U NIVERSITY OF F LORIDA T HE M OST I NTERESTING R OCKET IN THE W ORLD

O UTLINE Overview System Design Recovery Design Payload Design Testing

P ROJECT S UMMARY 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

O UTLINE Overview System Design Recovery Design Payload Design Testing

S YSTEM O VERVIEW

V EHICLE D IMENSIONS Diameter: 4 inches Length: inches Weight: 21 lbs ComponentWeight (lbs) Fins (2 with rollerons and 2 without)5.08 Electronics Bay6.23 Main Parachute/Shock Cord and Piston2.07 Drogue Parachutes and Shock Cord0.94 Nosecone0.72 Body Tube1.93 Motor Mount0.57 Motor Casing3.15 Additional Hardware and Components0.31 Total21 SectionLength (in) Nosecone15.75 Upper Airframe32 Mid Airframe13 Lower Airframe36 Total96.75

S TATIC S TABILITY M ARGIN The static stability margin is 1.06

M OTOR S ELECTION Cessaroni L pounds of propellant 2 Grains Total impulse of 645 lbf-s 3.16 second burn time

P ERFORMANCE Thrust-to-weight ratio Need above 1 for lift-off Rail exit velocity 68.5 ft/s

O UTLINE Overview System Design Recovery Design Payload Design Testing

V EHICLE R ECOVERY Dual Deployment Drogue release at apogee Main release at 700 ft AGL Drogue Parachute – 36” X-form Descent velocity of ft/s Main parachute – 96” Circular Descent velocity ft/s

V EHICLE R ECOVERY R EDUNDANCY 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

K INETIC E NERGY AT K EY P OINTS D RIFT C ALCULATIONS ComponentVelocity (ft/sec)Mass (slugs)Kinetic Energy (ft- lbf) Ascent Full Rocket ,949 Drogue Descent Nosecone/Upper Airframe Lower Airframe Main Descent Nosecone Upper Airframe Lower Airframe Wind Speed (mph) Total Drift (ft)

V EHICLE R EQUIREMENTS V ERIFICATION 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

O UTLINE Overview System Design Recovery Design Payload Design Testing

L ATERAL F LIGHT D YNAMICS (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

LFD P ROCEDURE 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

LFD F IN L AYOUT

ADP L AYOUT

P AYLOAD R EQUIREMENTS V ERIFICATION 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

O UTLINE Overview System Design Recovery Design Payload Design Testing

C OMPONENT T ESTING S UMMARY 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

F ULL S CALE L AUNCH Occurred on March 16, 2013 Launched with a Cesaroni L910 Reached an altitude of 5125 ft. Successful Recovery system Minimal Roll Exposed coding issues

Q UESTIONS ?