University of Florida The Most Interesting Rocket in the World

1. University of Florida The Most Interesting Rocket in the World

2. Outline • Overview • System Design • Recovery Design • Payload Design • Testing

3. Project Summary • Launch Vehicle • The launch vehicle is designed to reach an altitude of 5280 ft. • It contains the Lateral Flight Dynamics (LFD) Payload: • The Aileron Deflection Package (ADP) induces a controlled roll on the vehicle. • The LFD Fins house and control the Rollerons • The Rollerons act as a passive roll dampening system • Dual-deployment recovery

4. Outline • Overview • System Design • Recovery Design • Payload Design • Testing

5. System Overview

6. Vehicle Dimensions • Diameter: 4 inches • Length: 96.75 inches • Weight: 21 lbs

7. Static Stability Margin The static stability margin is 1.06

8. Motor Selection • Cessaroni L910 • 3.01 pounds of propellant • 2 Grains • Total impulse of 645 lbf-s • 3.16 second burn time

9. Performance • Thrust-to-weight ratio • 9.796 • Need above 1 for lift-off • Rail exit velocity • 68.5 ft/s

10. Outline • Overview • System Design • Recovery Design • Payload Design • Testing

11. Vehicle Recovery • Dual Deployment • Drogue release at apogee • Main release at 700 ft AGL • Drogue Parachute – 36” X-form • Descent velocity of 64.05 ft/s • Main parachute – 96” Circular • Descent velocity 20.37 ft/s

12. Vehicle Recovery Redundancy • Two Altimeters • Drogue Event • Apogee • 3 Second Delay • Main Event • 700 Feet AGL • 500 Feet AGL • Raspberry Pi • Ground-based manual override • Separation of Components

13. Kinetic Energy at Key PointsDrift Calculations

14. Vehicle Requirements Verification • Table 9 of FRR • All requirements are met • Full-scale test flight verifies safe and recoverable rocket • Successful motor change reduced added mass ballast • Utilized all available resources during verification

15. Outline • Overview • System Design • Recovery Design • Payload Design • Testing

16. Lateral Flight Dynamics (LFD) • Objectives • Introduce a measureable roll rate during flight after burn-out • Dampen roll rate with rollerons • Compare rollerons dampening time constant to natural dampening time constant • Determine rise time and percent overshoot of steady state roll rate, if achieved. • Requirements • Ailerons deflect with an impulse to induce roll • Rollerons inactively dampen roll rate

17. LFD Procedure • Procedures (after burnout) • Phase I • Motor burn • Rollerons remain locked • Ailerons remain neutral • Phase II • Ailerons step input command (7 degrees 0.7 seconds) • Rollerons locked • Rocket naturally dampens its roll rate • Phase II • Ailerons impulse deflect • Rollerons unlocked • Rollerons dampen out roll rate

18. LFD Fin Layout

19. ADP Layout

20. Payload Requirements Verification • Payload integration is confirmed • ADP is ground tested, does not effect stability • Payload objectives are updated to compensate changes in project plan • Must complete rolleron manufacturing • Must perform second full-scale flight test

21. Outline • Overview • System Design • Recovery Design • Payload Design • Testing

22. Component Testing Summary • All components of the launch vehicle have been tested • Recovery • Vacuum Test • Override • Continuity • Vehicle • Vibration • Launch Rehearsal • Openrocket Demonstrations • Launch Detection • Payload needs additional testing – planned • Aileron Deflection • Rolleron Functionality

23. Full Scale Launch • Occurred on March 16, 2013 • Launched with a CesaroniL910 • Reached an altitude of 5125 ft. • Successful Recovery system • Minimal Roll • Exposed coding issues

24. Questions?