Shock Cord: 5/8 Tubular Nylon Motor Retention: Aluminum sleeve

5. Vehicle Safety and Testing Structures verification – Fin load testing – Coupler joints – Motor retention testing Stability verification – RockSim – MATLAB

6. Recovery System Design Rocket Drogue: 24 round Descent Rate: 80 ft/s Rocket Main: 84 round Descent Rate: 21 ft/s Payload Drogue: Heavy Duty Streamers Descent Rate: Undetermined Payload Main: 60 round Descent Rate: 19.5 ft/s

7. Recovery Safety and Testing Black powder charge ground testing Parachute and streamer descent rate verification Payload bay separation testing Payload landing testing Flight computer & GPS testing in Avionics Bay and Payload Bay

8. Motor Choice Cesaroni K590 – Average Thrust = 591 N; Max Thrust = 724 N – Total Impulse = 1336.5 Ns – T.W. Ratio = 5.635

9. Motor Safety and Testing Static Motor Testing – Tests our ability to assemble a K590 Motor – Tests the burn profile of the motor to check with RockSim and online predictions

10. Flight Simulations MATLAB vs. RockSim

11. Why use MATLAB? MATLAB can easily be used in optimization – RockSim may only be optimized through tedious iteration. Time-consuming and inflexible Design space visualization – 3D/4D plots

12. Preliminary Results MATLAB 1DOF is surprisingly accurate when RockSim simulates a wind speed of zero

13. Future Work MATLAB model will be extended to 3DOF Compared with RockSim for various wind speeds RockSim and MATLAB models compared to launch data. Best-fit determined

14. Payload Design Two 1/8" G-10 fiberglass cards mated with XBee Pro 900 transmitter in between – One card holds: R-DAS Tiny, PerfectFlite altimeters, two batteries – Second card holds: GPS, transmitter card, temperature and humidity sensor, JPEG trigger Camera attached to inside of payload bay looking out

15. Payload Design

16. Science Value of Payload Experiment To test modern hydrologic theory – Comparing the theoretical total long and short wave radiation to recorded data To establish an accurate measurement of the environmental lapse rate for temperature and pressure

17. Predictions from Hydrologic Theory

18. Lapse Rates Temperature lapse rate estimated to be somewhere between 6°C/km and 10°C/km Pressure lapse rate found from Perfect Gas Law Source: Figure 3.2.2 from Applied Hydrology by Chow, Ven T., David R. Maidment, and Larry W. Mays. International ed. New York: McGraw-Hill, 20051988. Print.

19. Payload Testing Solar cell has range of 430 to 1100 nm. Test the voltage-to-W/m 2 -conversion-constant UV sensor voltage-to-W/m 2 -conversion- constant Sensor-to-RDAS configuration Note: Will need IR sensor to measure long wave radiation ( > 4 μm)