University of Florida IntimiGATOR PDR

UNIVERSITY OF FLORIDA INTIMIGATOR PDR

OUTLINE Project Organization Vehicle Design Payload Design Recovery System Component Testing Subscale Flight Simulations Outreach Future Work

PROJECT ORGANIZATION


MATERIAL AND DIMENSIONS Material: Blue tube Diameter: 6 inches Length: 115 inches Weight: 29 lbs

Component Weight (lbs)

Fins (2 with rollerons and 2 without) 5

Pneumatics Bay 1.5

Main Parachute/Shock Cord and Piston 3

Avionics Bay 3.25

Payload and Main Drogue Parachute Piston 0.25

Payload Main Parachute and Housing 4

Drogue Parachutes and Shock Cord 1.5

Nosecone and Pressure Payload 4.25

Body Tube 6.25

Total 29

Section Length (in)

Nosecone 24

Upper Airframe 44

Avionics Bay 3

Mid Airframe 16

Lower Airframe 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

1-Slots in fin align with barrel bolts2-Fin slides forward and down3-Set screw holds fin in place

FINS

Fins and mount made from ABS plastic on a rapid prototype machine


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 pre-programmed 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


COMPONENT TESTSWind Tunnel Testing Alex Fins, Body Tube, Camera

Shroud2/1/2012

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


PLANNED FLIGHT December 10th, Bunnell, FL Testing:

Fin mount assembly SMD Payload main parachute deployment Dual separation Live data transmission


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


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


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

Documents

University of Florida IntimiGATOR PDR