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