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UNIVERSITY OF FLORIDA
INTIMIGATOR PDR
OUTLINE
Project Organization
Vehicle Design
Payload Design
Recovery System
Component Testing
Subscale Flight
Simulations
Outreach
Future Work
PROJECT ORGANIZATION
OUTLINE
Project Organization
Vehicle Design
Payload Design
Recovery System
Component Testing
Subscale Flight
Simulations
Outreach
Future Work
MATERIAL
AND DIMENSIONS
Material: Blue tube
Section
Diameter: 6 inches
Nosecone
Upper Airframe
Length: 115 inches
Avionics Bay
Mid Airframe
Weight: 29 lbs
Lower Airframe
Component
Fins (2 with rollerons and 2 without)
Pneumatics Bay
Main Parachute/Shock Cord and Piston
Weight (lbs)
5
1.5
3
Avionics Bay
3.25
Payload and Main Drogue Parachute Piston
0.25
Payload Main Parachute and Housing
Drogue Parachutes and Shock Cord
4
1.5
Nosecone and Pressure Payload
4.25
Body Tube
6.25
Total
29
Length (in)
24
44
3
16
28
SYSTEM BREAKDOWN
STATIC STABILITY MARGIN
CG
CP
• The center of pressure (CP) is located 89.16" from the
nose tip
• The center of gravity (CG) is located 71.73" from the
nose tip
• The static stability margin is 2.87 which is within the
stable range of 1 to 3
FINS
Fins and mount made
from ABS plastic on a
rapid prototype machine
1-Slots in fin align with barrel
bolts
2-Fin slides forward and down
3-Set screw holds fin in place
OUTLINE
Project Organization
Vehicle Design
Payload Design
Recovery System
Component Testing
Subscale Flight
Simulations
Outreach
Future Work
SCIENCE MISSION DIRECTORATE PAYLOAD
Rests in the upper
airframe on top of the
piston
Ejects from the rocket at
apogee
Dual deployment
recovery
SCIENCE MISSION DIRECTORATE PAYLOAD
Payload legs spring open
upon ejection
Electronics requiring
sunlight are mounted on
the lid
Body made from blue
tube in order to not
interfere with
measurements
SCIENCE MISSION DIRECTORATE PAYLOAD
DESIGN
1 Arduino Microcontroller to sample analog
sensors and read output from Weatherboard and
GPS
Analog sensors will be compared to the preprogrammed output from the Weatherboard
All data is sent back to ground station via the
XBEE Pro 900
Camera attached to inside of payload bay looking
out
LATERAL FLIGHT DYNAMICS PAYLOAD
Purpose:
Introduce a determinable roll rate during flight
Evaluate roll dampening using rollerons
Ailerons deflect with an impulse to induce roll
Uses rollerons to in-actively dampen roll rate
Compares the rockets natural dampening to that of
rollerons
LATERAL FLIGHT DYNAMICS PAYLOAD
All components are locally manufactured
Wheel on Mill
Finished Wheel
Casing
LATERAL FLIGHT DYNAMICS
Uses pneumatic actuators to unlock rollerons and
deflect ailerons
Rollerons are locked using a cager
Rolleron
Cager
Aileron
Aileron Actuator
FLOW ANGULARITY PAYLOAD
Purpose is to use pressure transducers to
determine orientation of rocket
Transducer on nose cone tip measures stagnation
pressure
Dynamic pressure varies based on pitch and yaw
Significant calibration necessary
Wind tunnel testing to create non-dimensional
coefficients
Gyroscope onboard to cross-check data
FLOW ANGULARITY AND BOUNDARY
LAYER DEVELOPMENT PAYLOAD
INTEGRATION PLAN
Self contained unit in nose cone
Pressure transducers, microprocessor, battery
supply, analog data storage device
Transducers mounted flush with the surface of the
nose cone
All other electronics mounted to a bulkhead at the
nose cone’s base
Still allows ejection through nose cone
Useful data ends at apogee
OUTLINE
Vehicle Design
Payload Design
Recovery System
Component Testing
Subscale Flight
Simulations
Outreach
Future Work
RECOVERY
Dual Deployment on Vehicle and SMD Payload
Drogue released at apogee (both)
Main released at 700 ft (both)
VEHICLE RECOVERY
Drogue Parachute 36 inches in diameter
Descent velocity of 65 ft/s
Main parachute 96 inches in diameter
Descent velocity 18 ft/s
VEHICLE RECOVERY SYSTEMS
Drogue parachute directly below nosecone
Released during first separation event
Main parachute housed in middle airframe
between avionics bay and pneumatics bay
Released during second separation event
Separation between pneumatics bay and middle
airframe
SMD PAYLOAD RECOVERY
Drogue Parachute 36 inches in diameter
Descent rate of 25 ft/s
Main Parachute 36 inches in diameter
Descent rate of 12.5 ft/s
SMD PAYLOAD RECOVERY SYSTEMS
Drogue released during first separation event
Housed directly below vehicle main parachute
Main released from parachute housing during
secondary payload separation event
Main parachute will be stored in housing and ejected
using a piston system
SMD MAIN PARACHUTE HOUSING
OUTLINE
Project Organization
Vehicle Design
Payload Design
Recovery System
Component Testing
Subscale Flight
Simulations
Outreach
Future Work
COMPONENT TESTS
Wind Tunnel Testing
Alex
Fins, Body Tube, Camera
Shroud
2/1/2012
Simulation of Rocket Launch
Anthony
Accelerometer, R-DAS
1/10/2012
Wireless Data Transmission
Anthony
XBee's
1/10/2012
Static Motor Test (Full Scale)
Jason
Motor
1/6/2012
Parachute Testing
Lauren
Parachutes
1/15/2012
Shear Pins (Full Scale)
Robert
Body tube
2/4/2012
OUTLINE
Project Organization
Vehicle Design
Payload Design
Recovery System
Component Testing
Subscale Flight
Simulations
Outreach
Future Work
PLANNED FLIGHT
December 10th, Bunnell, FL
Testing:
Fin mount assembly
SMD Payload main parachute deployment
Dual separation
Live data transmission
OUTLINE
Project Organization
Vehicle Design
Payload Design
Recovery System
Component Testing
Subscale Flight
Simulations
Outreach
Future Work
FLIGHT SIMULATIONS
Used RockSim and MATLAB to simulate the
rocket’s flight
MATLAB code is 1-DOF that uses ode45
Allows the user to vary coefficient of drag for
different parts of the rocket
After wind tunnel testing, can get fairly accurate
CD values that can be used in the program
PRELIMINARY RESULTS
MATLAB code is compared with RockSim
Maximum altitude approximately 200 ft. lower
than RockSim but still slightly higher than a
mile
OUTLINE
Project Organization
Vehicle Design
Payload Design
Recovery System
Component Testing
Subscale Flight
Simulations
Outreach
Future Work
COMMUNITY OUTREACH
Gainesville High School
400 students throughout the school’s 6 periods
Interactive PowerPoint Presentation covering the
basics of rocketry
Derivations of relatable equations
Model rocket launches
COMMUNITY OUTREACH
PK Yonge Developmental and Research School
150 6th grade students
Interactive PowerPoint Presentation with videos
Model rocket launches
OUTLINE
Project Organization
Vehicle Design
Payload Design
Recovery System
Component Testing
Subscale Flight
Simulations
Outreach
Future Work
FUTURE WORK
Use wind tunnel data and subscale launch data
to further refine MATLAB code
Use RockSim to simulate various wind conditions
and launch angles
Design for a static stability margin between 1
and 3