UNIVERSITY OF FLORIDA THE MOST INTERESTING ROCKET IN THE WORLD

OUTLINE Overview System Design Recovery Design Payload Design Testing

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

OUTLINE Overview System Design Recovery Design Payload Design Testing

SYSTEM OVERVIEW

VEHICLE DIMENSIONS Diameter: 4 inches Length: 96.75 inches Weight: 21 lbs

Component Weight (lbs)

 

Fins (2 with rollerons and 2 without) 5.08

Electronics Bay 6.23

Main Parachute/Shock Cord and Piston 2.07

Drogue Parachutes and Shock Cord 0.94

Nosecone 0.72

Body Tube 1.93

Motor Mount 0.57

Motor Casing 3.15

Additional Hardware and Components 0.31

Total 21

Section Length (in)

Nosecone 15.75

Upper Airframe 32

Mid Airframe 13

Lower Airframe 36

Total 96.75

STATIC STABILITY MARGIN

The static stability margin is 1.06

MOTOR SELECTION Cessaroni L910

3.01 pounds of propellant 2 Grains Total impulse of 645 lbf-s 3.16 second burn time

PERFORMANCE Thrust-to-weight ratio

9.796 Need above 1 for lift-off

Rail exit velocity 68.5 ft/s

OUTLINE Overview System Design Recovery Design Payload Design Testing

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

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

KINETIC ENERGY AT KEY POINTS

DRIFT CALCULATIONS

Component Velocity (ft/sec) Mass (slugs) Kinetic Energy (ft-lbf)

AscentFull Rocket 795 .652 205,949

Drogue DescentNosecone/Upper Airframe

64.05 .294 603.1

Lower Airframe 64.05 .358 734.3Main Descent

Nosecone 20.37 .022 4.564Upper Airframe 20.37 .272 56.43Lower Airframe 20.37 .358 74.20

Wind Speed (mph)

Total Drift (ft)

0 05 524.4

10 1048.715 1573.120 2097.5

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

OUTLINE Overview System Design Recovery Design Payload Design Testing

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

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

LFD FIN LAYOUT

ADP LAYOUT

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

OUTLINE Overview System Design Recovery Design Payload Design Testing

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

FULL SCALE LAUNCH Occurred on March 16, 2013 Launched with a Cesaroni L910 Reached an altitude of 5125 ft. Successful Recovery system Minimal Roll Exposed coding issues

QUESTIONS?