university of florida the most interesting rocket in the world
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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. - PowerPoint PPT PresentationTRANSCRIPT
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UNIVERSITY OF FLORIDA THE MOST INTERESTING ROCKET IN THE WORLD
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OUTLINE Overview System Design Recovery Design Payload Design Testing
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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
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OUTLINE Overview System Design Recovery Design Payload Design Testing
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SYSTEM OVERVIEW
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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
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STATIC STABILITY MARGIN
The static stability margin is 1.06
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MOTOR SELECTION Cessaroni L910
3.01 pounds of propellant 2 Grains Total impulse of 645 lbf-s 3.16 second burn time
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PERFORMANCE Thrust-to-weight ratio
9.796 Need above 1 for lift-off
Rail exit velocity 68.5 ft/s
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OUTLINE Overview System Design Recovery Design Payload Design Testing
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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
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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
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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
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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
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OUTLINE Overview System Design Recovery Design Payload Design Testing
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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
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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
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LFD FIN LAYOUT
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ADP LAYOUT
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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
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OUTLINE Overview System Design Recovery Design Payload Design Testing
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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
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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
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QUESTIONS?