Transcript Presentation

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
